• 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 blade (12) comprising a turbine foot (P) carrying a blade (11) extending in a span direction (EV) ending in a vertex (S), the blade ( 11) comprising a leading edge (16) and a trailing edge (17) connected by an intrados wall (14) and an extrados wall, the trailing edge (17) having the intrados side (14) cooling slots (22, 24, 31). The trailing edge (17) comprises: - one or more first slots (31) close to the foot (P) which are fed by a lower cavity (29); one or more last slots (24) close to the apex (S) fed by an upper cavity (23); intermediate slots (22) located between the first slots (31) and the last slots (24) supplied with air by a downstream ramp (21); and in that the lower (29) and upper (23) and downstream (21) cavities are separately supplied at the foot (P).
    公开号:FR3041989A1
    申请号:FR1502074
    申请日:2015-10-06
    公开日:2017-04-07
    发明作者:Patrice Eneau；Sebastien Serge Francis Congratel；Charlotte Marie Dujol；Philippe Picot
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    DAWN HAVING A LEAK EDGE COMPRISING THREE REGIONS OF
    SEPARATE COOLING
    DESCRIPTION
    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 a motor 1, the outside air is admitted into an inlet sleeve 2 to pass through a fan 3 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 through a first and a second compression stage 4 and 6, before arriving in a combustion chamber 7, after which it relaxes by passing through a set of turbines 8 before being discharged to the back by generating thrust. The secondary flow is propelled directly backwards by the blower to generate a complementary thrust.
    The expansion in the turbines 8, which drives the compressor 4, 6 and the blower 3, takes place at high temperature because it occurs immediately after combustion. This turbine 8 is thus designed and sized to operate under severe conditions of temperature, pressure and fluid flow.
    Each turbine comprises a succession of stages each comprising a series of vanes carried by the motor shaft, the blades subjected to the most severe conditions being those of the first expansion stages, called high pressure stages.
    The increased performance requirements lead to the design of engines operating in increasingly severe environments, which involves increasing the temperature resistance of the high-pressure blades, and thereby reconsidering their cooling.
    Cooling is ensured by circulating inside the dawn fresh air taken upstream of the combustion and admitted at the bottom of the blade, to walk along an internal circuit of the blade.
    This circuit typically has a shape called trombone extending over the entire height of the blade, from the leading edge located upstream of the blade to the trailing edge located downstream of the dawn, upstream and downstream with respect to the direction of circulation of the fluid surrounding the blade in use. The cooling air circulating in the blade is evacuated from it by holes through its wall, which also make it possible to create on the outer surface of the blade a film of air colder than the air coming from of burning, to limit the temperature of the dawn.
    The object of the invention is to provide a blade structure for improving the efficiency of its cooling at the trailing edge of this blade.
    SUMMARY OF THE INVENTION For this purpose, the subject of the invention is a turbine engine turbine blade such as a turboprop engine or a turbojet engine, this blade comprising a foot carrying a blade extending in a span direction while ending by a top this 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 each connecting the leading edge to the trailing edge the trailing edge having on the intrados side a series of through slots fed with cooling air, characterized in that these slots comprise: - one or more first slots which are closest to the foot and which are fed by a cavity inferior of dawn; one or more last slots which are closest to the top and which are fed by an upper cavity of the blade; intermediate slots located between the first slots and the last slots and which are fed by a downstream ramp of the blade; and in that the lower cavity the upper cavity and the downstream ramp are supplied with air separately at the foot of the dawn
    With this arrangement, the cooling of the trailing edge can be improved at the top of the blade and at its base, that is to say in the vicinity of his foot. Indeed, the region of the top of the trailing edge is strongly constrained due in particular to the temperatures which are very high, and the base of the trailing edge is also strongly constrained because it supports all the centrifugal forces applied to the blade in use. The invention also relates to a blade thus defined, comprising a downstream duct for supplying air to the downstream ramp, this downstream duct being connected to the downstream ramp by a series of holes to ensure a calibrated supply of this downstream ramp. also a blade thus defined, wherein the lower cavity and the cooling ramp of the intermediate slots extend in the extension of one another in the span direction of the blade The invention also relates to a blade thus defined , comprising a single first slot and / or a single last slot. The invention also relates to a blade thus defined, wherein the upper cavity is located at the top of the blade being arranged to cool the top. The invention also relates to a blade thus defined, comprising a lateral intrados cavity located between the central duct and the intrados wall of the blade to form a heat shield protecting the central duct. The invention also relates to a blade thus defined, comprising an extrados lateral cavity located between the central duct and the extrados wall of the blade to form a heat shield protecting the central duct. The invention also relates to molding means for the manufacture of a blade thus defined, comprising a core intended to delimit at least a portion of the internal space of the blade during its manufacture by molding. 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
    FIG. 1 is a schematic view of a turbofan engine in longitudinal section;
    Figure 2 is a perspective view of a blade according to the invention;
    Figure 3 is a perspective view of a set of cores defining the inside of the blade according to the invention during its molding;
    Figure 4 is a cross-sectional view of a set of cores defining the inside of the blade according to a second embodiment of the invention;
    Figure 5 is a perspective view of a set of cores defining the inside of the blade according to the second embodiment of the invention;
    Figure 6 is a side view of a core assembly defining the blade according to a variant of the second embodiment of the invention.
    DETAILED PRESENTATION OF PARTICULAR EMBODIMENTS The blade according to the invention which appears in FIG. 2, where it is marked by 11, comprises a foot P carrying a blade 12 extending in a direction of radial span EV with respect to its axis. rotation AX. The blade 12 extends from a base or platform by which it is connected to the foot P to a vertex S corresponding to its free end, and it has an extrados wall and a lower surface wall 14. L extrados and intrados 14 are joined on the one hand at the leading edge 16 of the blade which corresponds to its upstream region AM, and secondly at its tapered trailing edge 17 which corresponds to its downstream region AV. The upstream and downstream are in relation to the direction of flow of the fluid surrounding the blade in use.
    As can be seen in FIGS. 3 and 4, the interior of this blade comprises a central duct 18 downstream of which extends a downstream duct 19 which runs along the central duct 18 in order to calibrate a downstream ramp 21. This downstream ramp 21 In turn, it supplies fresh air with a set of cooling slots 22 for the trailing edge 17. This blade also comprises other parts not shown, such as in particular an upstream duct and / or ramp, situated upstream of the central duct and arranged for provide cooling air at the leading edge.
    In the region corresponding to the apex S of the blade, the central duct 18 is extended by an upper cavity 23 for cooling the blade tip. This upper cavity 23 extends from the central or upstream portion to the downstream part of the blade, and it feeds by its downstream portion the last slot 24 for cooling the trailing edge. This last slot 24 is the one that is closest to the sun tip S along the span direction EV.
    As can be seen in FIG. 3, the central duct 18 extends over substantially the entire height of the blade along the span axis EV. The end of the central duct 18 which is located in the region of the top of the blade is connected to an upstream portion of the upper cavity 23 for supplying cooling air to the upper cavity.
    The central duct 18 and the upper cavity 23 fed by this central duct are defined during the manufacture of the blade by an element E forming part of a core, this core being removed for example by etching when the dawn has been removed. casting.
    The conduit 19 has a substantially smaller length than the conduit 18, it runs along the conduit 18 and its free end is located vis-à-vis the upper cavity 23. It communicates with the downstream ramp 21 by a series of calibrated holes 26 distributed and regularly spaced along the entire length of the ramp 21 along the span direction EV, and oriented perpendicularly to this direction EV. These communication holes 26 provide a calibrated supply of the ramp 21, so that the air flow is as homogeneous as possible in the different cooling slots of the trailing edge.
    The downstream duct 19 and the downstream ramp 21 are defined during the manufacture of the blade by a second element E2 constituting another part of the core which is removed after molding the blade by etching.
    Holes 25 may be made through the upper surface of the suction surface of the blade to evacuate the air circulating in its internal space while forming an outside air film along the intrados to isolate it from the heat. of the flow surrounding the dawn in use.
    As can be seen in FIG. 3, the downstream ramp 21 runs along the downstream duct 19 to comprise, like this duct 19, a free end 27 located opposite the upper cavity 23. But this downstream ramp 21 has a length less than the duct 19 along the span direction EV, because it does not start at the base of the blade.
    The downstream ramp 21 has a lower end 28 which is spaced from the base of the blade, so that this downstream ramp 21 supplies air to the slots 22 of the trailing edge which comprise the second slot starting from the base of the blade and the following until the penultimate slot before reaching the top of the blade.
    As indicated above, it is the downstream portion of the upper cavity 23 which supplies the last slot 24. But it is also a distinct lower cavity, marked by 29, which supplies the first slot with a distinct and independent supply, namely the slot 31. This slot 31 is the first slot of the trailing edge 17, starting from the base of the blade, that is to say the slot of the trailing edge 17 which is closest to the foot P of the 'dawn.
    Thus, the downstream ramp 21 extends in the extension of the lower cavity 29, the lower cavity 29 and the ramp 21 both along the downstream conduit 19. But the lower cavity 29 is fed directly with air from the foot P of the blade 11, instead of being fed by the downstream conduit 19, and it feeds only the first cooling slot 31 of the trailing edge 17 of the blade.
    During manufacture, the lower cavity 29 is also delimited by an element E3 forming another part of the core which is removed by etching at the end of the molding.
    Alternatively, the blade may be produced by the additive manufacturing process.
    Under these conditions, the air supply of the cooling slots of the trailing edge 17 is provided separately for the first slot 31 and for the last slot 24, respectively by the lower cavity 29 and the upper cavity 23. This supply is provided jointly by the ramp 21 for all the intermediate slots 22 which are located between the first slot 31 and the last slot 24.
    The slots of the trailing edge 17 can be distinguished into three zones, namely a first zone ZI close to the base comprising only the first slot in the example of the figures, a second intermediate zone Z2 having a series of intermediate slots, and a third zone Z3 corresponding to the vertex and having only the last slot in the example of the figures. These three zones Z1, Z2, Z3 are independently supplied with cooling air, so as to optimize and smooth the cooling of the trailing edge at best.
    It may be possible, if appropriate, to provide that the first zone Z1 comprises not only a first slot as in the example of the figures, but several contiguous first slots which are closest to the foot. In the same way, the third zone may also comprise not only one last slot as in the example of the figures, but several of the last contiguous slots located at the level of the apex of the blade, that is to say several last slots and not just one as in the example of the figures.
    As can be seen in FIG. 3, the boundary between the first zone Z1 and the second zone Z2 is located well below half the height of the blade along the span axis EV. In practice, the first slots, which correspond to the first zone Z1, extend about twenty percent of the height of the trailing edge along the axis EV starting from the base of the blade, that is to say starting from the platform separating the foot of the blade from the blade.
    Complementarily, the central duct 18 may be thermally insulated from the intrados and extrados walls of the blade by a lateral intrados cavity 32 and / or by an extrados lateral cavity 33, as illustrated in FIGS. and 5.
    The lateral cavity 32 then has a small thickness extending facing the majority of the surface of the duct 18, so as to form a heat shield: the duct 18 is then separated from the intrados wall by this lateral cavity 32 .
    The lateral cavity 33 which is of the same type, is similarly a heat shield which is located on the upper surface of the blade, to separate the conduit 18 from the extrados wall.
    Each lateral cavity 32, 33 is formed in one piece, and it runs along the intrados or extrados with a small thickness. It is delimited by a generally rectangular contour and it extends over most of the height of the blade and over the entire length of the upstream duct along the intrados, extrados or axis AX. Each lateral cavity 32, 33 is supplied with air via the foot of the blade in a direct manner, that is to say independently of the other ducts, cavities or ramps of the blade.
    In the example of the figures, the lateral cavities 32, 33 cover only the central duct 18, but their length can also be extended so that they also cover the downstream duct 19 in order to isolate it also from the intrados walls and / or extrados of the dawn. The length of the lateral cavities 32, 33 may also be extended upstream to cover other cavities of the blade. The separate and independent supply ducts 18 and 19 and the cavity 29 can be provided by three separate mouths each collecting air independently at the blade root. This distinct supply can also be provided, as shown schematically in Figure 6, by the same mouth 34, so as to facilitate the manufacture of the blade, located at the blade root and which splits into three separate channels to feed separately ducts 18, 19 and cavity 29. The invention optimizes the cooling of the trailing edge of a blade of a high pressure stage, by promoting the ventilation of the blade tip and the low blade area. without degrading that of the intermediate region of the trailing edge. The independent power supply of the first slot (s) makes it possible to better control the cooling of this zone to avoid, in particular, air shear phenomena at the entrance of these slots. It improves the cooling of the trailing edge in the region of the base of the blade which undergoes all the centrifugal forces applied to the blade in use. In practice, this region is prone to the appearance of breakaway primers at the connection fillet with the foot or the platform of the blade. The platform designates the generally flat portion of normal orientation to the span axis located between the blade and the foot. The independent supply of the last slot or slots optimizes the cooling of the trailing edge in the region of the summit where high temperatures give rise to significant constraints. These important constraints can result in burns, oxidation, and loss of material that can be significant.
    In a similar way, the independent supply of the intermediate slots makes it possible to preserve an adequate level of cooling for the median portion of the trailing edge. The implementation of a calibrated supply of the downstream feed ramp of the intermediate slots makes it possible to homogenize the cooling over the height, while limiting the overheating and the pressure drops. In general, the fact of distinguishing three zones for the cooling of the trailing edge makes it possible to calibrate or regulate more finely the cooling of the various parts of the trailing edge in order to increase the cooling in the critical portions for this edge of leak.
    In particular, thanks to three separate cooling air supply of the trailing edge, the risk of heterogeneous cooling disadvantaging the first slots and the last slots, for example due to internal turbulence, is excluded. The invention thus ensures optimum cooling in all circumstances for the critical parts of the trailing edge. m
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. A blade (12) for a turbomachine turbine such as a turboprop or a turbojet engine, this blade (12) comprising a foot (P) carrying a blade (11) extending in a span direction (EV) in terminating in a crown (S), said blade (11) comprising a leading edge (16) and a trailing edge (17) located downstream of the leading edge, said blade comprising a lower surface wall (14) and an extrados wall each connecting the leading edge (16) to the trailing edge (17) the trailing edge (17) having on the intrados side (14) a series of through slots (22,24,31) fed with cooling air, characterized in that these slots (22,24,31) comprise: - one or more first slots (31) which are closest to the foot (P) and which are fed by a lower cavity (29) dawn (11); one or more last slots (24) which are closest to the apex (S) and which are fed by an upper cavity (23) of the blade (11); intermediate slots (22) located between the first slots (31) and the last slots (24) and which are fed by a downstream ramp (21) of the blade (11); and in that the lower cavity (29), the upper cavity (23) and the downstream ramp (21) are supplied with air separately at the foot (P) of the blade (12).
    [2" id="c-fr-0002]
    2. blade (12) according to claim 1, comprising a downstream duct (19) supplying air to the downstream ramp (21), the downstream duct (19) being connected to the downstream ramp (21) by a series of holes (26) to ensure a calibrated supply of this downstream ramp (21).
    [3" id="c-fr-0003]
    3. blade (12) according to claim 1 or 2, wherein the lower cavity (29) and the ramp (21) for cooling the intermediate slots extend in the extension of one another in the direction of span (EV) of the blade (11).
    [4" id="c-fr-0004]
    4. blade (12) according to one of the preceding claims, comprising a single first slot (31) and / or a single last slot (24).
    [5" id="c-fr-0005]
    5. blade (12) according to one of the preceding claims, wherein the upper cavity (23) is located at the top (S) of the blade (11) being arranged to cool the top (S).
    [6" id="c-fr-0006]
    6. blade (12) according to one of the preceding claims, comprising a central duct (18) and a side intrados cavity (32) located between the central duct (18) and the intrados wall (14) of the blade (12) to form a heat shield protecting the central duct (18).
    [7" id="c-fr-0007]
    7. blade (12) according to one of the preceding claims, comprising a central duct (18) and an extrados lateral cavity (33) located between the central duct (18) and the extrados wall of the blade (12). ) to form a heat shield protecting the central duct (18).
    [8" id="c-fr-0008]
    8. Molding means for the manufacture of a blade according to one of claims 1 to 7, comprising a core (E1, E2, E3) for delimiting at least a portion of the internal space of the blade (11). ) when manufactured by molding.
    [9" id="c-fr-0009]
    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.
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3041989A1|2017-04-07|DAWN COMPRISING A LEAK EDGE COMPRISING THREE SEPARATE COOLING REGIONS
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    FR3037829A1|2016-12-30|CORE FOR MOLDING A DAWN WITH OVERLAPPED CAVITIES AND COMPRISING A DEDUSISHING HOLE THROUGH A CAVITY PARTLY
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    FR2955152A1|2011-07-15|Turbomachine i.e. open rotor type jet engine, for aircraft, has evacuation unit including envelope connected to structural annular walls and extended around enclosure to determine outer and inner annular cavities in space
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    FR2983517A1|2013-06-07|COLD TURBINE VANE FOR GAS TURBINE ENGINE.
    WO2020120862A1|2020-06-18|Turbine engine blade with improved cooling
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    FR3066551A1|2018-11-23|MOVABLE DAWN OF A TURBINE COMPRISING AN INTERNAL COOLING CIRCUIT
    FR3025835A1|2016-03-18|TURBOMACHINE TURBINE AUB COOLING AIR CIRCULATION SYSTEM
    同族专利:
    公开号 | 公开日
    US20180306035A1|2018-10-25|
    GB2558113B|2021-05-12|
    GB201805442D0|2018-05-16|
    GB2558113A|2018-07-04|
    WO2017060613A1|2017-04-13|
    FR3041989B1|2020-04-17|
    US10767491B2|2020-09-08|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2700530A|1948-08-27|1955-01-25|Chrysler Corp|High temperature elastic fluid apparatus|
    US3017159A|1956-11-23|1962-01-16|Curtiss Wright Corp|Hollow blade construction|
    US20050084370A1|2003-07-29|2005-04-21|Heinz-Jurgen Gross|Cooled turbine blade|
    US20080085193A1|2006-10-05|2008-04-10|Siemens Power Generation, Inc.|Turbine airfoil cooling system with enhanced tip corner cooling channel|
    EP2193859A1|2008-11-21|2010-06-09|United Technologies Corporation|Castings, casting cores, and mehtods|
    EP2604795A2|2011-12-15|2013-06-19|Rolls-Royce plc|Aerofoil blade or vane|
    US20140093386A1|2012-09-28|2014-04-03|Solar Turbines Incorporated|Cooled turbine blade with inner spar|EP3564486A1|2018-05-02|2019-11-06|United Technologies Corporation|Airfoil having improved cooling scheme|
    EP3633150A1|2018-10-01|2020-04-08|United Technologies Corporation|Multi-walled airfoil core|
    WO2021186122A1|2020-03-18|2021-09-23|Safran Aircraft Engines|Turbine blade comprising ribs between cooling outlets with cooling holes|
    WO2021186121A1|2020-03-18|2021-09-23|Safran Aircraft Engines|Turbine blade comprising three types of orifices for cooling the trailing edge|US8113780B2|2008-11-21|2012-02-14|United Technologies Corporation|Castings, casting cores, and methods|FR3057906B1|2016-10-20|2019-03-15|Safran Aircraft Engines|OPTIMIZED COOLING TURBINE TANK|
    法律状态:
    2016-10-06| PLFP| Fee payment|Year of fee payment: 2 |
    2017-04-07| PLSC| Publication of the preliminary search report|Effective date: 20170407 |
    2017-09-21| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2018-09-19| PLFP| Fee payment|Year of fee payment: 4 |
    2019-09-19| PLFP| Fee payment|Year of fee payment: 5 |
    2020-09-17| PLFP| Fee payment|Year of fee payment: 6 |
    2021-09-22| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1502074A|FR3041989B1|2015-10-06|2015-10-06|VANE WITH A LEAKING EDGE COMPRISING THREE DISTINCT COOLING REGIONS|
    FR1502074|2015-10-06|FR1502074A| FR3041989B1|2015-10-06|2015-10-06|VANE WITH A LEAKING EDGE COMPRISING THREE DISTINCT COOLING REGIONS|
    US15/765,334| US10767491B2|2015-10-06|2016-10-04|Blade comprising a trailing edge having three distinct cooling regions|
    GB1805442.9A| GB2558113B|2015-10-06|2016-10-04|Blade comprising a trailing edge having three distinct cooling regions|
    PCT/FR2016/052548| WO2017060613A1|2015-10-06|2016-10-04|Blade comprising a trailing edge having three distinct cooling regions|
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