• 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 such as a turbojet comprising: a foot carrying a blade and extending in a span direction ending in a vertex, the blade comprising a leading edge (17) and a trailing edge (18), with an intrados wall (20) and an extrados wall (21) spaced from one another and connecting the leading edge (17) to the trailing edge ( 18), this blade also comprising: cooling ducts (41, 52, 53, 47, 54, 56) in which circulates air collected at the bottom of the blade (12); a first and a second internal lateral cavity (37, 38) running along the intrados wall (20) to form a heat shield spaced apart from each other along the intrados wall (20); at least one portion of duct (53) extending from the intrados wall (20) to the extrados wall (21) between the first and second lateral recesses (37, 38).
    公开号:FR3057906A1
    申请号:FR1601523
    申请日:2016-10-20
    公开日:2018-04-27
    发明作者:Charlotte Marie Dujol；Sebastien Serge Francis Congratel；Patrice Eneau；Leandre Ostino；Michel Slusarz
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    DESCRIPTION
    TECHNICAL AREA
    The invention relates to a blade of an aircraft engine of the turbomachine type, such as for example a turbofan engine or a turboprop engine.
    PRIOR STATE OF THE ART
    As shown in FIG. 1, in such an engine marked with 1, outside air is admitted into an inlet sleeve 2 to pass through a blower 3 comprising a series of rotary blades before splitting into a central primary flow and a secondary flow surrounding the primary flow.
    The primary flow then passes through compression stages 4, 6 before arriving in a combustion chamber 7, after which it expands by passing through a set of turbines 8 before being evacuated towards the rear by generating thrust. The secondary flow is propelled directly to the rear by the blower to generate additional thrust.
    This motor 1 is delimited by an external casing 9 extending from its front part to form the air intake sleeve, to a rear part forming a flow evacuation duct, the front and the rear being considered in relation to the direction of advance of the aircraft equipped with this engine.
    The expansion in the turbines 8, which makes it possible to drive the compressor and the blower, takes place at high temperature because it occurs immediately after combustion, so that these turbines are designed to operate under severe temperature conditions , and pressure.
    Each turbine comprises a succession of stages each comprising a series of radially oriented vanes and regularly spaced around a central shaft of the engine. This central shaft carries the rotary elements of the turbine as well as the rotary elements of the compressor and the blower.
    The turbine blades which are subjected to the most severe conditions are those of the first expansion stages, namely the stages closest to the combustion zone, commonly called high pressure stages.
    In practice, the increased performance requirements imply improving the behavior of the high pressure turbine blades, in particular with regard to their temperature resistance. 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 fresh air which is taken from the turbojet engine upstream of the combustion. This air is admitted at the foot of the blade, to travel along an internal circuit of the blade in order to cool it, and it is evacuated out of the blade by holes passing through the wall of this blade and distributed over this wall. These holes are used to evacuate the cooling air, and to create on the outer surface of the blade a film of air colder than the air from the combustion, which also contributes to limiting the temperature of the blade. .
    The object of the invention is to propose a blade structure making it possible to improve the cooling efficiency of this blade.
    STATEMENT OF THE INVENTION
    To this end, the subject of the invention is a turbine blade of a turbomachine such as a turboprop or a turbojet engine, the blade comprising: a foot, a blade carried by the foot and extending in a direction of wingspan ending in a vertex, the blade comprising a leading edge and a trailing edge located downstream of the leading edge, the blade comprising a lower surface wall and an upper surface spaced apart from one other and connecting the leading edge to the trailing edge, this blade also comprising:
    - cooling conduits each extending laterally from the upper surface wall to an upstream inner wall or to a downstream inner wall;
    - an upstream side cavity and a downstream side cavity running along the lower surface to form a heat shield, being spaced from each other along the lower surface;
    - the upstream lateral cavity extending laterally from the lower surface wall to the upstream inner wall;
    - The downstream lateral cavity extending laterally from the lower surface wall to the downstream inner wall;
    - A cooling duct extending transversely from the lower surface wall to the upper surface wall between the upstream side cavity and the downstream side cavity.
    With this arrangement, the internal walls are distinct and separated from each other along the skeleton of the dawn. This separation into two parts promotes better resistance to thermal expansion that the dawn undergoes in service.
    The invention also relates to a blade thus defined, in which a duct extending from the upper surface wall to the upstream inner wall is connected to the duct extending from the upper wall to the lower wall which is itself - even connected to a conduit extending from the upper surface wall to the downstream internal wall, in an arrangement of the paperclip circuit type.
    The invention also relates to a blade thus defined, comprising a downstream ramp supplied by a conduit of the paper clip circuit, this downstream ramp extending transversely from the lower surface wall to the upper surface wall, and in which the lower surface wall comprises holes opening into the downstream ramp to form a film of external air for cooling the lower surface.
    The invention also relates to a blade thus defined, in which the downstream ramp is supplied from the duct by calibrated passages.
    The invention also relates to a blade thus defined, comprising a bath cavity extending from a central region from the top to the trailing edge, and at least one central duct directly supplying this bath cavity with air collected at the foot level.
    The invention also relates to a blade thus defined, in which the trailing edge comprises on the lower surface a series of through slots supplied with cooling air, and in which these slots comprise:
    - one or more last slots close to the top which are supplied by the bath cavity;
    - slots which are supplied by a downstream duct from the blade.
    The invention also relates to a blade thus defined, comprising an upstream circuit for cooling the leading edge of the blade.
    The invention also relates to foundry means for manufacturing a blade thus defined, comprising indentations and a set of cores intended for the formation of internal conduits and ramps, and internal cavities forming a screen.
    The invention also relates to a turbomachine turbine comprising a blade thus defined.
    The invention also relates to a turbomachine comprising a turbine thus defined.
    BRIEF DESCRIPTION OF THE DRAWINGS
    Figure 1 is a schematic view of a turbofan engine in longitudinal section;
    Figure 2 is a perspective view of a high pressure turbine blade;
    Figure 3 is a view of the blade according to the invention according to a section plane normal to its span direction;
    FIG. 4 is a side view showing an upstream circuit for cooling the leading edge of the blade according to the invention;
    FIG. 5 is a side view showing a central circuit and a central circuit for cooling the blade according to the invention;
    Figure 6 is a side view showing a downstream cooling circuit of the trailing edge of the blade according to the invention;
    FIG. 7 is a side view showing on the lower surface the various cooling circuits of the blade according to the invention other than its lateral circuit;
    FIG. 8 is a side view showing on the lower surface the various cooling circuits of the blade according to the invention;
    Figure 9 is a side view showing the upper surface of the different cooling circuits of the blade according to the invention.
    DETAILED PRESENTATION OF PARTICULAR EMBODIMENTS
    Dawn structure
    The blade according to the invention, identified by 11 in FIG. 2, comprises a foot P by which it is fixed to a rotary body (not shown) called a turbine disk, and a blade 12 carried by this foot P, with a platform 13 which connects the foot P to the blade 12. This blade 11 comprises internal circuits in which circulates cooling air admitted on the lower face 14 of the foot P.
    The blade 12 has a twisted shape around an axis known as of span EV perpendicular to an axis AX of rotation of the shaft carrying the blade, and it has a substantially rectangular outline starting from a base 16 by which it is connected to foot P.
    This blade 12 includes a leading edge 17 substantially parallel to the span direction EV and located upstream AM or before dawn, relative to the direction of advance of the engine which it equips. It also has a trailing edge 18 oriented roughly parallel to the leading edge 17 and spaced from the latter along the axis AX to be located downstream AV or rear of dawn. It also includes a vertex S roughly parallel to the base 16 and spaced from the latter in the direction of the span EV.
    The two main walls of this blade are its lower surface wall 20, visible in FIG. 2, and its upper surface wall, which are spaced apart from each other while being joined at the leading edge 17 , at the trailing edge 18, and in the region of the apex S.
    The leading edge 17 which is curved has cooling holes 22 passing through its wall, and the trailing edge 18 which is tapered comprises a series of cooling slots 23. These slots 23 are short in length and extending parallel to the direction of span EV, being spaced apart and in the extension of each other, and located a short distance from the trailing edge proper. Each slot 23 passes through the lower surface to blow air on the lower surface towards the trailing edge which is provided with external ribs channeling this air parallel to the axis AX.
    The underside wall has a series of holes 24 distributed substantially parallel to the leading edge 17 downstream thereof, and another series of holes 26 distributed substantially parallel to the trailing edge 18, and located upstream of the slots 23 These holes make it possible to form an air film on the external face of the lower surface to cool it.
    At its apex S, this blade has a closure wall perpendicular to the direction of span EV, which connects the walls of the lower and upper surfaces. This closure wall, which is not visible in FIG. 2, is set back towards the axis AX with respect to the free edges of the lower and upper surfaces, to form jointly with these edges a hollow portion, called in bathtub, which is open in the opposite direction to the axis AX.
    Another series of holes 27 passing through the lower surface wall along the top S, distributed parallel to the closure wall, makes it possible to form an air film on the external face of the lower surface in the region of the top S for the cool.
    This blade is a single piece made by casting a metallic material, using a set of cores to delimit the internal conduits, these cores being removed after casting and cooling, for example with a chemical attack process.
    FIGS. 4 to 9 show internal regions of the blade which are represented therein by the shapes of the cores making it possible to manufacture this blade. Thus, the shapes of these figures are in relief, but they constitute representations of the hollow shapes of dawn.
    The blade 11 according to the invention has five internal cooling circuits. It includes an upstream circuit 31; a central circuit 32; a median circuit 33 extending on either side of the central circuit; and a downstream circuit 34. In addition, a lateral circuit 36 mainly comprising an upstream lateral cavity 37 and a downstream lateral cavity 38 of small thickness which run along the lower surface being spaced apart from each other along the latter for constitute a heat shield.
    Upstream circuit
    As can be seen in FIG. 4, the upstream circuit 31 includes an upstream ramp 39 as well as an upstream conduit 41 supplying this ramp 39, and extending parallel to the span direction EV. The upstream conduit 41 extends from the base of the blade to collect air therein at its mouth 42, as far as a region of the apex S situated under the bath, that is to say under the closing wall. The upstream ramp 39 extends from the base 16 to the region under the bath, and it is supplied in a calibrated manner by calibrated passages 43 regularly spaced along the span direction EV, which each connect the upstream conduit 41 at the upstream ramp 39.
    Each passage 43 has a calibrated diameter, that is to say chosen to obtain in the area of the ramp 39 that it supplies a desired air flow. This calibrated supply of the upstream ramp 39 provides cooling of the impact type leading edge.
    Additionally, the upstream duct 41 includes turbulence promoters 44, that is to say elements forming a relief on its internal face, which generate turbulence in the air flow to increase the heat exchange with the walls of the dawn which delimit this conduit 41.
    The upstream duct 41 is thermally protected on the lower surface by the upstream lateral cavity 37 of the lateral circuit 36, so that it extends laterally from the upper surface wall 21 to an inner upstream wall 40 which separates it from the upstream cavity 37.
    Central circuit
    The central circuit 32 which appears in FIG. 5 comprises an upper cavity 46 called the bathtub cavity, and a central duct 47 which directly feeds this bathtub cavity 46, to cool the top. The central duct extends from the foot P of the dawn where it has an air intake mouth 48, and it opens into the bottom of the bath cavity 46.
    The bath cavity 46 extends longitudinally from a central region of the apex S, to the trailing edge 18, to supply fresh air to one or more of the slots 23 which are closest to the apex S.
    This bathtub cavity 46 is delimited laterally on the one hand by the upper surface over its entire length, and on the other hand by the lower surface in the rear part of the blade and by a downstream internal wall 49 which separates it from the downstream cavity 38 of the lateral circuit 36 in the central portion of the apex S corresponding to the front of this bath cavity 46.
    This bathtub cavity 46 is delimited along the axis of span EV by a bottom parallel to the closing wall and spaced from the latter, and by the closing wall.
    The central duct 47 and the front portion of the bath cavity 46 are thermally protected by the downstream lateral cavity 38 of the lateral circuit 36. As visible in FIG. 3, the central duct 47 extends laterally from the upper surface wall up to the downstream internal wall 49 which separates it from the downstream lateral cavity 38. Furthermore, the bath cavity 46 and the central duct 47 which feeds it, can be provided with turbulence promoters 50.
    Holes 27 passing through the lower surface towards this under-bath cavity make it possible to cool the external face of lower surface at the level of the apex S.
    Median circuit
    The median circuit 33 which is visible in FIG. 5 comprises three conduits 52, 53 and 54 communicating with each other in a paper clip arrangement, and a downstream ramp 56 supplied in a calibrated fashion by the third conduit 54. The conduits 52, 53 and 54 as well as the ramp 56 extend parallel to the span direction EV, the first and second duct 52 and 53 being located upstream of the central duct 47 of the circuit 32, while the third duct 54 and the ramp 56 are downstream of the conduit 47. In other words, the conduits of the median circuit 33 are located on either side of the central conduit 47.
    The first conduit 52, which runs along the upstream conduit 41 of the upstream circuit 31, collects air at the level of the foot P by its mouth 51 and it extends to a region under bathtub where it is connected to the second conduit 53 .
    This first conduit 52 extends laterally from the upper surface wall 21 to the upstream internal wall 40 which separates it from the upstream lateral cavity 37. As visible in FIG. 3, the first conduit 52, as well as the upstream conduit 41, are thermally protected on the lower surface by the upstream lateral cavity 37 of the lateral circuit 36.
    The second conduit 53 of the median circuit 33 runs along the first conduit 52 while being wider than the conduits 52 and 54 to extend laterally from the lower surface wall 20 to the upper surface wall 21. This second conduit 53 is connected in the region of the base 16 of the blade to the third conduit 54, this connection region extending into the foot P in a form of mouth 57 which is in fact closed. This closure is achieved after the blade body has been manufactured by casting by brazing a plate closing the opening 57, the shape 57 serving in fact to hold in position the core element delimiting the median circuit 33 during the operation of foundry manufacturing.
    As can be seen in FIG. 3, this second conduit 53 is mainly in contact with the internal walls of the blade. It has in section a large width laterally, but a small thickness in the direction of the length that is to say along the skeleton SQ. from dawn. This second conduit 53 thus has areas of contact with the lower surface and the upper surface which are not large, which limits its heating.
    The third conduit 54 is spaced from the second conduit 53 along the axis AX, and it extends from the base 16 to the region located under the bath cavity 46, parallel to the downstream ramp 56 which it runs along while being upstream of it. This third conduit 54 extends laterally from the upper surface wall 21 to the downstream internal wall 49 which separates it from the downstream lateral cavity 38.
    The downstream ramp 56 runs along the third conduit 54 while being supplied in a calibrated manner by the latter by means of a series of calibrated passages 58, which are spaced apart from one another along an axis parallel to the axis EV, and which extend ίο parallel to the axis AX to uniformly supply air to the downstream ramp 56. This downstream ramp 56 is not protected by the downstream side cavity 38: it extends laterally from the upper surface wall 21 up to the lower surface 20, and it feeds by means of the holes 26 passing through the lower surface 20, an external air film which covers and thermally protects the trailing edge 18 on the lower side.
    As visible in FIG. 3, the third conduit 54, as well as the central conduit 47 are thermally isolated from the lower surface 20 by the downstream lateral cavity 38. The conduits 52, 53, 54 as well as the ramp 56 are advantageously provided with promoters turbulence 59.
    Downstream circuit
    As visible in FIG. 6, the downstream circuit 34 comprises a downstream conduit 61 running along the downstream ramp 56. It extends parallel to the direction EV from a mouth 62 located at the level of the foot P, up to the cavity under bath 46 , and a ramp 63 supplying the trailing edge slots which are not supplied by the bath cavity 46. This downstream conduit 61 advantageously includes turbulence promoters 64.
    Lateral circuit
    The lateral circuit 36 which appears more clearly in FIG. 8 comprises an upstream lateral cavity 37 and a downstream lateral cavity 38 running along the lower surface, being spaced apart from each other along the latter. These cavities have a small thickness with respect to the thickness of the blade and the thicknesses of its various conduits and ramps.
    These cavities 37 and 38 are supplied by the same mouth 66 located in the foot P while being distinct which allows a homogeneous distribution of the air by limiting the zones of stagnation of the air. These lateral cavities are advantageously provided with turbulence promoters 67. In addition, holes such as the holes 24 passing through the lower surface 20 to open into these cavities 37, 38 ensure evacuation of the air while forming a film on the external face of the lower surface 20.
    The upstream lateral cavity 37 extends from the foot P to the region of the apex S having a generally rectangular outline. It ends under the bathtub, which appears in Figures 8 and 9 where it is marked with 68, so as not to cover it. It extends over a length sufficient to mask or cover the upstream conduit 41 as well as the first conduit 52 of the median circuit 33 over the majority of their height. It extends laterally from the lower surface wall to the upstream internal wall 40.
    The downstream lateral cavity 38 also extends from the foot P to the region of the summit S under the bath 68, also having a generally rectangular outline. It also ends under the bathtub so as not to cover it, and it extends over a length sufficient to cover the central duct 47 as well as the third duct 54 of the median circuit. It extends laterally from the lower surface wall 20 to the downstream internal wall 49.
    Benefits
    As can be seen in FIG. 3, the internal walls 40 and 49 are distinct and separated from each other along the skeleton SQ. Of the blade by the second conduit 53 of the central circuit 32. This separation into two parts of ia internal wall of the blade promotes better resistance to thermal expansion that the blade undergoes, the internal temperature of which differs from one part to another. In other words, the arrangement of the blade according to the invention makes it possible to limit the length of the central skeleton by dividing it into two parts to soften the internal structure.
    Generally, the upstream circuit 31 cools the leading edge 17 and an upstream portion of the upper surface 21; the central circuit 32 cools the bathtub and a portion of the top of the trailing edge 18; the middle circuit 33 cools the upper surface 21 and a downstream portion of the lower surface 20; and the downstream circuit 34 cools the trailing edge 18. The invention thus makes it possible to dissociate the air supply from the slots of the trailing edge and the intrados bores without penalizing the cooling of one zone relative to the other.
    The upstream and downstream side cavities 37, 38 thermally insulate the conduits of the circuit 33 to maintain the central regions of the blade at a lower temperature, which contributes to improving its mechanical strength. In particular, the fact that the central channel 47 is protected by the downstream lateral cavity 38 allows this channel to supply the cavity under bathtub with cooler air.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Turbine blade of a turbomachine such as a turboprop or a turbojet engine, the blade comprising: a foot (P), a blade (12) carried by the foot (P) and extending in a direction of wingspan (EV) ending with an apex (S), the blade (12) comprising a leading edge (17) and a trailing edge (18) located downstream of the leading edge (17), the blade (12) comprising a lower surface wall (20) and a lower surface wall (21) spaced from each other and connecting the leading edge (17) to the trailing edge (18), this blade comprising also:
    - cooling conduits (41, 52, 47, 54) each extending laterally from the upper surface wall (21) to an internal upstream wall (40) or to an internal downstream wall (49);
    - an upstream lateral cavity (37) and a downstream lateral cavity (38) running along the lower surface wall (20) to form a heat shield, being spaced apart from each other along this lower surface wall ( 20);
    - the upstream lateral cavity (37) extending laterally from the lower surface wall (20) to the upstream inner wall (40);
    - the downstream lateral cavity (38) extending laterally from the lower surface wall (20) to the downstream inner wall (49);
    - A cooling duct (53) extending transversely from the lower surface wall (20) to the upper surface wall (21) between the upstream side cavity (37) and the downstream side cavity (38).
    [2" id="c-fr-0002]
    2. Dawn according to claim 1, in which a duct (52) extending from the upper surface wall (21) to the upstream internal wall (40) is connected to the duct (53) extending from the wall upper surface (21) to the lower surface wall (20) which is itself connected to a duct (54) extending from the upper surface wall (21) to the downstream internal wall (49), according to a type arrangement paper clip circuit (33).
    [3" id="c-fr-0003]
    3. Dawn according to claim 2, comprising a downstream ramp (56) supplied by a conduit (54) of the paper clip circuit (33) this downstream ramp (56) extending transversely, from the lower surface (20) to the upper surface wall (21), and in which the lower surface wall (20) has holes opening into the downstream ramp (56) to form a film of external air for cooling the lower surface wall (21).
    [4" id="c-fr-0004]
    4. Dawn according to claim 3, in which the downstream ramp (56) is supplied from the conduit (54) by calibrated passages (58).
    [5" id="c-fr-0005]
    5. Dawn according to one of claims 1 to 4, comprising a bathtub cavity (46) extending from a central region from the top (S) to the trailing edge (18), and at least one central duct ( 47) directly supplying this under-bath cavity (46) with air collected at the foot (P).
    [6" id="c-fr-0006]
    6. Dawn according to claim 5, in which the trailing edge comprises on the lower surface a series of through slots (23) supplied with cooling air, in which these slots (23) comprise:
    - one or more last slots near the top (S) which are supplied by the bathtub cavity (46);
    - Slots (23) which are supplied by a downstream conduit (61) of the blade (12).
    [7" id="c-fr-0007]
    7. Dawn according to one of the preceding claims, comprising an upstream circuit (31) for cooling the leading edge (17) of the blade (12).
    [8" id="c-fr-0008]
    8. Foundry means for the manufacture of a blade according to one of claims 1 to 7, comprising indentations and a set of cores intended for the formation of internal conduits and ramps, and internal cavities forming a screen.
    [9" id="c-fr-0009]
    9. Turbomachine turbine comprising a blade according to any one of claims 1 to 7.
    [10" id="c-fr-0010]
    10. Turbomachine comprising a turbine according to the preceding claim.
    1/4
    S61325
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    引用文献:
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    FR3021699B1|2014-05-28|2019-08-16|Safran Aircraft Engines|OPTIMIZED COOLING TURBINE BLADE AT ITS LEFT EDGE|
    FR3021697B1|2014-05-28|2021-09-17|Snecma|OPTIMIZED COOLING TURBINE BLADE|
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    FR3041989B1|2015-10-06|2020-04-17|Safran Aircraft Engines|VANE WITH A LEAKING EDGE COMPRISING THREE DISTINCT COOLING REGIONS|US10815800B2|2016-12-05|2020-10-27|Raytheon Technologies Corporation|Radially diffused tip flag|
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    法律状态:
    2017-09-20| PLFP| Fee payment|Year of fee payment: 2 |
    2018-04-27| PLSC| Search report ready|Effective date: 20180427 |
    2018-09-19| PLFP| Fee payment|Year of fee payment: 3 |
    2019-09-19| PLFP| Fee payment|Year of fee payment: 4 |
    2020-09-17| PLFP| Fee payment|Year of fee payment: 5 |
    2021-09-22| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
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    US16/341,540| US11035235B2|2016-10-20|2017-10-18|Turbomachine blade with optimised cooling|
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