• 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:
    Provided is a turbomachine variable pitch angle stator vane guiding device, comprising a plurality of end-to-end inner ring angular sectors for forming an inner ring (26), each inner ring sector. comprising chimneys (24) extending radially across the inner ring sector, a plurality of cylindrical bushings (22) which are each mounted in a chimney of the inner ring from the inside and which are each intended to receive a guide pin (12) of a stator blade (4), a plurality of angular rectifying ring sectors which are placed end to end to form a reconstitution ring (36) and which are radially mounted by the interior on the inner ring, and a plurality of blocking members axially traversing the inner rings and reconstitution to assemble said rings together. The invention also relates to a method of assembling such a device.
    公开号:FR3014152A1
    申请号:FR1361878
    申请日:2013-11-29
    公开日:2015-06-05
    发明作者:Clementine Charlotte Marie Mouton；Olivier Belmonte
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The present invention relates to the general field of turbomachine compressors, in particular an airplane turbojet or turboprop engine. It is more specifically a device for guiding the rectifier vanes variable pitch angle of a compressor stage. The high-pressure compressor of an aviation turbine engine comprises several stages of rectifier blades with variable pitch angle that alternate with stages of moving blades. The stator vanes make it possible to modify the flow characteristics of the gases according to the operating speeds of the turbomachine. The rectifier vanes with variable pitch angle each comprise a control pivot at the head and a guide pivot at the foot, the control pivot passing through a stator housing (called housing) of the turbomachine and cooperating with a control member of the orientation of the blades, and the guide pin being movable in rotation in a sleeve housed in a recess of an inner ring of the turbomachine. From an action on the control member, it is thus possible to change the orientation of the blades of the stage concerned. Reference may be made to documents FR 2,556,410 and FR 2,723,614 which describe various configurations for guiding such rectifiers with variable pitch angle. The compressor housing is usually made of two half-shells to facilitate assembly. To reduce the mass and increase the performance of the whole, it has been proposed to make it in one piece (360 °). However, when the compressor housing is monobloc in the tangential direction, the mounting of the various parts of the compressor is considerably complicated. In particular, the use of a housing in two half-shells makes it possible to individually mount the compressor stator elements which then surround those of the rotor. With a monobloc housing, it is necessary to assemble alternately a rotor stage and then a stator stage. However, in certain compressor configurations, the rotor stage located downstream of the stator stage to be mounted can not be moved downstream because of the slope of the housing. Also, in this case, the only way to insert the stator vanes into their housings would be to move the inner ring as much as possible to the downstream rotor disk. However, this manipulation does not always allow to insert the stator vanes without damaging the vanes. Furthermore, for the design of the rotor line of the compressor, the ferrule line thereof must be as close as possible to the flow line of the gas stream passing therethrough. This has the effect of reducing the space under the vein, which requires decreasing the radial size of the guide device of the stator vanes. OBJECT AND SUMMARY OF THE INVENTION The main object of the present invention is therefore to provide a device for guiding the variable-pitch angle rectifier vanes without such disadvantages. According to the invention, this object is achieved by means of a turbomachine variable pitch angle rectifier blade guide device comprising a plurality of internal ring angular sectors disposed end to end in a circumferential direction to form an inner ring, each inner ring sector comprising chimneys crossing radially from one side of the inner ring sector, a plurality of cylindrical bushings which are each mounted in a chimney of the inner ring from the inside and which are each for receiving a guide pin of a stator blade, a plurality of angular rectifying ring sectors which are abutted in a circumferential direction to form a reconstitution ring and which are radially mounted by the inside the inner ring, and a plurality of blocking elements axially traversing the inner rings and reconstituting for assemble said rings together. The device according to the invention is remarkable in that the assembly of the various elements which constitute it (inner ring sectors, reconstitution ring sectors and bushings) and of the stator vanes is obtained by manipulations which take place entirely in radial directions (from the inside to the outside). In this way, it is possible to avoid any interaction between the rotor and the stator when mounting a stator stage after the assembly of a rotor stage. This device is thus perfectly suited to compressor casings which are monobloc (in the tangential direction). In addition, the radial size of such a device is limited. Preferably, each reconstitution ring sector has a U-shaped cross-section with an inner bottom portion and two radially outwardly extending lateral edges. In this case, the lateral edges of each reconstitution ring sector may each have orifices for the passage of a locking element. Also preferably, the reconstruction ring sectors are mounted on the inner ring so as to cover inter-sector areas of inner ring. Such an overlap of the ring sectors makes it possible to improve the tightness and the rigidity of the assembly. More preferably, each sector of the reconstruction ring has at its tangential ends cutouts for improving the sealing of the assembly. Likewise, again for the purpose of improving the seal, the device may further comprise sealing pads positioned between two adjacent inner ring sectors. Each inner ring sector may have a hole positioned angularly between two adjacent chimneys and axially passing through the inner ring sector from one side to the other for the passage of a locking element. These locking elements may each comprise a screw which is tightened in a crimped nut. The reconstitution ring sectors advantageously each carry on an inner face an abradable coating support intended to cooperate with wipers carried by a rotor. The invention also relates to a turbomachine compressor comprising at least one device as defined above and a turbomachine comprising such a compressor. The invention also relates to a method for assembling a turbomachine variable pitch angle rectifier blade guide device as defined above, the method comprising, successively, the insertion of pivots of control of the stator vanes through a monobloc housing casing, the radial assembly of all the inner ring sectors by inserting the guide pins of the stator vanes into the chimneys of said inner ring sectors, the insertion from the inside of the bushings into the chimneys of the inner ring sectors in order to take up the clearance existing between the chimneys and the guide pivots of the blades to allow the mounting of the inner ring sectors, the radial assembly by the interior of the reconstruction ring sectors on the inner ring sectors, and the insertion of the locking elements on the inner ring sectors and the assembly ring sectors for assembly. er the rings between them. The method may further include positioning sealing pads between two adjacent inner ring sectors. BRIEF DESCRIPTION OF THE DRAWINGS Other features and advantages of the present invention will be apparent from the description given below, with reference to the accompanying drawings which illustrate an exemplary embodiment thereof without any limiting character. In the figures: - Figure 1 is a schematic view of a compressor rectifier stage provided with a blade guide device according to the invention; Figure 2 is a perspective view of an inner ring sector of the guiding device of Figure 1; FIG. 3 is a perspective view of a reconstitution ring sector of the guiding device of FIG. 1; FIG. 4 is a perspective view showing the assembly between them of several inner ring sectors with rectifying ring sectors of the guiding device of FIG. 1; and FIG. 5 is a sectional view along VV of FIG. 4. DETAILED DESCRIPTION OF THE INVENTION FIG. 1 schematically represents a rectifier stage 2 of an aeronautical turbomachine compressor, for example a compressor. high-pressure of a turbojet or a 301 4 1 5 2 5 airplane turboprop. Such a rectifier stage is arranged upstream of a rotor stage (not shown) of the compressor. The rectifier stage 2 comprises a plurality of fixed vanes 4 with variable pitch angle which are arranged in the flow vein 6 of the gas flow passing through the compressor. Each blade 4 with variable pitch angle is in the form of a blade 8 ending at an outer radial end (or blade head) by a control pivot 10 (or upper pivot) and at an inner radial end ( or blade root) by a guide pin 12 (or lower pivot). The control pivot 10 of the blade 4 passes through a casing 14 of the one-piece casing (in the tangential direction) of the turbomachine and cooperates with a control member of the orientation of the blades. For this purpose, the control pivot typically ends with a head 16 on which is engaged one end of a control rod 18 whose other end cooperates with a control ring 20. The control rods 18 and the control ring 20 form the control member of the orientation of the blades 4. The rotation of the control ring around the longitudinal axis of the turbomachine 20 makes it possible to rotate the control rods and thus to simultaneously modify the orientation of all blades with variable pitch angle of the compressor stage. Each guide pin 12 is intended to rotate inside a hollow cylindrical sleeve 22 forming a pivoting support. These bushings 22 are housed in chimneys 24 formed in an inner ring 26 of the turbomachine, the bushing and the corresponding chimney being of substantially complementary shapes. More specifically, in accordance with the invention, the inner ring in which the chimneys 24 are formed is sectored, that is to say that it is in the form of a plurality of angular sectors of internal ring 26a (for example greater than 8, and preferably greater than 12) which are placed end to end in the tangential direction to form a 360 ° ring. Figure 2 shows in perspective an inner ring sector 26a. This comprises an outer face 28 which is intended to delimit inside the flow passage of the gas flow passing through the compressor, and an inner face 30 opposite to the outer face radially. The chimneys 24 (here four in number for the same sector of inner ring) pass radially right through the inner ring sector between its outer and inner faces. Each inner ring sector 26a also comprises a bore 31 which is positioned angularly between two adjacent chimneys and which passes axially through the inner ring sector from one side to the other between an upstream side face 32 and a downstream side face 34 of the main section. internal ring. This bore 31 is intended for the passage of a blocking element described later. Furthermore, the guide device according to the invention comprises a reconstitution ring 36 which is intended to come together radially from the inside on the inner ring 26. For this purpose, the reconstitution ring is sectored, c that is, it is also in the form of a plurality of reconstitution ring angular sectors 36a (for example greater than 8, and preferably greater than 12) which are placed end to end in the tangential sense to form a 360 ° ring. The number of reconstruction ring sectors is chosen such that a reconstruction ring sector overlaps at least two adjacent inner ring sectors 26a (as shown in FIG. 4). Figure 3 is a perspective view of a reconstruction ring sector 36a. This has a U-shaped cross-section with an inner bottom portion 38 and two side edges, namely an upstream side edge 40 and a downstream side edge 42 extending radially outwardly. This U-shaped cross-section makes it possible to radially receive the lateral faces 32, 34 and the inner face 30 of an inner ring sector 26a. As for the bottom 38, it bears on its inner face an abradable coating support 43 intended to co-operate with wipers carried by a rotor (not shown in the figures). The lateral edges 40, 42 of each reconstitution ring sector 36a each have orifices for the passage of a locking element. More specifically, in the example shown in FIG. 3, the upstream lateral edge 40 of each reconstitution ring sector comprises two notches 44 and the downstream lateral edge 42 has two holes 46 for the passage of locking elements. As represented in FIGS. 3 to 5, the blocking elements here each comprise a screw 48 which is tightened in a crimped nut 50, the screw being assembled from upstream to downstream and the nut being crimped in a sector of reconstitution ring 36a. The mounting of the guide device according to the invention is obvious from the foregoing. Once mounted the vanes of the rotor stage located directly downstream of the rectifier stage 2, the control pivots 10 of the vanes 4 are mounted radially from the inside in their housing in the housing casing 14. internal ring sectors 26a are then mounted radially from the inside by positioning the guide pivots 12 of the vanes in the chimneys 24 so as to form the inner ring 26.
    [0002] The sockets 22 are then inserted radially from the inside into the chimneys 24 around the guide pivots 12 of the vanes to take up the existing mounting clearance between the chimneys and the guide pivots of the vanes to allow the mounting of the inner ring sectors. .
    [0003] The reconstruction ring sectors 36a are then assembled on the inner ring sectors 26a by coming to position them radially from the inside on the inner ring sectors. The reconstruction ring sectors are more precisely mounted so as to make angularly coincide the holes 31 made in the inner ring sectors with the notches 44 and holes 46 formed in the reconstruction ring sectors. Furthermore, preferably, as shown in FIG. 4, the reconstitution ring sectors 36a are mounted on the inner ring so as to cover the inter-sector areas of the inner ring so as to improve the sealing of the inner ring. 'together. After mounting the reconstitution ring sectors, the screws 48 are inserted through the holes 31 made in the inner ring sectors and tightened in the nuts 50 previously crimped against the downstream side edge 42 of the reconstitution ring sectors. . The screws make it possible to ensure tangential blocking of the reconstitution ring.
    权利要求:
    Claims (4)
    [0001]
    REVENDICATIONS1. A turbomachine variable pitch angle rectifier blade guide apparatus comprising: a plurality of inner ring angular sectors (26a) abutted in a circumferential direction to form an inner ring (26), each internal ring comprising chimneys (24) radially traversing from one side to the inner ring sector; a plurality of cylindrical bushings (22) which are each mounted in a chimney of the inner ring from the inside and which are each adapted to receive a guide pin (12) of a stator blade (4); a plurality of reconstitution ring angular sectors (36a) which are abutted in a circumferential direction to form a reconstitution ring (36) and which are radially mounted from the inside to the inner ring; and a plurality of blocking members (48, 50) axially traversing the inner and replenishing rings to assemble said rings together. 20
    [0002]
    The device according to claim 1, wherein each reconstitution ring sector (36a) has a U-shaped cross section with an inner bottom portion (38) and two radially extending side edges (40, 42). outwards.
    [0003]
    3. Device according to claim 2, wherein the side edges (40, 42) of each reconstitution ring sector (36a) each have orifices (44, 46) for the passage of a locking element.
    [0004]
    4. Device according to any one of claims 1 to 3, wherein the reconstitution ring sectors (36a) are mounted on the inner ring (26) so as to cover inter-sector areas of inner ring. inserting the locking members (48, 50) on the inner ring sectors and the reconstitution ring sectors to assemble the rings together.
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    法律状态:
    2015-11-16| PLFP| Fee payment|Year of fee payment: 3 |
    2016-11-09| PLFP| Fee payment|Year of fee payment: 4 |
    2017-10-20| PLFP| Fee payment|Year of fee payment: 5 |
    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: 6 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 7 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 8 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1361878A|FR3014152B1|2013-11-29|2013-11-29|TURBOMACHINE VARIABLE CALIBRATION ANGLE RECTIFIER AUB GUIDING DEVICE AND METHOD OF ASSEMBLING SUCH A DEVICE|FR1361878A| FR3014152B1|2013-11-29|2013-11-29|TURBOMACHINE VARIABLE CALIBRATION ANGLE RECTIFIER AUB GUIDING DEVICE AND METHOD OF ASSEMBLING SUCH A DEVICE|
    RU2016125767A| RU2673361C1|2013-11-29|2014-11-19|Device for guiding adjustable stator blades of turbine engine and method of assembling said device|
    US15/100,205| US10280941B2|2013-11-29|2014-11-19|Guide device for variable pitch stator vanes of a turbine engine, and a method of assembling such a device|
    CA2931374A| CA2931374A1|2013-11-29|2014-11-19|Device for guiding synchronizing ring vanes with variable pitch angle of a turbine engine and method for assembling such a device|
    JP2016534994A| JP6523284B2|2013-11-29|2014-11-19|Guide arrangement for a variable pitch stator blade of a turbine engine and method of assembling said arrangement|
    CN201480064424.2A| CN105960510B|2013-11-29|2014-11-19|The guider and its assemble method of the variable pitching stator vane of turbogenerator|
    PCT/FR2014/052958| WO2015079144A1|2013-11-29|2014-11-19|Device for guiding synchronizing ring vanes with variable pitch angle of a turbine engine and method for assembling such a device|
    EP14809494.9A| EP3074609B1|2013-11-29|2014-11-19|Device for guiding synchronizing ring vanes with variable pitch angle of a turbine engine and method for assembling such a device|
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