Storage, transportation and replacement integrated device for power turbine unit body of aero-engine

Abstract

The invention discloses an aero-engine power turbine unit storage, transportation and replacement integrated device which comprises a clamping system, and the clamping system comprises a front clamping assembly connected with a stator of a power turbine unit and used for providing axial and radial supporting for the power turbine unit; the rear clamping assembly is connected with a stator of the power turbine unit body and used for being matched with the fuel gas generator to achieve centering positioning and axial pressing during external field replacement; the hoisting assembly is connected with the front clamping assembly and the rear clamping assembly and used for providing an integral hoisting function; and the auxiliary clamping assembly is matched with the rear clamping assembly and used for limiting the relative displacement of the power turbine unit body rotor and the power turbine unit body stator in the storage and transportation state. According to the invention, the integration of storage, transportation and replacement functions is realized, the power turbine unit body of the turboshaft engine can be supported and protected in the storage and transportation process, and the construction efficiency of replacement of the power turbine unit body and the interface connection quality are ensured under the condition of external field replacement.

Description

Technical Field

[0001] This invention relates to the field of external field maintenance technology for aero-engine unit bodies, and specifically to an integrated storage, transportation and replacement device for aero-engine power turbine unit bodies. Background Technology

[0002] As high-speed rotating thermodynamic machines, aero engines have extremely complex internal structures, including numerous thin-walled casings and high-precision rotor components such as blades and bearings. In condition-based maintenance and repair of aero engines based on unit structures, the storage and transportation of these unit structures are crucial. How to effectively reduce external damage to the engine unit structures while ensuring efficient transport and rapid replacement has significant engineering application value. For turboshaft engines, the power turbine unit is the area where transport and replacement efficiency is paramount.

[0003] Traditionally, transport aircraft assembly is completed by placing unit components onto non-dedicated brackets or wheeled pallets using lifting machinery. The brackets are then transported to the engine assembly point, where the unit components are again lifted by lifting machinery, flipped, and then docked. These operations are extremely heavy, difficult, and physically demanding, sometimes requiring significant force and necessitating two-person collaboration. Each step demands extreme care, especially when the unit components need to be placed without impact on the brackets, temporarily flipped, and docked with another unit component with a precision within two millimeters. Therefore, this process is quite time-consuming.

[0004] Currently, existing aero-engine unit brackets and support frames are mainly designed for the transport of large-volume and heavy units in civil high-bypass turbofan engines, providing basic functions such as fixing, attitude adjustment, and transport. However, existing brackets are primarily suitable for units with good independence, where the rotor can be supported by the stator load-bearing structure, and lack the ability to provide auxiliary support and positioning for the rotor. In contrast, when disassembling and assembling rotor components of turboshaft engine power turbine units, the load-bearing frame must remain stationary. This necessitates providing auxiliary support for the disassembled rotor structure, a requirement that existing brackets cannot meet. Summary of the Invention

[0005] In view of this, the present invention provides an integrated storage, transportation and replacement device for aero-engine power turbine units to solve the problem that existing aero-engine unit brackets do not have the ability to provide auxiliary support and positioning for the rotor.

[0006] This invention provides an integrated storage, transportation, and replacement device for aero-engine power turbine units, comprising: A clamping system is used to support and protect the power turbine unit in the storage and transportation state, and to connect the power turbine unit to the gas generator in the field replacement state. The clamping system includes: The front clamping assembly, connected to the stator of the power turbine unit, is used to provide axial and radial support for the power turbine unit. The rear clamping assembly is connected to the stator of the power turbine unit and is used to cooperate with the gas generator to achieve centering and axial clamping during field replacement. A lifting assembly, connected to the front clamping assembly and the rear clamping assembly, is used to provide overall lifting functionality; An auxiliary clamping assembly, in conjunction with the rear clamping assembly, is used to limit the relative displacement between the rotor of the power turbine unit and the stator of the power turbine unit in the storage and transportation state.

[0007] The beneficial effects of the aforementioned integrated storage, transportation, and replacement device for aero-engine power turbine units are as follows: This invention integrates storage, transportation, and replacement functions, providing support and protection for the turboshaft engine power turbine unit during storage and transportation. It also ensures efficient construction and high-quality interface connections during field replacement, significantly improving field maintenance efficiency. Through modular integration of the front clamping assembly, rear clamping assembly, lifting assembly, and auxiliary clamping assembly, and by integrating the lifting assembly to achieve overall lifting functionality, combined with the automated positioning design of the front clamping assembly, rear clamping assembly, and auxiliary clamping assembly, the switch from storage / transportation to field replacement can be directly completed, eliminating the need for multiple tooling replacement steps, reducing manual intervention, improving field replacement efficiency, and significantly shortening operation time.

[0008] In one optional embodiment, the auxiliary clamping assembly and the rear clamping assembly are disposed on the front and rear sides of the rotor interface plate of the power turbine unit rotor and clamp the rotor interface plate to limit the position of the power turbine unit rotor.

[0009] The beneficial effects of the above technical solution are as follows: by clamping from the front and rear, the weight and operating force of the power turbine unit rotor can be transferred to the clamping system to form a stable external support point. Without modifying the stator load-bearing frame, the power turbine unit rotor can be independently disassembled, repaired or replaced, which solves the functional gap of the existing bracket that can only support the stator and cannot assist in supporting the rotor.

[0010] In one alternative implementation, the auxiliary clamping assembly includes: The limiting member is connected to the rear clamping assembly and abuts against the front end of the rotor interface plate.

[0011] In one optional embodiment, the auxiliary clamping assembly further includes: The first buffer is disposed between the rear clamping assembly and the rotor interface plate to absorb the impact load during storage and transportation.

[0012] In one alternative implementation, the rear clamping assembly includes: The composite clamping frame is connected to the stator and lifting assembly of the power turbine unit; The clamping structure is mounted on the composite clamping frame and abuts against the rear end of the rotor interface plate of the power turbine unit rotor.

[0013] In one alternative embodiment, the composite clamping frame includes: Central tube; Multiple connecting spokes are arranged at intervals along the outer wall of the central cylinder; Multiple annular flange stops are respectively provided at the ends of the connecting spokes. The annular flange stops are connected to the stator of the power turbine unit and the hoisting assembly through a first detachable connector.

[0014] In one alternative embodiment, the clamping structure includes: A clamping claw ring includes a claw plate and a sliding cylinder connected therebetween, wherein the sliding cylinder is sleeved on the outer periphery of the central cylinder and is capable of moving axially; The clamping nut, which engages with the threaded center cylinder, is used to push the clamping claw ring to move axially to clamp the rotor interface plate of the power turbine unit rotor.

[0015] The beneficial effects of the above technical solution are as follows: the clamping nut and the center cylinder are threaded together to push the clamping claw ring to move axially. In the case of field replacement, the rotor interface plate of the power turbine unit rotor and the rotor of the aero-engine gas generator are axially clamped together, so as to achieve the purpose of controlling the connection quality between the power turbine unit rotor and the aero-engine gas generator.

[0016] In one alternative embodiment, the rear clamping assembly further includes a centering structure, the centering structure comprising: Spherical tie rods are distributed around the circumference of the central cylinder, and one end of each rod is equipped with a spherical pad. The pad nut, which engages with the threaded spherical tie rod, is used to push the spherical pad to cause the central cylinder to expand radially and press against the inner wall of the gas generator.

[0017] The beneficial effects of the above technical solution are as follows: When the rear clamping assembly is replaced in the field, it works with the gas generator to ensure the docking accuracy between the power turbine unit and the gas generator through the centering and positioning structure and axial clamping function. This solves the operational difficulties of collision-free placement and high-precision alignment in traditional docking, reduces the risk of assembly error, and achieves centering and positioning of the power turbine unit and the gas generator in the field replacement state.

[0018] In one alternative implementation, the hoisting assembly includes: The main beam has a front flange and a rear flange at both ends, the front flange being connected to the front clamping assembly and the rear flange being connected to the rear clamping assembly. Lifting rings, which are mounted on the main beam and can rotate, are used to connect lifting equipment.

[0019] In one alternative implementation, the front clamping assembly includes: The disc support cylinder contacts the front end of the power turbine unit rotor and provides radial and axial limiting for the front end of the power turbine unit rotor. The end cap is fixedly connected to the disk center support cylinder and connected to the stator of the power turbine unit through a second detachable connector.

[0020] In one optional embodiment, the end cap is disposed in the middle of the outer wall of the disk support cylinder so that an angle is formed between the end cap and the disk support cylinder, and the angle limits the front end of the power turbine unit rotor. And / or, a second buffer is also provided between the disc support cylinder and the front end of the power turbine unit rotor; And / or, a reinforcing rib is provided between the disc support cylinder and the end cover.

[0021] In summary, the technical solution of the present invention has the following advantages: This invention enables integrated storage, transportation, and assembly control of the power turbine unit structure, and provides the capability for positioning and assembly control of the power turbine unit rotor and stator. Through the cooperation of certain components in the clamping system, the coaxiality and axial tightness of the power turbine unit rotor and the gas generator rotor can be controlled during field replacement, thereby achieving the goal of controlling the interface connection quality between the power turbine unit rotor and the aero-engine gas generator.

[0022] This invention can avoid collision damage between the power turbine rotor and the power turbine unit stator. The clamping system, consisting of a front clamping assembly, a lifting assembly, a rear clamping assembly, and an auxiliary clamping assembly, supports the power turbine unit during storage and transportation, and limits the relative displacement between the rotor and the power turbine unit stator within the unit. This prevents the internal structure of the power turbine unit from colliding and being damaged during storage and transportation, and reduces damage during unit transportation. Attached Figure Description

[0023] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0024] Figure 1 A schematic diagram of the installation path for a certain type of aero-engine power turbine unit; Figure 2 A schematic diagram of the structure of an integrated storage, transportation and replacement device for an aero-engine power turbine unit provided by the present invention; Figure 3 A schematic diagram of the front clamping assembly of an integrated storage, transportation and replacement device for aero-engine power turbine unit provided by the present invention; Figure 4 A schematic diagram of the hoisting assembly of an integrated storage, transportation, and replacement device for an aero-engine power turbine unit provided by the present invention; Figure 5 A schematic diagram of the rear clamping assembly of an integrated storage, transportation and replacement device for an aero-engine power turbine unit provided by the present invention; Figure 6 A schematic diagram of the auxiliary clamping assembly of an integrated storage, transportation and replacement device for aero-engine power turbine unit provided by the present invention; Figure 7 This is a schematic diagram of the working process of the device in the field replacement scenario of the present invention.

[0025] Explanation of reference numerals in the attached figures: 101. Gas generator; 102. Power turbine unit; 201. Power turbine unit rotor; 2011. Rotor interface plate; 202. Power turbine unit stator. 203. Front clamping assembly; 301. Second buffer component; 302. Disc support cylinder; 303. End cap; 304. Reinforcing rib; 305. Front temporary bolt; 204. Lifting assembly; 401. Front flange; 402. Main beam; 403. Rear flange; 404. Lifting ring; 405. Rear temporary bolts. 205. Rear clamping assembly; 501. Annular flange stop; 502. Connecting spoke; 503. Center cylinder; 504. Claw plate; 505. Sliding cylinder; 506. Clamping nut; 507. Spherical tie rod; 508. Spherical pad; 509. Pad nut. 206. Auxiliary clamping component; 601. First buffer component; 602. Limiting component. Detailed Implementation

[0026] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0027] As high-speed rotating thermodynamic machines, aero engines have extremely complex internal structures, including numerous thin-walled casings and high-precision rotor components such as blades and bearings. In condition-based maintenance and repair of aero engines based on unit structures, the storage and transportation of these unit structures are crucial. How to effectively reduce external damage to the engine unit structures while ensuring efficient transport and rapid replacement has significant engineering application value. For turboshaft engines, the power turbine unit is the area where transport and replacement efficiency is paramount.

[0028] Traditionally, transport aircraft assembly is completed by placing unit components onto non-dedicated brackets or wheeled pallets using lifting machinery. The brackets are then transported to the engine assembly point, where the unit components are again lifted by lifting machinery, flipped, and then docked. These operations are extremely heavy, difficult, and physically demanding, sometimes requiring significant force and necessitating two-person collaboration. Each step demands extreme care, especially when the unit components need to be placed without impact on the brackets, temporarily flipped, and docked with another unit component with a precision within two millimeters. Therefore, this process is quite time-consuming.

[0029] Currently, existing aero-engine unit brackets and support frames are mainly designed for the transport of large-volume and heavy units in civil high-bypass turbofan engines, providing basic functions such as fixing, attitude adjustment, and transport. However, existing brackets are primarily suitable for units with good independence, where the rotor can be supported by the stator load-bearing structure, and lack the ability to provide auxiliary support and positioning for the rotor. In contrast, when disassembling and assembling rotor components of turboshaft engine power turbine units, the load-bearing frame must remain stationary. This necessitates providing auxiliary support for the disassembled rotor structure, a requirement that existing brackets cannot meet.

[0030] Furthermore, the assembly process of the power turbine rotor unit requires precise control of the rotor's coaxiality and avoidance of rotor tilting, necessitating assembly control capabilities. Existing technologies are also insufficient to meet the requirements for power turbine unit replacement and assembly.

[0031] There is an urgent need to design a multi-functional integrated device to assist in replacement, ensuring construction efficiency and interface connection quality during field replacement of unit components. Simultaneously, this tooling should play a clamping role during unit component storage and transportation to prevent damage during transit, which is crucial for reducing transport losses and significantly improving the maintainability of aero-engines.

[0032] Based on this, the present invention provides an integrated storage, transportation, and replacement device for aero-engine power turbine units, applied to turboshaft engines. The device includes a power turbine unit rotor, a power turbine unit stator, a front clamping assembly, a lifting assembly, an auxiliary clamping assembly, and a rear clamping assembly. Based on the design and integration of this device structure, the present invention can achieve the following functions: supporting and protecting the clamped power turbine unit during storage and transportation; and achieving reliable centering and positioning of the power turbine unit bladed disk assembly and the power turbine shaft during field replacement. Based on this integrated tooling, rapid replacement of aero-engine power turbine units can be achieved under field conditions, supporting condition-based maintenance of aero-engine units and improving the maintainability of aero-engines.

[0033] The specific embodiments of the present invention will be described in detail below with reference to the integrated storage, transportation and replacement device for aero-engine power turbine units.

[0034] According to an embodiment of the present invention, an integrated storage, transportation, and replacement device for aero-engine power turbine units is provided, combined with... Figures 1 to 7 As shown, a clamping system is included, which supports and protects the power turbine unit 102 in the storage and transportation state, and enables the connection between the power turbine unit 102 and the gas generator 101 in the field replacement state. The power turbine unit 102 includes a power turbine unit rotor 201 and a power turbine unit stator 202, which are assembled through a mating structure.

[0035] The clamping system includes a front clamping assembly 203, a rear clamping assembly 205, a lifting assembly 204, and an auxiliary clamping assembly 206. The front clamping assembly 203 connects to the stator 202 of the power turbine unit and provides axial and radial support for the power turbine unit. The rear clamping assembly 205 connects to the stator of the power turbine unit and, during field replacement, works with the gas generator 101 to achieve centering, positioning, and axial clamping. The lifting assembly 204 connects to the front clamping assembly 203 and the rear clamping assembly 205 to provide overall lifting functionality. The auxiliary clamping assembly 206 works with the rear clamping assembly 205 to limit the relative displacement between the rotor 201 and the stator 202 of the power turbine unit during storage and transportation, preventing them from colliding.

[0036] The aforementioned integrated storage, transportation, and replacement device for aero-engine power turbine units integrates storage, transportation, and replacement functions, significantly improving field maintenance efficiency. Through modular integration of the front clamping assembly, rear clamping assembly, lifting assembly, and auxiliary clamping assembly, and by integrating the lifting assembly 204 to achieve overall lifting functionality, combined with the automated positioning design of the front clamping assembly, rear clamping assembly, and auxiliary clamping assembly, the switch from storage / transportation to field replacement can be completed directly. This eliminates the need for multiple tooling replacement steps, reduces manual intervention, improves field replacement efficiency, and significantly shortens operation time.

[0037] The aforementioned integrated storage, transportation, and replacement device for aero-engine power turbine units, through the cooperation of auxiliary clamping assembly 206 and rear clamping assembly 205, restricts the relative displacement of the power turbine unit rotor 201 and power turbine unit stator 202 during storage, transportation, and disassembly / removal. This ensures that the power turbine unit rotor 201 remains stably supported after disassembly, meeting the special operating conditions of turboshaft engines where the stator remains stationary while the rotor is disassembled and reassembled independently. The front clamping assembly 203 connects to the power turbine unit stator 202, providing axial and radial bidirectional support. Combined with the coordinated fixation of the rear clamping assembly 205, it comprehensively restricts the displacement of the unit during storage, transportation, and docking, preventing structural deformation or collision damage.

[0038] This embodiment simultaneously meets the requirements of structural protection during storage and transportation and rapid docking during field replacement. It eliminates the need to replace specialized equipment, solves the equipment switching problem of tray transfer and lifting docking in traditional processes, and improves the convenience of field operations.

[0039] In some embodiments, the auxiliary clamping assembly 206 and the rear clamping assembly 205 are disposed on the front and rear sides of the rotor interface plate 2011 of the power turbine unit rotor 201 and clamp the rotor interface plate 2011 to limit the position of the power turbine unit rotor 201.

[0040] The rotor interface plate 2011 is a key connecting component of the power turbine unit rotor 201. The auxiliary clamping assembly 206 and the rear clamping assembly 205 form a bidirectional axial clamp on it, which can strictly limit the axial movement and radial sway of the power turbine unit rotor 201 during storage and transportation, fundamentally reducing the risk of structural damage during storage and transportation.

[0041] The rotor interface plate 2011 serves as the load-bearing transfer point of the power turbine unit rotor 201. By clamping it from the front and rear, the weight and operating force of the power turbine unit rotor 201 can be transferred to the clamping system, forming a stable external support point. Without modifying the stator load-bearing frame, the power turbine unit rotor 201 can be independently disassembled, repaired, or replaced, thus solving the functional gap of existing brackets that can only support the stator and cannot assist in supporting the rotor.

[0042] In some embodiments, the lifting assembly 204 includes a main beam 402 and a lifting ring 404. The main beam 402 has a front flange 401 and a rear flange 403 at both ends, which are welded to the main beam 402. The front flange 401 is connected to the front clamping assembly 203, and the rear flange 403 is connected to the rear clamping assembly 205. The lifting ring 404 is mounted on the main beam 402 and is rotatable. In field replacement scenarios, the lifting ring 404 connects to a crane and lifting tools provided at the field site, lifting the entire device when replacing the power turbine unit. The rotatable lifting ring of the lifting assembly 204, combined with a single or multiple lifting point design, allows for flexible adjustment of the unit's posture, avoiding the drawbacks of traditional brackets requiring multiple adjustments to the lifting machinery position, and further shortening operation time.

[0043] When connecting the hoisting assembly 204, the rear flange 403 is connected to the rear stator interface plate of the power turbine unit stator 202 by the rear temporary bolt 405. At the same time, the front temporary bolt 305 in the front clamping assembly 203 passes through the front stator interface plate of the power turbine unit stator 202 and is inserted into the front flange 401 of the hoisting assembly 204. The bolt is fixed by tightening the nut on the front temporary bolt 305.

[0044] It should be noted that the hoisting of the power turbine unit 102 can be done using a single hoisting point, but a double hoisting point or multiple hoisting point scheme can also be used.

[0045] In some embodiments, the rear clamping assembly 205 includes a composite clamping frame and a clamping structure. The composite clamping frame is connected to the stator 202 of the power turbine unit and the lifting assembly 204, and the structural design of the composite clamping frame fully matches the outer peripheral contour of the stator 202 of the power turbine unit. The clamping structure is disposed on the composite clamping frame and abuts against the rear end of the rotor interface plate 2011 of the rotor 201 of the power turbine unit rotor.

[0046] The composite clamping frame includes a central cylinder 503, connecting spokes 502, and an annular flange stop 501. The annular flange stop 501 is welded integrally with the connecting spokes 502 and the central cylinder 503. The central cylinder 503 is inserted into the gas generator 101 of the aero-engine during field replacement. Multiple connecting spokes 502 are provided, spaced circumferentially along the outer wall of the central cylinder 503. Multiple annular flange stops 501 are provided, corresponding to the ends of the connecting spokes 502. The annular flange stops 501 are connected to the stator 202 of the power turbine unit and the lifting assembly 204 via a first detachable connector. Combined with the front clamping assembly 203, they form two-point supports for the stator, restricting axial and radial displacement of the stator and ensuring the overall stability of the unit during storage and transportation.

[0047] The connecting spokes 502 can be arranged in five pieces, or other different numbers of spokes can be used, such as fewer than three pieces, four pieces or more than six pieces, seven pieces, etc. The connecting spokes 502 are arranged circumferentially along the outer wall of the central cylinder 503, and the circumferential distribution can be uniform or non-uniform.

[0048] The first detachable connector can be a rear temporary bolt 405. In the positioning and clamping scheme of the rotor and stator structure of the power turbine unit, the rear temporary bolt 405 passes through the annular flange stop 501 and the stator 202 of the power turbine unit, and is inserted into the rear flange 403 of the hoisting assembly. The bolt is fixed by tightening the nut on the rear temporary bolt 405.

[0049] The clamping structure includes a clamping claw ring and a clamping nut 506. The clamping claw ring includes a claw plate 504 and a sliding cylinder 505 connected together. The claw plate 504 and the sliding cylinder 505 are welded together. The sliding cylinder 505 is sleeved on the outer periphery of the central cylinder 503 and can move axially. The clamping nut 506 is threadedly engaged with the central cylinder 503 and is used to push the clamping claw ring to move axially. In the case of field replacement, it clamps the rotor interface plate 2011 of the power turbine unit rotor 201 axially with the rotor of the aero-engine gas generator 101, thereby controlling the connection quality between the power turbine unit rotor 201 and the aero-engine gas generator 101.

[0050] The assembly process of the power turbine rotor unit requires precise control of the rotor's coaxiality and avoidance of rotor tilting, necessitating assembly control capabilities. Existing technologies are also insufficient to meet the requirements for power turbine unit replacement and assembly. Therefore, the rear clamping assembly 205 also includes a centering structure, comprising a spherical tie rod 507 and a pad nut 509. The spherical tie rod 507 is distributed circumferentially along the central cylinder 503, with a spherical pad 508 at one end. The pad nut 509 is threadedly engaged with the spherical tie rod 507. After the pad nut 509 is tightened along the spherical tie rod 507, it pushes the spherical pad 508, causing the central cylinder 503 to bulge radially and press against the inner wall of the gas generator 101 of the aero-engine, ensuring the coaxiality of the power turbine unit rotor 201 and the rotor of the gas generator 101.

[0051] In this embodiment, the rear clamping assembly 205 cooperates with the gas generator 101 during field replacement. Through the centering and positioning structure and axial clamping function, it ensures the docking accuracy between the power turbine unit and the gas generator, solves the operational difficulties of collision-free placement and high-precision alignment in traditional docking, reduces the risk of assembly error, and realizes the centering and positioning of the power turbine unit 102 and the gas generator 101 in the field replacement state.

[0052] In some embodiments, the auxiliary clamping assembly 206 includes a limiting member 602, which is connected to the rear clamping assembly 205 and abuts against the front end of the rotor interface plate 2011.

[0053] The auxiliary clamping assembly 206 also includes a first buffer 601, which is disposed between the rear clamping assembly 205 and the rotor interface plate 2011 to absorb the impact load during storage and transportation.

[0054] Specifically, the first buffer 601 is a buffer pad, and the limiting component 602 is a limiting nut. The limiting nut and the central cylinder 503 of the composite clamping frame are threaded together. When the power turbine unit 102 is in the storage and transportation state, the auxiliary clamping assembly 206 is axially locked backward, and the clamping claw ring (made of claw plate 504 and sliding cylinder 505 welded together) is axially locked forward. The front and rear cooperation restricts the axial displacement of the power turbine unit rotor 201. At the same time, the end face friction prevents the power turbine unit rotor 201 from rotating under the accidental movement of external force, prevents the internal structure of the power turbine unit 102 from being damaged by mutual collision during storage and transportation, and reduces the loss of the power turbine unit 102 during transportation.

[0055] In some embodiments, the front clamping assembly 203 includes a disk support cylinder 302 and an end cap 303. The disk support cylinder 302 contacts the front end of the power turbine unit rotor 201 and provides radial and axial limiting for the front end of the power turbine unit rotor 201. The end cap 303 is welded to the disk support cylinder 302 and connected to the power turbine unit stator 202 via a second detachable connector, which is a front temporary bolt 305.

[0056] The end cap 303 is disposed in the middle of the outer wall of the disk support cylinder 302, so that the end cap 303 and the disk support cylinder 302 form an angle, which limits the front end of the power turbine unit rotor 201. Preferably, the angle is 90°, so that it can contact the two end faces of the front end of the power turbine unit rotor 201.

[0057] A second buffer 301 is also provided between the disk support cylinder 302 and the front end of the power turbine unit rotor 201. The second buffer 301 is a buffer rubber pad, which is bonded to the disk support cylinder 302. The second buffer 301 is set in an L-shape to match the included angle.

[0058] A reinforcing rib 304 is provided between the disc support cylinder 302 and the end cap 303 to enhance the connection strength between them. Specifically, the reinforcing rib 304 is provided between the disc support cylinder 302 and the end cap 303 by welding.

[0059] To achieve the functions of the integrated device, the power turbine unit and the clamping system need to work together. The following describes the working process of the integrated device in the case of external field replacement of the unit. The working process of the device in the case of external field replacement is as follows: Figure 7 As shown, it includes the following steps: Step 1: At the beginning of the operation, securely connect the device to the crane and lifting equipment provided in the field to ensure a stable and reliable lifting process.

[0060] Step 2: Remove the front clamping component 203 and the auxiliary clamping component 206 from the clamping system.

[0061] Step 3: Connect the power turbine unit rotor 201 to the gas generator rotor interface, precisely align the shaft center, and ensure smooth rotor operation.

[0062] Step 4: Connect the stator of the power turbine unit to the stator interface of the gas generator.

[0063] Step 5: After completing all the above steps, remove the remaining components of the clamping system, including the rear clamping unit and the lifting assembly, and clean the work area.

[0064] Finally, after confirming that all interface connections were correct, the external field replacement of the power turbine unit was completed, ensuring the normal operation of the equipment.

[0065] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and all such modifications and variations fall within the scope defined by the appended claims.

Claims

1. An integrated storage, transportation, and replacement device for aero-engine power turbine units, characterized in that, include: A clamping system is used to support and protect the power turbine unit (102) in the storage and transportation state, and to connect the power turbine unit (102) to the gas generator (101) in the field replacement state; The clamping system includes: The front clamping assembly (203) is connected to the stator (202) of the power turbine unit and is used to provide axial and radial support for the power turbine unit; The rear clamping assembly (205) is connected to the stator of the power turbine unit and is used to cooperate with the gas generator (101) to achieve centering and axial clamping during field replacement; The lifting assembly (204) is connected to the front clamping assembly (203) and the rear clamping assembly (205) to provide overall lifting functionality; The auxiliary clamping assembly (206), in conjunction with the rear clamping assembly (205), is used to limit the relative displacement between the rotor (201) of the power turbine unit and the stator (202) of the power turbine unit in the storage and transportation state.

2. The integrated storage, transportation, and replacement device for aero-engine power turbine units according to claim 1, characterized in that, The auxiliary clamping assembly (206) and the rear clamping assembly (205) are arranged on the front and rear sides of the rotor interface plate (2011) of the power turbine unit rotor (201) and clamp the rotor interface plate (2011) to limit the power turbine unit rotor (201).

3. The integrated storage, transportation, and replacement device for aero-engine power turbine units according to claim 2, characterized in that, The auxiliary clamping assembly (206) includes: The limiting member (602) is connected to the rear clamping assembly (205) and abuts against the front end of the rotor interface plate (2011); The first buffer (601) is disposed between the rear clamping assembly (205) and the rotor interface plate (2011) to absorb the impact load during storage and transportation.

4. The integrated storage, transportation, and replacement device for aero-engine power turbine units according to claim 2, characterized in that, The rear clamping assembly (205) includes: The composite clamping frame is connected to the stator (202) of the power turbine unit and the hoisting assembly (204); The clamping structure is set on the composite clamping frame and abuts against the rear end of the rotor interface plate (2011) of the power turbine unit rotor (201).

5. The integrated storage, transportation, and replacement device for aero-engine power turbine units according to claim 4, characterized in that, The composite clamping frame includes: Center tube (503); Multiple connecting spokes (502) are arranged at intervals along the outer wall of the central cylinder (503); Multiple annular flange stops (501) are respectively provided at the ends of the connecting spokes (502). The annular flange stops (501) are connected to the power turbine unit stator (202) and the hoisting assembly (204) through the first detachable connector.

6. The integrated storage, transportation, and replacement device for aero-engine power turbine units according to claim 5, characterized in that, The clamping structure includes: The clamping claw ring includes a claw plate (504) and a sliding cylinder (505) connected therebetween. The sliding cylinder (505) is sleeved on the outer periphery of the central cylinder (503) and is capable of moving axially. The clamping nut (506) is threadedly engaged with the center cylinder (503) and is used to push the clamping claw ring to move axially to clamp the rotor interface plate (2011) of the power turbine unit rotor (201).

7. The integrated storage, transportation, and replacement device for aero-engine power turbine units according to claim 5, characterized in that, The rear clamping assembly (205) further includes a centering structure, the centering structure comprising: A spherical tie rod (507) is distributed around the center tube (503) and a spherical pad (508) is provided at one end. The pad nut (509) is threaded into the spherical tie rod (507) and is used to push the spherical pad (508) to make the central cylinder (503) bulge radially and press against the inner wall of the gas generator (101).

8. The integrated storage, transportation, and replacement device for aero-engine power turbine units according to claim 1, characterized in that, The hoisting assembly (204) includes: The main beam (402) has a front flange (401) and a rear flange (403) at both ends, respectively. The front flange (401) is connected to the front clamping assembly (203), and the rear flange (403) is connected to the rear clamping assembly (205). The lifting ring (404) is mounted on the main beam (402) and is rotatable, and is used to connect lifting equipment.

9. The integrated storage, transportation, and replacement device for aero-engine power turbine units according to claim 1, characterized in that, The front clamping assembly (203) includes: The disc support cylinder (302) contacts the front end of the power turbine unit rotor (201) and provides radial and axial limiting for the front end of the power turbine unit rotor (201). The end cap (303) is fixedly connected to the disk support cylinder (302) and connected to the stator (202) of the power turbine unit through a second detachable connector.

10. The integrated storage, transportation, and replacement device for aero-engine power turbine units according to claim 9, characterized in that, The end cap (303) is disposed in the middle of the outer wall of the disk support cylinder (302) so that an angle is formed between the end cap (303) and the disk support cylinder (302), and the angle limits the front end of the power turbine unit rotor (201); And / or, a second buffer (301) is also provided between the disc support cylinder (302) and the front end of the power turbine unit rotor (201). And / or, a reinforcing rib (304) is provided between the disc support cylinder (302) and the end cap (303).

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