• 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:
    The invention relates to a turbomachine turbine blade (11), comprising a blade (12) extending in a span direction between a foot and an apex, a first internal lateral cavity (54) running along the intrados wall. (21) and a second internal lateral cavity (56) along the extrados wall. The blade (11) further comprises at least one internal central duct (53) configured to collect air for cooling the blade (12). The central duct (53) extends between the lateral cavities (54, 56), being separated from the lateral cavities (54, 56) to be at least partially thermally insulated from the intrados (21) and extrados walls. The lateral cavities (54, 56) communicate with each other in a junction region (72) located downstream of the central duct (53) over most of the height of the central duct in the span direction.
    公开号:FR3021698A1
    申请号:FR1454865
    申请日:2014-05-28
    公开日:2015-12-04
    发明作者:Charlotte Marie Dujol；Patrice Eneau
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] 1 TURBINE DAWN, COMPRISING A CENTRAL COOLING DUCT THERMALLY INSULATED OF WINDOWS OF THE DAWN BY TWO JOINT SIDE CAVITIES IN DOWNSTREAM OF THE CENTRAL CONDUIT DESCRIPTION TECHNICAL FIELD The invention relates to a turbomachine-type aircraft engine blade, such as by example a turbofan engine or a turbofan turboprop. STATE OF THE PRIOR ART In such an engine, the outside air is admitted into an inlet sleeve to pass through a fan comprising a series of rotating blades before splitting into a central primary flow and a secondary flow surrounding the primary flow. The primary flow is then compressed before arriving in a combustion chamber, after which it relaxes by crossing a set of turbines before being evacuated backwards generating thrust. The secondary flow is propelled directly backwards by the blower to generate a complementary thrust. The expansion in the turbines, which drives the compressor and the blower, takes place at high temperature because it occurs immediately after combustion. This turbine is thus designed and dimensioned to operate under severe conditions of temperature, pressure and fluid flow.
    [0002] Each turbine comprises a succession of stages each comprising a series of blades oriented radially and regularly spaced around a rotation shaft of the engine. This central shaft carries the rotating elements of the turbine as well as the rotary elements of the compressor and the fan. Concretely, the blades of the turbine which are subjected to the most severe conditions are those of the first stages of expansion of this turbine, namely the 3021698 2 stages closest to the combustion zone and which are commonly called high pressure stages. In general, the increased performance requirements and changing regulations lead to the design of smaller size 5 engines operating in increasingly severe environments. This involves increasing the strength and performance of the high pressure turbine blades, particularly with regard to their temperature resistance. Nevertheless, the existing improvements in the materials and coatings of these blades are not sufficient to enable them to withstand the high temperatures that can be achieved by the flow downstream of the combustion chamber. This situation leads to reconsider the cooling of these blades to improve it so that they can withstand these new operating conditions. This cooling is ensured by circulating inside these blades 15 fresh air which is taken from the turbojet engine upstream of the combustion. This air is admitted at the bottom of the dawn, to walk along an internal circuit of the dawn to cool it, and it is evacuated from the dawn by holes through the wall of this dawn and distributed on this wall. These holes serve to evacuate the cooling air, but they also create on the outer surface of the blade a film of air colder than the air resulting from the combustion, which also contributes to limiting the temperature of the air. 'dawn. To increase the cooling efficiency, the inner regions of the blade in which the cooling air circulates comprise artifices, that is to say, internal reliefs which disturb the fluid flow of the cooling air, to increase heat transfer from the wall of the blade to this cooling air circulating in the inner ducts of the blade. These cooling architectures are penalized by the fact that the length of the internal circuit of the blade gives rise to an air that is too warmly heated when it reaches the end of this circuit, so that its cooling efficiency is limited in the regions of end of course where one seeks on the contrary to obtain an increased cooling efficiency.
    [0003] The object of the invention is to provide a blade structure for improving the cooling efficiency of this blade. DISCLOSURE OF THE INVENTION The invention aims to at least partially solve the problems encountered in the solutions of the prior art. In this regard, the invention relates to a turbine blade of a turbomachine such as a turboprop or turbojet, the blade comprising: - a foot, - a blade carried by the foot and extending in one direction of span 10 ending in a vertex, the blade including a leading edge and a trailing edge located downstream of the leading edge, the blade comprising a lower pressure wall and an extrados wall, spaced apart one of the other and connecting the leading edge to the trailing edge, - a first internal lateral cavity along the intrados wall and a second internal lateral cavity along the extrados wall, - at least one central duct internally configured to collect at the foot of the cooling air for circulating in the blade to cool, the central duct extending between the lateral cavities, being separated from the lateral cavities to be thermally insulated from the walls of intrados and extrados by cavities l atérales. The lateral cavities communicate with each other, being joined by a junction region located downstream of the central duct and extending over most of the height of the central duct in the span direction. The two lateral cavities preferably form with the junction region a single cavity enveloping the central duct over most of the height of the central duct.
    [0004] The internal configuration of the blade, through which the internal lateral cavities communicate with each other, being united downstream of the central duct, allows better thermal insulation of the cooling air circulating in the central duct.
    [0005] The invention may optionally include one or more of the following features combined with one another or not. Advantageously, the junction region extends over the entire height of at least one of the first and second lateral recesses in the span direction. The junction region preferably extends over the entire height of the central duct in the span direction. According to a particular embodiment, the junction region has, in at least one section plane orthogonal to the span direction a U-shape open upstream. According to an advantageous embodiment, the ridge of the U has a substantially constant thickness in a longitudinal direction of elongation of the blade from the leading edge to the trailing edge. According to another advantageous embodiment, the central duct, the first lateral cavity has smooth internal surfaces. The lateral cavities preferably comprise turbulence promoters and / or deflectors, intended to promote the turbulence of the air inside the blade and / or to ensure a more homogeneous distribution of the cooling air. According to another embodiment, the blade comprises several distinct internal lateral cavities along the intrados and / or several distinct lateral cavities along the extrados. In this case, the junction region is preferably located in a downstream zone of the plurality of lateral cavities. The invention also relates to a molding assembly for the manufacture of a blade as defined above, comprising at least one cavity 25 and a set of cores for the formation of the inner conduit and lateral cavities. The invention also relates to a turbomachine turbine comprising a blade as defined above. Finally, the invention relates to a turbomachine comprising a turbine 30 as defined above. The turbine is then preferably a high pressure turbine 3021698 5 in which the blades are subjected to higher temperatures than in a turbomachine low pressure turbine. BRIEF DESCRIPTION OF THE DRAWINGS The present invention will be better understood on reading the description of exemplary embodiments, given purely by way of indication and in no way limiting, with reference to the appended drawings in which: FIG. 1 is a diagrammatic view of a turbofan engine in longitudinal section; Figure 2 is a schematic perspective view of a turbine blade according to a first embodiment of the turbojet engine shown in Figure 1; Figure 3 is a perspective view showing the hollow internal parts of a turbine blade according to the first embodiment of the invention; Figure 4 is a partial diagrammatic sectional view of the blade of the first embodiment in a section orthogonal to the span direction. DETAILED DESCRIPTION OF PARTICULAR EMBODIMENTS As can be seen in FIG. 1, a front part of a turbofan engine 1 comprises an inlet sleeve 2 in which the air is admitted before being sucked by the airfoils. a blower 3. After passing the blower region, the air splits into a central primary stream and a secondary stream that surrounds the primary stream. The primary air flow then passes through a first compressor 4 located immediately after the fan 3 while the secondary flow is propelled backwards to directly generate additional thrust by being blown around the primary flow.
    [0006] The primary flow then passes through a second compression stage 6, before reaching a chamber 7 where its combustion takes place after injection and vaporization of a fuel. After combustion, this primary flow is expanded in a high pressure turbine 8 and then in a low pressure turbine (not shown) to drive the compression stages and the fan in rotation, before being expelled towards the rear of the engine to generate a thrust . The turbomachine 1 and its components have a shape of revolution about a longitudinal axis AX. It comprises in particular an outer casing 9 also having a shape of revolution and extending from the front of the engine where it delimits the air inlet duct, to the rear part where it delimits the duct by which the primary and secondary flows are evacuated, the front and rear to be considered with respect to the direction of travel of the aircraft equipped with this turbojet engine. This housing 9 supports the rotating components located in the center of the engine and which comprise a rotary shaft carrying the blades of the fan as well as the compression stages and the turbine with their vanes. Such a blade, which is indicated by 11 in FIG. 2, comprises a foot P by which it is fixed to a not shown rotary body, called a turbine disk, and a blade 12 carried by this foot P and constituting the aerodynamic part of this dawn. As can be seen in FIG. 2, the blade 11 comprises between the foot P and the blade 12 an intermediate region 13 called a platform. The assembly formed by the foot P and the blade 12 is a single hollow piece integrally cast and having internal conduits through which circulates cooling air. These internal ducts not visible in Figure 2 comprise intake ports opening on the lower face 14 of the foot P and through which these ducts are supplied with fresh air. The hollow wall of the blade 12 has through holes and slots through which the cooling air is discharged. The blade 12 has a twisted left shape having a substantially rectangular contour, approximating a parallelepiped. It comprises a base 16 through which it is connected to the foot P and which extends approximately parallel to the axis of rotation AX. It also comprises a leading edge 17 oriented radially with respect to the axis AX and located at the upstream level AM of the blade, that is to say the front region of this blade, relative to to the direction of advancement of the engine that it equips in service. This blade also has a trailing edge 18 oriented approximately parallel to the leading edge 17 spaced from it along the axis AX to be located at the downstream region AV or rear of the 'dawn. It further comprises a vertex S approximately parallel to the base 16 and spaced therefrom in a radial direction relative to the axis AX. The two main walls of this blade are its intrados wall 21, which is the visible wall in FIG. 2, and its extrados wall which is the opposite wall spaced from the intrados wall, and which is not not visible in Figure 2 because it is masked by the intrados wall 21. The intrados and extrados walls are joined at the leading edge 17, at the trailing edge 18 and also in the S summit region of this dawn. These walls are spaced from one another at the base 16 to allow the admission of cooling air into the inner region of the blade.
    [0007] The leading edge 17 has a domed shape and is provided with a series of cooling holes 22 passing through the wall of the blade in this region. The trailing edge 18 has a tapered shape, and it comprises a series of cooling slots 23. These slots 23 are slots of short length spaced apart from each other being located in the extension of each other, for constitute an assembly that runs along the end of the trailing edge 18, each slot 23 passing through the lower surface wall 21. In operation, the fluid in which this blade 11 is located moves relative thereto from the edge Attack 17 towards the trailing edge 18 along the intrados 21 and the extrados. The pressure wall 21, which is subjected to significant heating in operation, has a series of holes 24 substantially parallel to the leading edge 17, located downstream of this leading edge, and another series of holes 26. substantially parallel to the trailing edge 18 being located upstream of the trailing edge 18 and slots 23 that it comprises. The series of holes 24 and 26 thus extend one and the other along the span direction EV of the blade, which is the radial direction with respect to the axis AX.
    [0008] The region of the summit S of the blade 11 has, unlike the leading edge 17 and the trailing edge 18, a certain thickness, and it also has a shape defining a hollow portion said bath. More concretely, this vertex S has a closing wall which connects the intrados and extrados walls, this closure wall having an orientation which is generally perpendicular to the intrados and extrados walls and parallel to the axis. AX, which corresponds to an orientation perpendicular to the span direction EV. This closing wall, which is not visible in FIG. 2, is set back towards axis AX with respect to the free edge of the intrados wall and at the free edge of the extrados wall, so that it constitutes, together with these edges, a hollow portion open in the direction opposite to the axis AX. A series of additional holes 27 through the intrados wall are provided along the S-vertex to provide significant cooling of this blade tip which is under significant stress because it constitutes the highest speed portion of the blade. compared to the fluid. The series of holes 27 extends parallel to the closure wall, and the blade comprises, complementarily, holes not visible in Figure 2 which pass through the closure wall to open into the hollow portion called bathtub which is at the top of the blade.
    [0009] As indicated above, such a blade is a hollow one-piece piece. It is manufactured by molding a titanium or other metal material, using a set of cores to delineate the inner ducts of its hollow portion and portions of rods to form its through holes. The cores, rods and the like are removed once the molding process is complete, typically with a chemical etching process capable of dissolving these elements without altering the molded material. In particular, the molding assembly of FIG. 3 comprises a central core intended for the manufacture of an internal central duct of the blade, and a monobloc peripheral core intended for the production of lateral cavities of the intrados and the extrados. .
    [0010] The molding assembly shown schematically in part in Figure 3 is used to manufacture the blade 11 shown in section in Figure 4. As such, Figure 3 shows internal regions of the blade 11 which is there represented by the shapes of the cores making it possible to manufacture this blade 11. In other words, the shapes which are in relief in FIG. 3 represent representations of the hollow shapes of the blade represented in FIG. 4. In the embodiment represented in FIG. 3 and in FIG. 4, the leading edge 17 and, to a lesser extent, the crown S are supplied with cooling air via an internal central duct 53 which extends from the foot P of the dawn to at the summit S of this dawn. The central duct 53 collects, at the foot P, cooling air to circulate in the blade 12. The air cooling the hollow region of the leading edge 17 is then discharged through the through holes 22 formed in the outer wall of the blade 12.
    [0011] The blade 11 of FIG. 3 also comprises a first lateral cavity 54 running along the intrados wall, and a second lateral cavity 56 running along the extrados. These two lateral cavities 54, 56 thermally isolate the central duct 53 of the intrados and extrados walls which are heated by the gas flows surrounding the blade 12. The air which is supplied to the leading edge 17 of the blade 11 and to a lesser extent at the top S through the central duct 53 is kept cool during its course in this duct, thanks to these lateral cavities which act as a heat shield between the colder central duct 53 and the walls of the duct. intrados 21 and extrados. For this purpose, the central duct 53 is physically separated from the lateral cavities 54, 56, between which it extends. In order to minimize heating and pressure drops within the blade 11 of FIG. 3, the central conduit 53 has smooth internal surfaces. As seen in Figure 3, the first lateral cavity 54 has a small thickness, and extends from the foot P to the region of the summit S having a generally rectangular contour. This first lateral cavity 54 has a width sufficient to mask or cover the central duct 53.
    [0012] Similarly, the second lateral cavity 56 also has a small thickness, and extends from the foot P to the region of the summit S. This second lateral cavity 56 has a generally rectangular contour, having a sufficient width to hide or cover the central duct on the side of the extrados.
    [0013] The cooling of the blade 11 is further optimized by minimizing the pressure losses in the inner central duct 53 in order to reduce the heat exchange, and on the contrary providing for turbulence promoters in the lateral cavities 54, 56. Each lateral cavity 54, 56 is advantageously provided with deflectors, disrupters and / or bridges to create turbulence in the circulation of the cooling air. Lateral cavities54, 56 thus have increased efficiency as a thermal screen because they absorb heat from the outer walls they run along. The air circulating in the central duct 53 is subjected to low pressure losses in order to circulate rapidly and to heat as little as possible. The two lateral cavities 54 and 56 surround the central duct 53 at least in the rear part of the central duct 53. They thus surround the inner central duct 53 about three quarters of its circumference. The lateral cavities 54, 56 are joined at the rear or downstream part of the blade 11 in a junction region 72 where they communicate with each other. The junction region 72 has, in at least one sectional plane orthogonal to the direction of wingspan EV, a U-shape open upstream. The ridge of the U has a substantially constant thickness 76 in the longitudinal direction AX of elongation of the blade 12 from the leading edge 17 to the trailing edge 18. The junction region 72 has a U-shape open upstream and a thickness 76 approximately constant, over the entire height 78 of the junction region 72 in the span direction EV.
    [0014] The junction region 72 allows the central conduit 53 to provide the leading edge 17 for supplying even cooler air with cooling air, thereby limiting the premature deterioration of the blade 12. The two cavities 54 56 with the junction region 72 constitute a single cavity surrounding the central duct 53 over the majority of the outer surface of the wall 58 of the inner central duct 53. The junction region 72 extends over most of the height 78 of this central duct 53. In practice, 3021698 11 and as visible in Figure 3, the height 78 or length of the junction region 72 in the span direction EV corresponds to the height or length of the first lateral cavity 54 according to EV scale direction. The height 78 of the junction region 72 also corresponds to the height or length of the inner central duct 53 in the span direction EV. The cooling air supply of the lateral cavities 54, 56 may be carried out separately by two feed ducts opening separately into the blade root, the lateral cavities then being united only in the region of the blade 12. It is possible to provide a single feed channel for the two lateral cavities having a U-shaped section in a cross-sectional plane to the span direction EV. The downstream of the extrados wall is devoid of through holes, in particular because of the too low air pressure in this region. The leading edge 17 of the blade is cooled by an upstream cooling ramp 62 which extends from the base 16 of the blade to the apex S. The leading edge 17 is not fed in such a way. direct by the foot P but through the central conduit 53, in a calibrated manner. This calibrated feed is provided by calibrated passages 64 regularly spaced along the span direction EV of the blade and which each connect the central duct 53 to the upstream ramp 62. Each passage 64 has a calibrated diameter, c ' that is to say selected at the design to get in the zone of the ramp 62 it feeds a desired air flow that is conditioned by the thermal dawn in this region. The wall of the blade 11 defining the leading edge 17 has unrepresented holes through which the air circulating in the upstream cooling ramp 62 passes through this wall to cool the leading edge 17. The cooling of the Leading edge 17 is partially impacted on the leading edge 17 of the cooling air from the upstream ramp 62. The cooling slots 23 of the trailing edge, including those located in the region from the top S, are supplied with cooling air, isolated from the air supply of the leading edge 17 or the top S. A downstream cooling ramp 66 extends from the foot P, where it is fed directly via this foot P, to the region of the summit S. The downstream ramp 66 supplies cooling air to the slots 23 of the trailing edge 18. The downstream ramp 66 is separated from the junction region 72, and more generally, lateral cavities 54, 56 by a transverse wall 74 extending substantially in the span direction EV and in a direction orthogonal to this direction and to the longitudinal direction AX of the blade 11. Since the central duct 53 is separated from the lateral cavities 54 56, the transverse wall 74 is devoid of direct mechanical contact with the wall 58 delimiting the central duct 53. In a non-illustrated variant of embodiment of FIG. 3, and in a similar manner to the cooling air supply of the edge 17, the cooling slots 23 of the trailing edge can be supplied with cooling air calibrated by the downstream ramp 66. Holes passing through the walls 15 of the blade and opening into the internal lateral cavities forming a heat shield can be provided to establish an optimal air flow in these cavities. Each of these holes is advantageously located at a depression zone to promote air circulation. Each of these holes ensures that the air collected at the bottom of the blade and which is fed into a cavity forming a heat shield, is sucked out of the blade after having walked into this cavity.
    权利要求:
    Claims (9)
    [0001]
    REVENDICATIONS1. A turbine blade (11) of a turbomachine such as a turboprop or a turbojet, the blade (11) comprising: a foot (P), a blade (12) carried by the foot (P) and extending according to a span direction (EV) ending with a top (S), the blade (12) including a leading edge (17) and a trailing edge (18) located downstream of the leading edge (17). ), the blade (12) comprising an intrados wall (21) and an extrados wall spaced from one another and connecting the leading edge (17) to the trailing edge (18), a first internal lateral cavity (54) along the intrados wall (21) and a second internal lateral cavity (56) running along the extrados wall, at least one internal central duct (53) configured to collect at the foot (P) cooling air for circulating in the blade (12) for cooling, the central duct (53) extending between the lateral cavities (54, 56), separated from the lateral cavities (54, 56) for to be isolated th ermally of the intrados (21) and extrados walls by the lateral cavities (54, 56), in which the lateral cavities (54, 56) communicate with one another, by being joined by a junction region (72) located in downstream of the central duct (53) and which extends over the majority of the height (78) of the central duct in the span direction (EV).
    [0002]
    2. blade (11) according to the preceding claim, wherein the junction region (72) extends over the entire height of at least one of the first and second lateral cavity (54, 56) according to the span direction (EV).
    [0003]
    3. blade (11) according to any preceding claim, wherein the junction region (72) has, in at least one sectional plane orthogonal to the span direction (EV), a U-shape open towards the upstream. 3021698 14
    [0004]
    4. blade (11) according to the preceding claim, wherein the ridge of the U has a thickness (76) substantially constant in a longitudinal direction (AX) of elongation of the blade (12) of the leading edge (17) to trailing edge (18). 5
    [0005]
    A blade (11) according to any one of the preceding claims, wherein the central conduit (53) has smooth inner surfaces and the lateral cavities (54,56) comprise turbulence promoters and / or baffles for increasing thermal exchanges inside the dawn (11). 10
    [0006]
    6. blade (11) according to any one of the preceding claims, wherein the blade (11) comprises a plurality of distinct internal lateral cavities along the intrados and / or several distinct lateral cavities along the extrados. 15
    [0007]
    A molding assembly for the manufacture of a blade (11) according to any one of claims 1 to 6, comprising at least one impression and a set of cores for the formation of the inner conduit and the lateral cavities.
    [0008]
    8. Turbine turbine (8) comprising a blade according to any one of claims 1 to 6.
    [0009]
    9. Turbomachine comprising a turbine (8) according to the preceding claim.
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    FR3057906B1|2016-10-20|2019-03-15|Safran Aircraft Engines|OPTIMIZED COOLING TURBINE TANK|
    法律状态:
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    申请号 | 申请日 | 专利标题
    FR1454865A|FR3021698B1|2014-05-28|2014-05-28|TURBINE BLADE, INCLUDING A CENTRAL COOLING DUCT THERMALLY INSULATED FROM THE BLADE WALLS BY TWO JOINT SIDE CAVITIES DOWNSTREAM FROM THE CENTRAL DUCT|FR1454865A| FR3021698B1|2014-05-28|2014-05-28|TURBINE BLADE, INCLUDING A CENTRAL COOLING DUCT THERMALLY INSULATED FROM THE BLADE WALLS BY TWO JOINT SIDE CAVITIES DOWNSTREAM FROM THE CENTRAL DUCT|
    PCT/FR2015/051373| WO2015181482A1|2014-05-28|2015-05-22|Turbine blade comprising a central cooling duct and two side cavities connected downstream from the central duct|
    US15/314,033| US10337333B2|2014-05-28|2015-05-22|Turbine blade comprising a central cooling duct and two side cavities connected downstream from the central duct|
    EP15732795.8A| EP3149281A1|2014-05-28|2015-05-22|Turbine blade comprising a central cooling duct and two side cavities connected downstream from the central duct|
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