• 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 for a turbomachine comprising a blade (50). The blade (50) has a leading edge (51), a trailing edge (53), an intrados wall (56) and an extrados wall (58) spaced from one another and connecting the edge of the blade. attack (51) at the trailing edge (53). The blade (50) further comprises at least one internal cavity (55) between the lower surface wall (56) and the upper surface wall (58), into which air (60, 66) is intended to flow. . According to the invention, the blade (50) comprises intersecting transverse partitions (72a, 74a), downstream of the cavity (55), so that air can flow from the cavity (55) towards the trailing edge (53) between the intersecting partitions (72a, 74a).
    公开号:FR3029242A1
    申请号:FR1461673
    申请日:2014-11-28
    公开日:2016-06-03
    发明作者:Stephane Mahias；Olivier Chantoiseau；Laurent Gilles Dezouche
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The invention relates to turbomachine blades. BACKGROUND OF THE INVENTION More specifically, the invention relates to heat exchange at the trailing edge of a turbomachine blade. STATE OF THE PRIOR ART A turbomachine blade comprises a blade. The blade has a leading edge, a trailing edge, a lower surface and an extrados wall spaced from each other and connecting the leading edge to the trailing edge. In known manner, the blade further comprises an internal cavity. The blades at the inlet of a compressor are in contact with particularly cold air. The cavity is traversed by air from the compressor, so as to heat the blade to prevent icing of the blade.
    [0002] However, a compressor inlet straightener vane, also a compressor inlet guide wheel vane, has a blade of particularly thin thickness especially with regard to the thickness of a turbine vane blade. This low thickness penalizes heat exchange inside the blade, especially those near the trailing edge. The compressor inlet straightener vanes are also generally more radially extended than the turbine blades. There is therefore a need to improve the heat exchange inside a turbomachine blade, while limiting the increase in the thickness of the blade of the blade. SUMMARY OF THE INVENTION at least partially solve the problems encountered in the solutions of the prior art. In this regard, the invention relates to a turbomachine blade. Dawn includes a blade. The blade includes a leading edge, a trailing edge, an intrados wall and an extrados wall spaced from each other and connecting the leading edge to the trailing edge. The blade further comprises at least one internal cavity between the intrados wall and the extrados wall, in which air is intended to circulate. According to the invention, the blade comprises intersecting transverse partitions, in an inter-crisscrossing internal volume arranged between the intrados wall and the extrados wall downstream of the cavity, so that air can circulate. from the cavity towards the trailing edge between the intersecting partitions. The intersecting transverse bulkheads allow the air circulating in the blade to cool or reheat the inside of the blade more efficiently, while limiting the increase in the thickness of the blade. In particular, intersecting transverse partitions improve the heat exchange between the air and the walls of the blade near the trailing edge. The blade is preferably a blade at the compressor inlet, the thickness of which, measured between the intrados wall and the extrados wall, is particularly small. In this case, the transverse partitions further limit the increase in the thickness of the blade, while simultaneously providing a suitable strength of the blade, and effective heating of the blade by the air flowing between the intersecting partitions.
    [0003] The air circulating in the blade comes in particular from a compressor for a turbomachine. The invention may optionally include one or more of the following features combined with one another or not. Advantageously, the intersecting transverse partitions extend to the trailing edge formed in part by the intersecting transverse partitions, so that air can circulate between the transverse partitions intersecting across the trailing edge. In this configuration, the trailing edge is formed in part by intersecting transverse partitions, which promotes all the better the heat exchange at the trailing edge. According to an advantageous embodiment, the intersecting transverse partitions are spaced apart from one another along the span direction of the blade. This spacing is for example regular in the direction of span of the blade. The air circulating in the blade preferably opens at the trailing edge with a direction substantially parallel to that of the air flowing along the intrados wall and the extrados wall, or substantially perpendicular to the trailing edge. According to another advantageous embodiment, the intersecting transverse partitions extend over at least the majority of the extent of the cavity in the span direction. This span direction is the radial direction of the blade. The intersecting transverse partitions preferably extend over substantially the entire extent of the trailing edge in the span direction of the blade. According to a particular embodiment, at least one of the intersecting transverse partitions extends from the intrados wall to the extrados wall. Preferably, the blade comprises an attachment portion, external or internal, delimiting an air inlet opening into the cavity. The intersecting transverse partitions preferably determine rows of cells whose longitudinal axes are both substantially parallel to a longitudinal direction of the blade and transverse to the air inlet. The axes of the cells are in particular substantially orthogonal to the air inlet. According to another embodiment, the intersecting transverse partitions form a regular mesh.
    [0004] This regular mesh preferably comprises a central row of cells of quadrilateral section. Two lateral rows of cells of triangular section are in particular arranged on either side of this central row.
    [0005] Alternatively, the cells can take other simple polygonal shapes, for example a regular hexagonal section. Moreover, it is possible that the cells are arranged in only two rows or in more than three rows. The intersecting transverse partitions are preferably inclined both with respect to the intrados wall and the extrados wall.
    [0006] Advantageously, all the transverse partitions are intersecting, so as to form braces. The invention also relates to a turbomachine compressor comprising at least one blade as defined above, the blade being an inlet straightener blade of the compressor.
    [0007] The invention further relates to a turbomachine comprising a compressor as defined above. The turbomachine is preferably a turboprop. Finally, the invention relates to a method of manufacturing a blade as defined above. The method comprises a step of manufacturing transverse partitions intersected by laser melting of metal powder. BRIEF DESCRIPTION OF THE DRAWINGS The present invention will be better understood on reading the description of exemplary embodiments, given purely by way of indication and in no way limiting, with reference to the appended drawings in which: FIG. 1 represents a diagrammatic sectional view longitudinal of a turboprop, according to a preferred embodiment of the invention; FIG. 2 is a diagrammatic representation, in side view, of an inlet stator blade of the compressor of the turbomachine shown in FIG. 1; FIG. 3 is a partial diagrammatic view of the blade of the blade shown in FIG. 2. DETAILED DESCRIPTION OF PARTICULAR EMBODIMENTS Identical, similar or equivalent parts of the different figures bear the same numerical references in order to facilitate the passage of FIG. one figure to another. FIG. 1 represents a turboprop 1 determining a power turbine axis 3. The turbomachine 1 comprises, from upstream to downstream, considering a path in the direction of the axis 3, a propeller 10, a gearbox 12, radial casing arms 4, for example four in number, a compressor 6, a combustion chamber 7, a high-pressure turbine 8 and a power turbine 9. The compressor 6, the combustion chamber 7, the high-pressure turbine 8 and the power turbine 9 are surrounded by a housing 5. They define in common with the housing 5 a primary vein 13 traversed by a primary flow flowing in the direction from upstream to downstream, represented by the arrow 11. This direction 11 also corresponds to the thrust force of the turbomachine in operation. The thrust of the gases at the outlet of the combustion chamber 7 drives the compressor 6 and the turbines 8 and 9 in rotation about the axis 3 of the power turbine. The rotation of the power turbine 9 about its axis 3 is transmitted to the propeller 10 via the gear 12, so as to rotate the propeller 10. The air flow stirred by the propeller is considered here as a secondary flow which determines for the vast majority of the propulsive energy of the turbomachine.
    [0008] The blades 40 are compressor inlet straightener blades 40 situated at the inlet of the compressor 6. They are fixed and serve to redirect the flow of air supplying the primary stream 13 in the axis 3 of the turbomachine 1. Referring to Figures 2 and 3, the blade 40 comprises a blade 50 extending radially in a span direction 43. The blade 50 comprises a leading edge 51 and a trailing edge 53. The leading edge 51 is connected to the trailing edge 53 by an intrados wall 56 and an extrados wall 58 spaced from one another. The compressor inlet straightener blade 50 has a height h (FIG. 2), that is to say the extent of the blade in the span direction, for example between 90 and 100 millimeters. The dawn rope, measured from the leading edge 51 to the trailing edge 53, is about 45 millimeters. Thus, the rope roughly corresponds to half the height of the dawn. The thickness of the intrados wall 56 or the extrados wall 58 near the leading edge 51 is in particular between 1 and 1.3 millimeters.
    [0009] The maximum thickness of the blade 50 between the trailing edge 51 and the leading edge 53 is about 6 millimeters, about fifteen times less than the height of the blade and about seven to eight times less than the rope of dawn. The blade 40 therefore has a particularly thin thickness, which implies significant constraints in terms of mechanical strength of the blade 40 and air circulation inside the blade 50, to heat it. The blade 40 is a fixed blade comprising an outer hooking portion 42 and an inner hooking portion 44 opposite to the outer hooking portion 42. The inner hooking portions 44 and outer 42 are located on both sides. other of the blade 50 along the span direction 43.
    [0010] The blade 40 is hooked to an outer casing (not shown) via the outer latching portion 42. The inner latching portion 44 is mechanically connected to an inner casing (not shown). In known manner, the blade 40 can in particular pivot around the outer hooking portion 42 relative to the outer casing, and around the inner hooking portion 44 relative to the inner casing.
    [0011] The blade 50 comprises an upstream portion 52 extending from the leading edge 51 and towards the downstream. In addition, the blade 50 has a downstream portion 54 extending downstream of the upstream portion 52. The upstream portion 52 comprises an internal cavity 55 into which an air inlet 42A delimited by the external hooking portion 42 opens. The air inlet 42A is delimited by the outer hooking portion 42. Air is intended to circulate in this cavity 55 via the air inlet 42A. The air is in particular hot air conveyed from the compressor 6 downstream of the vane 40. The internal cavity 55 extends between the intrados wall 56 and the extrados wall 58, and preferably constitutes the only cavity inside the blade 50. The cavity 55 is extended downstream of the blade by an internal crisscrossing volume 70 comprising a plurality of intersecting transverse partitions 72a, 74a between which air is intended to circulate. These intersecting transverse partitions 72a, 74a are inclined both with respect to the intrados wall 56 and the extrados wall 58, for the benefit of the mechanical reinforcement and the vibratory and acoustic behavior of these walls. These intersecting transverse partitions 72a, 74a are in correspondence of the downstream portion 54 of the blade. The internal crisscrossing volume 70 extends over an extension 75 along the span direction 43 equal to at least the majority of the extent h of the cavity 55 in the span direction 43, that is, ie the height h of dawn. Each of the intersecting partitions 72a, 74a extends inside the blade 50 from the inner surface of the intrados wall 56 to the inner surface of the suction wall 58. In the illustrated embodiment, the partitions transverse interspaces 72a, 74a extend to the trailing edge 53, i.e. the trailing edge 53 is formed in part by the intersecting transverse partitions 72a, 74a. As a result, air flows through the trailing edge. When the intersecting transverse partitions 72a, 74a also extend over the entire height h of the blade, it is the entire downstream portion 54 which delimits the internal interlacing volume 70.
    [0012] These intersecting partitions 72a, 74a comprise side walls 72a spaced apart from one another along the span direction 43, so as to form a first set of inclined partitions 72 with respect to the span direction 43. The first partitions 72a are parallel to each other.
    [0013] The intersecting transverse partitions 72a, 74a comprise a second set of partitions 74 formed of transverse partitions 74a inclined relative to the span direction 43 in the other direction relative to the partitions 72a of the first set of partitions 72. The second partitions 74a intersect with the first partitions 72a between the intrados wall 56 and the extrados wall 58. The second partitions 74a are parallel to each other and spaced from each other along the span direction 43. transverse partitions 72a, 74a are intertwined to form braces. In particular, the angle formed by two intersecting partitions 72a, 74a is substantially equal to 900. It is in particular between 1200 and 30 °. It is preferably between 85 ° and 95 °. The intersecting transverse partitions 72a, 74a form a regular mesh. This regular mesh comprises a central row of cavities 76 of quadrilateral section. Two lateral rows of cells 77, 78 of triangular section are arranged on either side of the central row. The longitudinal axes 73 of the cells 76 are substantially perpendicular to the span direction 43. The axes 73 are also substantially parallel to the longitudinal direction 57 of the blade 50. This longitudinal blade direction here corresponds substantially to that commonly called "line of skeleton "in the aeronautics industry, this skeleton line being between the leading edge and the trailing edge, equidistant between the intrados and extrados. More generally, the cells 76 extend in rows along the span direction 43. The longitudinal axes 73 of the cells 76 are also oriented along the skeleton line, so that the air passing through the partitions 72a, 74a opens into the primary stream 13 with a direction substantially parallel to that of the air which has bypassed the blade 40. The flow in the primary vein 13 is then all the less disturbed as the air discharged by the intersecting transverse bulkheads 72a, 74a at the trailing edge 53 and the air, at the trailing edge 53, which has circumvented the blade 40 have the same direction of flow.
    [0014] The outside of the blade 50 is in contact with particularly cold air arriving in the primary stream 13, upstream of the compressor. As a result, the blade 50 is heated by hot air introduced by the air inlet 42A along the arrow 60, circulating in the internal cavity 55 of the blade according to the arrows 62 and 64, then between the transverse partitions. intersecting 72a, 74a in the longitudinal direction 73 of the cells, before being evacuated at the trailing edge 53 in the direction of the arrow 66. The manufacturing process of the blade 40 comprises a step of manufacturing cross partitions intersecting 72a, 74a by melting laser metal powder. In general, the blade 40 is manufactured by additive manufacturing. The blade 40 shown in FIGS. 2 and 3 is a very fine compressor inlet straightener blade. In this respect, the greatest thickness 49 of the blade 50 is approximately 4.5 to 6 times greater than the thickness 59 of the pressure wall 56 or of the extrados wall 58. Moreover, the average thickness 61 of the blade at the trailing edge 53 is approximately equal to twice the average thickness 59 of the intrados or extrados wall along the longitudinal direction 57 of the blade.
    [0015] In this preferred configuration, the intersecting transverse partitions 72a, 74a confer both better heat exchange inside the blade 50, compatibility with the mechanical strength constraints of the blade 50, and compatibility with a small thickness of the blade 50, especially at the trailing edge 53.
    [0016] According to an alternative embodiment (not shown), the blade is a turbine wheel blade or a turbine nozzle blade. The constraints of small thickness of the trailing edge 53 are then less strong. When the blade is a turbine blade, the intersecting transverse bulkheads 72a, 74a serve to allow the cooling air to flow from the cavity 55 into the internal interlacing volume 70 towards the trailing edge 53. When the blade 40 is a turbine wheel blade, the blade 50 is carried by a foot and the cavity is supplied with air from the foot. The foot replaces the internal hooking portion 42 shown in Figure 2 and the outer hook portion 44 shown in this figure is replaced by the top of the blade.
    [0017] It is also conceivable that at least a portion of the air inside the blade 50 is discharged upstream of the trailing edge 53, for example through cooling outlet slots between sections of the interlacing walls. . Of course, various modifications may be made by those skilled in the art to the invention which has just been described without departing from the scope of the disclosure of the invention.
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. A turbomachine blade (40), comprising: a blade (50) comprising a leading edge (51) and a trailing edge (53), the blade (50) comprising a lower surface (56) and an upper surface (58); ) spaced from each other and connecting the leading edge (51) to the trailing edge (53), at least one inner cavity (55) between the intrados wall (56) and the upper surface (58), in which air (60, 62, 64, 66) is intended to circulate, in particular air coming from a compressor (6) for a turbomachine, characterized in that the blade (50) comprises intersecting transverse partitions (72a, 74a) in an intersecting internal volume (70) arranged between the intrados wall (56) and the extrados wall downstream of the cavity (55), so that that air can flow from the cavity (55) towards the trailing edge (53) between the intersecting partitions (72a, 74a).
    [0002]
    2. A turbomachine blade (40) according to the preceding claim, wherein the intersecting transverse partitions (72a, 74a) extend to the trailing edge (53) formed in part by the intersecting transverse partitions (72a, 74a), so that air can flow through the trailing edge (53).
    [0003]
    A turbomachine blade (40) according to any one of the preceding claims, wherein the intersecting transverse bulkheads (72a, 74a) are spaced from each other along the span direction (43) of the blade.
    [0004]
    4. A turbomachine blade (40) according to any one of the preceding claims, wherein the intersecting transverse partitions (72a, 74a) extend over at least the majority of the extent of the cavity (55) in the direction d span (43).
    [0005]
    A turbomachine blade (40) according to any one of the preceding claims, wherein at least one of the intersecting transverse bulkheads (72a, 74a) extends from the intrados wall (56) to the wall of extrados (58).
    [0006]
    6. blade (40) of a turbomachine according to any one of the preceding claims, wherein the blade comprises an attachment portion, external (42) or internal (44), delimiting an air inlet (42A) opening into the cavity (55), and in which the intersecting transverse partitions (72a, 74a) determine rows of cells (76, 77, 78) whose longitudinal axes (73) are both substantially parallel to a longitudinal direction of the and transverse to the air inlet (42A).
    [0007]
    7. A turbomachine blade (40) according to any one of the preceding claims, wherein the intersecting transverse partitions (72a, 74a) form a regular mesh, the regular mesh preferably comprising a central row of cells (76) of section in the form of a quadrilateral, on either side of which are arranged two lateral rows of cavities (77, 78) of triangular section.
    [0008]
    A turbomachine blade (40) according to any one of the preceding claims, wherein the intersecting transverse partitions (72a, 74a) are inclined both with respect to the intrados wall (56) and the wall of extrados (58).
    [0009]
    9. A turbomachine compressor (6) comprising at least one blade (40) according to any one of the preceding claims, the blade (40) being a compressor inlet straightener blade.
    [0010]
    10. Turbomachine (1) comprising a compressor (6) according to the preceding claim.
    [0011]
    11. A method of manufacturing a blade (40) according to any one of claims 1 to 8, comprising a step of manufacturing intersecting transverse partitions (72a, 74a) by melting metal powder laser.
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    同族专利:
    公开号 | 公开日
    US20160153467A1|2016-06-02|
    FR3029242B1|2016-12-30|
    US10337527B2|2019-07-02|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
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    US5370499A|1992-02-03|1994-12-06|General Electric Company|Film cooling of turbine airfoil wall using mesh cooling hole arrangement|
    US20120201653A1|2010-12-30|2012-08-09|Corina Moga|Gas turbine engine and cooled flowpath component therefor|
    SE526847C2|2004-02-27|2005-11-08|Demag Delaval Ind Turbomachine|A component comprising a guide rail or a rotor blade for a gas turbine|
    FR2948736B1|2009-07-31|2011-09-23|Snecma|EXTERNAL VIROLE SECTOR FOR AIRBORNE TURBOMACHINE AIRBORNE STATOR CROWN, COMPRISING SHOCK ABSORBING MOUNTS|
    US8894363B2|2011-02-09|2014-11-25|Siemens Energy, Inc.|Cooling module design and method for cooling components of a gas turbine system|FR3032173B1|2015-01-29|2018-07-27|Safran Aircraft Engines|Blower blade of a blowing machine|
    FR3056630B1|2016-09-26|2018-12-07|Safran Aircraft Engines|FLOW MONOBLOC BLOWER DISK FOR AIRCRAFT TURBOMACHINE|
    DE102017207028A1|2017-04-26|2018-10-31|MTU Aero Engines AG|SHEET SHEET FOR A FLOW MACHINE|
    US10844728B2|2019-04-17|2020-11-24|General Electric Company|Turbine engine airfoil with a trailing edge|
    法律状态:
    2015-11-13| PLFP| Fee payment|Year of fee payment: 2 |
    2016-06-03| PLSC| Publication of the preliminary search report|Effective date: 20160603 |
    2016-11-09| PLFP| Fee payment|Year of fee payment: 3 |
    2017-10-20| PLFP| Fee payment|Year of fee payment: 4 |
    2017-11-10| CD| Change of name or company name|Owner name: SNECMA, FR Effective date: 20170713 |
    2018-10-24| PLFP| Fee payment|Year of fee payment: 5 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 6 |
    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
    FR1461673A|FR3029242B1|2014-11-28|2014-11-28|TURBOMACHINE TURBINE, COMPRISING INTERCROSSED PARTITIONS FOR AIR CIRCULATION IN DIRECTION OF THE LEAK EDGE|FR1461673A| FR3029242B1|2014-11-28|2014-11-28|TURBOMACHINE TURBINE, COMPRISING INTERCROSSED PARTITIONS FOR AIR CIRCULATION IN DIRECTION OF THE LEAK EDGE|
    US14/948,648| US10337527B2|2014-11-28|2015-11-23|Turbomachine blade, comprising intersecting partitions for circulation of air in the direction of the trailing edge|
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