• 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 turbine blade (91) comprising a foot (P), a blade extending in a span direction (EV) ending in a vertex (S) and comprising a leading edge and a trailing edge and a lower pressure wall and an extrados wall, this blade further comprising: at least one upstream duct (93) configured to collect air at the foot (P) to cool the edge attacking by evacuating this air through holes through the wall of the leading edge; at least one downstream duct (96) separate from the upstream duct (93) and configured to collect air at the foot (P) to cool the trailing edge by evacuating this air through holes (97) passing through the intrados wall upstream of the trailing edge; an internal lateral cavity (101) running along the intrados wall to form a heat shield insulating the downstream duct (96).
    公开号:FR3021699A1
    申请号:FR1454869
    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] TECHNICAL FIELD The invention relates to an aircraft engine blade of the turbomachine type, such as for example a turbofan engine or a turboprop turbojet engine. 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. 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.
    [0002] 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 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 3021699 2 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 vanes 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.
    [0003] This cooling is ensured by circulating inside these vanes 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, 15 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 interior regions of the blade in which the cooling air circulates include 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 internal 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 strongly heated when it reaches the end of this circuit, so that its cooling efficiency is limited in the regions. end of course, and especially at the top of dawn where one seeks on the contrary to obtain an increased cooling efficiency. The object of the invention is to provide a blade structure for improving the cooling efficiency of this blade.
    [0004] SUMMARY OF THE INVENTION To this end, the subject of the invention is a turbine engine turbine blade such as a turboprop or a turbojet engine, this blade comprising a foot, a blade carried by this foot, this blade comprising a leading edge and a trailing edge located downstream of the leading edge, this blade comprising a lower pressure wall and an extrados wall laterally spaced from each other and each connecting the leading edge to the trailing edge, this blade comprising: at least one upstream duct collecting cooling air at the foot to cool the leading edge by evacuating this air through holes passing through the wall of the blade at its level; leading edge ; at least one downstream duct distinct from the upstream duct collecting cooling air at the foot to cool the trailing edge by evacuating this air through holes passing through the intrados wall upstream of the trailing edge; An internal lateral cavity running along the intrados wall to form a heat shield insulating the downstream duct of the intrados wall. With this arrangement, the cooling of the trailing edge is significantly improved by the formation of a cooling film on the external face of the intrados wall upstream of this trailing edge. Due to the supply via the downstream conduit which is thermally insulated, this air film also has a low temperature. The invention also relates to a blade thus defined, further comprising cooling slots passing through its intrados wall along its trailing edge and a downstream ramp for supplying cooling air to these cooling slots, as well as an upper cavity located at the top of the blade 25 for supplying air to the slot of the trailing edge which is closest to this top, this upper cavity being distinct from the downstream ramp and being supplied with air by the downstream duct . The invention also relates to a blade thus defined, comprising another internal lateral cavity along the extrados wall to form a heat shield 30 which thermally isolates the downstream duct of the extrados wall.
    [0005] The invention also relates to a blade thus defined, comprising an upstream ramp for supplying cooling holes to the leading edge, and an upstream feed pipe calibrated from this upstream ramp, and in which each internal lateral cavity forms a heat shield sufficient to insulate together this upstream duct and the downstream duct. The invention also relates to a blade thus defined, in which each internal lateral cavity is provided with turbulence promoters and / or deflectors to increase heat exchange, and wherein the upstream duct and the downstream duct have smooth walls to limit the pressure drops.
    [0006] The invention also relates to molding means for the manufacture of a blade thus defined, comprising indentations and a set of cores intended for the formation of internal ducts and ramps, and possibly internal cavities forming a screen. The invention also relates to a turbomachine turbine 15 comprising a blade as defined above. The invention also relates to a turbomachine comprising a turbine as defined above. BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a schematic view of a turbofan engine in longitudinal section; Figure 2 is a perspective view of a turbojet turbine blade shown in Figure 1; Fig. 3 is a perspective view showing the hollow inner portions of a turbine blade according to a first embodiment of the invention; FIG. 4 is a perspective view showing the hollow internal parts of a turbine blade according to a second embodiment of the invention; FIG. 5 is a perspective view showing the hollow internal parts of a turbine blade according to a third embodiment of the invention; FIG. 6 is a perspective view showing the hollow internal parts of a turbine blade according to a fourth embodiment of the invention. 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. 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 in a low pressure turbine not shown to drive in rotation the compression stages and the fan, before being expelled to the rear of the engine to generate a thrust. The engine 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 intake sleeve, to the rear part where it delimits the conduit through which the primary and secondary flow are evacuated, the front and rear to consider in relation to the direction of advancement of the aircraft equipped with this turbojet engine. This housing 9 supports the rotating components located at 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 blades. Such a blade, which is indicated by 11 in FIG. 2, comprises a foot P through which it is fixed to a not shown rotary body, called a turbine disc, and a blade 12 carried by this foot P and constituting the aerodynamic part. from this dawn.
    [0007] 3021699 6 As shown in Figure 2, the blade 11 comprises between the foot P and the blade 12 an intermediate region 13 called platform. The assembly formed by the foot P and the blade 12 is a single hollow piece integrally cast and having internal ducts through which circulates cooling air. These internal ducts not visible in Figure 2 comprise inlet mouths 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 by 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 situated at the upstream level AM of the blade, that is to say the front region of this blade, with respect 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 and spaced therefrom along the axis AX to be located at the downstream region AV or rear of the blade. '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.
    [0008] 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 apart 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 25 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. 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 has a series of cooling slots 23. These slots 23 are slots of short lengths spaced apart from each other by being located in the extension of one another. other, to constitute an assembly that runs along the end of the trailing edge 18. Each slot 23 passes through the wall of the blade to collect cooling air inside the blade and blow it on the wall of the blade. intrados at level 5 of the trailing edge. Complementarily, the trailing edge is provided with external ribs oriented parallel to the axis AX for channeling the cooling air. In operation, the fluid in which this blade 11 is located moves relative thereto from the leading edge 17 towards the trailing edge 18 along the intrados 21 and the extrados. The lower surface wall, which is subjected to significant heating in operation, has a series of holes 24 substantially parallel to the leading edge 17 being 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 15 of the blade, which is the radial direction relative to the axis AX. 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 this region of the top has a shape defining a hollow portion called bath. More concretely, this vertex S has a closure 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 the 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.
    [0009] The series of holes 27 extends parallel to the closure wall, and the blade comprises, in addition, 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.
    [0010] 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 operation is complete, typically with a chemical etching process capable of dissolving these elements without altering the molded material. The following figures show internal regions of the blade according to the invention which are represented by the shapes of the cores making it possible to manufacture this blade. In other words, the shapes that are in relief in the following figures 15 are representations of the hollow shapes of the blade according to the invention. The idea underlying the invention is to improve the cooling of the dawn on the intrados side in the region of the trailing edge and its top, this region being the first to deteriorate during the life of a dawn.
    [0011] This is ensured by a downstream duct which extends inside the blade being thermally protected from the intrados wall, and through holes in the intrados wall towards this duct, upstream of the edge. leakage, to form a cooling air film of the trailing edge on the side of the outer face of the intrados. This downstream duct extends in the direction of wingspan from the foot 25 to the top of the dawn to be fed with air directly to the foot and so that the air travels in the dawn without being warmed during its journey before being forced back by the cooling holes. The blade according to the invention which is marked 31 in FIG. 3 comprises an upstream ramp 32 extending from the base of its blade to its top S. This upstream ramp 32 cools the leading edge by through holes formed in the wall portion corresponding to the leading edge. This upstream ramp 32 is supplied calibrated by an upstream duct 33 which runs along this ramp 32, located downstream thereof, and which collects cooling air at the level of the foot. The calibrated supply is ensured by calibrated passages 34 regularly spaced along the direction of span EV of the blade and which each connect the upstream duct 33 to the upstream ramp 32. Each passage 34 is calibrated to obtain approximately a flow desired air in the cooling holes in the region of the ramp 10 fed by the passage in question. The desired airflow for a given hole or region is conditioned by the thermal stresses of the leading edge in the region cooled by this hole. Another duct, called downstream duct and which is marked by 36, runs along the upstream duct also extending substantially rectilinearly from the foot 15 of the blade to its apex S. The lower surface of the duct the blade comprises a series of through holes 37 distributed rectilinearly in the span direction being located at the downstream region of the downstream duct 36. Each through hole 37 thus communicates the downstream duct 36 with the outer face the intrados wall upstream of the trailing edge to form a cooling film on the outer face of this wall.
    [0012] The intrados wall comprises in the region of the trailing edge a series of cooling slots 38, regularly spaced and extending in line with one another in the span direction, to deliver to the trailing edge of the cooling air. These slots are fed by a downstream ramp 39 of the blade, which extends from the root of the blade, to the region of the summit S being situated between the downstream duct 36 and the trailing edge of the blade. 'dawn. This downstream ramp 39 collects air at its lower end located in the foot of the blade, and it delivers this air at the cooling slots 38 that it feeds. Complementarily, the blade according to the invention comprises an internal lateral cavity 41 of small thickness which runs along the intrados wall on the inner side of the blade to form a thermal shield protecting the upstream conduit 33 and the downstream conduit 36. of the heat to which the intrados wall is subjected. As can be seen in FIG. 3, this internal cavity 41 has a small thickness and a contour of rectangular shape. It extends in height, that is, along the span direction, from the root of the blade to its apex, and laterally has a sufficient extent to form a screen covering upstream and downstream ducts. This lateral cavity in which a flow of air can be established makes it possible to thermally insulate the upstream duct and the downstream duct of the intrados wall 10 in order to reduce the heating of the air which they convey. Under these conditions, the cooling of the trailing edge of the blade on the underside side is significantly improved by the presence of an external cooling air film which itself has a significant cooling efficiency because it is supplied with air by a downstream pipe thermally protected and therefore having a low temperature. According to a second embodiment of the invention corresponding to the blade 51 of FIG. 4, the downstream duct which is thermally protected to cool the intrados upstream of the trailing edge also provides fresh air to the slot of FIG. 20 cooling of the trailing edge which is closest to the top, so as to improve the cooling of this region. In this second embodiment, the blade 51 also comprises an upstream ramp 52 fed in a calibrated manner by an upstream duct 53 through calibrated passages 54. It also comprises a downstream duct 56 and its intrados wall is provided with a series of through holes 57 distributed in the direction of span EV at the downstream region of the conduit 56 to put this conduit in communication with the outer face of the intrados wall upstream of the trailing edge. The air circulating in the downstream duct 56 is discharged through these holes 57, to form there too a cooling film upstream of the trailing edge.
    [0013] The intrados wall of this blade 51 also has cooling slots 58 of the trailing edge fed by a downstream ramp 59, which also extends from the foot P to a region located below the top S. It also has an internal lateral cavity 61 of small thickness which runs along the intrados wall to form a heat shield protecting the upstream duct 53 and the downstream duct 56. All these elements 52 to 61 are identical to elements 32 to 41 of FIG. vane 31 with the difference that the downstream ramp 59 has a shorter length than the downstream ramp 39, and the downstream duct 56 feeds an upper cavity 63 which is located at the top of the blade S.
    [0014] The upper cavity 63 is located in the extension of the end of the downstream ramp 59 by being supplied with air by the downstream duct so as to supply the slot 64 of the trailing edge which is closer to the top than the slots 58, with cooler air to further improve the cooling of the dawn at the top of its trailing edge.
    [0015] This upper cavity 63 extends along a closing wall of the blade which joins the intrados and the extrados while being oriented in a direction perpendicular to the span direction EV. This upper cavity 63 is located downstream of the downstream duct 56 being delimited by the closure wall, the intrados wall and the extrados wall to extend to the trailing edge. It is connected to the upper end of the downstream duct 56 by an internal connecting channel 66. Thanks to this upper cavity 63, the top of the trailing edge of the blade benefits from efficient cooling resulting from the supply in this area of fresh air at a rate adjusted as needed.
    [0016] According to a third embodiment of the invention which is shown in FIG. 5, the upstream duct and the downstream duct which are thermally insulated by the internal cavity along the intrados wall, are also thermally insulated by another internal cavity. dawn along the extrados wall. In this third embodiment which appears in FIG. 5, the blade 71 also includes an upstream ramp 72 calibrated by an upstream duct 73 by means of calibrated passages 74 each connecting the upstream duct to the upstream ramp. . It also comprises a downstream duct 76 and through holes 77 its intrados wall being distributed in the span direction EV at the downstream region of the duct 76 to put this duct in communication with the outer face of the wall intrados upstream of the trailing edge. The air circulating in the downstream duct 76 is thus also discharged through these holes 77, to form a cooling film upstream of the trailing edge which significantly improves the cooling of this trailing edge. The intrados wall also has cooling slots 78 on the trailing edge supplied with air by a downstream ramp 79, this downstream ramp also extending from the foot P to the region of the crown S of the blade. The blade also has a thin internal lateral cavity 81 which runs along the intrados wall to form a thermal shield protecting the upstream duct 73 and the downstream duct 76 from the heat of the intrados wall.
    [0017] All these elements 72 to 81 are identical to the elements 32 to 41 of the blade 31 and to the elements 52 to 61 of the blade 51, with the difference that the upstream pipe 73 and the downstream pipe 76 have a thinner thickness. , and in addition to the first lateral cavity 81 along the intrados, this blade 71 further includes a second internal lateral cavity 82 which runs along the extrados. The presence of two internal lateral cavities 81 and 82, which respectively follow the intrados and the extrados, provides an increased thermal insulation of the upstream duct 73 and the downstream duct 76. The second internal lateral cavity 82 also has a small thickness, and it also extends from the foot P to the crown region S, having a generally rectangular outline, having a width sufficient to mask or cover the upstream and downstream ducts. Thanks to these two internal lateral cavities, the air that travels in the upstream duct and in the downstream duct is very slightly warmed during its journey, which contributes to further increase the efficiency of the cooling provided upstream of the trailing edge of the side. intrados, and cooling brought to the leading edge.
    [0018] According to a fourth embodiment of the invention, which is shown in FIG. 6, the downstream duct which is thermally protected to cool the intrados upstream of the trailing edge also provides fresh air to the slit. cooling the trailing edge which is closest to the top to improve the cooling of this region. In this fourth embodiment which appears in FIG. 6, the vane 91 also comprises an upstream ramp 92 fed in a calibrated manner by an upstream duct 93 via calibrated passages 94. It also comprises a downstream duct 96 and its wall. The intrados is provided with through-holes 97 distributed in the span direction EV at the downstream region of the duct 96 to put this duct in communication with the external face of the intrados wall upstream of the trailing edge. The air circulating in the downstream duct 96 is discharged through these holes 97, again to form a cooling film upstream of the trailing edge so as to significantly improve the cooling of this leak edge. The intrados wall also comprises cooling slots 98 of the trailing edge fed by a downstream ramp 99, which also extends from the foot P to the region of the summit S. This blade also comprises an internal lateral cavity 101 of thin thickness which runs along the intrados wall and another internal lateral cavity 102 of small thickness which runs along the extrados wall, to form two heat shields protecting the upstream duct 93 and the downstream duct 96. All these elements 92 to 102 are identical to the elements 72 to 82 of the blade 71, with the difference that the downstream ramp 99 has a shorter length than the downstream ramp 79, and the downstream duct 96 feeds an upper cavity 103 which is located at 25. level of the S summit of dawn. The upper cavity 103 is located in the extension of the end of the downstream ramp 99 by being supplied with air by the downstream duct 96 so as to feed the slot 104 of the trailing edge which is closest to the top with the cooler air so as to increase the cooling of the blade at the top of its trailing edge.
    [0019] This upper cavity 103 extends along a closing wall of the blade which joins the intrados and extrados being oriented in a direction perpendicular to the span direction EV. This upper cavity 103 is located downstream of the downstream duct 96 being delimited by the closure wall, the intrados wall and the extrados wall to extend to the trailing edge. It is connected to the upper end of the downstream duct 96 by an internal connecting channel 106. Thanks to this upper cavity 103, the top of the trailing edge of the blade benefits from efficient cooling resulting from the supply in this connection. area of fresh air at a rate adjusted as needed.
    [0020] In general, the upper cavity of the second and fourth embodiments of the invention makes it possible to feed the rear or downstream region of the top of the blade with fresh cooling air to improve its cooling. This cavity thus supplies the slot of the trailing edge which is closest to the top, and possibly the adjacent slots.
    [0021] Complementarily, holes through the intrados wall at the height of the upper cavity to open into this upper cavity may be provided to improve the cooling of the outer face of the intrados wall in the region of the top of the cavity. dawn. The upper cavity then provides fresh air which passes through the intrados wall to cool its outer face in addition to supplying air to the slot closest to the top, and in addition to cooling by thermal conduction of the walls. of the dawn which delimit this upper cavity. Moreover, holes passing through the walls of the blade and opening into the internal lateral cavities forming heat shield can be provided to establish an optimal air flow in these cavities. Each of these holes is preferably 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 conveyed in a cavity forming a heat shield, is sucked out of the blade, after having walked in this cavity. In the various embodiments, the cooling of the blade is further optimized by minimizing the pressure losses in each inner duct 3021699 15 there to reduce heat exchange, and providing on the contrary turbulence promoters in each side cavity to y increase heat exchange. The lateral cavities thus have an increased efficiency as a thermal screen because they absorb the heat coming from the external walls that they run along, and the air circulating in the internal ducts is subjected to little pressure drop so to circulate quickly to warm as little as possible. The internal ducts such as the upstream duct, the central duct and the downstream duct and have smooth internal walls to promote rapid circulation of cooling air by minimizing the heat exchange between the air and the walls 10 of the duct in which it fireplace. Each lateral cavity is advantageously provided with deflectors which promote air circulation in all regions of the cavity. In addition, the internal faces of the cavity are provided with disrupters and / or bridges to create turbulence in the air circulation to promote a high level of heat exchange between the air and the walls that it runs along. . 15
    权利要求:
    Claims (8)
    [0001]
    REVENDICATIONS1. A blade (31; 51; 71; 91) of a turbomachine turbine such as a turboprop or a turbojet, said blade (31; 51; 71; 91) comprising a foot (P), a blade carried by this foot (P) , said blade comprising a leading edge and a trailing edge located downstream of the leading edge, this blade comprising a lower surface wall and an extrados wall laterally spaced from each other and each connecting the leading edge at the trailing edge, said blade comprising: at least one upstream duct (33; 53; 73; 93) collecting cooling air at the foot (P) for cooling the leading edge; evacuating this air through holes passing through the wall of the blade at its leading edge; at least one downstream duct (36; 56; 76; 96) distinct from the upstream duct (33; 53; 73; 93) collecting cooling air at the foot (P) for cooling the trailing edge while evacuating this air through holes (37; 57; 77; 97) passing through the intrados wall upstream of the trailing edge; an inner lateral cavity (41; 61; 81; 101) running along the intrados wall to form a heat shield insulating the downstream duct (36; 56; 76; 96) of the intrados wall.
    [0002]
    2. A blade according to claim 1, further comprising cooling slots (58; 98) passing through its bottom wall along its trailing edge and a downstream ramp (59; these cooling slots (58; 98) and an upper cavity (63; 103) located at the apex (S) of the blade for supplying air to the slot (64; 104) of the trailing edge which is closest to this apex (S), this upper cavity (63; 103) being distinct from the downstream ramp (59; 99) and being supplied with air by the downstream duct (56; 96).
    [0003]
    3. A blade according to claim 1 or 2, comprising another internal lateral cavity (82; 102) running along the extrados wall to form a heat shield which thermally isolates the downstream duct (76; 96) of the extrados wall. 3021699 17
    [0004]
    4. blade according to one of claims 1 to 3, comprising an upstream ramp (32; 52; 72; 92) for supplying cooling holes to the leading edge, and an upstream duct (33; 53; 73; 93) of said upstream ramp (32; 52; 72; 92), and wherein each inner side cavity (41; 61; 81,82; 101,102) forms a heat shield of sufficient extent to jointly isolating this upstream conduit (33; 53; 73; 93) and the downstream conduit (36; 56; 76; 96).
    [0005]
    A blade according to claim 4, wherein each inner side cavity (41; 61; 81,82; 101,102) is provided with turbulence promoters and / or baffles for increasing heat exchange therein, and wherein Upstream duct (33; 53; 73; 93) and the downstream duct (36; 56; 76; 96) have smooth walls to limit pressure drops.
    [0006]
    6. Molding means for the manufacture of a blade according to one of claims 1 to 5, comprising indentations and a set of cores for the formation of internal ducts and ramps, and possibly internal cavities forming a screen.
    [0007]
    7. Turbomachine turbine comprising a blade according to any one of claims 1 to 5.
    [0008]
    8. Turbomachine comprising a turbine according to the preceding claim.
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    同族专利:
    公开号 | 公开日
    WO2015181488A1|2015-12-03|
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    US10662789B2|2020-05-26|
    CN106470782B|2020-05-08|
    CN106470782A|2017-03-01|
    US20170191368A1|2017-07-06|
    BR112016027014A8|2021-06-22|
    BR112016027014A2|2017-08-15|
    RU2016151765A3|2018-11-27|
    EP3149282A1|2017-04-05|
    FR3021699B1|2019-08-16|
    RU2016151765A|2018-06-28|
    RU2688090C2|2019-05-17|
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    法律状态:
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    2015-12-04| PLSC| Search report ready|Effective date: 20151204 |
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    优先权:
    申请号 | 申请日 | 专利标题
    FR1454869A|FR3021699B1|2014-05-28|2014-05-28|OPTIMIZED COOLING TURBINE BLADE AT ITS LEFT EDGE|
    FR1454869|2014-05-28|FR1454869A| FR3021699B1|2014-05-28|2014-05-28|OPTIMIZED COOLING TURBINE BLADE AT ITS LEFT EDGE|
    RU2016151765A| RU2688090C2|2014-05-28|2015-05-26|Turbine blade with optimized cooling of its trailing edge, comprising channels located upstream and downstream and inner side cavities|
    CN201580027801.XA| CN106470782B|2014-05-28|2015-05-26|Blade and related molding device, turbine and turbomachine|
    BR112016027014A| BR112016027014A8|2014-05-28|2015-05-26|turboengine turbine blade, molding means for manufacturing a blade, turbomachinery turbine and turbomachinery|
    EP15732800.6A| EP3149282A1|2014-05-28|2015-05-26|Turbine blade with optimised cooling at the trailing edge of same comprising upstream and downstream ducts and inner side cavities|
    CA2949920A| CA2949920A1|2014-05-28|2015-05-26|Turbine blade with optimised cooling at the trailing edge of same comprising upstream and downstream ducts and inner side cavities|
    PCT/FR2015/051382| WO2015181488A1|2014-05-28|2015-05-26|Turbine blade with optimised cooling at the trailing edge of same comprising upstream and downstream ducts and inner side cavities|
    US15/314,037| US10662789B2|2014-05-28|2015-05-26|Turbine blade with optimised cooling at the trailing edge of same comprising upstream and downstream ducts and inner side cavities|
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