• 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:
    Ring (36) for controlling a variable-pitch blade stage for a turbomachine, comprising at least one support member (40) on the housing and means for fixing it (52, 64) of this member, which comprise a sleeve (64) having an axial bore (66) for passage of said member or a member (52) for supporting said member, a slot (68) passing through said bore and configured to allow a substantially radial deformation of the sleeve , and an external thread (70) for screwing the sleeve into a thread (58) complementary to an orifice (56) of said body, said sleeve being configured so that, when it is screwed, it deforms from a first position wherein said member or support can be mounted and moved in said bore, to a second position in which said sleeve is radially constrained and mounted tightly on said member or support which is thus immobilized with respect to the sleeve.
    公开号:FR3029562A1
    申请号:FR1462120
    申请日:2014-12-09
    公开日:2016-06-10
    发明作者:Jeremy Edynak；Olivier Bazot
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The present invention relates to a ring for controlling a variable-pitch blade stage for a turbomachine. STATE OF THE ART A stage of this type comprises an annular row of variable-pitch stator vanes (also known as VSV), which are carried by an outer annular casing, generally a compressor of the turbine engine. Each blade comprises a blade which is connected at its radially outer end by a platen with a substantially circular contour to a radial cylindrical pivot which defines the axis of rotation of the blade and which is guided in rotation in a corresponding orifice of the outer casing. The radially inner end of the blade of each blade generally comprises a second cylindrical pivot extending along the axis of rotation of the blade and guided in rotation in an orifice of an inner casing of the compressor. The radially outer end of the outer pivot of each vane is connected by a connecting rod to a control ring rotated around the outer casing by cylinder actuating means or the like. The rotation of the control ring is transmitted by the rods to the outer pivots of the blades and rotates about their axes.
    [0002] The angular setting of the stator vanes in a turbomachine is intended to adapt the geometry of the compressor to its operating point and in particular to optimize the efficiency and the pumping margin of this turbomachine and to reduce its fuel consumption in the various flight configurations. .
    [0003] Each of these blades is movable in rotation about its axis between a first "open" or "full opening" position in which each blade extends substantially parallel to the longitudinal axis of the turbomachine, and a second "Close" or "quasi-closing" position in which the blades are inclined relative to the axis of the turbomachine and thus reduce the passage section 5 of air through the blade stage. The control ring must be centered and guided in rotation about its axis of rotation. In the current technique, the outer casing comprises tracks on which the inner periphery of the ring can come into contact by friction. The housing comprises members, such as skids, support and guiding on the tracks. The pads serve, on the one hand, to ensure the concentricity of the ring around the casing by adjusting clearance pads / casing and, secondly, to limit the deformation of the ring generated by the aerodynamic forces on the blades variable pitch acting on the kinematics during operation.
    [0004] It is indeed important to have radial clearances between the pads and the tracks of the casing, to allow thermal expansion of the housing and allow good kinematics of the wedging in all engine configurations. However, it has been found, particularly in the case of single-cylinder actuating means, that depending on the opening and closing ranges 20 of the variable-pitch blades, the cold games cause a misalignment of the ring. control against the housing, which negatively affects the accuracy of the setting. This misalignment consumes the cold games in a heterogeneous manner according to the wedging angle. The pads are attached to the body of the ring by fastening means. It has already been proposed to fix the pads by means of adjustment screws, each adjustment screw passing through a radial orifice of the body of the ring and having a first radially inner threaded end screwed into a tapped hole of a pad and a second end. radially externally threaded screwed into the ring on which is screwed a nut which bears on the body of the ring. The second threaded end has a standard pitch thread while the first threaded end has a metric fine pitch thread which allows fine adjustment of the backlash. This threaded connection is not blocked, there is a clearance between the pad and the adjusting screw. In operation, this presence of clearance causes, under the effect of surrounding vibrations, a relative displacement between the parts 5 leading to the destruction of the threaded connection. Therefore, the function of the pad is no longer assured. In addition, this wear has a direct impact on the blade angle of operating blades can impact the good operability of the engine (pumping in case of large number of worn pads on the same floor).
    [0005] The present invention provides a simple, effective and economical solution to at least some of the aforementioned problems. SUMMARY OF THE INVENTION The invention proposes a control ring of a variable-pitch blade stage for a turbomachine, comprising an annular body intended to extend around a housing, means configured to be connected to pivots of said blades, and means which are configured to cooperate with the casing in order to center and guide said body, and which comprise at least one support member on said casing, which is fixed to the body by fixing means, characterized in that said fixing means comprise at least one bushing which comprises: an axial bore for passing said member or a support member for said member, a through slot opening into said bore and configured to allow a substantially deformation radial bushing, and 25 - an external screw thread of the bushing in a thread complementary to an orifice of said body, said bushing being configured so that, during its screwing e, it cooperates with said body to deform substantially radially from a first position in which said member or support can be mounted and moved in said bore, to a second position in which said sleeve is radially constrained and tightly mounted on said member or support which is thus immobilized vis-à-vis the sleeve. It is thus understood that it is the screwing of the sleeve which ensures the attachment of the support member or its support vis-à-vis the housing. In the loosened or unscrewed position, the bushing is free without constraint and its internal bore has an internal diameter allowing assembly and displacement of the member or the support, and in particular its precise positioning with respect to the housing. In the tightened and tightened position, the bushing is radially constrained and its internal bore has a small internal diameter. The sleeve is thus mounted tightly on the member or the support to immobilize it vis-à-vis the housing in the precise position. This technology has the advantage of limiting the risk of degradation of the ring by limiting the direct transmission of torque therein. The ring according to the invention may comprise one or more of the following characteristics, taken separately from each other or in comparison with each other: said member or support comprises a cylindrical rod engaged axially in said bore, said member comprises at least one bearing pad on the housing, 20 - said pad is integral with said rod, and is for example formed in one piece with said rod, - elastically deformable means are interposed between the pad and the body for urging said pad against said casing, - said elastically deformable means comprise at least one compression spring, for example helical, mounted around said rod, said socket comprises at least a substantially frustoconical portion configured to cooperate with a frustoconical portion of said orifice for mounting the socket of said body, said socket comprises a cylindrical part comprising said external threading and said body comprises means configured to be connected to actuating means for rotation of said body about a casing of the turbomachine. The present invention also relates to a variable valve blade stage for a turbomachine, comprising an annular row of variable pitch vanes each comprising a blade and a cylindrical pivot at its radially outer end, the stage further comprising a housing annular having mounting holes of the blade pivots, characterized in that said pivots are connected by levers 10 to a ring as described above. The present invention also relates to a turbomachine, characterized in that it comprises at least one ring or at least one stage as described above. DESCRIPTION OF THE FIGURES The invention will be better understood and other details, characteristics and advantages of the invention will emerge more clearly on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which: FIG. 1 is a partial schematic half-view in axial section of turbomachine variable-pitch vane stages; FIG. 2 is a partial diagrammatic cross-sectional view of a turbomachine variable valve blade control ring according to the prior art; FIG. 3 is a partial schematic cross-sectional view of a turbomachine variable-pitch blade control ring according to the invention; - Figures 4a and 4b are schematic sectional views along the line IV-IV of Figure 3 and respectively represent two positions of the sleeve of the fastening means according to the invention.
    [0006] DETAILED DESCRIPTION FIG. 1 schematically shows, in axial section, a portion of a high-pressure compressor 10 of a turbomachine, in particular an aircraft turbomachine, with several stages, each stage comprising an annular array of moving blades 12 carried by the rotor (not shown) of the turbomachine and an annular row of fixed blades 14 forming rectifiers carried by a housing 16 of the stator of the turbomachine, the angular orientation of the blades 14 being adjustable to optimize the gas flow in the compressor 10. Each blade 14 comprises a blade 18 and a radially outer cylindrical pivot 20, connected by a disk or "plate" 22 extending perpendicularly to the axis 24 of the dawn in a housing 26 corresponding to the housing 16. The radially inner surface 28 of the disk is aligned with the inner wall 30 of the housing to not oppose the gas flow. The cylindrical pivot 20 of each blade 14 extends inside a cylindrical radial chimney 32 of the casing 16 and its radially outer end is connected by a rod 34 to a control ring 36 which surrounds the casing 16 and which is associated with actuating means (not shown) for rotating it in one direction or the other about the longitudinal axis of the housing 16 to drive the vanes 14 of an annular row rotating about their The vanes 14 are movable in rotation about their axes 24 between a closed or quasi-closed position and an open or fully open position. In the closed position, the blades 18 of the vanes are inclined 25 with respect to the longitudinal axis of the turbomachine and define between them a minimum section of air passage in the vein. The blades 14 are brought into this position when the turbomachine is at low speed or at idle, the flow of air flowing in the compressor then having a minimum value.
    [0007] In the open position, the blades 18 of the blades extend substantially parallel to the axis of the turbomachine so that the air passage section between the blades is maximum. The blades 14 are brought into this position when the turbomachine is at full throttle, the flow of air flowing into the compressor then having a maximum value.
    [0008] In the prior art, the casing 16 comprises at its outer periphery tracks 38 projecting from centering and guiding the rings 36, which are here schematically represented by dashed lines. Each ring 36 surrounds its guide track (s) 38. The reference J denotes the radial clearances that are provided cold between a ring 36 and its track (s) 38. These sets J must be large enough to allow thermal expansion of the casing 16 but do not allow to accurately adjust the angular positions of the blades 14. As best seen in Figure 2, these games J are adjusted via guide pads 40 which are fixed to the body of the ring 36 and which are configured to cooperate by support and sliding with the tracks 38 to ensure the concentricity of the ring around the housing and to limit the deformation of the ring generated by the aerodynamic forces on the blades 14 in operation. In the prior art shown in FIG. 2, each pad 40 is carried by a support member 42 having a rectangular chimney engaged in a radial orifice of the body of the ring 36. The support member 42 is fixed to the body of the ring. ring by means of an adjusting screw 44 which extends substantially radially in the orifice of the body of the ring, and which comprises a first threaded end 46 radially inner screwed into a threaded orifice of the chimney of the ring. support member 42 and a second radially outer threaded end 48 screwed into the ring on which is screwed a nut 50 which bears on the body of the ring 36. The second threaded end has a standard pitch thread while the first threaded end has a metric fine pitch thread which allows a fine adjustment of the clearance J under pad. As this threaded connection 3029562 8 is not locked, there is a clearance between the shoe and the adjusting screw, which is problematic as explained above. The invention overcomes this problem by means of new means for fixing the member or the guide shoe on the body of the ring. Figures 3, 4a and 4b show an embodiment of the invention in which the elements described in the foregoing are referenced by the same figures. The control ring 36 here comprises an annular body, which may be sectored and formed of at least two sectors circumferentially arranged end-to-end and connected to each other. As in the prior art shown in Figures 1 and 2, the body of the ring 36 comprises radial orifices in which are housed cylindrical pins carried by the rods. Each pin is generally centered and guided in rotation in an orifice by at least one bush bearing mounted in the orifice. As described in the foregoing, the body of the ring 36 further comprises actuator connection means, which may comprise, for example, a clevis bearing an axis on which is articulated an end of a piston rod. an actuator, when the latter is a jack for example. The ring 36 further comprises members, such as pads 40, bearing on the housing and in particular on tracks of the housing. In the example shown, each shoe 40 is connected to a cylindrical rod 52 and is formed in one piece with this rod 52. Alternatively, the pad 40 could be carried by a support member, similar to that of the Figure 2. This support member would then be integral with the cylindrical rod 52 and for example be formed in one piece with the latter. The cylindrical rod 52 is substantially smooth throughout its longitudinal extent. It is connected to the pad 40 by its radially inner end and comprises an external thread 54 at its radially outer end. The rod 52 is engaged in a substantially radial orifice 56 of the body of the ring 36, preferably radially from the inside of the ring. A nut 57 is screwed onto the outer thread 54 of the rod 52 to prevent its disengagement from the body of the ring, as will be explained in more detail in the following. In the example shown, the orifice 56 of the body of the ring essentially comprises three axial sections 56a, 56b, 56c, successive. The orifice 56 comprises a first radially external section 56a which has a substantially cylindrical general shape and comprises an internal thread 58. This section 56a opens at its radially external end onto the outer periphery of the ring body. The orifice 56 comprises a second radially inner section 56b which is substantially cylindrical and of smaller diameter than that of the first section 56a. This section 56b opens at its radially inner end on the inner periphery of the body of the ring. The orifice 56 finally comprises a third intermediate section 56c which is substantially frustoconical and extends between the sections 56a, 56b. The diameter of this section decreases radially from the inside to the outside. The radially outer end of larger diameter of the section 56c is connected to the radially inner end of the section 56a and is of substantially the same diameter as the section 56a. The radially inner end of the section 56c has a diameter smaller than that of the section 56a and is connected thereto by an annular shoulder 60 oriented radially inwards. The sections 56a, 56b, 56c are substantially coaxial. As can be seen in FIG. 3, an elastically deformable means, such as a compression spring 62, here helical, is mounted between the body of the ring 36 and the pad 40 so as to urge it towards the casing and allow it to be centered. compared to the latter. The spring 62 is here mounted around the rod 52, coaxially with it, and comprises a radially inner end bearing against a radially outer face 30 of the pad 40, and a radially outer end bearing against the shoulder 60 supra. The spring 62 is here at least partly housed in the section 56b of the orifice 56. As can also be seen in the drawings, the rod 52 has a length or longitudinal dimension greater than the radial dimension or thickness of the body of the 'ring. This length can be measured between the pad 40 and the thread 54, and correspond to the length of the smooth cylindrical portion of the rod. Thus, the rod can move in radial direction vis-à-vis the body of the housing and is locked inward by support 10 of the nut 56 on the body of the housing, and outwardly by support of the pad 40 on this body (the pad 40 having here a transverse dimension greater than that of the orifice). According to the invention, the fixing means of the pad 40 or its support member comprise a socket 64 as shown in FIGS. 3, 4a and 4b. The bushing 64 comprises: - an axial bore 66 for passage of the rod 52, - a through slot 68 opening into the bore 66 and configured to allow a substantially radial deformation of the bushing, and 20 - an external screw thread 70 of the socket in the thread 58 of the section 56a of the orifice 56. The bore 66 has a generally cylindrical shape. It has a diameter D greater than the diameter d of a section of the rod 52 (Figure 4a), when the sleeve 64 is in the free state without stress. The bore 66 extends over the entire longitudinal dimension of the bushing 64 and opens out at the longitudinal ends of the bushing. The slot 68 has an elongated rectilinear shape and extends along the longitudinal axis of the bushing 64. It extends over the entire longitudinal extent of the bushing and over its entire radial thickness, between the bore 66 30 and the outer peripheral surface of the socket.
    [0009] The slot 68 extends between two longitudinal edges 72 opposite the bushing. These edges 72 are separated from each other by a distance L corresponding to the width of the slot 68. In the example shown, the bushing 64 comprises two adjacent sections 64a, 64b, namely a section 64a upper or radially external and a lower section 64b or radially internal. The upper section 64a has a generally cylindrical shape and comprises the external thread 70. The lower section 64b has a generally frustoconical shape whose diameter decreases radially from the outside to the inside and substantially complementary to the section 56c of the orifice 56 of the body of the ring 36. As can be seen in FIGS. 4a and 4b, the sleeve 64 is deformable in the radial direction and may in particular be radially constrained. It is deformable from the unrestrained free position, shown in FIG. 4a, to a stressed position, shown in FIG. 4b, in which the edges 72 have been brought closer to each other and the Bore 66 adopts a diameter corresponding to the diameter d of the rod 52. In the latter position, the sleeve 64 is clamped radially on the rod 52 and immobilizes it radially with respect to the body of the ring. The pad 40 is thus made immobile vis-à-vis the body of the ring. According to the invention, the deformation of the sleeve 64 is obtained by screwing it into the orifice 56 of the casing body, as explained in detail in the following.
    [0010] The sleeve 64 is engaged from the outside in the orifice 56 of the body of the ring and the section 64a of the sleeve is partially screwed into the thread 58 of the orifice 56. The sleeve is then in the position shown in FIG. Figure 4a, that is to say in the free state without constraint. As explained in the foregoing, the rod 52 is engaged radially from within in the orifice 56 of the ring body as well as in the bore 66 of the bushing 64, until its thread 54 is it is located radially outside the sleeve 64 and can receive the nut 57. Previously, the spring 62 is mounted around the rod 52, between the pad 40 and the shoulder 60 of the body of the ring. The ring 36 can then be mounted around the casing of the turbomachine so as to adjust precisely the games J 5 above. These games are imposed by temporary wedges which are interposed between the pads 40 and the tracks of the housing. The mounting of these wedges causes a compression of the spring 62 which urges the pad 40 against the wedge and thus ensures that the clearance J corresponds exactly to the thickness of the shim used. The bushing 64 can then be screwed further and tightened in the orifice 56, so that its section 64b bears against the peripheral wall of the section 56c of the orifice, which results in a radial contraction of the socket 64 and its passage to the position shown in Figure 4b. The bushing 64 is then tightly mounted on the rod 52. The rod 52 and the pad 40 are then immobilized by friction in this position and the shim can be removed. The socket 64 is for example made of metal or composite material. The invention may also be adapted to the pads under the connecting bridges of the sectors of the ring body, preferably so that the upper part of the socket does not protrude from the upper face of the control ring. . The implementation of this invention makes it possible to eliminate the wear of the skids currently observed in the fleet, thus guaranteeing the good operability of the engine.
    [0011] The procedure for adjusting the games under pads is here simplified because it is no longer necessary to adjust the games by screwing and unscrewing the pad. 30
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Ring (36) for controlling a turbine stage (14) with variable pitch for a turbomachine, comprising an annular body intended to extend around a housing, means configured to be connected to pivots of said blades, and means (40) which are configured to cooperate with said housing to center and guide said body, and which include at least one bearing member (40) on the housing, which is secured to the body by securing means (52, 64), characterized in that said fixing means comprise at least one sleeve (64) which comprises: - an axial bore (66) for passage of said member or a member (52) for supporting said member; a through slot (68) opening into said bore and configured to allow a substantially radial deformation of the socket, and - an external thread (70) for screwing the socket into a thread (58) complementary to an orifice (56) of said body, said bushing being configured so that when its screwing, it cooperates with said body to deform substantially radially from a first position in which said member or support can be mounted and moved in said bore, to a second position in which said sleeve is radially constrained and mounted tightly on said organ or support which is thus immobilized vis-à-vis the socket.
    [0002]
    2. Control ring (36) according to claim 1, wherein said member (40) or support comprises a cylindrical rod (52) axially engaged in said bore (66).
    [0003]
    3. control ring (36) according to claim 1 or 2, wherein said member comprises at least one pad (40) bearing on the housing.
    [0004]
    4. control ring (36) according to claim 3, in accordance with claim 2, wherein said pad (40) is integral with said rod (52), and is for example formed integrally with said rod. 3029562 14
    [0005]
    5. Control ring (36) according to claim 3 or 4, wherein means (62) elastically deformable are interposed between the pad (40) and the body to urge said pad against said housing.
    [0006]
    The control ring (36) according to claim 5, wherein said elastically deformable means comprises at least one compression spring (62), for example helical, mounted around said rod (52).
    [0007]
    7. control ring (36) according to one of the preceding claims, wherein said sleeve (64) comprises at least a portion (64b) substantially frustoconical configured to cooperate with a frustoconical portion (56c) of said orifice (56) of mounting the socket of said body.
    [0008]
    The control ring (36) of claim 7, wherein said socket (64) comprises a cylindrical portion (64a) having said external thread (70). 15
    [0009]
    9. Vane stage (14) with variable pitch for a turbomachine, comprising an annular row of vanes (12) with variable pitch each comprising a blade (18) and a cylindrical pivot (20) at its radially outer end, the stage further comprising an annular housing (16) having mounting holes of the blade pivots, characterized in that said pivots are connected by levers to a control ring (36) according to one of the preceding claims.
    [0010]
    10. Turbomachine, characterized in that it comprises at least one control ring (36) according to one of claims 1 to 8 or at least one stage according to claim 9. 25
    类似技术:
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    CN107002504B|2019-04-16|
    JP6662877B2|2020-03-11|
    EP3230602A1|2017-10-18|
    US20190330996A1|2019-10-31|
    RU2017121560A3|2019-06-06|
    CN107002504A|2017-08-01|
    BR112017011842A2|2018-02-27|
    EP3230602B1|2018-11-21|
    US10662805B2|2020-05-26|
    JP2017537263A|2017-12-14|
    US20180266267A1|2018-09-20|
    RU2017121560A|2019-01-11|
    FR3029562B1|2016-12-09|
    CA2969639A1|2016-06-16|
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    US10753231B2|2016-06-09|2020-08-25|General Electric Company|Self-retaining bushing assembly|CN107882599B|2017-11-01|2021-02-09|中国航发湖南动力机械研究所|Integral turbine outer ring connecting structure and turbine engine|
    FR3075233B1|2017-12-15|2020-01-10|Areva Np|DEVICE AND METHOD FOR ANCHORING EQUIPMENT TO A CIVIL ENGINEERING STRUCTURE|
    FR3077851B1|2018-02-09|2020-01-17|Safran Aircraft Engines|CONTROL ASSEMBLY OF A VARIABLE SETTING BLADE STAGE FOR A TURBOMACHINE|
    CN110529432A|2019-08-13|2019-12-03|中国航发贵阳发动机设计研究所|A kind of casing for improving aerial engine fan entry guide vane and adjusting|
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    法律状态:
    2015-12-11| PLFP| Fee payment|Year of fee payment: 2 |
    2016-06-10| PLSC| Publication of the preliminary search report|Effective date: 20160610 |
    2016-12-02| PLFP| Fee payment|Year of fee payment: 3 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 4 |
    2018-06-29| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2018-11-27| PLFP| Fee payment|Year of fee payment: 5 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 6 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-11-18| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1462120A|FR3029562B1|2014-12-09|2014-12-09|CONTROL RING OF A VARIABLE SHIFT AUBRA STAGE FOR A TURBOMACHINE|FR1462120A| FR3029562B1|2014-12-09|2014-12-09|CONTROL RING OF A VARIABLE SHIFT AUBRA STAGE FOR A TURBOMACHINE|
    US15/533,529| US20180266267A1|2014-12-09|2015-11-24|Ring for controlling a stage of variable-setting vanes for a turbine engine|
    BR112017011842-4A| BR112017011842A2|2014-12-09|2015-11-24|variable-adjustment single-stage paddle ring for a turbomachine|
    CA2969639A| CA2969639A1|2014-12-09|2015-11-24|Ring for controlling a stage of variable-setting vanes for a turbine engine|
    PCT/FR2015/053182| WO2016092172A1|2014-12-09|2015-11-24|Ring for controlling a stage of variable-setting vanes for a turbine engine|
    JP2017529995A| JP6662877B2|2014-12-09|2015-11-24|Control ring for variable pitch vane stage of turbine engine|
    CN201580066380.1A| CN107002504B|2014-12-09|2015-11-24|The ring of the grade of the variable setting wheel blade of control for turbogenerator|
    RU2017121560A| RU2705128C2|2014-12-09|2015-11-24|Control ring of stage of blades with variable angle of installation for gas turbine engine|
    EP15817950.7A| EP3230602B1|2014-12-09|2015-11-24|Ring for controlling a stage of variable-setting vanes for a turbine engine|
    US16/445,034| US10662805B2|2014-12-09|2019-06-18|Control ring for a stage of variable-pitch vanes for a turbine engine|
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