A positioning and mounting device for turbine shroud and turbine disk of an aero-engine

Abstract

The application relates to the technical field of turbine disc guide vane assembly of an aero-engine, and discloses a positioning and mounting device for turbine disc guide vanes and turbine discs of an aero-engine. Through the positioning and mounting device, the installation operation of the turbine disc guide vanes and the turbine discs can be simplified, the positioning and mounting efficiency, precision and stability of the turbine disc guide vanes and the turbine discs of the aero-engine can be improved, the installation difficulty and cost can be reduced, and the assembly quality can be guaranteed.

Description

Technical Field

[0001] This invention relates to the field of aero-engine turbine guide vane assembly technology, and discloses a positioning and installation device for aero-engine turbine guide vanes and turbine disks. Background Technology

[0002] The working impeller of an aero-engine turbine rotor consists of a turbine disk, a turbine guide disk, turbine blades, and turbine blade locking plates. The annular turbine guide disk is connected to the turbine disk by an interference fit between the outer groove and the tooth of the turbine disk, and is fixed by fasteners on the inner side. The turbine guide disk needs to be axially pressed and limited, and then rotated circumferentially at a certain angle to achieve installation and removal relative to the turbine disk. The cold air guide cavity formed between the two plays a key role when the turbine rotor is working, realizing the airflow guidance for cooling the turbine blades, ensuring the normal operation of the turbine rotor, and affecting the overall operating condition of the engine.

[0003] The annular turbine guide plate is connected by an interference fit between the outer groove and the turbine disk teeth, and by fasteners on the inner side, which is essentially an interference fit connection between the two. In existing technology, during turbine guide plate installation and disassembly, the turbine disk is first supported and circumferentially fixed to the base. Then, a pressure tool is used to limit and circumferentially connect the turbine guide plate end face, ensuring contact between the turbine guide plate and the turbine disk end face. Installation and disassembly are achieved by manually striking the pressure tool with a hammer to rotate the turbine guide plate relative to the turbine disk circumferentially by a certain angle. The relative angle (i.e., circumferential position) between the turbine guide plate and the turbine disk is confirmed by manual marking. Because the mating position is a blind spot, installation and disassembly cannot be completed in one step. This results in problems such as needing to remove the pressure tool multiple times for inspection and confirmation, and the risk of bumps from manual striking. Assembly quality cannot be effectively guaranteed, and efficiency and stability are poor. Summary of the Invention

[0004] The purpose of this invention is to provide a positioning and installation device for turbine guide vanes and turbine disks in aero engines, which can simplify assembly operations, improve the efficiency and stability of turbine guide vane installation and disassembly, and ensure assembly quality.

[0005] To achieve the above-mentioned technical effects, the technical solution adopted by the present invention is as follows: A positioning and mounting device for a turbine guide vane and turbine disk of an aircraft engine, wherein the turbine guide vane is fastened to the turbine disk, comprising: The base structure includes a worktable, a hollow drive shaft, and a drive device; the drive device is fixed below the worktable; the lower end of the hollow drive shaft is connected to the drive device, and the upper end passes through the worktable and extends above the worktable. A stator structure is fixed on the worktable and has a first end tooth that engages with a protrusion on the end face of the turbine disk. The stator structure is used to support the turbine disk and provide circumferential stop. The rotor structure is connected to the hollow drive shaft and is fastened to the turbine guide plate. The rotor structure is provided with a second arc-shaped end tooth and an observation hole. The second arc-shaped end tooth is inserted into the arc-shaped notch of the turbine guide plate to drive the turbine guide plate to rotate with the hollow drive shaft. The observation hole is used to observe whether the mating holes between the turbine guide plate and the turbine plate are aligned. An axial limiting structure is provided, the axial limiting device including an axial limiting screw and a locking mechanism; one end of the axial limiting screw is fixed below the worktable, and the other end passes through the hollow transmission shaft and extends to the top of the rotor structure; the locking mechanism is rotatably connected to the rotor structure and fixed to the axial limiting screw.

[0006] Furthermore, the workbench is provided with mounting holes, and the walls of the mounting holes are provided with a plurality of slots along the radial direction; The stator structure includes a support ring fixed to the workbench, the lower end of the support ring is provided with a plurality of third end teeth, the third end teeth are inserted into the slot; the support ring is also provided with a plurality of fourth end teeth along the circumferential direction of the outer wall.

[0007] Furthermore, the stator structure also includes an anti-rotation ring, the lower end of which is provided with a plurality of fifth end teeth. The anti-rotation ring covers the outside of the support ring, and the fifth end teeth mesh with the fourth end teeth. The first end teeth are provided at the upper end of the anti-rotation ring, and the upper end of the anti-rotation ring abuts against the end face of the turbine disk.

[0008] Furthermore, the upper end face of the hollow drive shaft is provided with several third end teeth; The rotor structure includes a rotating disk with a through hole at its center. Several sixth end teeth are provided radially on the wall of the through hole. The rotating disk is sleeved on the upper end of the hollow transmission shaft, and the sixth end teeth mesh with the third end teeth. The second arc-shaped end teeth are arranged axially on the lower end face of the rotating disk.

[0009] Furthermore, the lower end face of the rotating disk is provided with an axial positioning ring along the axial direction. The axial positioning ring is located on the outer ring of the second arc-shaped end tooth and abuts against the upper end face of the turbine guide disk.

[0010] Furthermore, the observation hole is disposed on the rotating disk.

[0011] Furthermore, the rotor structure also includes a pressure ring, which is fixed to the upper end face of the rotating disk and is rotatably connected to the locking mechanism via a bearing.

[0012] Furthermore, the locking mechanism includes an open washer and a locking nut, the locking nut being connected to the axial limiting screw and pressing the bearing on the pressure ring with the open washer.

[0013] Furthermore, the driving device is a hand-cranked reducer, and the output shaft of the hand-cranked reducer is connected to the lower end of the hollow transmission shaft.

[0014] Compared with the prior art, the beneficial effects of this invention are: This invention utilizes the engagement of the first end tooth of the stator structure with the protrusion on the turbine disk's end face to support and circumferentially stop the turbine disk, ensuring it remains fixed and does not rotate circumferentially during installation. Simultaneously, a drive device rotates the hollow drive shaft, which in turn drives the rotor structure. The rotor structure engages with the arc-shaped notch of the turbine guide disk via the second arc-shaped end tooth, driving the turbine guide disk to rotate along with the hollow drive shaft, thus adjusting the relative angle between the turbine guide disk and the turbine disk. An axial limiting structure, using an axial limiting screw and locking mechanism, limits the axial movement of the rotor structure and turbine guide disk, preventing axial movement during installation and ensuring accuracy and stability. Furthermore, during rotation, the operator can observe the alignment of the mating holes between the guide disk and the turbine disk through an observation hole on the rotor structure; any misalignment can be adjusted promptly. The present invention, through the positioning and installation device, simplifies the installation operation of turbine guide vanes and turbine disks, improves the positioning and installation efficiency, accuracy and stability of aero-engine turbine guide vanes and turbine disks, reduces installation difficulty and cost, and ensures assembly quality. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the positioning and mounting device for the turbine guide vane and turbine disk of an aero-engine, as shown in the embodiment. Figure 2 This is a schematic diagram of the base structure in the embodiment; Figure 3 This is a schematic diagram of the workbench structure in the embodiment; Figure 4 This is a schematic diagram of the hollow drive shaft in the embodiment; Figure 5 This is a schematic diagram of the support ring structure in the embodiment; Figure 6 This is a cross-sectional view of the support ring in the embodiment; Figure 7 This is a cross-sectional view of the anti-rotation ring in the embodiment; Figure 8 This is a schematic diagram of the rotating disk in the embodiment; Figure 9 This is a cross-sectional view of the rotating disk in the embodiment; Figure 10 This is a cross-sectional view of the pressure ring in the embodiment; Figure 11 This is a schematic diagram of the cover plate in the embodiment; Figure 12 This is a schematic diagram of the structure of the open washer in the embodiment; Among them, 11-base, 12-drive device, 13-worktable, 131-mounting hole, 132-slot, 14-hollow drive shaft, 141-seventh end tooth, 21-support ring, 211-third end tooth, 212-fourth end tooth, 22-anti-rotation ring, 221-fifth end tooth, 222-first end tooth, 31-rotating disk, 311-sixth end tooth, 312-axial positioning ring, 313-observation hole, 314-second arc-shaped end tooth, 32-pressure ring, 33-cover plate, 41-axial limiting screw, 42-open washer, 43-locking nut, 51-turbine guide plate, 52-turbine disk. Detailed Implementation

[0016] The present invention will now be described in further detail with reference to the embodiments and accompanying drawings. However, this should not be construed as limiting the scope of the above-described subject matter of the present invention to the following embodiments; all technologies implemented based on the content of the present invention fall within the scope of the present invention.

[0017] See Figures 1 to 12 This invention provides a positioning and mounting device for a turbine guide vane and a turbine disk of an aircraft engine, wherein the turbine guide vane 51 is fastened to the turbine disk 52, comprising: The base structure includes a worktable 13, a hollow drive shaft 14, and a drive device 12; the drive device 12 is fixed below the worktable 13; the lower end of the hollow drive shaft 14 is connected to the drive device 12, and the upper end passes through the worktable 13 and extends above the worktable 13. The stator structure is fixed on the worktable 13 and has a first end tooth 222. The first end tooth 222 engages with the end face protrusion of the turbine disk 52. The stator structure is used to support the turbine disk 52 and stop its circumferential movement. The rotor structure is connected to the hollow drive shaft 14 and is fastened to the turbine guide plate 51. The rotor structure is provided with a second arc-shaped end tooth 314 and an observation hole 313. The second arc-shaped end tooth 314 is inserted into the arc-shaped notch of the turbine guide plate 51 to drive the turbine guide plate 51 to rotate with the hollow drive shaft 14. The observation hole 313 is used to observe whether the mating holes between the guide plate and the turbine plate 52 are aligned. An axial limiting structure is provided, the axial limiting device including an axial limiting screw 41 and a locking mechanism; one end of the axial limiting screw 41 is fixed below the worktable 13, and the other end passes through the hollow transmission shaft 14 and extends to the top of the rotor structure; the locking mechanism is rotatably connected to the rotor structure and fixed to the axial limiting screw 41.

[0018] This invention utilizes the first end tooth 222 of the stator structure to engage with the protrusion on the end face of the turbine disk 52, providing support and circumferential stop for the turbine disk 52, ensuring that the turbine disk 52 remains fixed and does not rotate circumferentially during installation. Simultaneously, the drive device 12 drives the hollow drive shaft 14 to rotate, which in turn drives the rotor structure to rotate. The rotor structure, through the second arc-shaped end tooth 314, engages with the arc-shaped notch of the turbine guide disk 51, driving the turbine guide disk 51 to rotate together with the hollow drive shaft 14, thus adjusting the relative angle between the turbine guide disk 51 and the turbine disk 52. The axial limiting structure, through the axial limiting screw 41 and locking mechanism, limits the rotor structure and turbine guide disk 51 in the axial direction, preventing axial movement during installation and ensuring installation accuracy and stability. Furthermore, during rotation, the operator can observe through the observation hole 313 on the rotor structure whether the mating holes between the guide disk and the turbine disk 52 are aligned; if misalignment is found, adjustments can be made promptly. The present invention, through the positioning and installation device, can simplify the installation operation of turbine guide plate 51 and turbine disk 52, improve the positioning and installation efficiency, accuracy and stability of aero-engine turbine guide plate 51 and turbine disk 52, reduce installation difficulty and cost, and ensure assembly quality.

[0019] Example This embodiment further elaborates on the positioning and mounting device for the turbine guide vane and turbine disk of an aero-engine, as detailed below.

[0020] See Figure 1 A positioning and mounting device for aero-engine turbine guide vane 51 and turbine disk 52 is disclosed. The turbine guide vane 51 is connected to the turbine disk 52 via an outer slot 132, and then positioned using the positioning and mounting device. The positioning and mounting device includes a base structure, a stator structure, and a rotor structure.

[0021] See Figures 1 to 4The base structure includes a base 11, a worktable 13, a hollow drive shaft 14, and a drive device 12. The base 11 is a frame, welded from square steel. The worktable 13 is fixed to the base 11 and has mounting holes 131. Several slots 132 are radially arranged on the wall of the mounting holes 131. The drive device 12 is a hand-cranked reducer, fixed to the base 11 and located below the worktable 13. The lower end of the hollow drive shaft 14 is connected to the output shaft of the hand-cranked reducer via a key. The upper end of the hollow drive shaft 14 passes through the mounting holes 131 of the worktable 13 and extends above the worktable 13, with several seventh end teeth 141 on its upper surface that mesh with the rotor structure. In this embodiment, the hollow drive shaft 14 provides power for the rotation of the rotor structure.

[0022] See Figures 5 to 7 The stator structure includes a support ring 21 and an anti-rotation ring 22. The support ring 21 is installed in the mounting hole 131 of the worktable 13 and fixed to the worktable 13 with screws. Moreover, a plurality of third end teeth 211 are provided at the lower end of the support ring 21. The third end teeth 211 are inserted into the slots 132 of the mounting hole 131, and the worktable 13 and the slots 132 provide support and circumferential stop for the support ring 21. A plurality of fourth end teeth 212 are also provided on the outer wall of the support ring 21, and the fourth end teeth 212 are evenly distributed circumferentially along the outer wall of the support ring 21.

[0023] See Figure 7 The lower end face of the anti-rotation ring 22 is provided with several fifth end teeth 221. The anti-rotation ring 22 covers the outside of the support ring 21, and the fifth end teeth 221 mesh with the fourth end teeth 212. The gap between the inner wall of the anti-rotation ring 22 and the outer wall of the support ring 21 meets the design requirements. The axial positioning of the anti-rotation ring 22 is achieved by the support ring 21 and the worktable 13, and the circumferential positioning of the anti-rotation ring 22 is achieved by the fifth end teeth 221 and the fourth end teeth 212. The upper end of the anti-rotation ring 22 is provided with several first end teeth 222. When the turbine disk 52 is placed on the anti-rotation ring 22, the upper end of the anti-rotation ring 22 abuts against the end face of the turbine disk 52, and the first end teeth 222 mesh with the protrusions on the lower end face of the turbine disk 52, thereby supporting the turbine disk 52 and stopping its circumferential movement.

[0024] See Figures 8 to 10The rotor structure includes a rotating disk 31 and a pressure ring 32. The rotating disk 31 has a through hole at its center, and several sixth end teeth 311 are radially arranged on the wall of the through hole. Furthermore, an axial positioning ring 312, an observation hole 313, and several second arc-shaped end teeth 314 are axially arranged on the lower end face of the rotating disk 31. All the second arc-shaped end teeth 314 are arranged in a ring, with the axial positioning ring 312 located on the outer ring of the second arc-shaped end teeth 314. In addition, several observation holes 313 are also provided on the end face of the rotating disk 31. After the turbine guide disk 51 and turbine disk 52 are installed on the anti-rotation ring 22, the rotating disk 31 is sleeved on the upper end of the hollow drive shaft 14. The sixth end teeth 311 of the rotating disk 31 mesh with the seventh end teeth 141 of the hollow drive shaft 14, realizing the transmission between the rotating disk 31 and the hollow drive shaft 14. A limiting step is provided at the upper end of the hollow drive shaft 14 to limit the position of the rotating disk 31 sleeved on the hollow drive shaft 14. Then, the second arc-shaped end tooth 314 is inserted into the arc-shaped notch of the turbine guide plate 51 to drive the turbine guide plate 51 to rotate with the hollow drive shaft 14; the axial positioning ring 312 abuts against the upper end face of the turbine guide plate 51 to achieve axial positioning of the turbine guide plate 51. When rotating the turbine guide plate 51, the alignment of the mating holes between the turbine guide plate 51 and the turbine plate 52 can be observed through the observation hole 313.

[0025] It should be noted that the through hole of the rotating disk 31 and the upper end of the hollow transmission shaft 14 can be center-fitted to ensure the coaxiality of the rotating disk 31 and the hollow transmission shaft 14, thereby improving the smoothness and accuracy of the transmission.

[0026] The pressure ring 32 is fixed to the upper end face of the rotating disk 31 by bolts. A thrust ball bearing is installed inside the pressure ring 32 to achieve a rotatable connection with the locking mechanism. Furthermore, a cover plate 33 is also fixed to the pressure ring 32 by bolts. (See attached image.) Figure 11 The cover plate 33 has a circular ring structure, and its inner diameter is smaller than that of the thrust ball bearing, thus axially limiting the thrust ball bearing and preventing it from accidentally dislodging from the pressure ring 32. In this embodiment, the thrust ball bearing decouples the rotating disk 31 from the axial limiting screw 41, ensuring that the rotating disk 31 can rotate around the axial limiting screw 41 under the drive of the hand-cranked reducer and the hollow drive shaft 14.

[0027] See Figure 1 , Figure 2 and Figure 12The axial limiting device includes an axial limiting screw 41, an open washer 42, and a locking nut 43. The lower end of the axial limiting screw 41 is fixed to the base 11 and located below the worktable 13. The upper end of the axial limiting screw 41 passes through the hollow drive shaft 14 and extends above the pressure ring 32. The open washer 42 is fitted onto the outside of the axial limiting screw 41 and placed on the thrust ball bearing. Then, the locking nut 43 is tightened onto the axial limiting screw 41, thereby pressing the open washer 42 and achieving overall limiting of the pressure ring 32, rotating disk 31, turbine guide disk 51, and turbine disk 52 along the axial direction.

[0028] In this embodiment, during the positioning and assembly process, the turbine guide plate 51 and turbine disk 52 assembly is placed on the anti-rotation ring 22. The turbine disk 52 is restricted by the anti-rotation ring 22 and cannot rotate. Then, the rotating disk 31, pressure ring 32, cover plate 33, open washer 42, and locking nut 43 are installed in sequence. Next, the hollow drive shaft 14 is driven to rotate by the output shaft of the hand-cranked reducer. The hollow drive shaft 14 drives the rotating disk 31 to rotate, and the rotating disk 31 drives the turbine guide plate 51 to rotate relative to the turbine disk 52. Through the observation holes 313 evenly distributed on the end face of the rotating disk 31, the alignment of the mating holes between the turbine guide plate 51 and the turbine disk 52 is observed in real time. When the mating holes between the turbine guide plate 51 and the turbine disk 52 are aligned, the rotation of the rotating disk 31 is stopped, thus achieving the purpose of installing the turbine guide plate 51. This embodiment uses the positioning and installation device to simplify the operation process of installing the turbine guide plate 51, avoid and reduce the risk of knocking, and improve the assembly quality and efficiency of the turbine guide plate 51.

[0029] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A positioning and mounting device for a turbine guide disk and a turbine disk of an aircraft engine, wherein the turbine guide disk (51) is fastened to the turbine disk (52), characterized in that, include: The base structure includes a worktable (13), a hollow drive shaft (14), and a drive device (12); the drive device (12) is fixed below the worktable (13); the lower end of the hollow drive shaft (14) is connected to the drive device (12), and the upper end passes through the worktable (13) and extends above the worktable (13); The stator structure is fixed on the worktable (13) and has a first end tooth (222). The first end tooth (222) engages with the protrusion on the end face of the turbine disk (52). The stator structure is used to support the turbine disk (52) and stop its circumferential movement. The rotor structure is connected to the hollow drive shaft (14) and is fastened to the turbine guide disk (51). The rotor structure is provided with a second arc-shaped end tooth (314) and an observation hole (313). The second arc-shaped end tooth (314) is inserted into the arc-shaped notch of the turbine guide disk (51) to drive the turbine guide disk (51) to rotate with the hollow drive shaft (14). The observation hole (313) is used to observe whether the mating holes between the turbine guide disk (51) and the turbine disk (52) are aligned. The axial limiting structure includes an axial limiting screw (41) and a locking mechanism. One end of the axial limiting screw (41) is fixed below the worktable (13), and the other end passes through the hollow transmission shaft (14) and extends above the rotor structure. The locking mechanism is rotatably connected to the rotor structure and fixed to the axial limiting screw (41).

2. The positioning and mounting device for turbine guide vanes and turbine disks of an aero-engine according to claim 1, characterized in that, The workbench (13) is provided with mounting holes (131), and the wall of the mounting holes (131) is provided with a plurality of slots (132) along the radial direction; The stator structure includes a support ring (21) fixed on the workbench (13). The lower end of the support ring (21) is provided with a plurality of third end teeth (211), which are inserted into the slot (132). The support ring (21) is also provided with a plurality of fourth end teeth (212) along the circumferential direction of the outer wall.

3. The positioning and mounting device for aero-engine turbine guide vanes and turbine disks according to claim 2, characterized in that, The stator structure also includes an anti-rotation ring (22), the lower end of which is provided with a plurality of fifth end teeth (221). The anti-rotation ring (22) covers the outside of the support ring (21), and the fifth end teeth (221) mesh with the fourth end teeth (212). The first end teeth (222) are provided at the upper end of the anti-rotation ring (22), and the upper end of the anti-rotation ring (22) abuts against the end face of the turbine disk (52).

4. The positioning and mounting device for turbine guide vanes and turbine disks of an aero-engine according to claim 3, characterized in that, The upper end face of the hollow drive shaft (14) is provided with several seventh end teeth (141); The rotor structure includes a rotating disk (31), the rotating disk (31) has a through hole at its center, and a plurality of sixth end teeth (311) are provided radially on the wall of the through hole. The rotating disk (31) is sleeved on the upper end of the hollow transmission shaft (14), and the sixth end teeth (311) mesh with the third end teeth (211). The second arc-shaped end teeth (314) are arranged axially on the lower end face of the rotating disk (31).

5. The positioning and mounting device for aero-engine turbine guide vanes and turbine disks according to claim 4, characterized in that, The lower end face of the rotating disk (31) is also provided with an axial positioning ring (312) along the axial direction. The axial positioning ring (312) is located on the outer ring of the second arc-shaped end tooth (314) and abuts against the upper end face of the turbine guide disk (51).

6. The positioning and mounting device for aero-engine turbine guide vanes and turbine disks according to claim 5, characterized in that, The observation hole (313) is provided on the rotating disk (31).

7. The positioning and mounting device for aero-engine turbine guide vanes and turbine disks according to claim 6, characterized in that, The rotor structure also includes a pressure ring (32), which is fixed to the upper end face of the rotating disk (31). The pressure ring (32) is rotatably connected to the locking mechanism through a bearing.

8. The positioning and mounting device for aero-engine turbine guide vanes and turbine disks according to claim 7, characterized in that, The locking mechanism includes an open washer (42) and a locking nut (43). The locking nut (43) is connected to the axial limiting screw (41) and presses the bearing on the pressure ring (32) with the open washer (42).

9. The positioning and mounting device for aero-engine turbine guide vanes and turbine disks according to claim 8, characterized in that, The drive device (12) is a hand-cranked reducer, and the output shaft of the hand-cranked reducer is connected to the lower end of the hollow transmission shaft (14).

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