![]() STATOR AUBING SECTOR OF A TURBOMACHINE
专利摘要:
A turbomachine stator blasting sector comprising at least two adjacent blades (10, 11), an outer plate (18) which connects the outer ends of the blades, and an inner plate (16) which interconnects the blades inner ends of the blades, wherein at least one first channel (24, 26, 28, 29) is formed in the outer plate (18) and / or the inner plate (16), the first channel and the plate being adapted to allow when the turbomachine is operating, a heat exchange between a hot fluid flowing in the first channel and a cold air flow passing between the blades. 公开号:FR3028575A1 申请号:FR1461200 申请日:2014-11-19 公开日:2016-05-20 发明作者:Matthieu Leyko;Christian Vessot 申请人:SNECMA SAS; IPC主号:
专利说明:
[0001] TECHNICAL FIELD The present invention relates to the field of heat exchangers installed in turbomachines. The invention also relates to the stator vanes which equip such turbomachines. The invention applies to any type of turbomachine, terrestrial or aeronautical, and in particular to an aircraft engine such as a turbojet or a turboprop. BACKGROUND The oil circuit of an aircraft engine provides the dual task of lubricating the rotating parts of the engine and removing the heat released in the engine. To cool the oil, the temperature of which generally does not exceed about 200 ° C for reasons of efficiency, different types of heat exchanger exist. Some heat exchangers use air as a cold source. These are oil / air heat exchangers or "ACOC" for "Air Cooled Oil Cooler". Two types of oil / air exchangers are usually used: block exchangers and finned exchangers. The finned exchangers (or "surface cooler" in English) have a generally rectangular surface on which are fixed, on one side of the surface, flow channels for the oil and, on the other side of the surface , blades or metal fins for the flow of air. The heat can thus be transferred from the hot oil to the metal blades by thermal conduction, these fins cooling in contact with the air. This type of exchanger is usually placed directly on the walls of a vein of air from the engine. In a double flow turbojet, the cold air in the vein of the secondary flow is generally used for oil / air heat exchange. [0002] 302 8 5 7 5 2 Block exchangers (or "brick cooler" in English) conventionally consist of a stack of metal plates traversed by the fluid to be cooled. These plates are spaced from one another and metal lamellae are placed between these plates, which are generally welded. The plates are supplied with fluid by orthogonal distributor pipes to these plates. The oil and air circuits remain segregated. The whole is placed in a stream of air, either directly in the vein or in a channel fed by a scoop. The aforementioned exchangers have the disadvantage of adding surfaces 10 rubbed (fins or plates) in the air flow and, therefore, generate significant pressure losses that penalize the performance of the engine. Finally, patent document WO 2013150248 A1 describes a stator blade of a turbomachine formed by a plurality of parts arranged relative to one another to define air flow passages between these parts. Oil to cool circulates in channels in the different parts of the blade. Although satisfactory, this solution is relatively complex. GENERAL PRESENTATION The present disclosure relates to a stator blading sector of a turbomachine. This sector comprises at least one blade, an outer plate (also called "platform") connected to the outer end of the blade, and an inner plate connected to the inner end of the blade. By "stator vane sector" is meant a portion of the stator vane of a turbomachine. This part comprises a number of vanes and is delimited, internally and externally, by trays (also called platforms, or walls) extending in the circumferential direction of the vane and connecting the ends (inner / outer) of the vanes between them. The number of blades of a blading sector 30 is greater than or equal to one and less than or equal to the total number of vanes of the blading. [0003] In general, in the present description, the axial direction corresponds to the direction of the axis of rotation of the rotor of the turbomachine, and a radial direction is a direction perpendicular to this axis. Likewise, an axial plane is a plane containing the axis of rotation of the rotor, and a radial plane is a plane perpendicular to this axis. The circumferential direction corresponds to the direction of the circumference of the stator vane of the turbomachine. On the other hand, unless otherwise stated, the adjectives "inner" and "outer" are used with reference to a radial direction so that the inner (ie radially inner) part of an element is closer to the axis of rotation than the outer (ie radially outer) part of the same element. Finally, upstream and downstream are defined with respect to the normal flow direction of the fluid (from upstream to downstream) between the stator vanes. [0004] At least one such blading sector is used as a heat exchanger and at least one first channel is formed in the outer plate and / or in the inner plate, the first channel and the plate being adapted to allow, when the turbomachine is running. a heat exchange between a hot fluid circulating in the first channel and a cold air flow 20 passing through the stator vane (ie passing between the vanes of the vane). In what follows, "air" means any gas that can be used as an oxidant in a turbomachine. In general, the heat exchange between the hot fluid and the cold air flow depends on the distance between the first channel and the surface of the plate licked by the cold air flow, as well as the thermal conduction of the material constituting the plateau. For example, the tray may be made of a metal or metal alloy having good thermal conductivity. In some embodiments, the blading sector comprises at least two blades and the first channel is formed in the outer plate 30 and / or the inner plate, between the two blades. [0005] In some embodiments, at least one second channel is formed in the blade, the second channel and the blade being adapted to allow, when the turbomachine is operating, a heat exchange between a hot fluid flowing in the second channel and a flow of cold air passing through the stator vane. In certain embodiments, the first and second channels are interconnected and define a circuit for the hot fluid, this circuit having a fluid inlet provided on the blading sector, through which the hot fluid enters the circuit, and a fluid outlet, also provided on the blading sector, through which the cooled hot fluid exits the circuit. The hot fluid can be a liquid, in particular oil. As an alternative to oil, the hot fluid may be a heat transfer fluid with heating value greater than that of air or even that of the oil. In some embodiments, the blades are exit straightening blades or "OGVs" for "Outlet Guide Vane". In particular, it may be secondary flow rectifying blades disposed at the outlet of the fan in a turbofan engine. The use as heat exchange surfaces of the existing surfaces, which are the surfaces of the inner or outer plates and / or the surfaces of the blades themselves, has the advantage of limiting the pressure losses compared with a heat exchanger. placed in the vein of fluid passing through the turbomachine, such a heat exchanger therefore implying an additional loss of aerodynamic thrust. Furthermore, in the case of an aircraft engine and when the vanes are exit straightening vanes placed in the secondary vein, the heat transfer from the hot fluid (eg oil) to the air represents an additional supply of energy into the secondary vein that is beneficial for engine performance. In addition, this heat input takes place over the entire height of the vein, which makes this solution more thermodynamically efficient than most known solutions. [0006] In addition to the features just mentioned above, the proposed device may have one or more of the following characteristics, taken alone or in technically possible combinations: the first channel is formed in the outer plate and / or or in the inner tray so that the distance between the first channel and the surface of the tray oriented towards the inside of the blading sector is substantially constant, - at least one blade forms one and the same piece with the outer plate 10 and / or with the inner plate, - at least one third channel is formed in the plate of the first channel (ie the plate in which the first channel is formed), the third channel and the plate being adapted to allow, when the turbomachine is running a heat exchange between a hot fluid circulating in the third channel and a cold air flow passing between the blades, - the and the third channel belong to adjacent circuits having fluid inlets and outlets such that the circumferential circulation direction of the hot fluid in the first channel is opposite to the circumferential circulation direction of the hot fluid in the third channel, at least one fourth channel is formed in the dawn of the second channel, the fourth channel and the blade being adapted to allow, when the turbomachine is operating, a heat exchange between a hot fluid flowing in the fourth channel and a cold air flow enveloping the blade, the second and fourth channels belong to adjacent circuits having fluid inlets and outlets such that the direction of radial circulation of the hot fluid in the second channel is opposite to the direction of radial circulation of the hot fluid. in the fourth channel. It will be noted here that it is a question of the direction of global circulation of the fluid in the radial / circumferential direction and not of the direction of punctual circulation of the fluid at a point of the channels. [0007] Such features are useful for ensuring temperature homogeneity on the surface of the blading sector. Indeed, the temperature of the hot fluid tends to decrease as it advances in its circuit. Also, by providing at least two (e.g. two or four) adjacent circuits with opposite flow directions, the temperature decreases in the two circuits compensate each other. This makes it possible to obtain the desired temperature homogeneity, which may have beneficial effects on the mechanical strength of the blading sector, the homogeneity of the air distribution in the vein and / or the effectiveness of the the heat exchange 10 carried out. The present disclosure also relates to a turbomachine stator vane comprising a plurality of vane modules each extending over an angular sector of the vane, the vane being formed by connecting the modules end-to-end. At least one of these modules may be formed by a blading sector as previously described. A blading module may therefore comprise, in its interior, at least one circuit for the circulation of a hot fluid, extending between an inlet and a fluid outlet. This input and this output may, for example, be arranged on opposite sides of the module. This configuration in module 20 allows a certain flexibility in terms of maintenance and assembly, compared to a system where each blade would be traversed by a circuit and where these circuits would be independent of each other. The present disclosure also relates to a turbomachine comprising at least one stator vane sector as previously described. [0008] Other features and advantages of the proposed blade sector will be apparent from the following detailed description of exemplary embodiments. This detailed description refers to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS The accompanying drawings are diagrammatic and are not to scale, they are intended primarily to illustrate the principles of the invention. [0009] In these drawings, from one figure (FIG) to the other, identical elements (or parts of element) are identified by the same reference signs. FIG 1 is an axial half-section of an example of an aircraft turbojet engine. FIG 2 is a perspective view of an example of a stator vane sector of a turbomachine. FIG 3 is a sectional view of the blading sector of FIG 2, in the radial plane the sector being shown in the non-assembled state. FIG 4 is a sectional view of the inner tray of the sector of FIG 2, according to the plane IV-IV of FIG 3, showing the channels formed in this tray. FIG 5 is a sectional view, similar to that of FIG 4, showing another channel configuration. FIG. 6 is a simplified representation of another example of blade sectors. FIG 7 is a simplified representation of another example of blading sector. FIG. 8 is a simplified representation of a possibility of mounting several adjacent two-to-two vane sectors in a stator vane. FIG 9 is a sectional view of the blade of FIG 2, in the X-X plane perpendicular to the radial direction. DETAILED DESCRIPTION OF EXAMPLE (S) Exemplary embodiments are described in detail below with reference to the accompanying drawings. These examples illustrate the features and advantages of the invention. However, it is recalled that the invention is not limited to these examples. FIG 1 is an axial half-section of the upstream portion of a double-flow double-body aircraft turbojet engine. A stator vane 9 is disposed downstream of the turbojet fan 2 in the secondary air stream 3. The stator vane 9 comprises an annular inner wall 302 and a ring-shaped outer wall 14. between which range of exit straightening blades 11 (or "OGV"). These vanes 11 are evenly distributed around the rotational axis A of the rotor of the turbojet engine. The inner annular walls 13 and outer 14 have a cylindrical general shape of axis A. In one embodiment, the stator vane 9 is formed of several modules connected end to end, each module comprising at least one blade and extending over an angular sector of the vane. In what follows, also called blading sector such a module. The modules 10 may all be identical, but not necessarily. An alternation of several types of modules is described below with reference to FIG. 8. In the example of FIG. 2, the blade module or sector 10 comprises two blades 11, 12 extending radially between an inner plate 16 and an outer plate 18. The inner plate 16 extends circumferentially between the inner ends of the blades 11, 12 and beyond these ends, while the outer plate 18 extends circumferentially between the outer ends of the blades 11, 12 and beyond these ends. When the blading sector 10 is integrated with the stator vane 9, the inner 16 and outer 18 platens each form part of the inner and outer annular walls 13 and 14, respectively. The inner plate 16 may be fixed on an annular wall of a hub casing which internally delimits a portion of the vein of the secondary flow. The outer plate 18 may be attached to an annular wall of a fan casing which delimits externally the same portion of the vein of the secondary flow. In FIG 2, the inner and outer plates 16, 18 and the vanes 11, 12 are shown in dashed lines so as to better visualize the oil circuits 21, 31 formed in the blading sector 10. The two circuits 21, 31 are separate and both comprise an inlet 22, 32 and an outlet 23, 33 of fluid. In the example, the input 22 and the output 23 of the first circuit 21 are located respectively at the ends of the inner plate 16, while the input 32 and the output 33 of the circuit 31 are respectively located at the ends of the inner plate 16. ends of the outer plate 18. In addition, the inlet 32 of the circuit 31 is located at the end of the outer plate 18, on the same side of the blade 11 as the inlet 22 of the circuit 21. [0010] The ends of the trays have been shown relatively close to one or other of the vanes. It is nevertheless possible to lengthen in the circumferential direction the inner 16 and outer 18 plates without changing the inter-blade spacing, so as to obtain the same spacing between the blades, that is to say obtain a regular distribution 10 blades over an angular extent of the blade constituted by several modules 10 connected end to end. In this case, it remains advantageous to have the inlets and outlets of the two oil circuits near the ends of the trays, in order to use as much as possible the surfaces of the trays for the heat exchange between the oil circuits and the air from the vein of the secondary stream that comes to lick these surfaces. The channels 24, 28, and 32, 34 described in the following are then generally elongated in the circumferential direction of the trays. To mount each module 10 at its location in the vein of the secondary flow and fluidly connect it to a neighboring module 10, there can be provided in the annular hub housing and in the annular fan housing lights corresponding to the positions inputs and outputs of the fluid circuits of each module. In this way, the connection of the fluid circuits from one module to another can be done by means of pipes, for example flexible pipes, connected to the modules and passing through the housings by the corresponding slots. With modules such as that of the example of FIG. 2, the output of a fluid circuit of a module can be connected to the input of the same fluid circuit on the neighboring module. Each circuit 21, 31 comprises two substantially parallel branches 30 which meet at the input and at the output of the circuit. Each circuit 21, 31 could, however, comprise only one branch. In the example, the circuits 21, 31 are substantially symmetrical to one another with respect to a median surface passing between the trays 16, 18. From its inlet 22 to its outlet 23, the first circuit 21 comprises two channels 24 (one for each branch) formed in the thickness of the inner plate 16, two channels 25 formed in the thickness of one of the blades 11 and extending over the entire height of this blade 11 from the inner plate 16 to the outer plate 18, two channels 26 formed in the thickness of the outer plate 18 and 10 extending between the blades 11 and 12, two channels 27 formed in the thickness of the another blade 12 and extending over the entire height of this blade 12, from the outer plate 18 to the inner plate 16, and - two channels 28 formed in the thickness of the inner plate 16. [0011] Analogously and symmetrically, from its input 32 to its output 33, the circuit 31 comprises: two channels 34 (one for each branch) formed in the thickness of the outer plate 18, two channels 35 formed in the thickness of the blade 12 and extending over the entire height of this blade 12, - two channels 36 formed in the thickness of the inner plate 16 and extending between the blades 11 and 12, - two channels 37 formed in the the thickness of the blade 11 and extending over the entire height of this blade 11, and 25 - two channels 38 formed in the thickness of the outer plate 18. The channels 26 and 36 may be formed in the outer plate and the inner tray, respectively, such that the distance between each channel and the tray surface oriented inwardly of the blading sector is substantially constant. This distance is for example between 1.0 mm and 10.0 mm (mm). This makes it possible to ensure, when the turbomachine is operating, an effective heat exchange between the hot fluid circulating in the channel and the flow of cold air licking the surface of the plate. In the blades 11, 12, the direction of flow of the oil in the first circuit 21 is opposite to the direction of circulation of the oil in the second circuit 31. More particularly, in this example, the oil of the first circuit 21 flows radially from the inside to the outside in the blade 11 (ie in the channels 25) while the oil of the second circuit 31 circulates radially from the outside to the inside in the blade 11 (ie in the channels 37). In addition, the oil of the first circuit 21 flows radially from the outside to the inside 10 in the vane 12 (ie in the channels 27) while the oil of the second circuit 31 circulates radially from the inside to the outside. outside in the blade 12 (ie in the channels 35). This cross circulation makes it possible to ensure satisfactory homogeneity of the temperature at the surface of the blades 11, 12. In FIG. 2, arrows indicate the direction of circulation of the oil in the circuits 21, 31. According to a variant, in a blade 11 or 12, the channels of the first circuit 21 and the channels of the second circuit 31 extend next to one another and are separated by a thickness of material of between 1.0 mm and 10.0 mm (millimeters ) to allow thermal exchange by conduction through the thickness of material between the hot fluid flowing in the channels of the first circuit 21 and the hot fluid flowing in the channels of the second circuit 31. This arrangement promotes the homogeneity of the temperature on the surface of the blades. The thickness of material between the channels in a blade can be predicted to be constant, i.e. uniform over the range of the channels. The blading area 10 may, for example, be constructed by a metal additive manufacturing process, equivalent to 3-D printing in a metallic material. The channels are thus directly created during the construction of the material block constituting the sector 10. Alternatively, the blading sector 10 can be constructed using more conventional manufacturing techniques. [0012] The two trays 16, 18 may for example each be formed by two machined plates 16A, 16B, 18A, 18B mounted one on top of the other and assembled by bolting or by any other suitable fastening means, as illustrated in FIG. 3. In this example, the two blades 11, 12 are formed integrally with the inner plates 16B, 18B of the two plates 16, 18, by machining a block at "0". The channels 24, 34, 26, 36 formed in the outer plate 18 and the inner plate 16 allow, when the turbomachine is operating, a heat exchange between the hot oil circulating in these channels and the flow of cold air passing between them. blades 11 and 12. The channels 25, 35, 27, 37 formed in the blades 11, 12 allow, when the turbomachine is operating, a heat exchange between the hot oil flowing in these channels and the cold air flow which envelops each In the example of FIGS. 1 to 4, the first and the second circuits 21, 31 are adjacent (ie extend one beside the other) in the vanes 11, 12 but not in the inner and outer plates 16 and 18. Thus, considering the inner plate 16, the second circuit 31 (ie the channels 36) extends in the space between the blades 11, 12, while the first circuit 21 (ie the channels 24, 28) extends out of this gap, as shown in FIGS. 2 and 4 FIGS. 5 and 6 show another example of blading sector 10 in which the first and second circuits 21, 31 are adjacent both in the blades 11, 12 and in the inner and outer plates 16 and 18. Furthermore, FIGS. the fluid inlets 22, 32 and exits 23, 33 are arranged in such a way that: - in the inner plate 16, the circumferential circulation direction of the hot fluid in the first circuit 21 is opposite to the circumferential circulation direction of the hot fluid in the second circuit 31, - in the first blade 11, the direction of radial circulation of the hot fluid in the first circuit 21 is opposite to the direction of radial circulation of the hot fluid in the second circuit 31, 3028575 13 - in the outer plate 18, the circumferential circulation direction of the hot fluid in the first circuit 21 is opposite to the circumferential circulation direction of the hot fluid in the second circuit 31, - in the second blade 12, the direction of ci radial reduction of the hot fluid 5 in the first circuit 21 is opposite to the direction of radial circulation of the hot fluid in the second circuit 31. The circuits 21, 31, as well as the direction of circulation of the hot fluid in these circuits are shown schematically on the FIG 6. FIG 5 is a sectional view, similar to that of FIG 4, which shows the channels 29, 39, 10 formed in the inner plate 16 and forming part of the circuits 21, 31. These channels 29 and 39 are adjacent (ie extend next to each other) while being separated by a seal 40. The path of the channels 29 and 39 is curvilinear so as to increase the distance traveled by the hot fluid and thus increase the heat exchange surface between the channels themselves and between each channel and the cold air flow which licks the surface of the inner plate 16 in the vein of the secondary flow. Channels 29, 39 may have different paths as in the example shown. As previously indicated, the circumferential circulation direction of the hot fluid in the channel 29 is opposite to the circumferential circulation direction of the hot fluid in the channel 39. For example, as illustrated by arrows in FIG. 5, the hot fluid flows from left to right in the channel 29 while the hot fluid flows from right to left in the channel 39. A curvilinear path such as that of the channels 29, 39 may advantageously be adopted for the channels 26, 36 of the blading sector 10 in the embodiment corresponding to FIG 2, since this increases the heat exchange surface between each channel and the flow of cold air passing between the blades. FIG. 7 represents another example of a blading sector. This example comprises four circuits 21, 31, 41, 51 dedicated to the circulation of the hot fluid. These four circuits are adjacent in the blades 11, 12 and 3028575 14 in the inner plates 16 and outer 18. In the blades, the direction of radial circulation of the hot fluid in two of these circuits 21, 51 is opposite to the direction of radial circulation hot fluid in the other two circuits 31, 41. [0013] In the inner plate 16, between the blades 11, 12, the circumferential circulation direction of the hot fluid in the circuit 21 is opposite to the circumferential circulation direction of the hot fluid in the circuit 31 (the circuits 41, 51 do not pass through the inner plate 16, between the blades 11, 12). In the outer plate 18, between the blades 11, 12, the circumferential circulation direction of the hot fluid in the circuit 41 is opposite to the circumferential circulation direction of the hot fluid in the circuit 51 (the circuits 21, 31 do not pass through the outer plate 18, between the blades 11, 12). It is not essential that all the modules of the vane be identical. It is indeed possible to alternate heat exchanger modules, for example of the same type as the blading sector 10 shown in FIG. 2 with modules of another type. In particular, a "spacer" vane module 60 comprising a single vane as shown in dashed lines in FIG. 8 can be provided between two heat exchanger modules 10. [0014] This module 60 may be dimensioned so as to obtain an even distribution of the output straightening vanes around the rotational axis A of the rotor of the turbojet engine. The heat exchanger modules 10 may themselves be evenly distributed around the axis A. The intermediate blading module 60 may not have a heat exchange function, which creates a circumferential space E without a heat exchanger. heat between two adjacent heat exchanger modules 10. In this configuration, it does not use the entire circumferential extent of the blade 9 for cooling. It is also possible to have no blading module in a more or less restricted circumferential space E between two heat-exchange modules 10. [0015] Thus, alternatively, the stator vane sector may comprise only one blade. For example, such a blading sector may have the shape of the intermediate bladder module 60 shown in FIG. 8, and include at least one channel in the outer platen and / or the inner platen. It is not essential for one channel to go from one tray to the other, each channel can traverse a single outer or inner tray from one end of the tray to the other end. In this case, the vane of the blading sector is not used for cooling the hot fluid channels. [0016] According to another variant, a single-blade vane sector may resemble the two-blade sector of FIG. 2 which would be without one of the two vanes. For example, in the case where only the blade 11 is present, the channels 26 and 36 respectively in the outer plate and the inner plate are kept to allow heat exchange between the hot fluids flowing in these channels and the flow of cold air that comes to lick the trays. The output 23 of the circuit 21, which ends the channels 26, is then disposed on the outer plate, while the output 33 of the circuit 31, which ends the channels 36, is disposed on the inner tray. [0017] According to yet another variant, a stator vane sector may comprise more than two vanes. For example, by repeating the diagram of the two-blade vane sector of FIG. 2, that is to say by continuing the circuits 21 and 31 so as to alternate for each circuit the passage in the outer plate and in the inner tray, there is obtained a blading sector 25 having an even number of blades. This has the advantage that the inlet and the outlet of the same hot fluid circuit are arranged on the same outer or inner plate. The fluidic connection of two adjacent vane sectors is thus facilitated, the outlet of a hot fluid circuit on one sector being adjacent to the inlet of the similar hot fluid circuit on the adjacent vane sector. [0018] The stator blading sector may also include an odd number of blades greater than or equal to three. Furthermore, FIG 9 is a sectional view of a four-duct blade which form channels of fluid circuits of a blading sector 5 such as that shown in FIG. 2 or as implemented according to FIG. the diagram shown in FIG 7. The interior walls of the ducts form sharp angles so as to optimize the fluid passage section without compromising the rigidity of the blade and the capacity of the blade to withstand the impact foreign bodies (ice, birds, etc.) that would strike his leading edge. The metal additive manufacturing processes are particularly suitable for the manufacture of blade sectors having such vanes provided with conduits of complex shapes. Furthermore, it is conceivable to circulate in the channels of fluid circuits of a blading sector not the oil, but a heat transfer fluid having a heating value higher than that of air or even that of oil, on the one hand to allow improved heat exchange and on the other hand to ensure that there will be no oil loss if a blade sector was to be damaged to the point of breaking a channel of fluid. The cooling of the oil of the lubricating circuit of the turbomachine can take place in a heat-transfer fluid / oil heat exchanger installed for example in the zone between the fan casing and the nacelle hood. Since each heat transfer fluid circuit is independent of the oil circuit, the circulation of the coolant can be carried out by dedicated pumps. The modes or examples of embodiment described in the present description are given by way of nonlimiting illustration, it being easy for a person skilled in the art, in view of this disclosure, to modify these modes or embodiments, or to envisage others, all remaining within the scope of the invention. On the other hand, the term "comprising one" should be understood as being synonymous with "comprising at least one", unless the opposite is specified. [0019] Finally, the various features of the embodiments or examples of embodiments described in the present disclosure may be considered in isolation or may be combined with each other. When combined, these characteristics can be as described above or differently, the invention is not limited to the specific combinations described above. In particular, unless otherwise specified or technical incompatibility, a feature described in connection with a mode or example of embodiment may be applied in a similar manner to another embodiment or embodiment. 10
权利要求:
Claims (10) [0001] REVENDICATIONS1. A turbomachine stator-blasting sector comprising at least one blade (11, 12), an outer plate (18) connected to the outer end of the blade, and an inner plate (16) connected to the end vane, in which at least one first channel (24, 26, 28, 29) is formed in the outer plate (18) and / or the inner plate (16), the first channel and the plate being adapted to to allow, when the turbomachine is operating, a heat exchange between a hot fluid circulating in the first channel and a cold air flow passing through the stator vane. [0002] Blade sector according to claim 1, wherein the blading sector (10) comprises at least two blades (11, 12) and the first channel (26, 29) is formed in the outer plate and / or the blade. inner tray, between the two blades. [0003] Blading sector according to claim 1 or 2, wherein at least a second channel (25, 27) is formed in the blade (11, 12), the second channel and the blade being adapted to allow, when the turbomachine operates, a heat exchange between a hot fluid flowing in the second channel and a cold air flow passing through the stator vane. [0004] The blading sector according to claim 3, wherein the first and second channels are interconnected and define a circuit (21) for the hot fluid, said circuit having an inlet (22) and an outlet (23) of fluid provided on the blading sector (10). [0005] Blading sector according to one of Claims 1 to 4, in which the first channel (24, 26, 28, 29) is formed in the outer plate (18) and / or in the inner plate (16). such that the distance between the first channel and the inwardly oriented plateau surface of the blading sector is substantially constant. [0006] Blade sector according to any one of claims 1 to 5, wherein at least one blade (11, 12) forms a single piece with the outer plate (18) and / or with the inner plate (16). ). [0007] The blading sector according to any one of claims 1 to 6, wherein at least one third channel (39) is formed in the plate (16, 18) of the first channel (29), the third channel and the plate being adapted to allow, when the turbomachine is operating, a heat exchange between a hot fluid flowing in the third channel and a cold air flow passing between the blades, and the first and the third channel (29, 39). belong to adjacent circuits (21, 31) having separate fluid inlets (22, 32) and outlets (23, 33) arranged in such a way that the circumferential circulation direction of the hot fluid in the first channel (29) is opposed to the circumferential circulation direction of the hot fluid in the third channel (39). 20 [0008] 8. Blading sector according to any one of claims 1 to 7, wherein - at least a second channel (25, 27) is formed in the blade (11, 12), the second channel and the blade being adapted to allow, when the turbomachine is operating, a heat exchange between a hot fluid flowing in the second channel and a cold air flow passing through the stator vane, - at least a fourth channel (35, 37) is provided in the blade (11, 12) of the second channel (25, 27), the fourth channel and the blade being adapted to allow, when the turbomachine is operating, a heat exchange between a hot fluid flowing in the fourth channel and a flow of cold air enveloping the blade, and - the second and fourth channels (25, 27, 35, 37) belong to adjacent circuits (21, 31) having inputs (22, 32) and outputs ( 23, 33) arranged in such a manner that, in a radial direction, the overall direction of flow of the luide hot in the second channel (25, 27) is opposite the direction of global circulation of the hot fluid in the fourth channel (35, 37). 10 [0009] 9. A turbomachine stator aperture comprising a plurality of vane modules each extending over an angular sector of the vane, the vane (9) being formed by connecting the vane modules end-to-end, wherein at least one modules are formed by a blading sector (10) according to any one of claims 1 to 8. [0010] 10. Turbomachine comprising at least one blading sector (10) according to any one of claims 1 to 8.
类似技术:
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同族专利:
公开号 | 公开日 FR3028575B1|2016-12-23|
引用文献:
公开号 | 申请日 | 公开日 | 申请人 | 专利标题 JP3015531B2|1991-09-06|2000-03-06|株式会社東芝|gas turbine| JPH10280908A|1997-04-09|1998-10-20|Toshiba Corp|Stator blade of gas turbine| EP1630358A2|2004-08-26|2006-03-01|United Technologies Corporation|A gas turbine engine frame with an integral fluid reservoir and air/fluid heat exchanger| EP1884625A2|2006-07-28|2008-02-06|General Electric Company|Heat transfer system and method for turbine engine using heat pipes|FR3064295A1|2017-03-23|2018-09-28|Safran Aircraft Engines|AIRMETER TURBOMACHINE INTERMEDIATE CASE COMPRISING A PLATEFORM SOLIDARITY LUBRICANT PASSING BIT| FR3064296A1|2017-03-23|2018-09-28|Safran Aircraft Engines|INTERMEDIATE CASE FOR AIRCRAFT TURBOMACHINE COMPRISING AN INTERMEDIATE PIECE BETWEEN A WAVE FOOT AND THE HUB| FR3064682A1|2017-03-31|2018-10-05|Safran Aircraft Engines|INTERMEDIATE CASE FOR AIRCRAFT TURBOMACHINE COMPRISING A LUBRICANT PASSING BIT CONNECTED TO A CARTER BOLT BY A CONNECTING PART| EP3736411A1|2019-05-10|2020-11-11|Hamilton Sundstrand Corporation|Gas turbine engine cooling system and method|
法律状态:
2015-11-10| PLFP| Fee payment|Year of fee payment: 2 | 2016-05-20| PLSC| Publication of the preliminary search report|Effective date: 20160520 | 2016-11-03| PLFP| Fee payment|Year of fee payment: 3 | 2017-10-20| PLFP| Fee payment|Year of fee payment: 4 | 2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 | 2018-10-24| PLFP| Fee payment|Year of fee payment: 5 | 2019-10-22| PLFP| Fee payment|Year of fee payment: 6 | 2020-10-21| PLFP| Fee payment|Year of fee payment: 7 | 2021-10-20| PLFP| Fee payment|Year of fee payment: 8 |
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申请号 | 申请日 | 专利标题 FR1461200A|FR3028575B1|2014-11-19|2014-11-19|STATOR AUBING SECTOR OF A TURBOMACHINE|FR1461200A| FR3028575B1|2014-11-19|2014-11-19|STATOR AUBING SECTOR OF A TURBOMACHINE| 相关专利
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