Disassembly and assembly device for turboshaft engine turbine blades

Abstract

The present invention discloses a disassembly and assembly device, in particular, a disassembly and assembly device for turboshaft engine turbine blades, which belongs to the technical field of design and manufacturing of tooling equipment for aircraft engine repair and maintenance. A disassembly and assembly device for turboshaft engine turbine blades is provided, which can effectively control the displacement and significantly improve the assembly and disassembly efficiency. The disassembly and assembly device includes a rotating support base, a lifting and adjusting component, and a blade assembly and disassembly mechanism. The lifting and adjusting component is arranged on the rotating support base in a lifting and adjusting manner in the height direction, and the blade assembly and disassembly mechanism is movably arranged on the top of the rotating support base in cooperation with the lifting and adjusting component. During the assembly and disassembly process of the turboshaft engine turbine blades, the turbine disc is fixed on the top of the rotating support base, and the turbine blades during the assembly and disassembly process are clamped into or out of the turbine disc through the blade assembly and disassembly mechanism in cooperation with the lifting and adjusting component.

Description

Technical Field

[0001] The present invention relates to a disassembly and assembly device, in particular to a disassembly and assembly device for turbine blades of a turboshaft engine, and belongs to the technical field of design and manufacturing of tooling equipment for repair and maintenance of aviation engines. Background Art

[0002] During the repair process of a certain imported turboshaft engine, the gas turbine blades, power turbine first-stage blades, and power turbine second-stage blades need to be disassembled and assembled multiple times. Sealing plates with sealing and vibration-damping functions are installed on both sides of the tenons of adjacent gas turbine blades, while the blade crowns of the power turbine first-stage blades and power turbine second-stage blades are serrated vibration-damping structures. These structural features dictate that when disassembling and assembling the blades, the blades need to be gradually and slowly moved axially along the entire circumference, and the axial displacement of the blades must be strictly controlled, with each movement not exceeding 1mm. However, during the actual disassembly and assembly process, the blades often get stuck with each other because the axial displacement of the blades cannot be effectively controlled. The operator needs to knock the blades back and forth repeatedly to keep the entire stage of blades on the same horizontal plane to ensure smooth assembly of the blades. This greatly increases labor intensity and reduces production efficiency.

[0003] Due to poor control of axial positioning and axial displacement during blade assembly, the sealing plates between gas turbine blades can be squeezed, deformed, or torn, compromising their sealing and vibration damping capabilities. Under the harsh operating conditions of high temperature, high pressure, high speed, and high centrifugal forces, the gas turbine blades and gas turbine disks present significant quality and safety risks. When subjected to external forces, the blade tenons, blade body, and blade shroud serrations can all potentially be damaged. This can lead to blade tenon fracture, blade body cracks, and blade shroud shedding during high-load engine operation. This can severely impact the quality of engine repair deliveries at the factory, cause significant losses to national property, and threaten the lives of pilots. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a disassembly and assembly device for turbine blades of a turboshaft engine, which can effectively control the displacement and significantly improve the assembly and disassembly efficiency.

[0005] The technical solution adopted to solve the above technical problems is: a disassembly and assembly device for turboshaft engine turbine blades, the disassembly and assembly device comprising a rotating support base, a lifting and adjusting component and a blade assembly and disassembly mechanism, the lifting and adjusting component being arranged on the rotating support base in a liftable manner along the height direction, and the blade assembly and disassembly mechanism being movably arranged on the top of the rotating support base with the cooperation of the lifting and adjusting component; during the assembly and disassembly process of the turboshaft engine turbine blades, the turbine disc is fixed on the top of the rotating support base, and the turbine blades during the assembly and disassembly process are clamped into or out of the turbine disc through the blade assembly and disassembly mechanism with the cooperation of the lifting and adjusting component.

[0006] Furthermore, the rotating support base includes a base, a rotating limit assembly and a supporting column. The supporting column is movably supported on the base through the rotating limit assembly. The lifting and adjusting assembly is sleeved on the supporting column above the rotating limit assembly. The blade assembly and disassembly mechanism is movably arranged on the top of the supporting column with the cooperation of the lifting and adjusting assembly.

[0007] The preferred embodiment of the above scheme is that the rotation limiting assembly includes a bearing sleeve, a turntable and a bearing component group, the turntable is fixedly supported on the upper end of the bearing sleeve, the middle and lower parts of the support column are movably sleeved in the bearing sleeve through the bearing component group, the bearing sleeve is fixed on the base, and the lifting and adjusting assembly is sleeved on the support column above the turntable.

[0008] Furthermore, the bearing assembly includes a rolling bearing in the middle and lower part and a planar support bearing in the middle and upper part. The base is composed of a disc with a diameter larger than the outer dimensions of the blade assembly and decomposition mechanism. The middle and lower parts of the support column are movably connected to the bearing sleeve through the rolling bearing and the planar support bearing respectively. The bearing sleeve is fixed at the geometric center of the disc.

[0009] A preferred embodiment of the above scheme is that the rotating support chassis further includes a locking brake assembly, and the supporting column during assembly and disassembly of the turboshaft engine is locked relative to the disc through the locking brake assembly.

[0010] Furthermore, the lifting and adjustment component includes a support sleeve and an adjustment sleeve. The adjustment sleeve is connected to the support column above the turntable through the support sleeve. The blade assembly and disassembly mechanism supported on the support sleeve can be lifted and lowered back and forth in the height direction through the cooperation between the support sleeve and the adjustment sleeve.

[0011] A preferred embodiment of the above scheme is that mutually adapted lifting threads are respectively provided on the outer side wall of the support sleeve and the inner side wall of the adjustment sleeve, and the support sleeve can be lifted and lowered back and forth in the height direction through the lifting threads in cooperation with the adjustment sleeve.

[0012] Furthermore, a rotating handle is provided on the adjustment sleeve, and the locking brake assembly includes a locking screw, an angular support block and a locking handle. A threaded hole is provided on the bearing sleeve between the rolling bearing and the plane support bearing, and the threaded end of the locking screw is screwed into the threaded hole. The other end of the locking screw is arranged on the base through the angular support block, and the locking handle is arranged on the locking screw outside the angular support block.

[0013] A preferred embodiment of the above scheme is that the blade assembly and disassembly mechanism includes at least a set of disassembly support plates, the assembly and disassembly support plates are cylindrical with one end open, and a mounting hole is provided on an end face of the assembly and disassembly support plate that is not open. The assembly and disassembly support plate that is detachably fixed to the top of the support sleeve through the mounting hole can be reciprocated and lifted in the height direction under the cooperation of the support sleeve and the adjustment sleeve; during the assembly and disassembly of the turbine blades, the turbine disc is fixed to the top of the support column, and the turbine blades during the assembly and disassembly process are clamped into or out of the turbine disc through the assembly and disassembly support plate under the cooperation of the support sleeve and the adjustment sleeve.

[0014] Furthermore, a support flange is provided on the outer side of the open end of the cylindrical assembly and disassembly support plate, and the cylindrical assembly and disassembly support plate and the support flange are an integral structure made of nylon material.

[0015] The beneficial effects of the present invention are as follows: the technical solution provided by the present application is to provide a disassembly and assembly device comprising a rotating support base, a lifting and adjusting assembly, and a blade assembly and disassembly mechanism, wherein the lifting and adjusting assembly is arranged on the rotating support base in a height-adjustable manner, and the blade assembly and disassembly mechanism is movably arranged on the top of the rotating support base in cooperation with the lifting and adjusting assembly; then, during the assembly and disassembly of the turbine blades of the turboshaft engine, the turbine disc is first fixed on the top of the rotating support base, and then the turbine blades during assembly and disassembly are engaged or disengaged from the turbine disc by the blade assembly and disassembly mechanism in cooperation with the lifting and adjusting assembly and an external disassembly driving force. In this way, when assembling and disassembling the turbine blades, the turbine blades can be initially engaged with the turbine disc through the sawtooth vibration damping structure in cooperation with the blade assembly and disassembly mechanism, and then the height of each descent is fixedly adjusted by the lifting and adjusting assembly, and then the turbine blades are manually knocked downward to gradually engage or disengage the turbine disc to complete the assembly and disassembly of the turbine blades. This solves the problem of blades being stuck together due to the lack of a reliable device in the prior art, and effectively controls the displacement of the turbine blades at each time, thereby significantly improving the assembly and disassembly efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 A schematic diagram of the three-dimensional structure of the disassembly and assembly device for a turbine blade of a turboshaft engine according to the present invention;

[0017] Figure 2 A cross-sectional view of a structure of a disassembly and assembly device for a turbine blade of a turboshaft engine according to the present invention;

[0018] Figure 3 The present invention is a cross-sectional view of another structure of the disassembly and assembly device for turbine blades of a turboshaft engine.

[0019] Marked in the figure are: rotating support base 1, lifting adjustment component 2, blade assembly and disassembly mechanism 3, base 4, rotation limit component 5, support column 6, bearing sleeve 7, turntable 8, bearing assembly 9, rolling bearing 10, plane support bearing 11, locking brake assembly 12, support sleeve 13, adjustment sleeve 14, rotating handle 15, locking screw 16, angle support block 17, locking handle 18, assembly and disassembly support plate 19, support flange 20. DETAILED DESCRIPTION

[0020] like Figure 1 、 Figure 2 as well as Figure 3The present invention illustrates a disassembly and assembly device for turboshaft engine turbine blades, which effectively controls displacement and significantly improves assembly and disassembly efficiency. The disassembly and assembly device comprises a rotating support frame 1, a lifting and adjusting assembly 2, and a blade assembly and disassembly mechanism 3. The lifting and adjusting assembly 2 is arranged on the rotating support frame 1 in a manner that allows it to be raised and lowered in height. The blade assembly and disassembly mechanism 3 is movably arranged on top of the rotating support frame 1 in cooperation with the lifting and adjusting assembly 2. During assembly and disassembly of the turboshaft engine turbine blades, the turbine disc is fixed to the top of the rotating support frame 1. During assembly and disassembly, the turbine blade is engaged or disengaged from the turbine disc via the blade assembly and disassembly mechanism 3 in cooperation with the lifting and adjusting assembly 2. The technical solution provided by the present application is to provide a disassembly and assembly device including a rotating support base, a lifting and adjusting assembly, and a blade assembly and disassembly mechanism. The lifting and adjusting assembly is arranged on the rotating support base in a height-adjustable manner, and the blade assembly and disassembly mechanism is movably arranged on the top of the rotating support base in cooperation with the lifting and adjusting assembly. Then, during the assembly and disassembly of the turbine blades of the turboshaft engine, the turbine disc is first fixed on the top of the rotating support base, and then the turbine blades during assembly and disassembly are engaged or disengaged from the turbine disc by the blade assembly and disassembly mechanism in cooperation with the lifting and adjusting assembly and an external disassembly driving force. In this way, when assembling and disassembling the turbine blades, the turbine blades can be initially engaged with the turbine disc through the sawtooth vibration damping structure in cooperation with the blade assembly and disassembly mechanism, and then the height of each descent is fixedly adjusted by the lifting and adjusting assembly. Then, the turbine blades are manually knocked downward to gradually engage or disengage the turbine disc to complete the assembly and disassembly of the turbine blades. This solves the problem of blades being stuck together due to the lack of a reliable device in the prior art, and effectively controls the displacement of the turbine blades at each time, thereby significantly improving the assembly and disassembly efficiency.

[0021] In the above embodiment, in combination with the structural characteristics of the turboshaft engine that needs to be disassembled and assembled, the present application provides that the rotating support base 1 includes a base 4, a rotating limit assembly 5, and a supporting column 6. The supporting column 6 is movably supported on the base 4 through the rotating limit assembly 5. The lifting and adjusting assembly 2 is sleeved on the supporting column 6 above the rotating limit assembly 5. The blade assembly and disassembly mechanism 3 is movably arranged on the top of the supporting column 6 in cooperation with the lifting and adjusting assembly 2. At this time, the rotating limit assembly 5 includes a bearing sleeve 7, a turntable 8, and a bearing assembly 9. The turntable 8 is fixedly supported at the upper end of the bearing sleeve 7. The middle and lower parts of the supporting column 6 are movably sleeved in the bearing sleeve 7 through the bearing assembly 9. The bearing sleeve 7 is fixedly mounted on the base 4. The lifting and adjusting assembly 2 is sleeved on the supporting column 6 above the turntable 8. Accordingly, the bearing assembly 9 includes at least a rolling bearing 10 in the middle and lower portion and a planar support bearing 11 in the middle and upper portion. The base 4 is formed of a disc having a diameter greater than the outer dimensions of the blade assembly and disassembly mechanism 3. The middle and lower portions of the support columns 6 are movably sleeved within the bearing sleeve 7 via both the rolling bearing 10 and the planar support bearing 11. The bearing sleeve 7 is fixedly mounted at the geometric center of the disc. Furthermore, to ensure safe operation during assembly and disassembly, the rotating support base 1 described in this application also includes a locking brake assembly 12, which locks the support columns 6 relative to the disc during assembly and disassembly of the turboshaft engine. The locking brake assembly 12 includes a locking screw 16, an angular support block 17 and a locking handle 18. A threaded hole is provided on the bearing sleeve 7 between the rolling bearing 10 and the plane support bearing 11. The threaded end of the locking screw 16 is screwed into the threaded hole. The other end of the locking screw 16 is arranged on the base 4 through the angular support block 17. The locking handle 18 is provided on the locking screw 16 outside the angular support block 17.

[0022] Furthermore, in order to more accurately determine the height of each lift, the lifting and adjustment component 2 described in the present application includes a support sleeve 13 and an adjustment sleeve 14. The adjustment sleeve 14 is sleeved on the support column 6 above the turntable 8 through the support sleeve 13. The blade assembly and decomposition mechanism 3 supported on the support sleeve 13 can be lifted and lowered back and forth in the height direction through the cooperation between the support sleeve 13 and the adjustment sleeve 14. A more preferred embodiment is that mutually adapted lifting threads are respectively provided on the outer wall of the support sleeve 13 and the inner wall of the adjustment sleeve 14. The support sleeve 13 can be lifted and lowered back and forth in the height direction through the lifting threads in cooperation with the adjustment sleeve 14. In order to facilitate the lifting operation, the present application also provides a rotating handle 15 on the adjustment sleeve 14.

[0023] As an important component of the present invention's technical solution, to facilitate support of turbine blades, the blade assembly and disassembly mechanism 3 described herein includes at least a set of disassembly support plates 19. These plates are cylindrical with one end open and have mounting holes defined on the unopened end surface. Removably secured to the top of the support sleeve 13 through these mounting holes, the plates 19 can be raised and lowered in the vertical direction in coordination with the sleeve 13 and the adjustment sleeve 14. During assembly and disassembly of the turbine blades, the turbine disc is secured to the top of the support column 6. During assembly and disassembly, the turbine blades are engaged and disengaged via the plates 19 in coordination with the sleeve 13 and the adjustment sleeve 14. Given the multiple disassembly and assembly of gas turbine blades, power turbine stage 1 blades, and power turbine stage 2 blades required during turboshaft engine repair, as well as the geometrical requirements of these three blade types, the present invention further provides a support flange 20 on the outer side of the open end of the cylindrical assembly and disassembly support plate. The cylindrical assembly and disassembly support plate and the support flange 20 are constructed as a single, integral structure made of nylon.

[0024] In summary, the turboshaft engine turbine blade disassembly and assembly lifting device of the present application is designed with a nylon support plate and a retaining ring to prevent the blades from being damaged by collisions and falling to the ground during assembly. The blades are axially positioned using the device support plate, and the axial displacement of the blades relative to the turbine disk is precisely controlled through the movement of the M64×2 threaded pair. It effectively solves the problem of damage to the sealing plates and blades caused by inaccurate axial positioning and unreliable control of axial displacement during disassembly and assembly of adjacent blades. It ensures that the blades can be assembled smoothly, prevents human errors, reduces labor intensity, improves assembly efficiency, ensures the quality of assembled products, meets the needs of rapid equipment delivery, and reserves wartime field repair technology. Specific embodiments

[0026] The purpose of this application is to develop a turbine blade subassembly and lifting device to address the shortcomings of the above-mentioned prior art. Figure 1 As shown, a shaft with a thrust ball bearing and a deep groove ball bearing is mounted on the base. A turntable drives the shaft for free rotation, while a brake lever limits rotation when not required. A handle rotates the adjustment screw with an M64×2 thread. The number of turns of the adjustment screw determines the axial displacement of the blade according to the desired position.

[0027] During disassembly, the turbine disc is mounted onto the shaft and secured with washers and nuts. Rotating the adjusting screw 180° relative to the turntable precisely controls the blades' movement from the disc grooves to just 1mm. Once all blades are fully released from the disc grooves, the support plate and retaining ring prevent them from accidentally falling. This effectively prevents blades from becoming stuck due to large differences in axial displacement between adjacent blades, reduces the need for operators to repeatedly strike the blades, reduces labor intensity, ensures disassembly quality, and improves production efficiency.

[0028] During assembly, rotate the "adjusting screw" according to the axial position requirements and adjust the "support plate" of the lifting device to the required axial position height. The entire stage of blades is positioned by the flat support of the "support plate" so that the entire stage of blades remain on the same horizontal plane, ensuring that the gas turbine blade seals and the first and second stage turbine blades of the power turbine with serrated blade crowns can be installed smoothly. Rotating the "adjusting screw" 180° relative to the "turntable" can accurately control the entire stage of blades to only enter 1mm relative to the wheel disc at a time. Prevent the sealing sheets between the gas turbine blades from being squeezed, deformed, or torn; prevent potential damage to the tenons, blade bodies, and blade crown serrations of the power turbine blades after being subjected to external forces, thereby improving the quality of engine assembly.

[0029] The gas turbine disc is made of nickel alloy. The edge of the disc is processed with 43 fir-tree-shaped tenons with a 20° bevel. 43 gas turbine blades are installed in the fir-tree-shaped tenons. The gas turbine blades are nickel alloy "single crystal" blades without blade crowns. Sealing plates are installed on both sides of the tenons of adjacent blades. A sub-assembly and lifting device is designed according to the structure of the gas turbine rotor.

[0030] The creativity of this application lies in the innovative design and manufacture of a lifting device for disassembling and assembling turbine rotor blades. Through bearing support and threaded screwing, the lifting and lowering adjustment position of the turbine rotor is precisely controlled, and the entire stage of blades is reasonably supported. At the same time, the blades are protected by a support plate tray to prevent them from accidentally falling.

[0031] The implementation effects are as follows:

[0032] This technology has been successfully applied to the disassembly and assembly of nearly 70 engine turbine rotors. It can be extended to the disassembly and assembly of turbine rotor blades of other turboshaft, turbojets, turbofans and gas turbine engines. It has good application prospects and high economic and military value.

Claims

1. A disassembly and assembly device for a turbine blade of a turboshaft engine, characterized by: The disassembly and assembly device comprises a rotating support base (1), a lifting and adjusting component (2) and a blade assembly and disassembly mechanism (3); the lifting and adjusting component (2) is arranged on the rotating support base (1) in a manner that it can be lifted and lowered in the height direction; the blade assembly and disassembly mechanism (3) is movably arranged on the top of the rotating support base (1) in cooperation with the lifting and adjusting component (2); during the assembly and disassembly of the turbine blades of the turboshaft engine, the turbine disc is fixed on the top of the rotating support base (1); during the assembly and disassembly process, the turbine blade is inserted into or removed from the turbine disc by the blade assembly and disassembly mechanism (3) in cooperation with the lifting and adjusting component (2); The rotating support chassis (1) further comprises a locking brake assembly (12), and the supporting column (6) is locked relative to the disc by the locking brake assembly (12) during the assembly and disassembly of the turboshaft engine. The lifting and adjusting component (2) comprises a support sleeve (13) and an adjusting sleeve (14); the adjusting sleeve (14) is sleeved on the supporting column (6) above the turntable (8) through the support sleeve (13); and the blade assembly and disassembly mechanism (3) supported on the support sleeve (13) can be lifted and lowered reciprocally in the height direction through the cooperation between the support sleeve (13) and the adjusting sleeve (14).

2. The disassembly and assembly device for a turboshaft engine turbine blade according to claim 1, characterized in that: The rotating support chassis (1) comprises a base (4), a rotating limit assembly (5) and a supporting column (6); the supporting column (6) is movably supported on the base (4) through the rotating limit assembly (5); the lifting and adjusting assembly (2) is sleeved on the supporting column (6) above the rotating limit assembly (5); and the blade assembly and disassembly mechanism (3) is movably arranged on the top of the supporting column (6) in cooperation with the lifting and adjusting assembly (2).

3. The disassembly and assembly device for a turboshaft engine turbine blade according to claim 2, characterized in that: The rotation limiting assembly (5) includes a bearing sleeve (7), a turntable (8) and a bearing assembly (9); the turntable (8) is fixedly supported on the upper end of the bearing sleeve (7); the middle and lower parts of the support column (6) are movably sleeved in the bearing sleeve (7) through the bearing assembly (9); the bearing sleeve (7) is fixed on the base (4); and the lifting adjustment assembly (2) is sleeved on the support column (6) above the turntable (8).

4. The disassembly and assembly device for a turboshaft engine turbine blade according to claim 3, characterized in that: The bearing assembly (9) includes a rolling bearing (10) in the middle and lower part and a planar support bearing (11) in the middle and upper part. The base (4) is composed of a disc having a diameter larger than the outer dimensions of the blade assembly and decomposition mechanism (3). The middle and lower parts of the support column (6) are movably sleeved in the bearing sleeve (7) through the rolling bearing (10) and the planar support bearing (11). The bearing sleeve (7) is fixed at the geometric center of the disc.

5. The disassembly and assembly device for a turboshaft engine turbine blade according to claim 1, 2, 3 or 4, characterized in that: Mutually adapted lifting threads are respectively provided on the outer side wall of the support sleeve (13) and the inner side wall of the adjustment sleeve (14); the support sleeve (13) can be lifted and lowered reciprocally in the height direction in cooperation with the adjustment sleeve (14) through the lifting threads.

6. The disassembly and assembly device for a turboshaft engine turbine blade according to claim 5, characterized in that: A rotating handle (15) is also provided on the adjustment sleeve (14). The locking brake assembly (12) includes a locking screw (16), an angular support block (17) and a locking handle (18). A threaded hole is provided on the bearing sleeve (7) between the rolling bearing (10) and the plane support bearing (11). The threaded end of the locking screw (16) is screwed into the threaded hole. The other end of the locking screw (16) is arranged on the base (4) through the angular support block (17). The locking handle (18) is provided on the locking screw (16) outside the angular support block (17).

7. The disassembly and assembly device for a turboshaft engine turbine blade according to claim 6, characterized in that: The blade assembly and disassembly mechanism (3) comprises at least one set of disassembly support plates (19), the disassembly support plates (19) being cylindrical with one end open, and a mounting hole being provided on an end face of the disassembly support plate (19) which is not open. The disassembly support plate (19) is detachably fixed to the top of the support sleeve (13) through the mounting hole and can be reciprocated and lifted in the height direction under the cooperation of the support sleeve (13) and the adjustment sleeve (14); during the assembly and disassembly of the turbine blades, the turbine disc is fixed to the top of the support column (6), and the turbine blades in the assembly and disassembly process are inserted into or withdrawn from the turbine disc through the disassembly support plate (19) under the cooperation of the support sleeve (13) and the adjustment sleeve (14).

8. The disassembly and assembly device for a turboshaft engine turbine blade according to claim 7, characterized in that: A support flange (20) is further provided on the outer side of the open end of the cylindrical assembly and disassembly support plate. The cylindrical assembly and disassembly support plate and the support flange (20) are an integral structure made of nylon material.

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