• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a turbine engine turbine blade (1) comprising an upper surface (11), a lower surface (12), a leading edge (13), a trailing edge (14) and a bath (2). ) at its top, said bath (2) is defined by a flange (2a) and comprises at least one internal rib (3) which is spaced from the flange (2a) defining the bath (2), characterized in that said internal rib (3) is shaped to define inside the bath a cavity (4), within which the passage of leakage flows (5) is limited.
    公开号:FR3027951A1
    申请号:FR1460618
    申请日:2014-11-04
    公开日:2016-05-06
    发明作者:Remi Philippe Oswald Olive；Maesschalck Cis Guy Monique De；Sergio Lavagnoli；Guillermo Paniagua
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to turbomachine turbine blades. It finds particularly advantageous application in the case of high pressure turbines out of the combustion chamber of a turbojet engine. GENERAL TECHNICAL FIELD AND STATE OF THE ART It is conventionally provided between the blades of a turbomachine turbine and the inner face of the ring in which said rotor rotates, a game at the top of the blade which allows the rotation of said rotor. Due to the movement of the rotor and the pressure difference between the intrados and the extrados of the blades, leakage flows are created in the clearance between the top of each blade and the inner face of the ring. These flows, and the vortices they create at the extrados, are the source of numerous aerodynamic and aerothermal problems that directly affect the performance of the turbomachine. The clearance between the top of the blades and the inner surface of the ring is generally adjusted to reduce these flows. Nevertheless, the reduction of this clearance increases the risk of contacts between the blades 20 and the inner surface of the ring and greatly limits the life of the blades; in addition, it also causes an increase in the temperature of the blade tips, which also has an impact on the life of the blades. To overcome this drawback, it is conventionally known to provide baths at the top of the blades, which limits the contact area between the blade and the ring. These baths are generally defined by a rim which delimits a closed contour and which extends for this purpose, at the level of the top of the blade, along the extrados and the intrados, from the leading edge to the edge leak.
    [0002] Bath configurations designed to optimize the aerodynamic and aerothermal performance of the vanes have been proposed. For example, patent application WO2009 / 115728 is known from the applicant, who proposes an exemplary configuration of a blade top comprising a bathtub at its top. The bath comprises a cavity in which is disposed a wall forming a baffle, said wall not being connected to the rim defining the bath.
    [0003] The known solutions in the prior art to date, however, are insufficient in particular given the performance requirements of the new-generation turbojets. GENERAL PRESENTATION OF THE INVENTION A general object of the invention is to increase the aerodynamic and aerothermal performance of turbine blades. In particular, the invention proposes a bathtub structure at the top of the blades which allows an increase in the efficiency of the turbine.
    [0004] It should be noted here that in the case of turbojet engines, an increase in turbine efficiency is directly reflected in the efficiency and the specific consumption of the turbojet engine itself. This is why the proposed solution is advantageously used in the case of turbojet turbine high pressure turbine blades. In particular, according to one aspect, the invention consists of a turbomachine turbine blade comprising an extrados, a lower surface, a leading edge and a trailing edge and thus a bathtub at its top, said bath is defined by a flange and comprises an internal rib which is spaced from the rim defining said tub, characterized in that said internal rib is shaped to define inside the tub a cavity, within which the passage of leakage flows is limited. In another aspect, the internal rib comprises an upper surface, a lower surface, a leading edge and a trailing edge, the intrados of the internal rib being spaced in a substantially constant manner from the underside of the blade, and the upper surface of the inner rib being spaced in a substantially constant manner from the upper surface of the blade. According to a further aspect, the internal rib comprises an upstream extension at its leading edge.
    [0005] According to an additional aspect, the internal rib comprises a downstream extension at its trailing edge. In another aspect, an upstream opening is made in the rim at the leading edge. In a further aspect, the upstream opening is made in the flange on the intrados and on a leading edge end portion of the extrados. According to an additional aspect, a downstream opening is made in the rim at the trailing edge. In another aspect, the downstream opening is made in the flange 20 only on the underside. DESCRIPTION OF THE FIGURES Other characteristics, objects and advantages of the present invention will appear on reading the detailed description which follows, and with reference to the appended drawings, given by way of non-limiting examples and in which: FIG. 1 shows a perspective view of a top of a blade of a mobile wheel on which a bath has been made according to a first embodiment of the invention; FIG. 2 represents a perspective view of an apex of a blade of a mobile wheel on which a bath has been made according to a second embodiment of the invention; FIG. 3 represents a perspective view of an apex of a blade of a mobile wheel on which a bath has been made according to a third embodiment of the invention; FIG. 4 represents a perspective view of an apex of a blade of a mobile wheel on which a bath has been made according to a fourth embodiment of the invention; FIG. 5 represents a view from above of the blade according to the third embodiment of the invention; - Figure 6 shows a top view of the blade according to the fourth embodiment of the invention; FIG. 7 represents a view from above of the blade according to a fifth embodiment of the invention; - Figure 8 shows a top view of the blade according to the fifth embodiment of the invention which specifies the direction of leakage flows relative to the leading edge of the blade; - Figure 9 shows a top view of the blade according to the first embodiment which specifies the structure of the extrados; - Figure 10 shows a view of a turbine on which is represented the axis of said turbine; 11 represents a top view of a blade on which is represented a skeleton line of said blade. turbojet high pressure turbine. In the turbojet, the turbine comprises a disk on which is mounted circumferentially a plurality of blades 1. This disk and the blades are placed inside a ring located downstream of a combustion chamber. The blades of the turbine and the ring are dimensioned so that the clearance between the ring and the blades is limited.
    [0006] Such a blade 1 has an aerodynamic profile and has a convex extrados 11 and a concave intrados 12 which extend one and the other between on the one hand a rounded upstream edge which forms a leading edge 13 and a on the other hand a trailing edge 14. At its top, intended to be facing the inner face of the ring, the blade 1 has a bath 2 defined by a flange 2a which borders a bottom 2b of said bathtub in s' extending along the upper surface 11 and the lower surface 12, from the leading edge 13 to the trailing edge 14 The upper surface 11 comprises a bend 110 which is located near the leading edge 13 of the dawn 1. The upper surface 11 comprises two portions which are separated by the elbow 110: a leading edge portion 111 which is located between the leading edge 13 and the elbow 110; a central portion 112 which is situated after the elbow 110, and which is separated from the leading edge 13 by the leading end portion 111. An internal rib 3 is disposed inside said bath 2, said inner rib 3 being of the same height as the rim 2a. This internal rib 3, as shown in FIGS. 5 and following, is closed on itself and thus forms a cavity 4 inside the bath 2, so as to limit the passage of the leakage flows 5 to the 4. The fact of limiting the passage of most of the leakage flows 5 inside the cavity 4 makes it possible to improve the aerothermal properties of the blade 1 by limiting the heating of the cavity 4. 5. The fact of limiting the heating of the cavity 4 makes it possible to create a relatively cold zone at the top of the blade 1 which serves to cool the entire top of the blade, and thus to increase the life of dawn. The cavity 4 does not communicate with the cooling circuit 10 of the blade, it is indeed a portion of the bottom 2b of the bath 2 which is surrounded by the internal rib 3. Moreover, as shown on each Figures 1 to 7, the inner rib 3 has an aerodynamic shape and thus comprises: - a convex upper surface 31 located in front of the upper surface 11 of the blade 1; A concave intrados 32 situated in front of the intrados 12 of the blade 1; a leading edge 33 situated in front of the leading edge 13 of the blade 1; a trailing edge 34 situated opposite the trailing edge 14 of the blade 1. The upper surface 31 of the internal rib 3 is spaced in a constant manner from the extrados 11 of the blade 1, and the lower surface 32 of the internal rib 3 is also spaced in a constant manner from the underside of the vane 1. Thus, the internal rib 3 has a shape similar to the rim 2a defining the bath 2, and the cavity 4 has a This internal rib 3 makes it possible to recover a portion of the loading force of the leakage flows 5, which come to bear on said internal rib 3. More precisely, the leakage flows 5 come from divide into two distinct streams 51 and 52 at the leading edge 33 of the internal rib 3 (FIGS. 5 to 7), the first stream 51 passing between the extrados 11 of the blade 1 and the extrados 31 of the internal rib 3, and the second stream 52 passing between the intrados 12 of the blade 1 and the intrados 32 of the internal rib 3. During the ur passage, the first stream 51 is pressed on the flange 2a along the upper surface 11 of the blade 1, and the second flow 52 is pressed on the lower surface 31 of the inner rib 3, thus allowing recovery of the 'load effort. This recovery of the loading force of the leakage flows 5 makes it possible to increase the aerodynamic performance of the blade 1. As shown in FIG. 5, the leakage flows 5 have a direction that is substantially perpendicular to a tangent 3 13 According to an alternative embodiment, and as seen in FIGS. 3 to 7, the internal rib 3 may comprise an upstream extension 331 located at the leading edge 33 of the rib. 3, or a downstream extension 341 located at the trailing edge 34 of the inner rib 3. The upstream extension 331 comprises a first end which is connected to the leading edge 33 of the internal rib 3, and a second end. end which is located opposite the leading edge 13 of the blade 1. In a similar manner, the downstream extension 341 comprises a first end which is connected to the trailing edge 34 of the internal rib 3, and a second end 20 end that are t located opposite the trailing edge 14 of the blade 1. When the internal rib 3 comprises an upstream extension 331, the leakage flows 5 divide into two separate streams 51 and 52 at the end of the upstream extension 331 which is located in front of the leading edge 13 of the blade 1. The upstream extension 331 and the downstream extension 341 make it possible to increase the surface of the internal rib 3 on which the second stream 52 presses during its passage through According to an additional embodiment, the internal rib 3 may comprise an upstream extension 331 and a downstream extension 341 simultaneously. The upstream extensions 331 or downstream 341 thus make it possible to improve the aerodynamic performance of the blade 1 by recovering a greater load load.
    [0007] According to another variant embodiment, and as can be seen in FIGS. 2, 4, 6 and 7, the rim 2a of the top of the blade 1 which delimits the bath 2 comprises an upstream opening 131 situated at the edge of the bath. 13, as well as a downstream opening 141 located at the trailing edge 14. The embodiment thus presented comprises an upstream opening 131 and a downstream opening 141, but according to a further variant, the rim 2a may comprise only an upstream opening 131 without downstream opening 141, or a downstream opening 141 without an upstream opening 131. The upstream opening 131 makes it possible on the one hand to limit the mass of the vane 1 at its top, which is important in view of the speed of rotation of the blade 1, and secondly to increase in a controlled manner the amount of leakage flows 5 entering the bath to increase the recovery of the load forces by l 1. Preferably, the upstream opening 131 is performed mainly in the portion of the flange 2a located on the lower surface 11 of the blade 1. More specifically, the upstream opening 131 is formed on the flange 2a located on the leading edge end portion 111 of the extrados 11. Such upstream opening 131 can channel the leakage flows 5 entering through said upstream opening 131 both in the cavity between the intrados 12 of the blade 1 and the intrados 32 of the internal rib 3, and both in the cavity between the extrados 11 of the blade 1 and the extrados 31 of the internal rib 3. With such an upstream opening 131, the leakage flows 5 entering through said upstream opening 131 are mainly channelized in the cavity between the lower surface 12 of the blade 1 and the lower surface 32 of the internal rib 3. Thus, such an upstream opening 131 makes it possible to increase the recovery of the load forces by increasing the flow rate of the second flow 52 , so that leakage flows 5 come to support frontage on the lower surface 32 of the rib 3, and also increasing the flow rate of the first stream 1, so that the leakage flows 5 come to press more on the upper surface 11 of the blade 1. It is preferable that the upstream opening 131 is made in the rim 2a on the lower surface 12 of the blade 1 and on the end portion of the leading edge 111 because, given the angle of incidence of the leakage flows 5 with respect to the leading edge 13 of the blade 1: an upstream opening 131 made solely in the rim 2a on the leading edge end portion 111 of the upper surface 11 of the blade 1, it would be possible to channel the leakage flows 5 only in the cavity between the upper surface 11 of the blade 1 and the upper surface 31 of the internal rib 3; an upstream opening made only in the rim 2a on the intrados 12, would only channel the leakage flows 5 into the cavity between the intrados 12 of the vane 1 and the intrados 32 of the internal rib 3 ; The downstream opening 141 allows on the one hand, in a manner similar to the upstream opening 131, to limit the mass of the blade 1 at its top, and on the other hand to facilitate the evacuation of leakage flows. The good evacuation of the leakage flows 5 thus makes it possible to limit the heating of the bath 2 due to the stagnation of the leakage flows 5 in the bath 2. Preferably, the downstream aperture 141 is made only in the rim 2a on the upper surface 11 or on the lower surface 12 of the vane 1. According to one possible preferential variant, the downstream aperture 141 is formed in the rim 2a on the intrados 12 of the blade 1. Such opening makes it possible to evacuate the leakage flows 5 in an optimal manner and makes it possible to keep an acceptable clearance between the top of the blade 1 and the inner face of the ring in which the blade 1 is rotated. According to a further variant, and as visible in FIGS. 4, 6 and 7, the internal rib 3 comprises an upstream extension 331 or a downstream extension 341, and the rim 2a which defines the bath 2 comprises an upstream opening 131 or an opening downstream 141. Of course, it is possible that the internal rib 3 comprises an upstream extension 331 and a downstream extension 341, and that the rim 2a comprises an upstream opening 131 and a downstream opening 141. In an advantageous manner, the distance between the leading edge 13 of the blade 1 and the leading edge 33 of the internal rib 3 is between 1% and 25% of the axial rope of the blade. The axial chord is the projected of the rope of the blade 1 on the Y axis of the turbine, the Y axis of the turbine being illustrated in FIG. 10. In the case where the internal rib 3 comprises an upstream extension 331 , the distance between the leading edge 13 of the blade 1 and the end of the upstream extension 331is between 1% and 25% of the axial cord of the blade.
    [0008] In addition, preferably, the distance between the trailing edge 14 of the blade 1 and the trailing edge 34 of the internal rib 3 is between 1% and 25% of the axial rope of the blade. In the case where the internal rib 3 comprises a downstream extension 341, the distance between the trailing edge 14 of the blade 1 and the end of the downstream extension 341 is between 1% and 25% of the axial cord of the blade . According to an advantageous variant, the spacing between the extrados 11 of the blade 1 and the upper surface 31 of the internal rib 3 is between 1% and 30% of the maximum thickness E of the blade. The maximum thickness E of the blade is the maximum distance between the lower surface 12 and the upper surface 11 of the blade 1, said maximum distance E being taken orthogonally to the skeleton line S of the blade as illustrated. in Figure 11. The skeleton line S is constituted by the set of equidistant points of the intrados 12 and the extrados 11 of the blade 1. According to a preferred variant, the spacing between the intrados 12 30 of the blade 1 and the underside 32 of the internal rib 3 is between 1% and 30% of the maximum thickness E of the blade.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Turbomachine turbine blade (1) comprising an upper surface (11), a lower surface (12), a leading edge (13), a trailing edge (14) and a bath (2) at its top, said bath (2) is defined by a flange (2a) and comprises an internal rib (3) which is spaced from the flange (2a) defining said bath (2), characterized in that said internal rib (3) is shaped to delimit inside the bath a cavity (4), within which the passage of leak flows (5) is limited.
    [0002]
    2. blade according to claim 1, characterized in that the internal rib (3) comprises an upper surface (31), a lower surface (32), a leading edge (33) and a trailing edge (34); intrados (32) of the inner rib (3) being spaced in a substantially constant manner from the intrados (12) of the blade, and the upper surface (31) of the inner rib (3) being spaced apart by substantially constant manner of the extrados (11) of the blade (1).
    [0003]
    3. blade according to claim 2, characterized in that the internal rib (3) comprises an upstream extension (331) at its leading edge (33).
    [0004]
    4. blade according to claim 2 or 3, characterized in that the internal rib (3) comprises a downstream extension (341) at its trailing edge (34).
    [0005]
    5. blade according to one of the preceding claims, characterized in that an upstream opening (131) is formed in the flange (2a) at the leading edge (13).
    [0006]
    6. blade according to claim 5, characterized in that the upstream opening (131) is formed in the flange (2a) on the intrados (12), and on a leading edge end portion (111). of the extrados (11).
    [0007]
    7. blade according to one of the preceding claims, characterized in that a downstream opening (141) is formed in the flange (2a) at the trailing edge (14).
    [0008]
    8. blade according to claim 7, characterized in that the downstream opening (141) is formed in the flange (2a) only on the intrados (12).
    [0009]
    9. Turbine disk, characterized in that it comprises vanes (1) according to one of the preceding claims.
    [0010]
    10. Turbine high-pressure turbine, characterized in that it comprises vanes (1) according to one of claims 1 to 8.
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    法律状态:
    2015-11-04| PLFP| Fee payment|Year of fee payment: 2 |
    2016-05-06| PLSC| Publication of the preliminary search report|Effective date: 20160506 |
    2016-11-08| PLFP| Fee payment|Year of fee payment: 3 |
    2017-10-20| PLFP| Fee payment|Year of fee payment: 4 |
    2018-10-24| PLFP| Fee payment|Year of fee payment: 5 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 6 |
    2020-04-10| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20200304 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 7 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1460618|2014-11-04|
    FR1460618A|FR3027951B1|2014-11-04|2014-11-04|BATH OF SUMMIT OF DAWN OF A TURBINE OF TURBOMACHINE|FR1460618A| FR3027951B1|2014-11-04|2014-11-04|BATH OF SUMMIT OF DAWN OF A TURBINE OF TURBOMACHINE|
    US15/524,246| US10408076B2|2014-11-04|2015-11-03|Turbine blade having an end cap|
    JP2017524414A| JP6573977B2|2014-11-04|2015-11-03|Turbine blade with end cap|
    RU2017119187A| RU2704504C2|2014-11-04|2015-11-03|Turbine blade with end cover|
    BR112017008587-9A| BR112017008587A2|2014-11-04|2015-11-03|turbomachine turbine blade, turbine disc and turborreator high pressure turbine|
    PCT/FR2015/052954| WO2016071620A1|2014-11-04|2015-11-03|Turbine blade having an end cap|
    CN201580059701.5A| CN107075956B|2014-11-04|2015-11-03|Turbo blade with end cap|
    CA2966688A| CA2966688A1|2014-11-04|2015-11-03|Turbine blade having an end cap|
    EP15797142.5A| EP3215714B1|2014-11-04|2015-11-03|Turbine blade with tip cap|
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