• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    A turbomachine comprising at least one stator vane sector (10) and a fluid distribution circuit (22), the stator vane sector comprising at least one vane (12), a fluid inlet (25a), a fluid outlet (25b) and a channel (24a) fluidly connecting the fluid inlet and the fluid outlet extending at least partially into the blade (12), the blade and the channel being adapted to allow, a heat exchange between a hot fluid passing through the channel and a flow of cold air passing through the blading sector, the fluid distribution circuit (22) having a supply line (22a) and a recovery line ( 22b), the fluid inlet (25a) being fluidly connected to a bypass tap (23a) of the supply line (22a) while the fluid outlet (25b) is fluidly connected to a bypass tap (23b). ) of the recovery line (22b).
    公开号:FR3034474A1
    申请号:FR1552802
    申请日:2015-04-01
    公开日:2016-10-07
    发明作者:Sebastien Chalaud；Christian Vessot
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The present invention relates to the field of turbomachines equipped with a cooling circuit, in particular, but not only, for cooling the oil of the turbomachine. In particular, the invention relates to cooling circuits where a heat exchange is carried out wholly or partly in turbomachine stator vanes. The term "turbomachine" refers to all gas turbine engines producing a motive power, among which there are notably turbojets providing a thrust required for propulsion by reaction to the high speed ejection of hot gases, and Turbomotors in which the motive power is provided by the rotation of a motor shaft. For example, turboshaft engines are used as engines for helicopters, ships, trains, or as an industrial engine. Turboprops (turbine engine driving a propeller) are also turboshaft engines used as aircraft engines. STATE OF THE PRIOR ART The oil circuit of an aircraft engine provides the dual task of lubricating the rotating parts of the engine and of discharging the heat released into the engine. To cool the oil, the temperature of which generally does not exceed a predetermined temperature for reasons of efficiency, different types of heat exchanger exist. Some heat exchangers use air as a cold source. For example, patent document WO 2013150248 A1 discloses a stator blade of a turbomachine formed by a plurality of parts arranged relative to each other 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. Moreover, in order to optimize the known cooling circuits, particular, but not only, attempts are made to reduce the pressure losses in the oil circuit. PRESENTATION OF THE INVENTION The present disclosure relates to a turbomachine comprising at least one stator vane sector and a fluid distribution circuit, the stator vane sector comprising at least one blade, a fluid inlet, a fluid outlet and a channel fluidly connecting the fluid inlet and the fluid outlet extending at least partly in the blade, the blade and the channel being adapted to allow, when the turbomachine is operating, an exchange thermal between a hot fluid passing through the channel and a cold air flow passing through the stator vane sector, the fluid distribution circuit having at least one supply line and at least one recovery line separate from the conduit the fluid inlet being fluidly connected to a bypass tap of the supply pipe while the fluid outlet is fluidly connected to a bypass tap of the pipe recovery. The hot fluid to be cooled is for example oil. In this case, the supply line can be connected to a pump of a lubrication circuit of the turbomachine, which pump is provided to discharge to the supply line the hot oil collected after lubrication of the rotating parts of the engine. The recovery line may be connected to a tank of the lubrication circuit, to return the cooled oil to this tank through its passage in at least one stator vane section.
    [0002] By "stator vane sector" is meant a portion of the stator vane of a turbomachine. This part comprises a certain number of vanes and is delimited, for example internally and externally, by trays (also called plateforrnes, or walls) extending in the circumferential direction of the vane and connecting the ends (internal / external). paddles between them, but not necessarily. The number of blades in a blading sector is greater than or equal to one and less than or equal to the total number of blade blades. 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. Similarly, 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.
    [0003] On the other hand, unless otherwise stated, the adjectives "internal" and "outer" or "inner" and "outer" are used with reference to a radial direction so that the inner (ie radially inner) portion of an element is closer to the axis of rotation than the outer (ie radially outer) part of the same element. Finally, unless otherwise indicated upstream and downstream are defined in relation to the normal flow direction of the fluid (from upstream to downstream) between the stator vanes. It is understood that the turbomachine comprises one or more stator vane sectors (hereinafter, and unless otherwise indicated "blading sector"), that each blading sector comprises one or more blades. One or more of these blading sectors each comprise at least one fluid inlet (hereinafter, and unless otherwise indicated, "inlet"), at least one fluid outlet (hereinafter, and unless otherwise indicated, "outlet"). And at least one channel. In each vane section equipped with a channel, the channel extends at least in part in at least one vane and fluidly connects the inlet and the outlet of each vane sector. Of course, each of these channels and the blades containing one or more of these channels are configured to be able to exchange heat between a hot fluid flowing in the channel (s) and a cold air flow passing through the at least one sector. 20 stator blading. It is understood that the channel connects the input and the output. Of course, there may be a single channel that extends between one or more inputs and one or more outputs. Conversely, there may be several channels each connected to a single input and / or a single output. According to yet another variant, there are as many inputs and outputs as there are channels. In the case where there are several channels, these channels can extend in a single blade or in several different blades. For example, there may be a single channel per dawn. Of course, each channel can subdivide into subchannels. In another example, there may be a single channel that extends into several blades. Of course, this is applicable to for each blading area. Subsequently, and unless otherwise indicated, by the "vane / dawn / inlet / outlet / channel" is meant "at least one" or "the" vane / vane / inlet / outputs / channels.
    [0004] Moreover, the terms "hot" and "cold" are to be considered relative to one another, the fluid being hotter than air while the air is colder than the fluid. In what follows, "air" means any gas that can be used as an oxidizer 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 constituent material of dawn. For example, the blade may be made of a metal or metal alloy having good thermal conductivity. It will be understood that the inlet, the outlet and the channel form a bypass circuit with respect to the fluid distribution circuit. In other words, a branch circuit comprises an input, an output, and the channel or channels extending between this input and this output. Of course, in the case where a single channel connects several inputs to several outputs, the branch circuit then comprises all of these inputs and outputs and the channel that extends between these inputs and outputs. Thus, hot fluid circulates in the distribution circuit, and a portion of this hot fluid is directed into the blade, bypassing the distribution circuit.
    [0005] When the blading comprises a plurality of bypass circuits, each blading sector may comprise one or more bypass circuits, each of these bypass circuits conducts a portion of the hot fluid to one or more blades for cooling the hot fluid. Such a structure can effectively cool the hot fluid while minimizing the pressure losses throughout the cooling circuit, the cooling circuit comprising the distribution circuit and the branch circuit or circuits. In addition, with respect to a series cooling circuit, the bypass circuits maximize the temperature difference between the hot and the cold air, so that cooling in each channel is maximized. Moreover, in the case where there are several branch circuits, in the event of failure of a bypass circuit, for example in the event of rupture of a blade, the cooling of the hot fluid remains ensured at least in part by the other branch circuits.
    [0006] In some embodiments, the stator blading sector includes an inner platen connected to the inner end of the blade and an outer platen connected to the outer end of the blade, the fluid inlet. and the fluid outlet being both formed in one tray among the inner tray and the outer tray while the channel partly extends into the other tray among the inner tray and the outer tray. It is therefore understood that with respect to the blade, the inlet and the outlet are arranged on one and the same side, in the same plate, while the channel extends in the blade and in the opposite plate. Of course, this latter plate and the channel are adapted to allow, when the turbomachine is operating, a heat exchange between a hot fluid passing through the channel and a cold air flow passing through the stator vane sector. Such a structure makes it possible to improve the cooling of the fluid flowing in the channel, since in this case the heat exchange surfaces are located not only at the level of the blade but also at the level of the internal plate and / or the outer tray. The arrangement of the inlet and the outlet of a bypass circuit on the same side of a plate, and on the same side as the fluid distribution circuit with respect to the air stream passing through the The stator blading can be advantageous especially in the case where the fluid distribution circuit is connected to a lubrication circuit of the turbomachine arranged on the same side with respect to the air stream. Indeed, the fluidic connections between the said inlets and outlets and the fluid distribution circuit, as well as the fluidic connections between the said distribution circuit and the lubrication circuit, do not in this case need to cross the stream of fluid. 'air. However, it is not excluded, without departing from the scope of the invention, to provide that at least one such fluidic connection passes through the air stream, for example through a service arm separated from the vane sectors. In some embodiments, the stator vane sector includes a plurality of vanes, the channel extending into at least two of the vanes. According to one variant, the stator vane sector comprises an inner plate connected to the inner end of each of the vanes and an outer plate connected to the outer end of each of the vanes, the channel extending into the inner plate and in the outer tray.
    [0007] Such configurations using both the inner and outer plates to integrate the cooling channel further improve the heat exchange between the hot fluid and the cold air as the hot fluid passes through the channel. . Indeed, almost all of the surface of a stator vane section licked by cold air passing through the stator vane can be used as a heat exchange surface.
    [0008] In some embodiments, the channel has the same number of passages in each of the vanes, each passage being formed by a subchannel, or a channel pass. In some embodiments, the channel extends in the same linear length in each of the blades. Of course, the linear length of the channel in a blade is the sum of the lengths of each of the passages. Such structures allow, alone or in combination, to reduce the temperature differences between each blade. In some embodiments, the blading sector comprises a plurality of blades, at least two blades each comprising a channel, the blades and channels being adapted to allow, when the turbomachine is operating, a heat exchange between a hot fluid passing through the channel and a flow of cold air passing through the stator vane sector, the vane channel being distinct from the channel of the other vane, the vane sector comprising as many fluid inlets and fluid outlets as channels, each channel being respectively fluidically connected to a fluid inlet and a fluid outlet separate from the fluid inlet and the fluid outlet of the other channel. In other words, it is understood that a first channel extends in a first blade and a second channel extends in a second blade. According to a variant, a third channel extends in a third blade, etc. Each channel is independent of the other channels, the input and output of each channel being different from the inputs and outputs of the other channels. Of course each channel may have a single or multiple inputs and a single or multiple outputs. Each channel and the blade in which it is formed are adapted to allow, when the turbomachine is operating, a heat exchange between a hot fluid passing through the channel and a cold air flow passing through the stator vane section. Of course, another channel, distinct from the first, second, etc. channels, can extend into one or more blades, for example in the first blade and in the second blade, or in separate blades.
    [0009] It is also understood that each input / output is respectively connected to a bypass tap of the supply / recovery line. For example, the supply / recovery lines respectively comprise as many branch taps as the input / output blading sector. According to one variant, each blade comprises a channel, each channel of one blade being distinct from the channels of the other blades, the blade sector comprising as many fluid inlets and fluid outlets as channels, each channel being respectively connected. fluidically at a separate input and output of the input and output of the other channel. Of course, if there are multiple blade sectors the above configurations can be applied to each of the blade sectors. For example, according to one variant, each blade of each blading sector comprises a channel fluidly connected to an inlet and an outlet as described above. Such a structure makes it possible to form as many branch circuits as the blade sector or sectors a / have blades. Such configurations make it possible to form a large number of independent branch circuits, whereby the cooling of the hot fluid is improved without increasing the pressure drop within the cooling circuit. In some embodiments, the turbomachine comprises at least two stator vane sectors, each stator vane sector including at least one vane, a fluid inlet, a fluid outlet, and a channel fluidly connecting the inlet. of fluid and the fluid outlet extending at least partly in the blade, the blade and the channel of each of the blade sectors being adapted to allow, when the turbomachine operates, a heat exchange between a hot fluid passing through each channel and a flow of cold air passing through the stator vane sector, the fluid inlet of each stator vane sector being fluidly connected to a bypass tap of the supply line while the fluid outlet of each stator vane sector is fluidly connected to a bypass tap of the recovery line.
    [0010] It is understood that there are at least as many branch circuits as vane sectors, each vane sector comprising at least one branch circuit. Of course, each blading sector may comprise one or more blades while each bypass circuit may extend only in a blade or in several blades, in one or both of the eventual platens of the blading sector 5 in question. etc. Such configurations make it possible to form a large number of independent bypass circuits, whereby the cooling of the hot fluid is improved without increasing the pressure drop within the cooling circuit.
    [0011] In some embodiments, the supply line forms a first supply line while the channel, the fluid inlet, and the fluid outlet respectively form a first channel, a first fluid inlet, and a first fluid outlet. fluid, the distribution circuit comprising a second supply line, the direction of flow of the fluid in the first supply line being opposed to the direction of flow of the fluid in the second supply line while the blading sector. stator comprises a second fluid inlet, a second fluid outlet and a second channel fluidly connecting the second fluid inlet and the second fluid outlet 20 extending at least partly in the dawn, dawn and second channel being adapted to allow, when the turbomachine is operating, a heat exchange between a hot fluid passing through the second channel and a cold air flow through The second fluid inlet is fluidly connected to a bypass tap of the second supply line while the second fluid outlet is fluidly connected to a bypass tap of the recovery line. . According to one variant, the recovery pipe forms a first recovery pipe while the distribution circuit 30 comprises a second recovery pipe, the direction of flow of the fluid in the first recovery pipe being opposite to the direction of circulation of the fluid within of the second recovery line, the first outlet being fluidly connected to a bypass tap of the first recovery line while the second outlet is fluidly connected to a bypass tap of the second recovery line. Of course, the distribution circuit may have a single supply line and two recovery lines, two supply lines and a single recovery line, or two supply lines and two recovery lines. For example, the supply lines extend circumferentially while the fluid flow directions within the supply lines are opposite in the circumferential direction. Such configurations make it possible to homogenize the overall temperature of the components along the feed / recovery lines, and thus to reduce the mechanical stresses resulting from the local temperature differences. In some embodiments, the stator vane sector includes an inner plate connected to the inner end of the blade and an outer plate connected to the outer end of the blade, the fluid distribution circuit being less in tab formed in a tray 15 among the inner plate and the outer plate. This makes it possible to cool the hot fluid during its flow in the part of the distribution circuit formed in the plate. In some embodiments, the bypass tap of the supply line and / or bypass tap of the recovery line is / are equipped with an isolation valve. Of course, when a blading sector has several inputs / outputs, there can be one valve per inlet and one valve per outlet, or an inlet manifold can be arranged upstream according to the fluid flow of the inlet and another manifold disposed downstream of the outlet (the upstream and downstream being considered in the direction of flow of the fluid in the channel), a single isolation valve being disposed at the inlet of the collector d input and / or output of the output collector. Thus, it is possible to fluidly isolate respectively all or part of the blading sector, or only the entire blading sector. This makes it possible, for example, to considerably limit the loss of the fluid in the event of the rupture of a channel in a blading sector. In some embodiments, the fluid is a liquid, especially oil. In some embodiments, the fluid is a heat transfer fluid, the delivery circuit comprising a heat exchanger configured to exchange heat between the coolant and another fluid, especially oil. In some embodiments, the blades are output straightening vanes or "OGVs" for "Outlet Guide Vane" in English.
    [0012] In particular, it may be secondary air flow straightening vanes disposed in the vein at the outlet of the fan in a turbofan engine. More commonly called "secondary vein" such vein passage of secondary air flow. The use as heat exchange surfaces of the existing surfaces of the blade surfaces themselves and possibly the inner and / or outer plate surfaces has the advantage of not increasing the aerodynamic drag compared to a heat exchanger. a separate heat exchanger projecting into the air stream, such a separate heat exchanger involving additional aerodynamic drag and hence additional aerodynamic thrust loss. 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 to the air represents an additional supply of energy in the secondary vein that is beneficial for engine performance. In addition, this heat supply takes place over the entire extent of the vein in the radial direction, hereinafter called "radial height of the vein", which makes this solution more thermodynamically efficient than most solutions Known. BRIEF DESCRIPTION OF THE DRAWINGS The invention and its advantages will be better understood on reading the detailed description given below of various embodiments of the invention given as non-limiting examples. This description refers to the pages of appended figures, in which: FIG. 1 represents an axial half-section of an example of an airplane turbojet engine; FIG. 2 is a simplified representation of a first embodiment of blading sector; FIG. 3 represents a first variant of the first embodiment; FIG. 4 represents a second variant of the first embodiment; FIG. 5 is a simplified representation of a second embodiment of FIG. embodiment of the blading sector; FIG. 6 is a simplified representation of a third blading sector embodiment; FIG. 7 is a simplified representation of a fourth blading sector embodiment; and - Figure 8 shows a variant of the fourth embodiment. DETAILED DESCRIPTION OF EXEMPLARY EMBODIMENTS It is stated that for the sake of clarity and brevity, the figures are very schematic representations. Those skilled in the art will readily understand that the teaching of this specification applies to all forms and variants of turbomachine stator vane sector. FIG. 1 is an axial half-section of the upstream portion of a turbomachine 1, in this example a double-flow double-body aircraft turbojet engine. A stator vane 9 is disposed downstream of the fan 2 of the turbojet engine 1, in the secondary air duct 3. The stator vane 9 comprises an annular inner wall 13 and an annular outer wall 14 between which extend blades 12 of output rectification (or "OGV"). These vanes 12 are evenly distributed around the rotational axis A of the rotor of the turbojet engine. The inner annular walls 13 and 25 outer 14 have a generally cylindrical shape of axis A. In one embodiment, the stator vane 9 is formed of several stator vane sectors, or modules, connected end-to-end, each blading sector comprising at least one blade and extending over an angular sector of the blading. The blading areas may all be identical, but not necessarily. Some or all of these blading areas may be used as heat exchangers. The sectors of bladed heat exchangers are, for example, of the same type as those described below. In the example of FIG. 2, the blading module or sector 35 comprises two blades 12 extending radially between an inner platen 16 and an outer platen 18. The inner platen 16 extends circumferentially between the ends internal blades 12 and beyond one of these ends, while the outer plate 18 extends circumferentially between the outer ends of the blades 12 and beyond one of these ends on the same side as the inner plate 16 and 5 in the same angular extent in the circumferential direction. When the blading sector 10 is integrated with the stator vane 9, the inner plate 16 and outer plate 18 each form part of the inner annular walls 13 and outer 14, respectively. The inner plate 16 may be attached to 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 fixed on an annular wall of a fan casing which delimits externally the same portion of the vein of the secondary flow. A cooling circuit 20, in this example for cooling turbojet engine oil as a hot fluid, comprises a distribution circuit 22 and a plurality of bypass circuits 24. The distribution circuit 22 comprises a supply line 22a and a recovery pipe 22b. In this first embodiment, each branch circuit 24 comprises a channel 24a which extends in a single blade 12 over the entire radial height H of the blade 12 between the inner plate 16 and the outer plate 18, and fluidly connects a fluid inlet 25a and a fluid outlet 25b. In this example, the fluid inlets 25a and the fluid outlets 25b are all formed in the same plate, namely the inner plate 16. By inlet 25a or fluid outlet 25b formed in a plate, is meant in this example that the plate has at least one orifice through which the channel 24a opens on the opposite side to the secondary vein, this orifice being intended to be fluidly connected to the supply line 22a or to the recovery line 22b. In addition, each blade 12 of the blading sector 10 includes a channel 24a. Thus, in this example, the blading sector 10 comprises as many channels 24a, inputs 25a and 25b (or as many branch circuits 24) as blades 12. Each inlet 25a is fluidly connected to a bypass tap 23a of the supply line 22a while each outlet 25b is fluidly connected to a bypass tap 23b of the recovery line 22b. The flow direction of the fluid in the cooling circuit 20 is indicated by the arrows. Each stitch 23a and 23b comprises an isolation valve 26. It is thus possible to cut off the circulation of the oil in a channel 24a, and to isolate it completely from the distribution circuit 22.
    [0013] The channel 24a formed in each vane 12 allows, when the turbojet engine is operating, a heat exchange between the hot oil circulating in this channel and the cold air flow which envelops each of the vanes 12. In addition, the two passages of the channel 24a in a blade 12 may be arranged parallel to each other and sufficiently close to each other to allow a heat exchange between the oil flowing in a passage in a direction of flow "go" and l oil circulating in the other passage in a direction of circulation "return" opposite. In this way, it is possible to relatively average the oil temperatures in the two passages corresponding to opposite flow directions of the oil in a branch circuit 24, which reduces the temperature differences of the oil in the same dawn. Of course, the passages may be rectilinear and / or curvilinear. The blading area 10 may, for example, be constructed by a metal additive manufacturing process, equivalent to a 3-D printing in a metallic material. The channels are thus directly created during the construction of the block of material constituting the sector 10. Alternatively, the blading sector 10 can be built using more conventional manufacturing techniques. In this example, the distribution circuit 22 extends circumferentially and on the inside with respect to the inner plate 18. Thus, the distribution circuit 22 is disposed outside the stator vane 9. According to a variant shown in FIG. 3, the distribution circuit 22 is partly integrated in the vane sectors 10 ', in this example in the internal trays 16. The fluid inlets and the fluid outlets of the bypass circuits 24 coincide in this example with Bypass taps 23a and 23b of the supply and recovery lines of the distribution circuit 22. In this example, the supply and recovery pipe portions included in an inner tray 16 include couplings 27 for connecting them to each other. respectively to portions of the supply lines and recovery of the adjacent blading sectors 10 '. Moreover, a bypass circuit 24 may comprise isolation valves 26, which in this example can be accommodated in the thickness and / or on the radially inner surface of an inner plate 16.
    [0014] According to another variant, it is possible to include only portions of the supply pipe in the inner plate 16, while in the embodiment described above with reference to FIG. It remains disposed completely outside the stator vane and therefore does not require connections 27. In fact, the temperature of the fluid flowing in a feed pipe is generally higher than that of the fluid flowing in a pipe. recovery. The use of internal trays 16 as an additional heat exchange surface for the fluid thus finds greater interest with the fluid of a feed line. According to yet another variant shown in FIG. 4, the fluid flowing in the cooling circuit 20 is a heat transfer fluid which exchanges heat with the oil of the turbojet engine 1 in a heat exchanger 28.
    [0015] Fig. 5 shows a second blading sector embodiment 100, similar to the blading sector 10 of the first embodiment except for the channel of each branch circuit. Thus, the identical elements retain the same numerical reference while the modified elements have their reference sign incremented by 25 "100". Each channel 124a of the blading sector 100 extends over the entire radial height H of the vanes 12 and extends in the outer plate 18, over all or part of the circumferential circumferential expanse Z. Thus, in this example the inlets and outlets 25a and 25b are formed in one tray, namely the inner tray 16, while the channel 124a extends into the other tray, namely the outer tray 18. The inputs and outputs 25a and 25b of a branch circuit 24 are not necessarily arranged in the extension of the blade 12 in which extends the branch circuit. Alternatively, it is possible to arrange the inputs and outputs 25a and 25b always in the inner plate 16 but in the vicinity of a blade 12 adjacent to that in which the branch circuit extends. In this way, the channel 124a has a portion that extends into the inner plate and connects with the portion of the same channel that extends into the blade. The internal plate 16 is therefore also used for the heat exchange between the fluid of a bypass circuit 24 and the air passing through the blading sector. This principle can be applied to a blading sector comprising more than one blade, as described below with reference to FIG. 6. According to another variant, it is possible to integrate portions of the pipe into the inner plate 16. supply circuit feed, or even portions of the recovery line, in the same manner as previously indicated with reference to Figure 3. Figure 6 shows a third embodiment of blading sector 200, similar to blading sector 10 of the first embodiment with the exception of the branch circuit. Thus, the identical elements retain the same numerical reference while the modified elements have their reference sign incremented by "200". The branch circuit 224 comprises a single channel 224a which extends in the two vanes 12. The channel 224a extends over the entire radial height H of each of the vanes 12, as well as in the inner and outer plates 16 and 18 , over substantially the entire circumferential extent Z1 of the blading sector 200. In this example, the blading sector 200 comprises only one branch circuit 224. In order to homogenize the thermal diffusion of the hot fluid in the different blades 12, the channel 224a is divided into two sub-channels 224aa in the blade 12 which is traversed first by the channel 224a considered in the direction of the fluid flow within the channel 224a of the upstream downstream from the inlet 25a to the outlet 25b, and at each crossing of the blade 12 by the channel 224a. Thus, each blade 12 has an identical number of passages of the channel 224a, in this example four passages. The inputs and outputs 25a and 25b of the branch circuit 224 are arranged in the inner plate 16, in the vicinity of a circumferential end of the plate opposite the blade 12 at which the channel 224a branches off the plate 16 at dawn 12. In this way, the inner platen 16 is used over substantially its entire circumferential extent for the heat exchange between the bypass circuit fluid 224 and the air passing through the blading sector. Fig. 7 shows a fourth blading sector embodiment 300, similar to the blading sector 10 of the first embodiment except for the branch circuit and the distribution circuit. Thus, the identical elements retain the same numerical reference while the modified elements have their reference sign incremented by "300". Note that Figure 7 shows two adjacent blade sectors 300.
    [0016] In this example, the distribution circuit 322 includes a first supply line 322aa, a second supply line 322ab and a single recovery line 322b, these conduits extending circumferentially. As indicated by the arrows, the flow direction of the fluid within the first supply line 322aa is opposed to the flow direction of the fluid within the second supply line 322ab. In this example, the branch circuit 324 in each blading sector 300 comprises two channels, namely a first channel 324a and a second channel 324b. The first channel 324a fluidly connects a first input 325aa and a first output 325ba extending into the two blades 12 of the blading sector 300, and into the outer platen 18. The second channel 324b fluidly connects a second input 325ab and a second output 325bb extending into the two blades 12 of the blading sector 300, and in the outer plate 18.
    [0017] Thus, in this example, the first and second channels 324a and 324b extend over the entire radial height H of the two adjacent blades 12 of the blading sector 300, and over the entire circumferential extent Z of the outer plate 18 between them. 12. Of course, the first and second inlets 325a and 325a b are respectively fluidly connected to the branch taps 323aa and 323ab of the first and second supply lines 322aa and 322ab while the first and second outlets 325ba and 325bb are respectively fluidly connected to the branch taps 323ba and 323bb of the recovery line 322b.
    [0018] Furthermore, the first and second inputs 325aa and 325ab and the first and second outputs 325ba and 325bb are arranged so that the fluid flow directions within the first and second channels 324a and 324b are opposite. In this example, the first input 325aa and the second output 325bb are arranged, in the circumferential direction, in the vicinity of the same blade among the two vanes 12 of the blading sector 300 while the first output 325ba and the second input 325ab are arranged, in the circumferential direction, in the vicinity of the other blade among the two blades 12 of the blading sector 300. The fluid flow directions firstly within the first and second supply ducts 322aa and 322ab, and secondly within the first and second channels 324a and 324b allow a great temperature homogeneity on the one hand within each blading sector 300, and on the other hand between each of the sectors of Blading 300 forming the blade 9 of the turbojet engine 1. In order to obtain such a homogeneity of temperature, it is advantageous for the first and second supply ducts 322aa and 322ab to be arranged parallel to one another and to close to each other to allow a heat exchange between the fluid flowing in the two pipes. This arrangement is all the more advantageous in a configuration where in each supply line, the fluid tends to cool as it goes, which is particularly the case when the first and second lines of supply are arranged in the inner plate 16 so as to achieve a heat exchange with the air of the vein. It is furthermore preferable that the inlet fluid temperatures of the first and second supply lines respectively are substantially the same. The mutual heat exchange between the fluid flowing in the two pipes in opposite flow directions allows the fluid temperatures in these two pipes to be homogenized, and consequently to obtain a relatively homogeneous fluid temperature between the respective inlets 325aa and 325ab of the branch circuits 324 of the various blading sectors 300. According to a variant shown in FIG. 8, to further improve the homogeneity of the temperature of each blading sector 35 300 ', the third and fourth channels 324c and 324d extend into two adjacent blade areas 300 '. It is therefore understood that each bladed area 300 'comprises two distinct portions of the third channel and two distinct portions of the fourth channel, the two third channel portions and the two fourth channel portions of the apartment respectively at two thirds and two fourths respectively. separate channels 5. These third and fourth channels 324c and 324d extend, in each of the blading sectors 300 'over the entire radial height H of a blade 12. In addition, these third and fourth channels 324c and 324d extend over the entire circumferential extent of the outer plate 18 of one of two adjacent blade sectors 300 'between the two adjacent blades 12 respectively belonging to the two adjacent distinct blade sectors 300'. Thus, the third and fourth channels 324c and 324d comprise connectors 330 to ensure their fluidic continuity between two adjacent blade sectors 300 '. These third and fourth channels 324c and 324d respectively fluidly connect a third input 324ac with a third output 325bc and a fourth input 324ad with a fourth output 325bd. The third and fourth inputs 325ac and 325ad and the third and fourth outputs 325bc and 325bd are arranged such that the fluid flow directions within the third and fourth channels 324c and 324d are opposite. Of course, the third and fourth inlets 325ac and 325ad are respectively fluidly connected to the branch taps 323ac and 323ac of the first and second supply lines 322aa and 322ab while the third and fourth outlets 325bc and 325bd are respectively fluidly connected to the taps. bypass 323bc and 323bd of the recovery line 322b. Of course according to another variant not shown the first and second supply lines 322aa and 322ab and / or the recovery line 322b are formed at least in part in the inner trays 16 of the blade sectors 300 or 300 ', similarly to the variant of the first embodiment of FIG. 3. Although the present invention has been described with reference to specific exemplary embodiments, it is evident that modifications and changes can be made to these examples without depart from the general scope of the invention as defined by the claims. In particular, individual features of the various illustrated / mentioned embodiments may be combined in additional embodiments. Therefore, the description and drawings should be considered in an illustrative rather than restrictive sense. In particular, the configuration of the channels can be combined and transposed from one embodiment / example / variant to another.
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. A turbomachine comprising at least one stator vane sector (10, 100, 200, 300) and a fluid distribution circuit (22, 322), the stator vane sector comprising at least one vane (12), a fluid inlet (25a, 325aa), a fluid outlet (25b, 325ba) and a channel (24a, 124a, 224a, 324a) fluidly connecting the fluid inlet (25a, 325aa) and the fluid outlet (25b, 325ba) extending at least partly in the blade (12), the blade and the channel being adapted to allow, when the turbomachine is operating, a heat exchange between a hot fluid passing through the channel and a flow of air cold passing through the stator vane sector, the fluid distribution circuit (22, 322) having at least one supply line (22a, 322aa) and at least one recovery line (22b, 322b) separate from the conduit the fluid inlet (25a, 325aa) being fluidly connected to a bypass tap (23a, 323aa) of the supply line ion (22a, 322aa) while the fluid outlet (25b, 325ba) is fluidly connected to a bypass tap (23b, 323ba) of the recovery line (22b, 322b).
    [0002]
    The turbomachine according to claim 1, wherein the stator vane sector (100, 200, 300) comprises an inner plate (16) connected to the inner end of the blade (12) and an outer plate (18). ) connected to the outer end of the blade (12), both the fluid inlet (25a, 325aa) and the fluid outlet (25b, 325ba) in one of the inner plate (16). and the outer plate (18) while the channel (124a, 224a, 324a) extends partly in the other plate among the inner plate (16) and the outer plate (18).
    [0003]
    The turbomachine according to claim 1 or 2, wherein the stator vane section (200, 300) comprises a plurality of vanes (12), the channel (224a, 324a) extending in at least two vanes (12). .
    [0004]
    The turbomachine according to claim 3, wherein the stator vane sector (200) comprises an inner plate (16) connected to the inner end of each of the vanes (12) and an outer plate (18) connected thereto. at the outer end of each of the blades (12), the channel (224a) extending into the inner plate (16) and into the outer plate (18).
    [0005]
    5. Turbomachine according to any one of claims 1 to 4, wherein the blading sector (10, 100) comprises a plurality of blades (12), at least two blades (12) each comprising a channel (24a, 124a). , the blades and the channels being adapted to allow, when the turbomachine is operating, a heat exchange between a hot fluid passing through the channel and a cold air flow passing through the stator vane sector, the channel (24a, 124a) a blade (12) being distinct from the channel (24a, 124a) of the other blade (12), the blade sector (10, 100) comprising as many fluid inlets (25a) and fluid outlets (25b) as channels (24a, 124a), each channel (24a, 124a) being respectively fluidly connected to a fluid inlet (25a) and a fluid outlet (25b) separate from the fluid inlet (25a) and the fluid outlet (25b) of the other channel (24a, 124a).
    [0006]
    A turbomachine according to any one of claims 1 to 5, comprising at least two stator vane sectors (10, 100, 200, 300), each stator vane section comprising at least one vane (12). a fluid inlet (25a, 325aa), a fluid outlet (25b, 325ba) and a channel (24a, 124a, 224a, 324a) fluidly connecting the fluid inlet (25a, 325aa) and the fluid outlet ( 25b, 325ba) extending at least partly in the blade (12), the blade and the channel of each of the blade sectors being adapted to allow, when the turbomachine is operating, a heat exchange between a fluid heat passing through each channel and a flow of cold air passing through the stator vane sector, the fluid inlet (25a, 325aa) of each stator vane sector being fluidly connected to a bypass tapping (23a, 323aa) of the supply line (22a, 322aa) while the fluid outlet (25b, 325ba) of each blading sector is fluidly connected at a bypass tap (23b, 323ba) of the recovery line (22b, 322b). 35
    [0007]
    The turbomachine according to any of claims 1 to 6, wherein the supply line forms a first supply line (322aa) while the channel, the fluid inlet and the fluid outlet respectively form a first channel (324a), a first fluid inlet (325aa) and a first fluid outlet (325ba), the distribution circuit (322) comprising a second supply line (322ab), the flow direction of the fluid in the first supply line (322aa) being opposed to the flow direction of the fluid in the second supply line (322ab) while the stator vane section (300) comprises a second fluid inlet (325ab) a second fluid outlet (325bb) and a second channel (324b) fluidically connecting the second fluid inlet (325ab) and the second fluid outlet (325bb) extending at least partially into the blade (12) , dawn and the second channel being ada to allow, when the turbomachine is operating, a heat exchange between a hot fluid passing through the second channel and a cold air flow passing through the stator vane sector, the second fluid inlet (325ab) being fluidly connected to a bypass tap (323ab) of the second supply line (322ab) while the second fluid outlet (325bb) is fluidly connected to a bypass tap (323bb) of the recovery line (322b).
    [0008]
    The turbomachine according to any one of claims 1 to 7, wherein the stator vane section (10 ') comprises an inner plate (16) connected to the inner end of the blade (12) and an inner plate (16). outer plate (18) connected to the outer end of the blade (12), the fluid distribution circuit (22) being at least partly formed in a plate of the inner plate (16) and the outer plate (18). ).
    [0009]
    9. A turbomachine according to any one of claims 1 to 8, wherein the bypass tap (25a, 325aa) of the supply line (22a, 322aa) and / or the branch tap (25b, 325bb) of the recovery line (22b, 322b) is / are equipped with an isolation valve (26).
    [0010]
    10.Turbornachine according to any one of claims 1 to 9, wherein the fluid is a liquid, especially oil. 3034474 23
    [0011]
    11.Turbomachine according to any one of claims 1 to 9, wherein the fluid is a heat transfer fluid, and wherein the distribution circuit comprises a heat exchanger (28) configured to exchange heat between the heat transfer fluid and 5 another fluid, especially oil.
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    同族专利:
    公开号 | 公开日
    US20180087392A1|2018-03-29|
    CN107438707B|2021-02-09|
    EP3277937A1|2018-02-07|
    EP3277937B1|2019-08-28|
    FR3034474B1|2019-08-09|
    WO2016156743A1|2016-10-06|
    CN107438707A|2017-12-05|
    US11156114B2|2021-10-26|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2474258A|1946-01-03|1949-06-28|Westinghouse Electric Corp|Turbine apparatus|
    US4645415A|1983-12-23|1987-02-24|United Technologies Corporation|Air cooler for providing buffer air to a bearing compartment|
    EP0743435A1|1995-05-15|1996-11-20|Aerospatiale Societe Nationale Industrielle|Precooling heat exchange arrangement integral with mounting structure fairing of gas turbine engine|
    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|
    US5782076A|1996-05-17|1998-07-21|Westinghouse Electric Corporation|Closed loop air cooling system for combustion turbines|
    JP3457831B2|1997-03-17|2003-10-20|三菱重工業株式会社|Gas turbine blade cooling platform|
    JPH10280908A|1997-04-09|1998-10-20|Toshiba Corp|Stator blade of gas turbine|
    US7926289B2|2006-11-10|2011-04-19|General Electric Company|Dual interstage cooled engine|
    WO2011075013A1|2009-12-17|2011-06-23|Volvo Aero Corporation|Arrangement and method for closed flow cooling of a gas turbine engine component|
    US10145253B2|2012-04-05|2018-12-04|Safran Aircraft Engines|Stator vane formed by a set of vane parts|
    FR3028576B1|2014-11-19|2016-12-23|Snecma|TURBOMACHINE STATOR AUBING SECTOR COMPRISING HOT FLUID CIRCULATION CHANNELS|US10196932B2|2015-12-08|2019-02-05|General Electric Company|OGV heat exchangers networked in parallel and serial flow|
    FR3059353B1|2016-11-29|2019-05-17|Safran Aircraft Engines|AIRBOARD TURBOMACHINE EXIT OUTPUT AUDE COMPRISING A LUBRICANT-BENDED ZONE HAVING AN IMPROVED DESIGN|
    GB201801165D0|2018-01-24|2018-03-07|Rolls Royce Plc|Oil pipe assembly|
    CN108386275B|2018-03-05|2019-05-10|清华大学|A kind of compressor air inlet machine cooling system and its cooling means|
    US11130582B2|2018-08-03|2021-09-28|Rolls-Royce Corporation|Systems and methods of optimizing cooling and providing useful heating from single phase and two phase heat management in propulsion systems|
    FR3093530B1|2019-03-08|2021-04-02|Safran Aircraft Engines|Turbomachine comprising a heat exchanger formed in a platform|
    US11165309B2|2019-05-10|2021-11-02|Hamilton Sundstrand Corporation|Motor cooling system and method|
    FR3099797B1|2019-08-07|2021-09-10|Safran Aircraft Engines|ISOLATION OF A TURBOMACHINE STATOR BLADE HEAT EXCHANGER IN THE EVENT OF A LEAK|
    DE102019135339A1|2019-12-19|2021-06-24|Rolls-Royce Deutschland Ltd & Co Kg|Aircraft gas turbine engine|
    FR3107560B1|2020-02-21|2022-02-04|Safran Aircraft Engines|ISOLATION OF A TURBOMACHINE HEAT EXCHANGER IN THE EVENT OF LEAKAGE BY AN ELECTRICAL AND HYDROMECHANICAL DISTRIBUTOR|
    法律状态:
    2016-04-07| PLFP| Fee payment|Year of fee payment: 2 |
    2016-10-07| PLSC| Publication of the preliminary search report|Effective date: 20161007 |
    2017-04-06| PLFP| Fee payment|Year of fee payment: 3 |
    2018-02-23| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170707 |
    2018-03-22| PLFP| Fee payment|Year of fee payment: 4 |
    2019-03-25| PLFP| Fee payment|Year of fee payment: 5 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 6 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1552802A|FR3034474B1|2015-04-01|2015-04-01|TURBOMACHINE EQUIPPED WITH A DRAINING SECTOR AND A COOLING CIRCUIT|
    FR1552802|2015-04-01|FR1552802A| FR3034474B1|2015-04-01|2015-04-01|TURBOMACHINE EQUIPPED WITH A DRAINING SECTOR AND A COOLING CIRCUIT|
    PCT/FR2016/050728| WO2016156743A1|2015-04-01|2016-03-31|Turbine engine provided with a bladed sector and a cooling circuit|
    US15/563,188| US11156114B2|2015-04-01|2016-03-31|Turbomachine provided with a vane sector and a cooling circuit|
    CN201680021255.3A| CN107438707B|2015-04-01|2016-03-31|Turbine engine provided with blade sectors and cooling circuit|
    EP16717189.1A| EP3277937B1|2015-04-01|2016-03-31|Turbine engine provided with a bladed sector and a cooling circuit|
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