COOLING OF ENGINE COMPONENTS

专利摘要:
A component, for example a bearing surface component such as a turbine blade (4) or a guide vane (3), for a gas turbine engine, comprising first and second walls (100, 110) defining at least a passage (3R) for supplying cooling fluid to a portion, for example, a trailing edge portion (40), of the component (3, 4) to be cooled, said portion (40) comprising a slot (105) through which the cooling fluid passes from the passage (3R) to an outlet of the slot for cooling the portion (40), wherein the slot (105) comprises at least one side wall (100), preferably a pair of walls opposing sides (100, 110), each having a surface profile defining an array of channels (102, 112) for the passage of cooling fluid therethrough and wherein the surface profile defining each of said channel arrays ( 102, 112) is corrugated, i.e. curved in a manner regular, with the respective networks of channels (102, 112) in the two side walls (100, 110) inclined relative to each other. The resulting transversely corrugated internal cooling arrangement promotes improved cooling of the trailing edge or other portion (40) of the component by controlling the flow of cooling air through and escaped from the slot (105). .
公开号:FR3029959A1
申请号:FR1562089
申请日:2015-12-09
公开日:2016-06-17
发明作者:Tsun H Wong；Peter T Ireland；Kevin P Self
申请人:Rolls Royce PLC；
IPC主号:

专利说明:

[0001] This invention relates to the cooling of engine components, in particular gas turbine engines. More particularly, but not exclusively, it relates to components such as turbine blades and guide vanes which employ internal cooling arrangements to effect cooling thereof, and in particular to such components which utilize an arrangement slot cooling system for cooling one or more particular portions thereof, such as a trailing edge portion. It is well known in various types of gas turbine engines, particularly those in the field of aviation, to employ internal cooling arrangements for bearing surface components such as turbine blades and guide vanes. The airfoil component typically comprises a pressure wall and a suction wall, and has leading and trailing edges, with the walls defining at least one internal passage for supplying cooling fluid, generally the air of cooling, one or more internal cooling element (s) in the form of one or more holes and / or slot (s) for film cooling when the cooling air passes through and outside of these and outside the component. It is often difficult to provide the trailing edge portion, in particular of such a bearing surface component, with an effective cooling arrangement, because of its narrow geometry and the limitations of conventional casting techniques in being able to to form reliably and accurately the one or more hole (s) and / or cooling slot (s) required in such a region of the component. An example of a known hole-based internal cooling arrangement for the trailing edge portion of a turbine blade is illustrated in US Patent No. US3819295. Here two sets of drilled holes provided in the trailing edge portion of the blade form passageways which connect an internal cooling fluid supply passage (typically air) to the rear trailing edge of the dawn. Each set of holes is inclined relative to each other so that passageways of one set intersect with those of the other set, thereby forming a lattice with the intersecting knots acting as turbulence generators and multipliers. region for better convective heat transfer from the dawn body to the cooling fluid. However, this cooling arrangement is difficult, time consuming and expensive to manufacture. It also leaves large areas of uncooled material in the hub and tip regions of the blade where space is limited and thus holes can not be drilled or even formed by casting because of the too small size that they would need to have. In contrast, slit cooling of various kinds for the trailing edge portion of a bearing surface component has been used in many known designs of turbine blades and guide vanes, and with respect to arrangements In the case of simple multi-hole cooling, the use of continuous internal slot feed between the internal cooling passage and the trailing edge at the rear of the component results in high performance film cooling with high cooling efficiency. . This is mainly because slit feeding produces a continuous coverage of the cooling film, with no gaps or gaps in it that typically occur when using rows of holes. Although in some existing arrangements based on the use of holes, it would sometimes be possible to use double rows of holes which are offset relative to each other in order to improve the cooling film coverage, this strategy can be difficult to practice at the trailing edge of a bearing surface component due to insufficient space available to accommodate such an arrangement. An example of a slot-based internal cooling arrangement known for the trailing edge portion of a turbine blade is shown in U.S. Patent No. 4,407,632. Here a trailing edge slot is formed with an internal network of pedestals extending across its width, where selected pairs of pedestals are connected by a barrier wall attached to either the pressure side or the suction side of the pedestal. slot. The barriers extend only a portion of the path through the slot in order to trip, or interrupt, the thermal boundary layer of cooling air flow, which allows for better heat transfer from the body of the body. dawn to cooling fluid. However, this cooling arrangement design is characterized by many sharp edges to the various elements within the slot, making casting difficult and resulting in reduced mechanical durability.
[0002] Another example of a slot-based internal cooling arrangement is shown in International Patent Application WO2005 / 083236A1. Here a blade comprises an interior space defined between two walls (suction side and pressure side), with a cooling fluid inlet 5 at a leading edge and a cooling fluid outlet at the level of a trailing edge so that the interior space forms a passage through which the coolant flows. The passage contains two sets of specially arranged and shaped ribs projecting inwardly from the walls of the respective suction and pressure side so as to form respective channels for the flow of cooling fluid through the interior passage from the leading edge to the trailing edge. The respective channel flow directions are each at an angle inclined relative to the radial airfoil direction and change to a smooth curve of the leading edge of the channels at the trailing edge of the channels. However, the channel directions in each set are at an inclined angle to each other near the leading edge so that they intersect in that region, whereas in the trailing edge region the channels are join to form common exit channels at the trailing edge. In the middle, the ribs in each set are connected at their respective intersections, but otherwise the flows in the channels can mix. However, this cooling arrangement design is, like that of the above-mentioned US Pat. No. 4,4076,32, still difficult to cast, due to the complex arrangement of the ribs, and it is also impossible to extend the arrangement 25 particularly in the trailing edge region itself of the blade, where the space is limited and casting cores have minimum size constraints. Another disadvantage of many known slot-based cooling arrangements, including those of US4407632 and WO2005 / 083236A1 discussed above, is the need to control the mass flow of coolant through the slot if the efficiency The cooling arrangements must be optimized, which the arrangements described above fail to do. This is because the pressure difference between the slot flow and the external gas path to the component must be above a predetermined minimum level in order to maintain the required coolant flow. However, the present manufacturing techniques for the airfoil components in particular do not allow for a fairly consistent production of trailing edge cooling slots which are thin enough to adequately control the mass flow of coolant alone. For example, in the context of typical casting processes, a very narrow slot would require a particularly narrow core, which would be brittle and easily broken, rendering it commercially unsustainable for mass production. There is therefore a need in the art for new and improved internal cooling arrangements in the airfoil and other components that utilize slot-based cooling, as well as methods for their efficient manufacture. This leads to better mass flow control of coolant and thus better pressure drop and resultant heat recovery during the passage of cooling fluid through such arrangements. A main object of the present invention is therefore to meet this need. Accordingly, aspects of the present invention relate to a motor component, a cooling arrangement for a motor component, a gas turbine engine having the component or a component having the cooling arrangement, and a method of cooling a portion containing a slot of a motor component. In a first aspect, the present invention provides a component for a gas turbine engine, comprising first and second walls defining at least one passage for supplying cooling fluid, for example, cooling air, a portion of the component to be cooled, said part comprising a slot through which a cooling fluid passes from the passage to an outlet of the slot to effect the cooling of the part, wherein the slot comprises at least one side wall having a surface profile defining a network of channels for the passage of cooling fluid therethrough, and wherein the surface profile defining said channel array is corrugated. In particularly preferred embodiments of the first aspect above, the slot may comprise a first side wall having a first surface profile defining a first channel network for the passage of cooling fluid, for example, air of cooling, therethrough, and a second sidewall opposite the first sidewall, having a second surface profile defining a second channel array for the passage of coolant therethrough, where each said first and second surface profiles are corrugated and the channels of the first network are oriented so as to be non-parallel to the channels of the second network. These preferred embodiments may therefore in some contexts be conveniently referred to as "transversely corrugated" internal cooling arrangements. In embodiments of this first aspect of the invention, the channel network (s) may be provided in a portion of the slot which may extend over any longitudinal portion of the slot. . Thus, in some embodiments, only one longitudinal portion of the slot, i.e., a first longitudinal portion of the slot smaller than its overall longitudinal length, may be provided with said one or more network (s). channels in one or more respective sidewall portions thereof. In this case, the slot may thus comprise a second longitudinal part, in particular a downstream part, downstream of the first part, preferably upstream, containing said one or more network (s) of channels which does not contain a such a network of channels in it. For example, such a downstream non-grooved portion of the slot may have one or more internal or (a) even or partially regular (s) and / or flat (s) face (s), although this may be subjected to one or more of these internal faces or surfaces including one or more optional surface formations, for example, one or more deflector members, as will be defined and described in more detail below. However, in other embodiments, it may be possible for substantially the entire longitudinal length of the slot to be provided with said one or more network (s) of channels in one or more sidewall (s). respective of them. Other optional and / or preferred features of the surface profiles of the respective one or more sidewall (s) of the slot, as well as optional and / or preferred features of the component itself, will be defined in more detail below. In a second aspect, the present invention provides a cooling arrangement for a gas turbine engine component, wherein the component comprises first and second walls defining at least one passage for supplying cooling fluid, for example , the cooling air, a part of the component to be cooled, said part comprising a slot through which a cooling fluid passes from the passage to an outlet of the slot to effect the cooling of the part, where the cooling arrangement comprises at least one side wall of the slot which has a surface profile defining an array of channels for the passage of cooling fluid therethrough, and wherein said surface profile defining said channel array is corrugated. In particularly preferred embodiments of the second aspect above, the cooling arrangement may comprise a first sidewall of the slot having a first surface profile defining a first channel array for the passage of cooling fluid therethrough. this, and a second side wall, opposite the first side wall, having a second surface profile defining a second channel network for the passage of cooling fluid therethrough, wherein each of said first and second profiles surface is wavy and the channels of the first network are oriented so as to be non-parallel to the channels of the second network. In a third aspect, the present invention provides a gas turbine engine comprising at least one component according to the first aspect or any embodiment thereof, or at least one component having a cooling arrangement according to the second aspect. or any embodiment thereof. In a fourth aspect, the present invention provides a method of cooling a portion of a component of a gas turbine engine during operation, wherein the component comprises first and second walls defining at least one passage for feeding in cooling fluid, for example cooling air, the part thereof, said part comprising a slot through which the cooling fluid passes from the passage to an outlet of the slot, wherein the slot comprises at least one wall sidewall having a surface profile defining an array of channels for the passage of cooling fluid therethrough, and wherein the surface profile defining said channel array is corrugated, wherein the method comprises, during operation of the motor, the passage of the cooling fluid, for example the cooling air, from the passage at the outlet of the slot through the slot so that the coolant passes 29959 7 along said network of corrugated channel channels in the at least one side wall. In particularly preferred embodiments of the method of the fourth aspect above, wherein the slot comprises a first side wall having a first surface profile defining a first channel network for passage of cooling fluid therethrough. and a second side wall, opposite to the first side wall, having a second surface profile defining a second channel network for the passage of cooling fluid therethrough, wherein each of said first and second surface profiles is corrugated and the channels of the first network are oriented so as to be non-parallel to the channels of the second network, the method may comprise, during operation of said engine, the passage of the cooling liquid, for example the cooling air, the passage at the exit of the slot through the slot so that the cooling fluid passes along said first and second streamlined channel array in the respective first and second sidewalls. In particularly preferred embodiments of the method of the fourth aspect above, the cooling fluid, for example the cooling air, passes from the passage to the outlet of the slot through the slot so that the coolant passes along said first and second corrugated channel networks in the respective first and second sidewalls while further passing between at least one or more channels / channels of the first network and at least one or more channels / channels of the second network.
[0003] Other optional and / or preferred features of the method of the fourth aspect above will be defined in more detail hereinafter in connection with the further discussion of other optional and / or preferred features of the component itself. As used herein, the term "corrugated" as applied to the sidewall surface profile or the respective sidewall surface profile defining the respective network or network of channels therein means that the surface profile is defined by a regular waveform curve which changes direction regularly over at least a portion of its pitch (wavelength), preferably at least a major part of its pitch (wavelength). In many preferred embodiments, the corrugated nature of the respective sidewall surface profile or sidewall surface profile may be as defined by a wave function which varies in the direction of the height substantially continuously over at least a portion of its pitch (wavelength), preferably a major part of its pitch (wavelength): in other words, the sectional profile of the surface forming each channel may be such that a tangent to the channel defining surface, perpendicular to the longitudinal channel direction, has a varying orientation angle (relative to the general plane of the respective side wall of the component) substantially continuous over at least a portion of its curve, preferably over at least a major part of its curve, between one side of the channel and an opposite side thereof. In many embodiments the corrugated nature of the respective sidewall surface profile or sidewall surface profile may be such that it is defined by a regular curvature surface at least in peak and / or valley (or hollow) of it.
[0004] Preferably, therefore, the channels in the respective side wall surface or side wall surface are defined by a surface profile substantially without any sharp corners or sharp edges, ie substantially without any corner or edge. which have an inclined boundary between two adjacent surface portions thereof. This feature may assist, among other advantages of embodiments of the invention as discussed elsewhere herein, in reducing the harmful stress concentrations in the insulated portions of the side walls of the channels. In embodiments of the invention a wide variety of waveform shapes or functions may be used to define the corrugated surface profile (s) that define the respective channels. The corrugated surface profile or each corrugated surface profile may be a waveform of any suitable mathematical function or combination of two or more mathematical functions (e.g., different functions in different parts or regions of the curve defining the surface profile). The waveform may preferably be a regular repetition wave having a wavelength (i.e. not) and / or substantially constant amplitude. For example, the wave function that defines the surface profile or each surface profile defining the respective channels may be a sinusoidal wave function, i.e., defined by a sine wave. Alternatively, a polynomial function (e.g. cubic or quadratic) or exponential wave function may define the surface profile.
[0005] In other embodiments, the surface profile may be defined by a combination of two or more different waveform or shape functions, each defining a region or a different portion of the curve defining the surface profile of a surface. given channel. For example, a peak region between two adjacent channels and / or a valley or valley region of a given channel may each be independently defined by a partially circular, partially parabolic or partially hyperbolic curve, or a portion of the one of the other wave functions defined above, with each pair of valley / valley-peak region pairs being connected by a substantially straight tangential line. In some embodiments, the curve or shape function that defines a valley or valley portion of any given channel may even be different from the curve or shape feature that defines a peak portion thereof . For example, in one exemplary aspect, a valley portion or trough of a channel, particularly a base region thereof, may be somewhat flattened, particularly flattened in the lower the valley or valley, while a neighboring peak portion may be a little more curved with respect to it. This feature may for example help to reduce any tendency of the channel to be blocked by debris or deposits accumulated during use. In many embodiments, the inner sidewalls of each channel may be configured such that the inner shape of the channel is substantially symmetrical around a midplane intersecting in two the sectional profile defining the channel sidewalls. However, in other embodiments, the inner sidewalls of each channel may be configured so that the internal shape of the channel is substantially asymmetric about such a midplane, in other words in a given channel the The overall slope of one of its sidewalls may be different from, i.e., steeper or shallower than, the general slope of the opposing sidewall among its sidewalls. This feature can, for example, be used for better control of the direction of coolant flow along the channels either by encouraging or discouraging the flow of fluid on peaks between adjacent channels, depending on the overall geometry of the arrangement.
[0006] In many embodiments of the invention, the channels within the network or each respective network may be substantially parallel to each other. In many embodiments, the channels within the network or each respective network may be substantially straight over at least a portion, preferably a major portion, of their longitudinal length. In other words, each channel may have a central longitudinal axis which is a substantially straight line on at least a portion, preferably a major portion, of its length. However, in other embodiments, the channels within the network or each respective network may have a central longitudinal axis which itself varies in direction along at least a portion, for example, a major or minor portion, of its length. In other words, the central longitudinal axis may itself be defined by a wave function such as one of those defined above, so that the channels themselves are undulating, wavy or twisted. in their axis or longitudinal direction (e). In many embodiments of the invention, the channels within the network or each respective network may be substantially equidistant.
[0007] In many practical embodiments of the present invention, the component to be cooled and including the slit through which the coolant passes to effect cooling of the portion may be any engine component that utilizes a coolant. slot-based internal cooling arrangement. In many practical examples the component may be a bearing surface section component, such as a turbine blade or a guide vane. In such cases, the first and second walls which define the at least one passage for the supply of cooling fluid, which in many examples can also define the side walls of the slit of the part to be cooled, can be constituted by a suction wall and a pressure wall of the bearing surface section, and may further define the leading and trailing edges of the bearing surface. In addition, in many practical embodiments of the present invention, the portion of the component to be cooled and including the slot through which the coolant passes to effect cooling of the portion may be any portion of the component which utilizes such a slit-based cooling arrangement to effect cooling thereof, in particular for cooling one or more side walls, for example a pair of two opposite side walls thereof. this. In many embodiments, this portion of the component may often be a trailing edge portion thereof, which in the case of airfoil section motor components such as turbine blades and guide vanes present often practical challenges for effective internal cooling thereof for the reasons mentioned above. However, the embodiments of the invention may be applied also to other parts of airfoil-section components or other engine components that likewise utilize a slot-based cooling arrangement for cooling purposes. of these, in particular for cooling one or more side walls (s) thereof. More particularly, embodiments of the invention may be more useful in cooling arrangements where specific or customized control of pressure losses and / or heat flux and / or cooling fluid mass flow through a slot-based cooling arrangement may be desirable or necessary.
[0008] As already mentioned, in particularly preferred embodiments of the invention, the slot may comprise first and second side walls, preferably opposite and facing each other, which have first and second surface profiles. respective ones defining respective first and second networks of channels for the passage of cooling fluid, for example cooling air, therethrough, wherein each of said first and second surface profiles is corrugated and the channels of the first network. are oriented so as to be nonparallel to the channels of the second network. In some of these preferred embodiments, the channels in the first array may be generally oriented with their longitudinal axes at a first angle to the radial direction of the component (i.e., radial to an axis of the engine in which the component is to be installed) and the channels in the second network may be generally oriented with their longitudinal axes at a second angle to the radial direction of the component, where the first and second angles are each greater than 0 ° and less than 180 ° with respect to said radial direction (the two angles being defined on the same axial side of this radial direction), and the first and second angles are different from each other, it is that is, not equal. The difference between said first and second angles may be referred to as the "included angle" for convenience.
[0009] In various practical embodiments, the included angle may be selected from variable values thereof, as desired or necessary, to assist in controlling the cooling fluid mass flow rate through the respective channels. and thereby to help control the overall flow of cooling fluid through the slot itself. However, as a typical example, one of the first and second angles may be in the range of about 30 ° to about 60 ° with respect to said radial direction, and the other of the first and second angles may be in the range of about 120 ° to about 150 °, which gives an included angle in the approximate range of about 60 ° to about 120 °. Of course, however, other values of first angle, second angle and included angle may be appropriate. By increasing the included angle to higher values, for example to a higher value within the preferred range above, it may be possible in some embodiments to thereby reduce the flow of cooling fluid. inside the slot causing additional pressure loss due to the interaction between the individual streams of coolant in the two channel networks. This reduced flow can also be used to increase the degree of temperature increase of the coolant as it flows through the slot, which can increase the overall convective cooling efficiency of the coolant. arrangement. In addition or alternatively, the height (or depth) and / or the width of the channel or each channel in one and / or the other of the first and second networks can be chosen from among such values. Such variables, again as desired or necessary, to further assist in controlling the mass flow rate of coolant through the respective channels, and hence the overall flow rate of coolant through the slot. In some of the particularly preferred embodiments defined above comprising respective first and second networks of channels formed by the surface profiles of the first and second side walls of the slot, the distance transversely crossing the slot between the peaks. of the channel definition surface of the first network and the peaks of the channel definition surface of the second network may be selected from such variable values thereof, so that a transverse deviation or separation (e) minimum (e) between the first and second networks is chosen to be of a predetermined value. In some embodiments, this value may for example be zero, in this case, the peaks of the channel definition surface of the first network and the peaks of the channel definition surface of the second network may join or abut or may even be united or joined together or may even be confused, while in other embodiments, this value may be, for example non-zero, in this case the peaks of the channel definition surface of the first network and the peaks of the channel defining surface of the second grating may be spaced from each other by any suitable distance (for example, a short distance, such as about 0.01 or 0.05 or 0.1 mm at about 0.2 or 0.5 or 0.7 or 1.0 or 2.0 or 3.0 mm, or even perhaps greater than 3.0 mm) to define a gap between them. This selection of any separation or gap between the respective peaks of the respective channel-defining surfaces of the first and second networks can further be exploited to further assist in controlling the mass flow of cooling fluid through them. respective channels, and thus the overall flow of coolant through the slot. If desired or necessary, in cases where such separation or deviation exists between the respective peaks of the respective channel-defining surfaces of the first and second networks, one or more may be provided, in particular a plurality of base members in said gap for connecting or joining the respective channel peaks. In this way, the structural integrity of the arrangement can be improved. A particularly useful feature of various preferred embodiments of the invention is that the shape and configuration of the channels in the first and second gratings in the respective first and second side walls of the slot are such that cooling flowing in any given channel (s) (or one or more selected channels / channels) from, respectively, the first or second networks is forced or pushed or encouraged to switch or Deflecting the flow in a respective channel, respectively, of the second or first network, as the case may be, as the coolant flows through the slot from its upstream end to its downstream end. Thus, a resultant "reflection" of the cooling fluid flow direction, from a channel in a side wall of the one-channel slot in the opposite side wall, can occur as it flows through the slot.
[0010] This increased interaction between the respective fluid flows in the first and second channel networks may further contribute to the increase in pressure loss in the fluid flow as it passes through the slot, further reducing Its flow rate therethrough further enhances the heat extraction from the portion of the component to be cooled as the coolant flow passes through the channels in the slot. In order to further improve this phenomenon of switching, deflection or reflection of the cooling fluid as it flows along the channels of the respective network (s), and / or even when flows out of the respective channel network (s) and / or into a portion of the slot downstream of the channel network (s), in some embodiments of the invention, at least one one of the slit sidewalls (or any part thereof), and / or preferably at least one or more of the channels themselves in one and / or the other of the arrays, may / may be provided with at least one deflector member configured to deflect or change the direction of flow of a coolant stream when it reaches or abuts the latter; during its passage through the respective channel (s) and / or through the slot. In some embodiments a plurality of baffle members may be provided in each, or at or near the outlet mouths of, at least some of a plurality of channels (e.g. in a corresponding valley or valley). ) in one and / or the other of the networks, for example, spaced longitudinally along the respective channel, in order to bring the direction of flow of a flow of cooling fluid passing through these to be deflected or changed several times when it comes on or against the elements as it passes through the channel / channels and / or the slot. In general, it may be preferable for the number of such "reflections" or coolant flow direction changes as it passes along the channels and through the slot to be as large as possible or as much as possible. suitably accommodating, in order to maximize the overall pressure drop in the cooling fluid stream as it passes through the slot and thereby improve the overall cooling efficiency of the arrangement. The or each baffle element can have any suitable size, shape, configuration, location and positioning in the slot or channel, as the case may be, in order to most suitably control and perform a desired deflection or reflection behavior of the coolant flow when it comes on or against it. The or each deflector element may for example be provided within a respective channel, for example, with at least a portion of the element in a low or hollow region of the channel. Alternatively, the or each baffle member may be provided with at least a portion thereof protruding from a sidewall of the respective channel and within that channel, and / or even at the within another channel, in particular a channel of a respective network different from this respective channel. In another variant, the or each deflector member may be provided with at least a portion thereof projecting from a side wall of the slot itself or a portion thereof. not actually containing the channel (s), for example with at least a portion of the baffle element protruding either (i) in a respective channel to interact with a flow of coolant therein or out of the or, (ii) in a region of the slot adjacent to and downstream of the outlet or outlet mouth of one or more respective channels / channels to interact with a flow of cooling fluid after it's gone out of it. In the latter case, and where a plurality of these baffle members are provided, they may be located in a spaced-apart configuration in the radial direction of the component. Suitable forms of deflector members may include, for example, one or more walls, ribs, shoulder (s), tab (s), buttress (s), plate (s), flat (s) or other similar formations. In the case where one of these deflector elements has a generally elongated shape or extent, it may be substantially straight, or alternatively arcuate, curved, inclined ( s), twisted (s) or any other appropriate configuration, depending for example on the overall geometry of the arrangement and the available space. In embodiments in which they are provided, said at least one baffle member (s) may preferably be integrally formed with the respective slot side wall or the baffle member (s). respective channel on or in which they are located. In embodiments in which they are provided, said one or more baffle element (s) may further serve to increase the strength of the respective lateral wall (s). ) and they can also increase the heat flow between the side walls defining the slot, which helps to reduce the thermal stresses therein. In some embodiments of the invention, at least one or more of the channels of the network or at least one respective network may each have a downstream portion, in particular an end portion, which has a longitudinal direction which is different from that of a major upstream part of it. In some of these embodiments, the respective channel (s) may comprise a downstream end portion that is configured to cause the flow of coolant fluid therein to exit the channel (s) at an angle predetermined exhaust, in particular a predetermined exhaust angle with respect to the general longitudinal flow direction of the fluid through the slot or alternatively with respect to a flow direction of the gas or other fluid external to the component at the or in the vicinity of the slot outlet. This feature can be used to improve the film cooling effect of coolant flow after it exits the slot. Alternatively or additionally, in some embodiments, at least some of the channels of one of the gratings may terminate at or near the exit of the slot by respective mouth portions which each combine together. with corresponding respective mouth portions of at least some of the respective channels of the other one of the arrays so as to form respective escape openings having a predetermined shape and / or geometry. For this purpose, in some forms the respective mouth portions of the channels of the network may be substantially of the same shape as the respective mouth portions of the channels of the other array, with two respective sets of mouth portions which are either substantially in phase or out of phase with each other, or alternatively, partially in phase or partially out of phase. In this manner, respective exhaust openings having a predetermined shape and / or geometry can be created by the relative degree of phase or phase shift alignment and / or shaping of the respective mouth portions of the channels. each of the networks. However, in other forms of the respective mouth portions, channels of at least one of the networks may have a shape or configuration modified from that of the main channel bodies of that network, in order to further provide more flexibility in choosing an optimal shape and / or geometry for the respective exhaust openings. This modified shape or configuration may even be, for example, a shape different from the shape of the respective respective mouth portions of the channels of the other of the gratings, which provides even more flexibility in adapting the shape and / or the geometry of the exhaust openings. Thus, in general, the shape and / or overall geometry of the respective exhaust apertures can be selected to generate a coolant exhaust stream or jet out of the slot, with particular desired flow characteristics, e.g. flow rate, direction, cross-sectional shape or area, or other aspects of flow geometry. In practice, therefore, the shape and configuration of the respective mouth portions of the appropriate channels can generally be adapted to optimize the exhaust flow geometry and thus the film cooling efficiency as the flow exits the slot. . Further, in some embodiments the arrangements of the two opposite sides of the slot outlet may be of different shape, for example, in order to adapt and optimize the respective cooling effects of the cooling air flow. when parts of it come out of the slot on opposite sides of it. In certain embodiments of the invention, it may be possible to further improve the cooling effect by film of cooling fluid passing along the channels within the slot by providing in the portion of the component to cooling one or more through holes in one or more of the slit sidewalls, wherein the through hole (s) allows / allow a portion of the coolant in channels of one or more of the arrays to flow therefrom through the slot side wall to an outer surface (e.g., the outer wall surface of the suction side) of the component in order to perform 3029959 18 film cooling on this outer surface. said one or more through hole (s) can be located in any desired or appropriate longitudinal location along the slot, particularly at any longitudinal position along the portion of the slot which contains said one or more network (s) of channels therein. For example, said one or more through hole (s) may be usefully located in a region of the slot containing a downstream portion, for example, a half or other major or minor portion downstream , of this longitudinal part of the slot which contains said one or more network (s) of 10 channels in it. The number of said one or more through hole (s) may be arbitrary and these may be oriented at any suitable angle, for example inclined at an acute angle to the general longitudinal direction of the slot, for facilitate the flow of cooling fluid therefrom when the main coolant flow passes along the main volume of the slit. This feature of one or more through hole (s) may be useful in arrangements where it is expected that the temperature of the coolant may increase significantly as it passes through the slot due to the increased degree of cooling. heat transfer resulting from the improved geometry of the arrangement. In this situation, the provision of such "short" through holes in the slit side wall (s) may help to deliver a low temperature coolant directly to the exit of the slit. In the practical implementation of the embodiments of the invention, the channels of the or each grating may be formed in the respective slot side wall by various techniques. In a manufacturing process, which may optionally be used in less preferred embodiments, although it is still possible within the scope of the invention, the channels in the or each array may be formed by casting, preferably by casting integrally with the main body of the respective side wall. Thus, in these embodiments the channels of the or each array may constitute, and may be formed as, a particular integral surface pattern extending in and / or out of the general plane of the respective slot sidewall and formed of one piece with this one.
[0011] However, in an alternative manufacturing method, which may advantageously be used in more preferred embodiments, the channels in the or each array may be formed as an integral member of the respective slot side wall by a method of layer deposition (or layered additive manufacturing process (ALM), as it is sometimes called), for example the one known as direct laser deposition.
[0012] In this technique, a powder of the material from which the sidewalls, and therefore also the channels therein, are to be made of, for example, particles of a metal alloy, is applied to a substrate or core. or a previously applied or formed layer thereof, and then subjected to laser radiation to melt or fuse the powder at an elevated temperature and bond it to the underlying substrate or layer. These ALM methods, techniques and apparatuses are in principle well known and widely available in the art, and will be well understood and easily put into practice by those skilled in the art. In certain other embodiments of the invention, the trailing edge slot may itself be conical in its general longitudinal (flow) direction, so that its average width decreases from its upstream end to its downstream end. In such embodiments, the part (s) or region (s) of the respective slot side wall (s) which contains / contain the respective lattice (s) ( s) of channels, i.e. which define the corrugated slot portion, may extend sufficiently far upstream to extend into that portion of the slot which widens with increasing of width, whereby the general planes of the opposite side wall portions which define the resultant corrugated slot portion are substantially non-parallel with the width of the increased corrugated slot section 25 crossing a direction upstream thereof. This feature may be particularly useful in the case of an ALM process being used for the manufacture of the component, where it can generally be advantageous to be able to extract or remove excess, remaining powder, or waste materials. this after the formation of the fluted side walls by such an ALM process: the resulting widened (i.e. widened) width of the slot at the point of entry into the downstream region thereof containing the The channels formed by ALM can thus facilitate access to this downstream region and thus the elimination of unused powder or waste thereof. As already mentioned, the present invention and its embodiments may be applied to any portion of another motor component or airfoil section that utilizes a slot based cooling arrangement to effect its cooling. In many applications, the portion of the component to which the invention is applied may be a trailing edge portion of a bearing surface section component such as a turbine blade or a guide blade, although can be applied to other parts of these components too. In addition, the invention and its embodiments may be applied to other motor components apart from the bearing surface section components, and indeed in some embodiments the invention may be applied to various other types of motor component 10 which also utilize a slot-based cooling arrangement to effect cooling thereof. Within the scope of this application, it is expressly contemplated that the various aspects, embodiments, examples and variants, and in particular the individual features thereof, appearing in the preceding paragraphs, in the claims and / or in the following drawings and description may be taken independently or in any combination. For example, the features defined or described in connection with an embodiment are applicable to any embodiment and all embodiments, unless otherwise indicated, or to the extent that such features are inconsistent. Embodiments of the invention will now be described in detail, by way of example only, with reference to the accompanying drawings, in which: Figure 1 is an isometric exploded view of a typical cooled gas turbine engine. , single stage showing guide vanes, turbine rotor vanes, platform structures and other components; FIG. 2 is a cross-sectional view of a representative example of a typical load-bearing section component such as a guide vane, showing, among other things, its trailing edge portion at which the various embodiments of the invention can be applied; Figure 3 is a perspective view of a bearing surface component according to an embodiment of the invention; Figure 4 (a) is an exploded perspective view of the airfoil component of the embodiment of Figure 3, showing the arrangement of channels formed in the inner wall of the suction side of the airfoil; Figure 4 (b) is another perspective exploded view, from the direction opposite to that of Figure 4 (a), of the same airfoil component of Figure 3, showing the arrangement of formed channels. in the inner wall of the pressure side of the airfoil; Figure 5 is an enlarged fragmentary partial fragmentary sectional view of area A5 of the airfoil component shown in Figure 4 (a), illustrating the included angle between the channels in the interior walls of the side walls. suction and pressure of the bearing surface; Figure 6 is an explanatory sectional view of a wavelength of the side wall surface profile which defines the various channels; Figure 7 (a) is a generalized end perspective view (from the trailing edge end) of the bearing surface component of Figures 3 and 4; Figures 7 (b), (c), (d) and (e) are various enlarged end perspective views, in accordance with various alternative embodiments of the invention, of the component area A7 as shown in FIG. FIG. 7 (a) shows various exhaust outlet configurations through which the cooling air exits the trailing edge slot, which exhaust outlets are formed by the combination of various mutual configurations of parts of the mouth of opposing channels in the exit region of the slot; FIGS. 8 (a) and 8 (b) are respectively enlarged turned end views of the mutual configurations of the opposed channel mouth portions in the slot exit regions of the arrangements shown in FIG. (c) and 7 (b); Fig. 9 is an enlarged partial enlarged fragmentary sectional view of part of the slot sidewalls and a channel arrangement of another embodiment of a bearing surface component according to the invention; showing the various flows of cooling air being reflected between the respective networks of channels in the respective side walls by an arrangement of one or more "inner" deflector members, also showing the various flows cooling air when they exit the slot and arrive on and / or flow on or around one or more other (s) "external" deflector member (s) " arrangement; Fig. 10 (a) is an exploded perspective view of another embodiment of the bearing surface component, corresponding to that of Fig. 4 (a), but showing an alternative configuration of the channels in the inner wall. the suction side of the bearing surface slot; Figure 10 (b) is an enlarged partial exploded view of the area A1 0 of the airfoil component shown in Figure 10 (a), showing the alternative channel pattern, particularly in their exit regions, in more detail. ; FIG. 10 (c) is an exploded partial enlarged fragmentary partial view of the airfoil component as shown in FIG. 10 (b), showing the cooling air flows being redirected before exiting the slot. due to the fact that the respective channels are curved in this region of the slot; Fig. 11 is a partial exploded perspective view of another embodiment of the cooling arrangement according to the invention, showing the integration of cooling through holes in the wall of the suction side of the edge slot. leakage to improve the film cooling on the outside of this suction side of the component; and Figures 12 (a), 12 (b) and 12 (c) are cross-sectional views of three further exemplary embodiments, which may be particularly useful in the context of a load-bearing surface component manufactured by a layer layer additive / layer additive manufacturing method (ALM) in which the trailing edge slot sidewall regions which are provided with channel arrays extend various distances in that region of the leakage slot in which its width widens, whereby the removal of powder in excess thereof after the formation of channels by ALM can be facilitated. Figure 1 of the accompanying drawings is an isometric exploded view of a typical single-stage, cooled-gas turbine engine 1 showing the nozzle guide vanes (VGNs) 2 (with their respective bearing surfaces 3), rotor vanes; 4 (with their respective bearing surfaces 5), inner and outer platforms 6, 8, an HP turbine disk 10, and pre-rotation nozzles 12, as well as the cover plate and locking plates having an HP turbine support housing 14 and ring ring segments 16. The HPT 4 and VGN 2 blades are cooled using high pressure air (HP) from the compressor which has bypassed the combustion chamber and is therefore relatively cold compared to the gas temperature.
[0013] Typical cooling air temperatures are in the range of about 800 to about 1000 K. Gas temperatures may be greater than about 2100 K. Cooling air from the compressor that is used to cool Hot turbine components are not used fully to extract work from the turbine. Extraction of coolant flow therefore has an adverse effect on the operating efficiency of the engine. It is therefore important to use this cooling air as efficiently as possible. Thus, maximizing the cooling efficiency of any cooling airflow around, around or inside the components, particularly those based on an internal cooling arrangement, is a primary concern in the design of arrangements. cooling with optimized cooling efficiency. Figure 2 shows - as a representative, but typical example - a bearing surface section component, such as a guide vane 3, showing inter alia its trailing edge portion 40 at which the embodiments of the present invention can be applied. The trailing edge portion 40 includes a trailing edge slot 105 therein, through which slot 105 a coolant, e.g., cooling air, passes the internal cooling passage 3R (in this case the rear cooling passage 3R) to the outer trailing edge of the component. The flow of cooling fluid exiting the trailing edge slot 105 is designated 105F. Although the component here is shown as a guide vane 3, it should be understood that it may equally well be a turbine vane 4, or indeed any other component having a bearing surface inside the engine which relies on an internal cooling arrangement, in particular slot-based, for cooling at least a trailing edge portion of the component. In the exemplary component 3, 4 shown here, it comprises front and rear cooling passages 3R, each of which is supplied with cooling air, for example that designated 34 directed into the rear cooling passage 3R, through example, from an external source. In the exemplary component 3, 4 shown here, the rear cooling passage 3R has an impact plate 36 having holes therein through which cooling fluid air passes from the rear passage 3R to cool the side section. suction of the bearing surface. However, it should be understood that such an impact plate 36 is quite optional, and many alternative internal cooling arrangements of the main body of the airfoil that employ one or more internal wall (s) (s). ) additional (particularly perforated wall (s)), one or more impact tube (s) or plate (s), or even other inserts in the various cooling passages, may be possible . Embodiments of the present invention described further below relate to the trailing edge portion 40 of the airfoil component 3, 4. In all the remaining drawings mentioned below, the same or corresponding characteristics in the 10 various embodiments are designated by the same reference numbers throughout the document for simplicity. Although the embodiments described further below and illustrated in the drawings relate to a trailing edge portion of a bearing surface component such as a turbine blade or a guide vane, it should be understood that The invention is not exclusive to these and other embodiments of the invention may be applied to cooling arrangements for other parts of such airfoil components or even to cooling arrangements for other purposes. other motor components apart from the components having a bearing surface section.
[0014] According to a first embodiment of the invention, as shown in Figures 3, 4 (a) and 4 (b), a bearing surface component 3, 4 comprises walls on the suction and pressure side 100 , 110, respectively. The trailing edge portion 40 of the component 3, 4 comprises a "transversely corrugated" portion 105C which includes a first channel array 102 formed in the inner wall of the suction side 100 of the bearing surface trailing edge slot. 105 in the slot portion 105C. The downstream portion of the transversely corrugated slot portion 105C is an exit slot portion 105E that does not include such transversely corrugated channels therein. As shown in Figure 4 (b), a second channel network 112 is formed in the inner wall of the pressure side 110 of the airfoil in the slot portion 105C. Each channel array 102, 112 is a set of straight, equidistant, parallel, repetitive waves on or in the respective surface sidewall of the slot section 105C. By way of example only, a typical scale of dimensions for a typical turbine blade or guide vane can employ a combined total depth of first and second channels 102, 112 in the range of about 0.3 to at about 1.0 mm, for example, about 0.6 mm. As is more clearly shown in Figure 5, the first channel network 102 (defining first cooling air streams 102F) is at a first inclination angle 102a relative to the radial direction R of the component (this is that direction which is radial with respect to the longitudinal axial direction of the engine when the component is mounted therein), and the second channel network 112 (defining second cooling air streams 112F) is at a second angle inclination 112a with respect to this radial direction. The first and second angles 102a, 112a are different, so that an included angle α is defined between them, as shown in Figure 5. In this way, the two channel arrays 102, 112 are oriented so as to be inclined at an angle to one another, and so that the peaks of the channels 102, 112 of one network periodically overlap or cross the peaks of the channels 112, 102 of the other network. The included angle α between the channels in the two arrays 102, 112 is a parameter that can be varied to control the flow parameters, particularly flow rate and flow direction, of the cooling air that flows in and along the various channels 102, 112 within the slot 105. For example, an increase in the included angle may be used to reduce the flow of cooling air through the slot 105 causing additional pressure losses due to the interaction between the individual air flows in the two sets of channels 102, 112. This reduced flow rate also increases the temperature increase of the cooling air 25 when it passes through the slot 105, which can lead to increased overall efficiency of the convection cooling process. FIG. 5 shows, as a representative example, examples, (i) of a first cooling air flow 102F reflected at a baffle wall 148 "internal" (i.e. in the transversely corrugated portion 105C of the slot 105) in the slot 105 and (ii) another first cooling air stream 102F arriving at and / or submerging an outer baffle rib member 150 "(c that is, outside the transversely corrugated portion 105C of the slot 105) in the slot exit portion 105E. These features will be discussed further below in connection with the embodiment shown in FIG. 9.
[0015] The pitch and pitch of the channels 102, 112 may also vary and may be independently selected, with other variable parameters as discussed herein, to optimize throughput, direction, and possibly other flow parameters. Further, a preferred form of each channel is that defined by a sine wave function, an example of which is shown in FIG. 6. As shown here, each channel 102, 112 is preferably formed by sidewalls and peaks and valleys which are curved in a regular manner and have no sharp edges or sharp corners, in order to minimize or substantially avoid undesirable stress concentrations in the slot sidewalls or channels 102, 112 themselves. Various other mathematical wave functions may instead be used to define the shape of the various channels, examples of which have already been mentioned above. The cross-sectional shape of the channels may be yet another parameter which may be chosen to contribute to an overall optimization of the flow behavior of the cooling air as it passes along and through the slot 105. it is desired or necessary, for example, to further contribute to controlling the flow behavior of the cooling air - in particular the mass flow of cooling air - as it passes along and through the slot 105, the separation distance between the corrugations or channels on the suction side and the pressure side 102, 112 can also be varied and chosen to have an optimum value. Thus, the peaks of the channel formations of a network 102, 112 may, in some exemplary forms, join or come into abutment or even merge into peaks of the channels of the other network 112, 102, whereas in Other exemplary forms the respective sets of channel peaks may be separated from each other by a deviation or a separation distance of at least a predefined minimum value. This feature will be discussed further below in connection with the embodiments shown in Figures 7 (a) through (e). As shown by some examples in Figures 7 (a) and 7 (b) to (e), the open mouth portions of the various channels at their respective downstream ends may be adapted in their shape and / or configuration. to assist in controlling the cooling air outlet flow 35 as it exits the exhaust outlets thus formed at the downstream end of the corrugated slot portion of the trailing edge 105C. Figures 7 (b) to (e) 3029959 27 show various end perspective views, from the trailing edge 40 of the airfoil, of the generalized end perspective view of Figure 7 (a), showing various exhaust outlet configurations through which the cooling air exits from the trailing edge slot portion 105C, which exhaust outlets are formed by the combination of opposing channel mouth portions in the exhaust region. the downstream end of the slot portion 105C so as to have varying degrees of alignment or non-alignment (i.e. varying degrees being in phase or out of phase). For example: Figure 7 (b) shows the opposed channel mouth portions 102, 112 to be substantially in phase (and thus aligned), with the respective sets of peaks of the respective channel formations being separated by a gap relatively small separation 130; Figure 7 (c) shows the opposite channel mouth portions 102, 112 to be substantially out of phase (and thus out of alignment), with the respective sets of peaks of the respective channel formations substantially abutting or contacting each other. others without gap between them; Figure 7 (d) shows the opposite channel mouth portions 102, 112 to be substantially out of phase (and thus misaligned), with the respective sets of peaks of the respective channel formations being separated by a relatively large separation gap. 140; and Figure 7 (e) shows the opposite channel mouth portions 102, 112 to be substantially out of phase (and thus misaligned), but with the respective sets of peaks of the respective channel formations being united together or merged with each other. others, as at sites 144.
[0016] The arrangement shown in Figure 7 (b) is shown more clearly in Figure 8 (b), and that in Figure 7 (c) shown more clearly in Figure 8 (a). Figures 8 (a) and 8 (b) also illustrate, by way of example, exhaust outlet configurations that may help shape in particular the cooling air streams as they exit the 105C trailing edge corrugated slot. For example, the geometry shown in Figure 8 (a) tends to produce well-defined coalescence jets, exit air at the exit plane, while the geometry shown in Figure 8 (b) tends to to produce a more uniform output stream. It should also be noted that the exit jets here maintain a skew amount for a short distance beyond the limit of the slot exhaust apertures, so that optimum film coverage does not occur. may not necessarily be produced by the geometry shown in Figure 8 (a). The above-mentioned pressure drop which advantageously occurs when the cooling air passes through and along the various channels 102, 112 can also be controlled to a certain extent by the following inertial pressure losses when the Airflow changes direction at the respective slot sidewalls 100, 110 due to the cross-spatial relationship between the two channel networks 102, 112 (at the included angle a - see Figure 5). Thus, at the sides of the slot portion 105C the airflow is "reflected" from each side wall 100, 110 and switches from one channel network 102/112 to the other channel network 112 / 102. This behavior is shown schematically in Figure 9.
[0017] Particularly in the case of embodiments employing relatively low flow rate systems, this pressure loss can further be exploited by introducing, as shown in Figure 9, one or more longitudinal deflector walls (s). ) internal (s) 148 either in the channels 102, 112 themselves, or any gap between the respective slot sidewalls 20, or in any separation gap (as mentioned above) between the opposite peaks of the forming channels of respective networks 102, 112 in the corrugated portion of slot 105C. As shown in FIG. 9, the or each baffle wall 148 reflects the airflows 102F into the respective channels 102 of the first network when they arrive thereon so that they are reflected and deflected, as at the sites FR, to become respective airflows 112F in respective channels 112 of the second network. Optionally this pressure drop can be further exploited by further introducing, as also shown in FIG. 9, one or more longitudinal / longitudinal deflector rib member (s) 150 in a portion of the slot 105, particularly the non-waved portion 105E thereof, immediately downstream of the wavy portion of slot 105C. said one or more deflector rib member (s) 150 may be, for example, in the form of at least one elongated wall, rib, shoulder or flat of material which projects from within the slot portion 105E and on which the various air streams arrive and are deflected or redirected (or submerged) as they pass along and out of the respective channel (s) at the level of their respective exhaust outlets. Such an arrangement of a plurality of radially spaced deflector ribs 150 is illustrated by way of example in FIG. 9. The air flows corresponding to an impact on the respective deflector rib members 150 are designated FI and the air flows corresponding to submersion of the respective deflector rib members are designated FO. It will also be noted in FIG. 9 that, for example, the channels 112 in the pressure side wall 110 of the slot section 105C are at an angle to the radial direction of the R component (see FIG. 5) different and greater than that of the channels 102 in the wall of the suction side 100 of the slot section 105C. The steeper angle with respect to the radial direction R of the pressure wall channels 112 results in a reflection deflection with a higher angle of reflection and / or degree of impact (s), thus possibly improving the effect. pressure drop. Also shown in FIG. 9, by way of example, is the advantageous displacement of a hot air flow FH flowing on the wall of the outside pressure side 110 of the component somewhat away from this surface of wall of the outer pressure side in the trailing edge region of the component, as a result of the impact and submersion of the air flows FI and FO exiting the corrugated slot section 105C and interacting with the elements of the Deflector rib 150. This displacement effect can thus help to reduce the harmful heat transfer of such hot air flows FH outside the pressure side wall surface in the component leak edge region. . In addition to improving the inertial pressure losses, the presence of said at least one deflector wall (s) 148 and / or rib member (s) 150 may further serve to increase the mechanical strength of the wall (s). (s) respective slit side (s), and can also increase the heat flow from the pressure side to the suction side, or vice versa, of the trailing edge slot, which helps reduce the thermal stresses in it. The additional pressure loss caused by the interaction of the cooling air flows in the two channel networks 102, 112, and the inertial pressure losses that occur where the air flows change direction at the walls Slots and / or at the respective internal baffle walls 148, mean that the channels 102, 112 each with larger characteristic dimensions, e.g. pitch and / or ripple height (see FIGS. 8 (a)), may be capable of being used to achieve a particular pressure and mass flow rate of cooling air. This allowed increase in channel dimensions may also be useful in reducing the susceptibility of the arrangement, or the risk of channels 102, 112, to clogging, for example, through the accumulation of combustion deposits or other deposits (such as dirt, pollution or environmental residues) when using the engine. In addition, the wavy channels 102, 112 should not be limited to completely straight channels. In certain other embodiments, to provide better film cooling efficiency after the cooling air flows leave the trailing edge corrugation slot portion 105C, at least some of the channels in at least one one, and preferably both, of the arrays may be configured such that the flux escapes at a specific predetermined angle from the general longitudinal flow direction of cooling air through the trailing edge slot, or alternatively with respect to a flow direction of gas or other fluid external to the component at or near the slit exit at the trailing edge of the component. An example of this is shown in Figures 10 (a), (b) and (c), where the inclined flow direction 102F in the most upstream of each channel 102 curves (for example at the region 102B ) so as to become an output stream 102E which is oriented substantially parallel to the external gas flow outside the component adjacent to the exit of the slot portion 105C. Likewise, the oppositely inclined flow direction 112F in the most upstream portion of each channel 112 curves (e.g., at region 112B) to become an output stream 112E which is similarly oriented substantially parallel to the external gas flow outside the component adjacent to the exit of the slot portion 105C. In the previous embodiment illustrated in FIG. 10, the straightening of the channels as they approach their exhaust outlets, while remaining continuous and thus providing a generally uninterrupted air flow over its length, If desired, it is also possible to intrinsically increase the pitch of the channels as defined perpendicularly to the airflow direction (see FIGS. 6 and 8 (a)), thereby increasing the individual flow area of the channels in this direction. region and thereby helping to reduce the occurrence of channel blockage, for example, by deposits or debris.
[0018] Further, in certain other embodiments (not shown in the drawings), portions of at least some of the channels near their exhaust openings or outlets may, if desired, be shaped to create a flow. continuous and more uniform exhaust air as it exits the slot portion 105C in its entirety from the mouth portions of individual channels. This can be achieved for example by flattening the channels in the vicinity of their mouth portions. Of course, careful optimization of such flattening may be necessary to maximize the film cooling efficiency of the total exhaust air flow.
[0019] As shown in Figure 11, in another embodiment one or more, for example, a plurality or series of cooling through holes 160 may be provided in one (or possibly two) side walls, for example, particularly the suction side wall 100, the trailing edge slot 105 to improve the film cooling 20 outside this suction side 110 of the component. This may for example be useful for the purpose of providing a 160F "short" flow and exhaust path directly at the slot outlet for cooling the air passing through the slot which can be expected to increase very much. The temperature resulting from the improved degree of heat transfer resulting from the improved geometry of the internal air flow arrangement. Referring again to the embodiment of FIG. 11, the ability of the embodiments of the invention to adjust the mass flow rate and the pressure drop across slot 105 allows the possibility of using through cooling holes through suction surface film 160 near the trailing edge 190 of the component, as shown in Figure 11. Typically, the use of suction surface films near the back of a bearing surface This is often undesirable because of the tendency of the films applied to this region to rise quickly from the surface, which has a very negative effect on the aerodynamic efficiency. However, the use of such an embodiment of the invention as illustrated herein to reduce the pressure ratio across the film holes may cause the films to escape onto the suction surface with blow and momentum ratios sufficiently low to remain on this surface. Referring to Figs. 12 (a), 12 (b) and 12 (c), there are shown other arrangements of embodiments which may be particularly useful in the context of a manufactured bearing surface component. by a layer layer additive (ALM) deposition process. In each of these arrangements the longitudinal extent of the trailing edge slot 105 can be defined between maximum points W max and minimum W min, with the width of the slot becoming larger upstream from the latter to the first. In the arrangement shown in Fig. 12 (a), the regions of the trailing edge slot sidewalls 100, 110 which are provided with channel networks 102, 112 therein, i.e. side walls defining the corrugated slot portion 105C extend from a distance of up to, but substantially not within, the region 105W of the trailing edge slot 105 in which its width widens, that is, up to an upstream limit point as at El. In this manner, the general planes of the opposite side wall portions which define the resulting corrugated slot section 105C are substantially parallel. In the arrangement shown in Fig. 12 (b), the regions of the trailing edge slot sidewalls 100, 110 which are provided with channel networks 102, 112 therein, i.e. portions of the side walls defining the corrugated slot portion 105C extend a significant distance in the region 105W from the trailing edge slot 105 in which its width widens, and to an upstream limit point 25 as at E2. In this manner, the general planes of the opposite side wall portions which define the resulting corrugated slot section 105C are substantially non-parallel, with the width of the corrugated slot portion 105C increasing in an upstream direction. Also, in the arrangement shown in FIG. 12 (c), the regions of the leak edge slot side walls 100, 110 which are provided with channel networks 102, 112 therein, i.e. i.e. those portions of the sidewalls defining the corrugated slot portion 105C, extend a similar significant distance in the region 105W from the leakage slot 105 in which its width widens, and to an upstream limit point similar to E3 which can substantially correspond in terms of location at the E2 limit point in Figure 12 (b). Again, in this manner, the general planes of the opposing sidewall portions which define the resulting corrugated slit section 105C are substantially non-parallel, with the width of the corrugated slit portion 105C increasing in an upstream direction. However, in this latter arrangement of FIG. 12 (c) the height of one or more of the channels 102 ', 112' in one and / or the other of the networks (on one or both sides of the slot section 105C), in particular these channels 102 ', 112' at, towards or increasingly towards the upstream limit point E3, may have increased height or depth or increased height or depth in the direction of this limit point E3, to occupy or fill more than the internal transverse width of the trailing edge slot section 105C as its width widens in the region 105W. The arrangements shown in these three Figures 12 (a), 12 (b) and 12 (c) may be particularly useful in the context of load-bearing surface components manufactured by a layered layer additive (ALM) manufacturing process. as it allows excess powder or other manufacturing debris to be more easily removed from the trailing edge slot after formation of the various channels in the environment limited spatial area of this component region. If desired or necessary in one of the foregoing embodiments described and illustrated with reference to the accompanying drawings, one or more, for example, a series or a plurality of notches, teeth or crenellations may be provided at the or on a lip of the slot outlet, in order to further modify the mixing properties between the cooling air stream exiting the slot and the main stream flow of gas outside the component and wherein the Outgoing cooling air flows out of the slot. It should be understood that the above description of the embodiments and aspects of the invention has been given solely by way of non-limiting examples, and various modifications may be made from what has been specifically described and illustrated. while remaining within the scope of the invention as defined in the appended claims. Throughout the description and claims of this specification, the terms "include" and "contain" and variations of the terms, for example "including" and "include" mean "including but not limited to", and are not intended to (and not) exclude other fragments, additives, components, integers or steps.
[0020] Throughout the description and the claims of this specification, the singular includes the plural unless the context opposes it. In particular, when the indefinite article is used, the specification must be understood as considering plurality as well as singularity, unless the context opposes it. In addition, the features, integers, components, elements, features or properties described in conjunction with a particular aspect, embodiment or example of the invention should be understood to be applicable to any other aspect, embodiment or example described herein, unless they are incompatible with them. 15 20 25 30

权利要求:
Claims (17)
[0001]
REVENDICATIONS1. Component (3, 4) for a gas turbine engine, comprising first and second walls (100, 110) defining at least one passage (3R) for supplying cooling fluid to a portion (40) of the component to be cooled, said a portion (40) comprising a slot (105) through which the passage coolant (3R) passes an outlet of the slot (105) for cooling the portion (40), wherein the slot (105) comprises at least one side wall (100, 110) having a surface profile defining an array of channels (102, 112) for the passage of cooling fluid therethrough, and wherein the surface profile defining said channel network (102, 112) is corrugated.
[0002]
The component of claim 1, wherein the slot (105) comprises a first sidewall (100) having a first surface profile defining a first channel array (102) for passage of coolant therethrough , and a second side wall (110), opposite the first side wall (100), having a second surface profile defining a second channel array (112) for the passage of cooling fluid therethrough, wherein each said first and second surface profiles are corrugated and the channels of the first array (102) are oriented so as to be nonparallel to the channels of the second array (112).
[0003]
The component of claim 1 or 2, wherein the or each surface profile of the slot side wall or respective slot side wall (100, 110) is defined by a regular wave-shaped curve that changes direction in at least a portion of its pitch, wherein the sectional profile of the surface forming each channel (102, 112) of the respective grating is such that a tangent to the channel defining surface perpendicular to the longitudinal channel direction, has an orientation angle which varies, with respect to the general plane of the respective side wall (100, 110), substantially continuously over at least a portion of its curve between one side of the channel (102 , 112) and an opposite side thereof.
[0004]
The component of claim 3, wherein the channels (102, 112) in the respective sidewall surface or sidewall surface (100, 110) are defined by a substantially borderless surface profile. or wedge having an inclined boundary between two adjacent surface portions thereof. 5
[0005]
The component of claim 3 or 4, wherein the wave function defining the or each corrugated surface profile defining the respective channels (102, 112) is a waveform defined by a mathematical function or a combination of two or more mathematical functions that define / define a regular repetition wave having a substantially constant amplitude and / or wavelength.
[0006]
The component of claim 5, wherein the wave function defining the or each corrugated surface profile defining the respective channels (102, 112) is selected from a sinusoidal wave function, a polynomial wave function, an exponential wave function, or a combination of two or more different shape or wave functions, each defining a region or a different part of the curve defining the surface profile of a given channel (102, 112). 20
[0007]
7. Component according to one of the preceding claims, wherein: the channels (102, 112) within the or each respective network are substantially parallel to each other, and / or the channels (102, 112) to within the or each respective network are substantially equidistant. 25
[0008]
A component according to any one of claims 2 to 7, when dependent on claim 2, wherein the channels in the first array (102) are generally oriented with their longitudinal axes at a first angle (102a) relative to to the radial direction of the component and the channels in the second array (112) are generally oriented with their longitudinal axes at a second angle (112a) with respect to the radial direction of the component, wherein the first and second angles (102a, 112a) are each greater than 0 ° and less than 180 ° with respect to said radial direction, the two angles (102a, 112a) being defined on the same axial side of this radial direction, and the first and second angles (102a, 112a) are different from each other. 3029959 37
[0009]
The component of claim 8, wherein the difference between the first and second angles (102a, 112a) is an included angle of from about 60 ° to about 120 °. 5
[0010]
A component according to any one of claims 2 to 9, when dependent on claim 2, wherein a distance transversely traverses the slot (105) between peaks of the channel defining surface of the first network (102). ) and peaks of the channel definition surface of the second array (112) are selected from such variable values thereof, so that a minimum gap or cross separation (e) between the first and second networks (102, 112) is chosen to be of a predetermined value.
[0011]
11. A component according to any one of claims 2 to 10, when dependent on claim 2, wherein at least one of the slot sidewalls (100, 110) and / or at least one or more of channels (102, 112) themselves in one or both of the networks is / are provided with at least one deflector member (148, 150) configured to reflect, deflect or change the direction of flow of a cooling fluid stream when it arrives thereon or against it during its passage through the respective channel (s) (102, 112) and / or through the slot (105).
[0012]
The component of any one of claims 2 to 11, when dependent on claim 2, wherein: (i) at least one or more of the channels (102, 112) of the network or at least one of respective network each have a downstream portion (102E, 112E) which has a longitudinal direction which is different from that of a major portion, upstream (102F, 112F) thereof; and / or (ii) at least some of the respective channels (102, 112) in one of the networks terminate in respective mouth portions which each combine with respective mouth portions corresponding to least some of the respective channels (112, 102) of the other of the arrays so as to form respective escape openings having a predetermined geometry and / or shape. 3029959 38
[0013]
13. Component according to one of the preceding claims, which is manufactured by a method selected from a casting process or a layered additive manufacturing process or layered deposition. 5
[0014]
14. Cooling arrangement for a component (3, 4) of a gas turbine engine, wherein the component (3, 4) comprises first and second walls (100, 110) defining at least one passage (3R) for supplying cooling fluid to a portion (40) of the component to be cooled, said portion (40) comprising a slot (105) through which the cooling fluid passes from the passage (3R) to an outlet of the slot (105) for cooling the portion (40), wherein the cooling arrangement comprises at least one side wall (100) of the slot (40) which has a surface profile defining a network of channels (102) for the passage of cooling fluid therethrough, and wherein said surface profile defining said channel network (102) is corrugated; and optionally wherein the cooling arrangement comprises a first side wall (100) of the slot (105) having a first surface profile defining a first channel network (102) for the passage of cooling fluid therethrough ci, and a second side wall (110), opposite the first side wall (100), having a second surface profile defining a second channel array (112) for the passage of coolant therethrough, wherein each of said first and second surface profiles is corrugated and the channels of the first array (102) are oriented so as to be non-parallel to the channels of the second array (112).
[0015]
A gas turbine engine comprising at least one component (3, 4) according to any one of claims 1 to 13, or at least one component (3, 4) having a cooling arrangement according to claim 14.
[0016]
16. A method of cooling a portion of a component (3, 4) of a gas turbine engine during operation, wherein the component (3, 4) comprises first and second walls (100, 110). ) defining at least one passage (3R) for supplying cooling fluid to the portion (39) thereof, said portion (40) including a slot (105) through which the coolant passes from the passage (3R) at an outlet of the slot (105), wherein the slot (105) comprises at least one side wall (100) having a surface profile defining an array of channels (102) for the passage of coolant through the one and in which the profile of the surface defining said channel network (102) is corrugated, wherein the method comprises, during the operation of the motor, the passage of the cooling fluid from the passage (3R) to the outlet of the slot (105) through the slot (105) so that the coolant does not along said corrugated channel network (102) in the at least one sidewall (100).
[0017]
The method of claim 16, wherein the slot (105) comprises a first side wall (100) having a first surface profile defining a first channel network (102) for the passage of cooling fluid therethrough. ci, and a second side wall (110), opposite the first side wall (100), having a second surface profile defining a second channel array (112) for the passage of coolant therethrough, wherein each of said first and second surface profiles is corrugated and the channels of the first array (102) are oriented so as to be non-parallel to the channels of the second array (112) wherein the method comprises, during operation of said motor, the passing the cooling fluid from the passage (3R) to the outlet of the slot (105) through the slot (105) so that the coolant passes along said first and second channel networks corrugated profiles (102, 112) in the respective first and second sidewalls (100, 110), and optionally the method comprises passing the cooling fluid from the passage (3R) to the outlet of the slot (105) through the slot (105) so that the cooling fluid passes along said first and second corrugated channel networks (102, 112) in the respective first and second side walls (100, 110) while further passing between at least one or more channels / channels (102) of the first network and at least one or more channels / channels (112) of the second network. 35

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同族专利:

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公开号 | 公开日

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GB2533315B|2017-04-12|

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GB2533315A|2016-06-22|

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DE102015015598A1|2016-06-16|

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US10196901B2|2019-02-05|

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US20160169003A1|2016-06-16|

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法律状态:
2016-12-27| PLFP| Fee payment|Year of fee payment: 2 |

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2017-06-16| CA| Change of address|Effective date: 20170517 |

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2017-12-22| PLSC| Search report ready|Effective date: 20171222 |

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2017-12-27| PLFP| Fee payment|Year of fee payment: 3 |

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2019-12-26| PLFP| Fee payment|Year of fee payment: 5 |

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2021-06-25| RX| Complete rejection|Effective date: 20210520 |

优先权:

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申请号 | 申请日 | 专利标题

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GB1422322.6A|GB2533315B|2014-12-16|2014-12-16|Cooling of engine components|

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