• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
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    • 专利摘要:
    The invention relates to a blade (51) of a turbomachine turbine such as a turboprop or a turbojet, this blade comprising a foot (P), a blade carried by this foot (P) and extending in a span direction (EV) terminating in a crown (S), said blade comprising a lower intrados wall and an extrados wall, and: at least one duct (53) configured to collect cooling air at level of the foot (P) and to circulate it in the blade to cool it; holes and / or slots (55, 67) made in its walls for discharging cooling air out of this blade; an upper internal cavity (52) located at the top (S) of the blade to cool it; and wherein at least one of the conduits (53) directly feeds the upper cavity with cooling air collected in the foot (P).
    公开号:FR3021697A1
    申请号:FR1454864
    申请日:2014-05-28
    公开日:2015-12-04
    发明作者:Charlotte Marie Dujol；Patrice Eneau；Brou De Cuissart Sebastien Digard；Matthieu Jean-Luc Vollebregt
    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 3021697 2 engines operating in increasingly harsh 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 traditional cooling architectures are penalized by the fact that the length of the internal circuit of the blade gives rise to air that is too strongly heated when it reaches the end of this circuit, so that its cooling efficiency is limited in the end-of-the-course regions, and in particular at the level of the dawn top where, on the contrary, it is sought 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 and extending according to the invention. a span direction terminating in a vertex, this blade including a leading edge and a trailing edge located downstream of the leading edge, this blade including a lower intrados wall and a spaced extrados wall; laterally from each other and each connecting the leading edge to the trailing edge, this blade comprising: at least one duct configured to collect cooling air at the root of the blade and for circulate it in the blade to cool it; holes and / or slots made in its walls to evacuate outside this blade the cooling air; an upper internal cavity located at the top of the blade to cool this blade tip; And wherein at least one of the conduits directly feeds the upper cavity with cooling air collected in the foot. The invention also relates to a blade as defined above, wherein the upper cavity extends from the front to the rear of the blade, for supplying at least one cooling slot of the trailing edge of the blade.
    [0005] The invention also relates to a blade as defined above, wherein the intrados wall has at least one through hole or through slot which opens into the upper cavity. The invention also relates to a blade as defined above, comprising a first internal lateral cavity which runs along the intrados wall while being separated from the direct supply duct, to form a heat shield which thermally isolates this duct. direct supply of the intrados wall. The invention also relates to a blade as defined above, further comprising a second internal lateral cavity along the extrados wall while being separated from the direct supply duct, to form a heat shield which thermally isolates this duct. feeding directly to the extrados wall.
    [0006] The invention also relates to a blade as defined above, in which each internal lateral cavity is provided with turbulence promoters and / or deflectors in order to increase the heat exchange, and in which each direct supply duct presents smooth walls to limit pressure drops.
    [0007] The invention also relates to a blade as defined above, in which the direct supply duct of the upper cavity is an upstream ramp for cooling the leading edge of the blade. The invention also relates to a blade as defined above, in which the direct supply duct is a central duct exclusively dedicated to the supply of cooling air to the upper cavity. The invention also relates to a blade as defined above, in which the two lateral cavities are joined by a junction zone situated downstream of the direct supply duct to constitute a single cavity enveloping three quarters of the circumference of this cavity. Direct feed duct extending over most of the length of this direct supply duct. The invention also relates to a blade as defined above, comprising a downstream ramp supply of cooling slots of the trailing edge located in the intrados wall, and a downstream duct calibrated supply of this downstream ramp which is thermally insulated by each side cavity.
    [0008] The invention also relates to a blade as defined above, comprising an upstream ramp for supplying cooling holes to the leading edge, and a calibrated supply upstream duct of this upstream ramp which is thermally insulated by each lateral cavity. The invention also relates to molding means for the manufacture of a blade as defined above, comprising impressions 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 comprising a blade as defined above.
    [0009] 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 inner portions of a turbine blade according to a fourth embodiment of the invention; Fig. 7 is a perspective view showing the hollow internal parts of a turbine blade according to a fifth embodiment of the invention; Fig. 8 is a perspective view showing the hollow inner portions of a turbine blade according to a sixth 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 into which 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.
    [0010] The primary stream 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 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 inlet sleeve 10 to the rear part where it delimits the duct through 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.
    [0011] 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 slits of short lengths extending along the span direction and spaced apart. others being located in an extension of each other at a short distance from the trailing edge. Each slot 23 passes through the wall of the blade to collect cooling air inside the blade and blow it on the pressure side wall at the trailing edge. Complementarily, the trailing edge is provided with external ribs oriented parallel to the axis AX for channeling the cooling air from these slots. 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, 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.
    [0012] The region of the crown 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 delimiting a so-called hollow portion 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 together with these edges is a hollow portion open in the opposite direction to the axis AX. A series of additional holes 27 passing through the intrados wall is provided along the S-vertex to ensure significant cooling of this blade tip which is under significant stress because it constitutes the part having the highest velocity relative to to the fluid.
    [0013] The series of holes 27 extends parallel to the closure wall, and the blade has, in addition, holes not visible in FIG. 2 which pass through the closure wall to open into the hollow portion called the bathtub which is at the top of the blade. As indicated above, such a blade is a hollow one piece piece. It is made by molding a metal material, using a set of cores to delineate the inner ducts of its hollow portion as well as 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.
    [0014] 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 figures that follow are representations of the hollow shapes of the blade according to the invention.
    [0015] The idea underlying the invention is to improve the cooling of the blade in the region of the intrados wall which is in the vicinity of the trailing edge and the top of the blade, since Practice this area is the first to deteriorate during the life of a dawn.
    [0016] This is achieved by providing in the region of the apex of the blade an upper cavity extending from the front to the rear of the blade and which is fed directly with air from the root of the blade by a conduit. supply of this upper cavity. The air taken from the foot thus travels straight ahead, in a substantially rectilinear manner, to the upper cavity. The length of the path of this air, in the supply duct, so that it reaches the upper cavity is thus less than or equal to the length of the blade in the span direction EV. In other words, by carrying out a direct supply, this duct makes it possible to minimize the heating of the air supplied to the upper cavity.
    [0017] In the first embodiment corresponding to FIG. 3, this supply duct is formed by a cooling ramp of the leading edge situated upstream. In the other embodiments, corresponding to FIGS. 4 to 8, this supply duct is constituted by a central duct of the blade, that is to say located substantially midway between its leading edge and its trailing edge.
    [0018] In the first embodiment of the invention, the blade, which is indicated by 31 in FIG. 3 where it is shown, thus comprises internal ducts arranged to provide in the region of the top of the blade on the underside side. cooling air as cool as possible in order to increase cooling efficiency.
    [0019] The interior of this blade 31 thus has in its upstream region, identified by AM, an upstream ramp 32 oriented along its span direction EV and which runs along its leading edge. This upstream ramp 32 directly feeds an upper cavity 33 of the blade, while supplying fresh air cooling holes 5 through the wall portion forming the leading edge of the blade. This upstream ramp 32 extends from the foot of the blade, marked by P, and through which it is supplied with air directly to the top of the blade identified by S. The upper cavity 33 which is located near the top extends along the closing wall of this blade 31 and along its intrados wall, from the front to the rear of the blade which is marked by AV. These two walls are not visible in Figure 3 since it is a representation of the hollow regions of this dawn. The entire portion of the apex S of the blade 31 which is located on the side of its underside, over substantially its entire length and in particular to the downstream end of this vertex S is thus supplied with air by the upper cavity 33 which is itself fed by the upstream ramp 32 forming duct. The upper cavity 33 reaches the trailing edge of the blade, in the downstream region AV, for supplying fresh air with at least one cooling slot of this trailing edge, namely the slot closest to the top which corresponds to the one of the most severely stressed areas of dawn. This upper cavity 33 runs along the intrados wall extending over a little less than half the width or thickness of the blade, that is to say it has a width less than half the distance separating the intrados and extrados walls. It is bounded laterally by a first face 34 which runs along the intrados and a second face 36 spaced from the first. The first face 34 and the second face 36 are joined to the front and rear of this upper cavity. The upper cavity 33 is delimited vertically by a bottom 37 parallel to and spaced from the closing wall and, by an upper face 38 which is the lower face of the closure wall.
    [0020] In the region of the crown S of the blade, the intrados wall may have through holes, not shown, allowing the upper cavity 33 to further cool the outer face of the intrados wall in this region. The interior of the blade 31 further comprises a downstream ramp 41 extending along the trailing edge from the foot P to the region of the summit S to terminate under the rear portion of the upper cavity 33. This downstream ramp 41 feeds a series of cooling slots of the trailing edge, not visible in Figure 3. The majority of the cooling slots of the trailing edge are thus supplied with air by the downstream ramp 41, but it is the upper cavity which feeds the slot or slots closest to the top S, which is a region subject to greater thermal stresses. The slots near the top are thus fed with cooler air and / or having a higher flow rate than the others. The blade of Figure 3 further comprises a first central duct 42, a second central duct 43 and a downstream duct 44, oriented in the span direction, 15 and communicating with each other in a so-called trombone arrangement. The first central duct 42 which runs along the upstream ramp 32 collects air at the root of the blade, and communicates at the level of the summit S with the second central duct 43 to supply it with air. This second central duct 43 is connected at the level of the base of the blade 20 with the downstream duct 44 to supply air. This downstream duct 44 extends rectilinearly from the foot P to the summit S, parallel to the downstream ramp 41 which it runs along being located upstream of this downstream ramp 41. As can be seen in the figure, the end Downstream conduit 44 terminates in the region of the summit S along the second face 36 of the upper cavity 33 to bypass it. The intrados wall may be provided with through holes allowing the conduits 42, 43, 44 to provide cooling air on the outer face of this wall to cool it by forming an outer film. The intrados wall may comprise at the level of the downstream duct 44 through holes through which this downstream duct 44 provides air cooling the outer face 30 of the intrados wall upstream of the trailing edge of the blade.
    [0021] Complementarily or alternatively to these cooling holes of the intrados wall upstream of the trailing edge, the downstream duct 44 can feed the downstream ramp 41 by a series of unrepresented calibrated passages, regularly spaced from each other along from the EV scale direction. In this case, instead of being supplied by the second duct 43, the downstream duct 44 then directly collects cooling air at the level of the root of the blade, so that the air that it supplies to the downstream ramp is as fresh as possible. Thus, depending on the design choice, the downstream ramp 41 may be fed calibrated by the downstream conduit 44, or it may instead be fed directly into the region of the root of the blade. These passages are then calibrated to obtain approximately a desired air flow rate in each cooling slot of the trailing edge. The desired airflow for a given slot is conditioned by the thermal stresses of the trailing edge in the region cooled by this slot.
    [0022] In a second embodiment of the invention shown in FIG. 4, the blade which is marked by 51 comprises an upper cavity 52 which is fed directly by a central duct 53 entirely dedicated to this upper cavity 52. in the first embodiment of FIG. 3, the supply duct of the upper cavity does not participate in the cooling of the leading edge. In this blade 51 of Figure 4, there is further provided a first lateral cavity 54 along the intrados wall, and a second lateral cavity 56 along the upper surface. These two lateral cavities thermally insulate the central duct and a calibrated supply upstream duct of a cooling ramp of the leading edge of the blade, the walls of the intrados and extrados which are heated by the gas flows surrounding the blade. The upper cavity 52 of this blade 51 has a shape substantially identical to that of the blade 31 of FIG. 3. It is located close to the vertex S, extends along the closure and intrados walls, the front to the rear of the blade 3021697. Again, the entire portion of the top S located on the underside is supplied with air by the upper cavity 52, over substantially its entire length to the rear end. This upper cavity 52 also extends to the trailing edge, to supply fresh air at least the slot closest to the summit S, marked by 55, and possibly 5 a few adjacent slots. The thickness of this upper cavity 52 is also less than half the thickness of the blade. It is delimited laterally by a first face 57 which runs along the intrados and a second face 58 spaced from the first face, these faces being joined at the front and at the rear. In the vertical direction, the upper cavity 52 is delimited by a bottom 59 parallel to the closure wall, and by the lower face 61 of this closure wall. In the region of the crown S of the blade, the intrados wall may also have through-holes for cooling the outer face of the intrados wall in the region of the crown.
    [0023] The central duct 53 feeds the upper cavity 52, extending from the root P of the blade through which it is supplied with air, to the top of this blade, where it opens entirely into the bottom 59 of this upper cavity. 52. The leading edge of the blade 51 is cooled by an upstream ramp 62 which extends from the base of the blade to the top S, but which is fed not directly by the foot, but by an upstream duct 63 in a calibrated manner. This calibrated supply is provided by calibrated passages 64 regularly spaced along the span direction EV of the blade and which each connect the upstream duct 63 to the upstream ramp 62. Each passage 64 has a calibrated diameter, it is that is to say chosen at the design to obtain in the zone of the ramp 62 that it feeds a desired air flow 25 which is conditioned by the thermal of the blade in this region. The wall of the blade comprises in the region of the leading edge unrepresented holes, through which the air circulating in the ramp passes through the wall to cool the outer face of the leading edge. As seen in FIG. 4, the first lateral cavity 54 has a small thickness, and extends from the foot P to the region of the summit S 3021697 14 having a generally rectangular contour. This first lateral cavity 54 ends under the upper cavity 52 so as not to cover it. It has a width sufficient to mask or cover the central duct 53 and the upstream duct 63 which runs along this central duct.
    [0024] Similarly, the second lateral cavity 56 also has a small thickness, and it extends from the foot P to the region of the summit S but covering the upper cavity 52. This second lateral cavity has a generally rectangular contour , having a width sufficient to mask or cover the central duct as well as the upstream duct 63 and the upper cavity 52 on the extrados side. Thanks to these two lateral cavities, the air that is supplied to the upper cavity 52 by the central duct 53 is kept cool during its path in this duct, thanks to the heat shields that form the lateral cavities 54 and 56. The air supplied by the upstream duct 63 is also kept cool during its journey in this upstream duct. As indicated above, the one or more trailing edge cooling slots located in the region of the summit S are supplied with air by the upper cavity 52. The other trailing edge slots, indicated by 67, are supplied by a downstream ramp 66 which extends from the foot P, where it is fed directly via this foot, to the region of the summit S to terminate under the rear part of the upper cavity 52. The slots 67 are thus fed in air by the downstream ramp 66, but it is the upper cavity 52 which supplies the slot or slots closest to the top S with cooler air and / or having a higher flow rate.
    [0025] In the third embodiment of the invention which is shown in FIG. 5, the blade which is marked 71 also comprises an upper cavity 72 fed by a dedicated central duct 73 which is thermally insulated by two lateral cavities 74 and 76. These two lateral cavities also isolate a calibrated supply upstream duct 30 of a cooling ramp of the leading edge of the blade.
    [0026] In this third embodiment, the two lateral cavities 74 and 76 are joined at the rear or downstream part of the blade to envelop this central duct 73 on three quarters of its circumference, so as to offer better thermal insulation for this conduit 73.
    [0027] The upper cavity 72 has a shape substantially identical to that of the blades of Figures 3 and 4. It is located near the top S, extends along the closing walls and the intrados, from the front to the back of the blade. All the portion of the top S located on the intrados side is supplied by this upper cavity 72, over its entire length to the rear end. This upper cavity 72 also extends to the trailing edge, to feed at least the slot closest to the top S, marked 75, and possibly some adjacent slots. The thickness of this upper cavity 72 is also less than half the thickness of the blade. It is delimited laterally by a first face 77 which runs along the intrados and a second face 78 spaced from the first, these faces being united at the front and at the rear. In the vertical direction, the upper cavity 72 is delimited by a bottom 79 parallel to the closure wall, and by the lower face 81 of this closure wall. In the region of the crown S of the blade, the intrados wall may also have through-holes for cooling the outer face of the intrados wall in the region of the crown.
    [0028] The central duct 73 feeds this upper cavity 72, extending from the root of the blade through which it is supplied with air, to the summit S, where it opens entirely into the bottom 79 of the upper cavity. The leading edge of the blade 71 is cooled by an upstream ramp 82 which extends from the base of the blade to the top S, and which is fed by an upstream conduit 83 in a calibrated manner by means of passages. calibrated regularly spaced along the EV span direction of the dawn and which each connect the upstream duct to the upstream ramp. The wall of the blade comprises in the region of the leading edge unrepresented holes, through which the air of the ramp passes through the wall to cool the outer face of the leading edge.
    [0029] The first lateral cavity 74 has a small thickness and extends from the foot to the region of the summit S having a generally rectangular contour. It ends under the upper cavity 72 without covering it. It has a width sufficient to mask or cover the central duct 73 and the upstream duct 83 5 along the central duct. The second lateral cavity 76 also has a small thickness, and it extends from the foot to the region of the summit S but covering the upper cavity 72. It has a generally rectangular contour, having a width sufficient to hide or cover the central duct 73 and the upstream duct 83 and the upper cavity 72 on the extrados side. Unlike the second embodiment, the two lateral cavities 74 and 76 are here joined at the rear or downstream instead of being separate. In this way, these two lateral cavities surround the central duct 73 over three-quarters of its circumference so as to further improve its thermal insulation of the external environment, so that it can supply the upper cavity 72 which it feeds. an even cooler air. As can be seen in FIG. 5, these two cavities are joined by a junction zone situated downstream with respect to the central duct and which extends over the majority of the height of this central duct. These two cavities with their junction zone 20 thus constitute a single cavity enveloping the central duct on the majority of its external surface. In practice, and as shown in FIG. 5, the height or length of the junction zone along the span direction EV corresponds to the height or length of the first lateral cavity along the span direction EV. The supply of these two lateral cavities can be carried out separately by two supply ducts taking air separately in the blade root, the lateral cavities then being united only in the region of the blade. It may also be possible to provide a single feed channel for the two lateral cavities having a cross-sectional shape corresponding to that of the letter U. The at least one trailing-edge cooling slot located in the region of the summit S is supplied with The remaining trailing edge slots, identified by 86, are fed by a downstream ramp 87 which extends from the foot, where it is fed directly via this foot, to the air through the upper cavity 72. to the region of the summit S to terminate under the rear portion of the upper cavity 72.
    [0030] In a fourth embodiment of the invention shown in FIG. 6, the blade which is marked by 91 also comprises an upper cavity 92 fed by a central duct 93 which is isolated by two lateral cavities 94 and 96. embodiment, the trailing edge is cooled by a downstream ramp which is fed in a calibrated manner by a downstream conduit.
    [0031] The upper cavity 92 has a shape substantially identical to that of the blades of Figures 3 to 5. It is located near the top S, extends along the closing walls and the intrados, from the front to the back of the blade. All the part of the top S located on the underside side is supplied with cooling air by this upper cavity 92, all along its length to the rear end. This upper cavity 92 also extends to the trailing edge, to feed at least the slot closest to the summit S, marked by 95, and possibly some adjacent slots. This upper cavity 92 is bounded laterally by a first face 97 which runs along the intrados and a second face 98 spaced from the first face, these faces being joined at the front and at the rear. It is delimited vertically by a bottom 99 20 parallel to the closure wall, and by the lower face 101 of this closure wall. In the region of the summit S, the intrados wall may also include through holes to cool the outer face of the intrados wall in the region of the summit. The central duct 93 feeds the upper cavity 92 extending from the root of the blade through which it is supplied with air, to the summit S, where it opens completely into the bottom 99. The leading edge of the blade 91 is cooled by an upstream ramp 102 which extends from the base of the blade to the top S, being fed by an upstream duct 103 in a calibrated manner by means of calibrated passages 105 regularly spaced along the vane direction direction EV of the dawn and which each connect the upstream duct 103 to the upstream ramp 102. The wall of the blade has in the region of the leading edge 3021697 18 through holes through which the air of the ramp cools the outer face of the leading edge. The first lateral cavity 94 has a small thickness and extends from the foot to the region of the summit S having a generally rectangular contour. It ends under the upper cavity 92 without covering it. It has a width sufficient to mask or cover the central duct 93 and the upstream duct 103 which runs along this central duct 93. The second lateral cavity 96 also has a small thickness, and extends from the foot to the region the top S but covering the upper cavity 92. It has a generally rectangular contour, of sufficient width to hide or cover the central duct 93 and the upstream duct 103 and the upper cavity 92 on the side of the extrados. The at least one trailing edge cooling slot in the region of the summit S is supplied with air by the upper cavity 92. The other 15 trailing edge slots, indicated by 106, are supplied by a downstream ramp. which extends from the foot to the region of the summit S. This downstream ramp 107 is here supplied calibrated by a downstream conduit 108 which extends from the foot of the blade to the region of its S top where it bypasses a rear portion of the upper cavity 92. This downstream duct 108 is located between the central duct 93 and the downstream ramp 107, and it is masked neither by the lateral cavity 94 nor by the lateral cavity 96 The downstream duct 108 calibrates the downstream ramp 107 by means of a series of calibrated passages 109 regularly spaced from one another along the span direction EV and each joining the downstream duct to the ramp 107.
    [0032] In a fifth embodiment of the invention shown in FIG. 7, the blade which is marked 111 also has an upper cavity 112 fed by a central duct 113 which is isolated by two lateral cavities 114 and 116. The trailing edge is also cooled by a downstream ramp supplied calibrated by a downstream duct, but this downstream duct is thermally protected by side cavities of the blade so as to provide cooler air for cooling the trailing edge. The upper cavity 112 has a shape substantially identical to that of the blades of Figures 3 to 6. It is located near the top S, extends along the walls 5 closing and intrados, from the front to the back of the blade. The entire portion of the top S located on the underside side is supplied with cooling air by this upper cavity 112, all along its length to the rear end. This upper cavity 112 also extends to the trailing edge, to feed at least the slot closest to the top S, marked 115, and possibly some adjacent slots 10. This upper cavity 112 is delimited laterally by a first face 117 which runs along the intrados and a second face 118 spaced from the first face, these faces being joined at the front and at the rear. It is delimited vertically by a bottom 119 parallel to the closure wall, and by the lower face 121 of this closure wall. The central duct 113 feeds the upper cavity 112, extending from the root of the blade through which it is supplied with air, to the summit S, where it opens entirely into the bottom 119. The leading edge of the blade 111 is cooled by an upstream ramp 122 which extends from the base of the blade to the top S, fed by an upstream duct 123 in a calibrated manner by means of calibrated passages 124 regularly spaced along the direction d EV span of the blade and which each connect the upstream duct 123 to the upstream ramp 122. The wall of the blade has in the region of the leading edge through holes through which the air of the ramp cools the face outer edge of the leading edge. The first lateral cavity 114 has a small thickness and extends from the foot to the crown region S having a generally rectangular contour. It ends under the upper cavity 112 without covering it, and it has a width sufficient to hide or cover the central duct 113 and the upstream duct 123 which runs along the central duct 113, and the downstream duct calibrated supply of the ramp downstream.
    [0033] The second lateral cavity 116 also has a small thickness, and it extends from the foot to the region of the summit S but covering the upper cavity 112. It has a generally rectangular contour, of sufficient width to hide or cover the central duct 113, the upstream duct 123 and the upper cavity 112 on the extrados side, as well as the downstream calibrated supply duct of the downstream ramp. The cooling slot 115 of the trailing edge located in the region of the summit S is supplied with air by the upper cavity 112. The other trailing edge slots, identified by 126, are fed by the downstream ramp 127 which extends from the foot to the region of the summit S. This downstream ramp 127 is here supplied calibrated by the downstream duct 128 which extends from the foot of the blade to the region of its summit to terminate at the summit S bypassing the upper cavity 112. This downstream duct 128 is located between the central duct 113 and the downstream ramp 127. The downstream duct 128 supplies the downstream ramp 127 with a calibrated a series of calibrated passages 129 regularly spaced from each other and each joining the downstream duct 128 to the ramp 127. As shown in FIG. 7, the lateral cavities 114 and 116 are here arranged to cover the upstream duct 123, the central duct 113 and the downstream conduit 128 so as to jointly cover these three elements to thermally isolate them from the intrados wall and the extrados wall. In a sixth embodiment of the invention shown in FIG. 8, the blade which is identified by 131 also has an upper cavity 132 fed by a central duct 133, but this latter is isolated by a single lateral cavity 134 located on the intrados side. This makes it possible to simplify the manufacture of the blade while offering satisfactory cooling efficiency because, in practice, the intrados wall tends to heat up significantly more than the extrados wall. The upper cavity 132 has a shape substantially identical to that of the blades of Figures 3 to 7. It is located near the top S, extends along the walls 3021697 21 closing and intrados, from the front 'at the back of the blade. The entire portion of the top S located on the underside side is supplied with cooling air by this upper cavity 132, all along its length to the rear end. This upper cavity 132 also extends to the trailing edge, to feed at least the slit closest to the top S, marked 135, and possibly some adjacent slits. This upper cavity 132 is delimited laterally by a first face 137 which runs along the intrados and a second face 138 spaced from the first face, these faces being joined at the front and at the rear. It is delimited vertically by a bottom 139 10 parallel to the closure wall, and by the lower face 141 of this closure wall. The central duct 133 feeds the upper cavity 132 extending from the root of the blade through which it is supplied with air, to the top S, where it opens completely into the bottom 139. The leading edge of the blade 131 is cooled by an upstream ramp 142 which extends from the base of the blade to the top S, which is fed by an upstream duct 143 in a calibrated manner by means of calibrated passages 144 which are regularly spaced along of the direction of span EV of the dawn and which each connect the upstream duct 143 to the upstream ramp 142. The wall of the blade has in the region of the leading edge through holes through which the air of the ramp cools the outer face of the leading edge. The lateral cavity 134 has a small thickness and extends from the foot to the region of the summit S having a generally rectangular contour. It ends under the upper cavity 132 without covering it. It has a width sufficient to mask or cover the central duct 133 and the upstream duct 143 which runs along this central duct 133. The cooling slot 135 of the trailing edge located in the region of the summit S is supplied with air by the cavity 132. The other slots of the trailing edge, identified by 146, are fed by a downstream ramp 147 which extends from the foot to the region of the summit S.
    [0034] 3021697 22 This downstream ramp 147 is here supplied calibrated by a downstream duct 148 which extends from the root of the blade to the region of its summit to end at the summit S bypassing the upper cavity 132 This downstream duct 148 is situated between the central duct 133 and the downstream ramp 147. The downstream duct 148 calibrates the downstream ramp 147 by means of a series of calibrated passages 149 regularly spaced from one another along of the span direction EV and each joining this downstream duct 148 to the ramp 147. As shown in FIG. 8, the lateral cavity 134 covers the upstream duct 143 as well as the central duct 133 and the downstream duct 148 so as to thermally isolating these three elements from the intrados wall to reduce the heating of the air they convey. As will be understood, generally, in each of the embodiments of the invention, the region of the apex is supplied with air by the upper cavity with respect to the entire portion of the vertex extending along from the intrados.
    [0035] The other parts of the top are supplied with air by the other ducts, ramps or cavities of the blade, as in particular the upstream ramp and optionally the upstream duct, the downstream ramp and possibly the downstream duct, and if necessary the second lateral cavity along the extrados. In the various embodiments, the upper cavity makes it possible to significantly improve the cooling of the region of the top of the blade, in particular by providing very fresh air to the slot of the trailing edge which is the closest to the Mountain peak. This upper cavity also provides cooling by thermal conduction of the walls of the blade which delimit, such as the closing wall of the blade.
    [0036] On the other hand, holes passing through the walls of the blade and opening into the inner heat-shielding side cavities may be provided to establish optimum 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 conveyed into a cavity forming a heat shield, is sucked out of the blade after having traveled into this cavity.
    [0037] In the different embodiments, the cooling of the blade is further optimized by minimizing the pressure losses in each internal duct to reduce heat exchange, and on the contrary providing for turbulence promoters in each lateral cavity for therein. increase heat exchange.
    [0038] 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 losses so to circulate quickly to warm as little as possible. 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 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 inner faces of the cavity are provided with disrupters and / or bridges 15 to create turbulence in the air circulation to promote a high level of heat exchange between the air and the walls it lanyard. 20
    权利要求:
    Claims (14)
    [0001]
    REVENDICATIONS1. Blade (31; 51; 71; 91; 111; 131) of a turbomachine turbine such as a turboprop or a turbojet engine, this blade comprising a foot (P), a blade carried by this foot and extending in a direction d span (EV) ending with a top (S), this blade comprising a leading edge and a trailing edge located downstream of the leading edge, this blade comprising a lower surface wall and a wall of extrados spaced laterally from each other and each connecting the leading edge to the trailing edge, said blade comprising: -at least one conduit (32; 42; 53; 73; 93; 113; 133) configured to collect cooling air at the foot of the blade and to circulate it in the blade to cool it; holes and / or slots (55, 67, 75, 86, 95, 106, 115, 126, 135, 146) formed in its walls for discharging the cooling air out of this blade; an upper internal cavity (33; 52; 72; 92; 112; 132) located at the top of the blade for cooling this blade tip (S); and wherein at least one of the conduits (32; 52; 73; 93; 113; 133) directly feeds the upper cavity (33; 52; 72; 92; 112; 132) with cooling air collected in the foot (P).
    [0002]
    2. blade (31; 51; 71; 91; 111; 131) according to claim 1, wherein the upper cavity (33; 52; 72; 92; 112; 132) extends from front to rear; the blade to feed at least one cooling slot (55; 75; 95; 115; 135) of the trailing edge of the blade.
    [0003]
    3. blade (31; 51; 71; 91; 111; 131) according to claim 1 or 2, wherein the intrados wall has at least one through hole or through slot which opens into the upper cavity (33; 72; 92; 112; 132).
    [0004]
    4. blade (51; 71; 91; 111; 131) according to one of the preceding claims, comprising a first internal lateral cavity (54; 74; 94; 114; 134) which runs along the pressure wall while being separated from the direct supply duct (53; 73; 93; 113; 133) to form a heat shield which thermally isolates this direct supply duct (53; 73; 93; 113; soffit. 5
    [0005]
    The blade (51; 71; 91; 111) according to claim 4, further comprising a second internal lateral cavity (56; 76; 96; 116) extending along the extrados wall while being separated from the direct supply conduit. (53; 73; 93; 113) to form a heat shield which thermally isolates this direct supply duct (53; 73; 93; 113) from the extrados wall. 10
    [0006]
    The blade (51; 71; 91; 111) according to claim 4 or 5, wherein each inner side cavity (54,56; 74,76; 94,96; 114,116; 134) is provided with turbulence promoters. and / or deflectors to increase the heat exchange, and wherein each direct supply duct (53; 73; 93; 113) has smooth walls to limit the pressure losses.
    [0007]
    7. blade (31) according to one of the preceding claims, wherein the direct supply duct (32) of the upper cavity (33) is an upstream ramp (32) for cooling the leading edge of the dawn. . 20
    [0008]
    8. blade (51; 71; 91; 111; 131) according to one of claims 1 to 6, wherein the direct feed duct is a central duct (53; 73; 93; 113; 133) exclusively dedicated to supplying cooling air to the upper cavity (53; 72; 92; 112; 132). 25
    [0009]
    9. blade (71) according to claim 5, wherein the two lateral cavities (74, 76) are joined by a junction zone located downstream of the direct supply duct (73) to form a single cavity enveloping three quarters the circumference of this direct supply duct (73) extending over most of the length of this direct supply duct (73). 3021697 26
    [0010]
    10. A blade (111; 131) according to claim 4, comprising a downstream ramp (127; 147) for supplying cooling slots (126; 146) from the trailing edge located in the intrados wall, and a downstream duct (128; 148) calibrated supply of this downstream ramp (127; 147) which is thermally insulated by each side cavity (114,116; 134).
    [0011]
    The blade of claim 4, including an upstream ramp (62; 82; 102; 122; 142) for supplying cooling holes to the leading edge, and an upstream line (63; 83; 103; 123; 143) of said upstream ramp (62; 82; 102; 122; 142) which is thermally insulated by each side cavity (54,56; 74,76; 94,96; 114,116; 134).
    [0012]
    12. Molding means for the manufacture of a blade according to one of claims 1 to 7, comprising indentations and a set of cores for the formation of internal conduits and ramps, and possibly internal cavities forming a screen.
    [0013]
    13. A turbomachine turbine comprising a blade according to any one of claims 1 to 7.
    [0014]
    14. Turbomachine comprising a turbine according to the preceding claim. 25
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    同族专利:
    公开号 | 公开日
    CA2950127A1|2015-12-03|
    CN106460526A|2017-02-22|
    EP3149280A1|2017-04-05|
    JP2017526845A|2017-09-14|
    RU2016151772A|2018-07-02|
    US10689985B2|2020-06-23|
    BR112016027042A2|2017-08-15|
    BR112016027042A8|2021-06-29|
    JP6731353B2|2020-07-29|
    WO2015181497A1|2015-12-03|
    US20170183969A1|2017-06-29|
    CN106460526B|2019-01-04|
    RU2697211C2|2019-08-13|
    RU2016151772A3|2018-11-22|
    FR3021697B1|2021-09-17|
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    优先权:
    申请号 | 申请日 | 专利标题
    FR1454864A|FR3021697B1|2014-05-28|2014-05-28|OPTIMIZED COOLING TURBINE BLADE|FR1454864A| FR3021697B1|2014-05-28|2014-05-28|OPTIMIZED COOLING TURBINE BLADE|
    RU2016151772A| RU2697211C2|2014-05-28|2015-05-27|Turbine blade with optimized cooling|
    CN201580027696.XA| CN106460526B|2014-05-28|2015-05-27|Turbo blade with optimised cooling|
    BR112016027042A| BR112016027042A8|2014-05-28|2015-05-27|turbomachinery turbine blade, molding means for manufacturing a blade, turbomachinery turbine and turbomachinery|
    CA2950127A| CA2950127A1|2014-05-28|2015-05-27|Turbine blade with optimised cooling|
    JP2016569440A| JP6731353B2|2014-05-28|2015-05-27|Turbine blades with optimized cooling|
    PCT/FR2015/051397| WO2015181497A1|2014-05-28|2015-05-27|Turbine blade with optimised cooling|
    EP15729543.7A| EP3149280A1|2014-05-28|2015-05-27|Turbine blade with optimised cooling|
    US15/312,688| US10689985B2|2014-05-28|2015-05-27|Turbine blade with optimised cooling|
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