An assembly device and method for a turbine bucket of an aeroengine

Abstract

This invention provides an assembly device and method for an aero-engine turbine baffle, relating to the field of aero-engine assembly technology. The device includes: a frame assembly comprising a base plate with fixed columns on the base plate and a long crossbeam between the columns, with a support plate at the top of each column; a mandrel assembly and a tubular support, the support being fixed to the long crossbeam; the mandrel assembly comprising a steel pipe, the bottom end of which is fixed in the support, and the top end of which passes through the support plate; an annular positioning seat and an annular turbine disk pressure plate, the positioning seat having a positioning groove for assembling the turbine disk; the turbine disk pressure plate being pressed and fixed onto the turbine disk; and a retaining ring assembly, a turbine elastic retaining ring, and a clamping assembly. This invention solves the technical problem of the retaining ring not being able to be quickly tightened in confined spaces, achieving rapid tightening of the retaining ring within 30 seconds, thus improving effective assembly time and assembly success rate.

Description

Technical Field

[0001] This invention relates to the field of aero-engine assembly technology, and more specifically to an assembly device and method for aero-engine turbine baffles. Background Technology

[0002] The turbine is a core component of the engine structure. New generation aero engines often adopt measures such as simplifying the structure, reducing weight, and increasing temperature and speed to improve engine performance and efficiency, but this also brings great difficulties and challenges to the engine assembly process.

[0003] A turbine disk assembly for a certain type of engine consists of a turbine disk, turbine blades, front and rear turbine baffles, and an open-end retaining ring. The front and rear baffles are installed at the intake and exhaust ends of the turbine disk, respectively, to secure the turbine blades mounted in the tenon grooves on the turbine disk rim. The assembly structure of the turbine disk and the front and rear baffles employs a large interference fit in both radial and axial directions. The front and rear baffles are secured and protected by the spring-loaded release of the retaining ring, which has an open structure installed between the baffles and the turbine disk. The release of the retaining ring requires applying a significant external force along the perpendicular surface of the front and rear baffles to deform them. During assembly, the low-pressure turbine disk is heated, and the front and rear baffles are then frozen separately. The front and rear baffles and the retaining ring are then quickly installed onto the heated low-pressure turbine disk, and pressure is applied to deform the baffles, causing the retaining ring to spring open.

[0004] Assembly process for the baffle and elastic retaining ring: Installing the rear baffle and elastic retaining ring: Install the turbine disc onto the device → Heat the turbine disc → Refrigerate the turbine rear baffle → Install the elastic retaining ring onto the turbine disc → Tighten the elastic retaining ring → Install the turbine rear baffle → Apply pressure to the rear baffle → The elastic retaining ring springs open. Installing the front baffle and elastic retaining ring: Heat the turbine disc → Refrigerate the turbine front baffle → Install the elastic retaining ring onto the turbine disc → Tighten the elastic retaining ring → Install the turbine front baffle → Apply pressure to the front baffle → The elastic retaining ring springs open.

[0005] The turbine disk and front and rear baffles are characterized by high material rigidity, large interference fit, structural inconvenience in applying force, and limited operating space. Currently, there is a lack of effective assembly methods for assembling such turbines with large interference fits, resulting in common problems such as short effective temperature difference operating time, baffle seizure, insufficient axial elastic deformation, difficulty in opening the elastic retaining ring, repeated disassembly and assembly, low assembly success rate, and long cycle time. Summary of the Invention

[0006] In view of this, the present application provides an assembly device and assembly method for turbine baffles of aero-engines. It adopts temperature difference assembly technology, slider-type mechanical retaining ring tightening mechanism and hydraulic clamping technology, which solves the technical problems of difficulty in tightening retaining rings in narrow spaces, low baffle assembly success rate, difficulty in elastic deformation of baffles causing retaining rings to fail to pop out, low assembly efficiency and difficulty in ensuring quality.

[0007] This application provides the following technical solution: an assembly device for an aircraft engine turbine baffle, comprising:

[0008] A frame assembly, the frame assembly including a base plate, uprights fixed on the base plate, long crossbeams arranged between the uprights, and a support plate arranged at the top of the uprights;

[0009] A mandrel assembly and a tubular support, the support being fixed to the long crossbeam, the mandrel assembly including a steel pipe, the bottom end of the steel pipe being fixed in the support, and the top end of the steel pipe passing through the support plate;

[0010] It also includes a circular positioning seat and a circular turbine disk pressure plate. The positioning seat is sleeved on the steel pipe and fixedly assembled on the support plate. The positioning seat has a positioning groove for assembling the turbine disk. The turbine disk pressure plate is sleeved on the steel pipe and is pressed and fixed on the turbine disk by a nut on the steel pipe.

[0011] It also includes a retaining ring assembly, which includes a disc-shaped support sleeve that is detachably fixed to the top of the steel pipe. The support sleeve has multiple L-shaped support plates evenly arranged radially from the center to the edge. The retaining ring assembly also includes a retaining plate, which is movably connected to the vertical section of the support plate through an adjustment mechanism, allowing the retaining plate to move relative to the support plate. The bottom end of the retaining plate is conical.

[0012] It also includes a turbine elastic retaining ring, which is installed at the baffle assembly of the turbine disk. The bottom end of the retaining plate is located on the outer ring of the turbine elastic retaining ring. The distance between the retaining plate and the support plate is reduced by the adjustment mechanism, so that the bottom end of the retaining plate pushes the turbine elastic retaining ring to quickly retract towards the center, thereby leaving a gap between the turbine elastic retaining ring and the turbine disk for installing the turbine baffle.

[0013] It also includes a clamping assembly, which includes a pressure plate detachably fixed to the top of the steel pipe. A pressure ring is vertically fixed to the edge of the pressure plate, and the bottom end of the pressure ring presses against the turbine baffle. The clamping assembly also includes a jack assembly, which is mounted above the pressure plate and is used to apply pressure to the turbine baffle through the pressure ring. This causes the turbine baffle to deform and create a gap, allowing the turbine elastic retaining ring to spring open freely from the gap and engage between the turbine disk and the turbine baffle, thus completing the assembly of the turbine baffle.

[0014] According to one embodiment of this application, the opening position of the turbine elastic retaining ring coincides with the 0 position of the turbine disk.

[0015] According to one embodiment of this application, the adjustment mechanism includes a screw and a nut that cooperate with each other, and the vertical section of the support plate is movably connected to the clamping plate through the screw to adjust the distance between the clamping plate and the support plate.

[0016] According to one embodiment of this application, the support includes a tubular fixing seat, the bottom edge of which extends outward to form a fixing outer ring, which is fixed to the long crossbeam to fix the support.

[0017] According to one embodiment of this application, the jack assembly includes a shim ring mounted on the top of the steel pipe above the pressure plate, an adapter shaft sleeved inside the shim ring, a jack mounted on the top of the adapter shaft, and a nut mounted on the top of the jack for fixation.

[0018] According to one embodiment of this application, the jack is a hollow hydraulic jack and is used in conjunction with a manual hydraulic pump.

[0019] According to one embodiment of this application, the frame assembly further includes a roller and a locking device, the roller and the locking device being respectively mounted on the base plate to realize the movement and locking of the frame assembly.

[0020] According to one embodiment of this application, the frame assembly further includes a handrail fixed to the upright and a pad fixed to the long crossbeam, the support is fixed to the pad, and a storage box is also provided on the long crossbeam.

[0021] The present invention also provides an assembly method for an aircraft engine turbine baffle, applied to the assembly device for an aircraft engine turbine baffle as described above, comprising:

[0022] The positioning seat, support and spindle assembly are fixedly installed on the frame assembly, the turbine disk is installed on the positioning seat, and the turbine disk pressure plate is pressed and fixed on the turbine disk by the nut on the steel pipe;

[0023] The installed chassis assembly with turbine disc is sent to a heating furnace for heating at 200°C for at least 15 minutes. At the same time, the turbine baffle is placed in dry ice for cooling for at least 30 minutes.

[0024] Remove the frame assembly from the heating furnace, install the turbine elastic retaining ring on the baffle assembly of the turbine disk, and then install the retaining ring assembly on the top of the steel pipe, so that the bottom end of the retaining plate is located on the outer ring of the turbine elastic retaining ring. By adjusting the adjustment mechanism, reduce the distance between the retaining plate and the support plate, so that the bottom end of the retaining plate pushes the turbine elastic retaining ring to quickly retract towards the center, thereby leaving a gap between the turbine elastic retaining ring and the turbine disk for installing the turbine baffle.

[0025] Remove the turbine baffle from the dry ice and quickly install it into the gap;

[0026] Remove the retaining ring assembly and install the clamping assembly at the top of the steel pipe, so that the bottom end of the pressure ring presses against the turbine baffle. Apply pressure to the turbine baffle through the jack assembly and the pressure ring, so that the turbine baffle deforms and creates a gap, allowing the turbine elastic retaining ring to spring freely out from the gap and snap into the turbine disk and the turbine baffle, thus completing the assembly of the turbine baffle.

[0027] According to one embodiment of this application, the assembly process of the turbine baffle is further comprising: first completing the assembly process of the turbine rear baffle, and then completing the assembly process of the turbine front baffle; wherein, when assembling the turbine rear baffle, the hub of the turbine disk is placed upward, and when assembling the turbine front baffle, the hub of the turbine disk is placed downward.

[0028] Compared with the prior art, the beneficial effects that at least one technical solution adopted in the embodiments of this specification can achieve include at least:

[0029] 1. The snap ring assembly and operation method of this invention solve the technical problem that snap rings cannot be tightened quickly in narrow spaces, and achieves rapid tightening of snap rings within 30 seconds, thereby improving the effective assembly time and achieving a 100% assembly success rate.

[0030] 2. The embodiments of this invention employ a jack structure, solving the technical problem of difficult elastic deformation of rigid structures. It achieves continuously adjustable pressure from 0 to 30 tons, reducing labor intensity by over 90% and increasing assembly efficiency by over 70%.

[0031] 3. The embodiments of the present invention integrate multiple functions of the device, reducing the number of repetitive installation and positioning and component installations, saving operation waiting time, and significantly improving work efficiency. Attached Figure Description

[0032] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0033] Figure 1 This is a front view of the assembly device of the present invention in the state of retracted elastic retaining ring;

[0034] Figure 2 This is a front view of the assembly device of the present invention in the state of pressing the turbine baffle;

[0035] Figure 3 This is a schematic diagram of the assembly of the turbine disk, turbine baffle and elastic retaining ring in the assembly device of this embodiment of the invention;

[0036] Figure 4a This is a front view of the frame assembly structure in the assembly device of this embodiment of the invention;

[0037] Figure 4b This is a top view of the frame assembly structure in the assembly device of this invention embodiment;

[0038] Figure 5a This is a front view of the support structure in the assembly device of this embodiment of the invention;

[0039] Figure 5b This is a top view of the support structure in the assembly device of this embodiment of the invention;

[0040] Figure 6a This is a front view of the positioning seat structure in the assembly device of this embodiment of the invention;

[0041] Figure 6b This is a top view of the positioning seat structure in the assembly device of this invention embodiment;

[0042] Figure 7 This is a top view of the pressure plate structure in the assembly device of this invention embodiment;

[0043] Figure 8 This is a schematic diagram of the central shaft assembly structure of the assembly device according to an embodiment of the present invention;

[0044] Figure 9a This is a front view of the card retractor assembly in the assembly device of this embodiment of the invention;

[0045] Figure 9b This is a top view of the retractable ring assembly in the assembly device of this embodiment of the invention;

[0046] Figure 10 This is a schematic diagram of the wheel seat structure in the assembly device of this invention embodiment;

[0047] Figure 11 This is a schematic diagram of the adapter shaft structure in the assembly device of this invention embodiment;

[0048] Figure 12 This is a schematic diagram of the clamping component structure in the assembly device of this invention embodiment;

[0049] in, Figure 1 , Figure 2 , Figure 3In the middle, 1-frame assembly, 2-support, 3-first screw, 4-first positioning seat, 5-first pressure plate, 6-spindle assembly, 7-adjusting shim, 8-retractable retaining ring assembly, 9-second pressure plate, 10-second positioning seat, 11-first nut, 12-double-ended bolt, 13-set screw, 14-quick release pin, 15-first pin, 16-fine steel wire rope, 17-second nut, 18-wheel seat, 19-bearing, 20-pin, 21-moving handle clamping screw, 22-second pin, 23-support block, 24-lifting eye screw, 25-fourth nut, 26-adapter shaft, 27-elevating ring, 28-clamping assembly, 29-jack, Ⅰ-turbo disc, Ⅱ-elastic retaining ring at the rear panel, Ⅲ-elastic retaining ring at the front panel, Ⅳ-rear panel, Ⅴ-front panel;

[0050] Figure 4a and Figure 4b In the middle, 101-handrail, 201-base plate, 301-column, 401-storage box, 501-support plate, 601-pad plate, 701-long crossbeam;

[0051] Figure 8 In the middle, 102-first support block, 202-steel pipe, 302-fifth nut, 402-second support block;

[0052] Figure 9a In the middle, 103-support sleeve, 203-support plate, 303-fourth pin, 403-clamping plate, 503-third pin, 603-third nut, 703-screw;

[0053] Figure 12 In the middle, 104-lower pressure plate, 204-pressure ring, 304-second screw, 404-fifth pin. Detailed Implementation

[0054] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0055] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0056] like Figure 1As shown, an embodiment of the present invention provides an assembly device for an aircraft engine turbine baffle, comprising:

[0057] The frame assembly 1 includes a base plate 201, on which columns 301 are fixed, and a long crossbeam 701 is arranged between the columns 301. A support plate 501 is arranged at the top of the columns 301.

[0058] The mandrel assembly 6 and the tubular support 2 are fixed to the long crossbeam 701. The mandrel assembly 6 includes a steel pipe 202, the bottom end of which is fixed in the support 2, and the top end of which passes through the support plate 501. In a specific implementation, the mandrel assembly 6 also includes a first support block 102 and a second support block 402 disposed on the steel pipe 202. The structure of the mandrel assembly 6 is as follows: Figure 8 As shown;

[0059] It also includes an annular positioning seat (the positioning seat includes a first positioning seat 4 for the turbine rear baffle and a second positioning seat 10 for the turbine front baffle) and an annular turbine disk pressure plate (the turbine disk pressure plate includes a first pressure plate 5 for the turbine rear baffle IV and a second pressure plate 9 for the turbine front baffle V). The positioning seat is sleeved on the steel pipe 202 and fixedly assembled on the support plate 501. The positioning seat has a positioning groove for assembling the turbine disk I. The turbine disk pressure plate is sleeved on the steel pipe 202 and is pressed and fixed on the turbine disk I by the fifth nut 302 on the steel pipe 202. The structure of the positioning seat is as follows: Figure 6a and Figure 6b As shown, the structure of the pressure plate is as follows: Figure 7 As shown;

[0060] It also includes a retaining ring assembly 8, which includes a disc-shaped support sleeve 103. The support sleeve 103 is detachably fixed to the top of the steel pipe 202, and an adjusting pad 7 is provided between the support sleeve 103 and the steel pipe 202. Multiple L-shaped support plates 203 are evenly arranged radially from the center to the edge of the support sleeve 103. The retaining ring assembly 8 also includes a retaining plate 403. The retaining plate 403 is movably connected to the vertical section of the support plate 203 through an adjusting mechanism and a fourth pin 303 and a third pin 503, allowing the retaining plate 403 to move relative to the support plate 203. The bottom end of the retaining plate 403 is conical. The structure of the retaining ring assembly 8 is as follows: Figure 9a and Figure 9b As shown;

[0061] It also includes a turbine elastic retaining ring (the turbine elastic retaining ring includes an elastic retaining ring II for the rear baffle IV and an elastic retaining ring III for the front baffle V), the turbine elastic retaining ring is installed at the baffle assembly of the turbine disk I, the bottom end of the retaining plate 403 is located at the outer ring of the turbine elastic retaining ring, and the distance between the retaining plate 403 and the support plate 203 is reduced by the adjustment mechanism, so that the bottom end of the retaining plate 403 pushes the turbine elastic retaining ring to quickly retract towards the center, so as to leave a gap between the turbine elastic retaining ring and the turbine disk I for installing the turbine baffle;

[0062] It also includes clamping assembly 28, such as Figure 12 As shown, the clamping assembly 28 includes a lower pressure plate 104, which is detachably fixed to the top of the steel pipe 202. The edge of the lower pressure plate 104 is vertically fixed to the pressure ring 204 by a second screw 304 and a fifth pin 404. The bottom end of the pressure ring 204 presses against the turbine baffle (the turbine baffle includes a rear baffle IV and a front baffle V). The clamping assembly 28 also includes a jack assembly, which is mounted above the lower pressure plate 104 and is used to apply pressure to the turbine baffle through the pressure ring 204, causing the turbine baffle to deform and create a gap. This allows the turbine elastic retaining ring to spring freely out from the gap and engage between the turbine disk I and the turbine baffle, thus completing the assembly of the turbine baffle.

[0063] In this embodiment, the opening position of the turbine elastic retaining ring coincides with the 0 position of the turbine disk I.

[0064] In a specific implementation, the adjustment mechanism includes a screw 703 and a third nut 603 that cooperate with each other. The vertical section of the support plate 203 is movably connected to the clamping plate 403 through the screw 703 to adjust the distance between the clamping plate 403 and the support plate 203.

[0065] In specific implementation, the support 2 includes a tubular fixing seat, the bottom edge of which extends outward to form a fixing outer ring. The fixing outer ring is fixed to the long crossbeam 701 to fix the support 2, such as... Figure 5a and Figure 5b As shown.

[0066] In specific implementation, the jack assembly includes a shim ring 27 mounted on the top of the steel pipe 202 above the pressure plate. An adapter shaft 26 is sleeved inside the shim ring 27. A jack 29 is mounted on the top of the adapter shaft 26, and a fourth nut 25 is fitted onto the top of the jack 29 for fixation. The structure of the adapter shaft 26 is as follows: Figure 11 As shown.

[0067] In practical implementation, the jack 29 is a hollow hydraulic jack and is used in conjunction with a manual hydraulic pump.

[0068] In a specific implementation, the frame assembly 1 further includes a roller and a locking device, which are respectively mounted on the base plate 201 to realize the movement and locking of the frame assembly 1. The roller includes a wheel seat 18 mounted on the base plate 201, and the wheel seat 18 is assembled using a second nut 17, a bearing 19, and a pin 20. The structure of the wheel seat 18 is as follows: Figure 10 As shown; the locking device includes a movable handle clamping screw 21 mounted on the base plate 201, and a support block 23 is provided at the bottom end of the movable handle clamping screw 21. The support block 23 is fixed by a second pin 22. The frame assembly 1 can be easily moved by the rollers and the locking device.

[0069] In a specific implementation, the frame assembly 1 also includes a handrail 101 fixed to the upright 301 and a pad 601 fixed to the long crossbeam 701. The support 2 is fixed to the pad 601 by a first screw 3 and a first pin 15. A storage box 401 is also provided on the long crossbeam 701. Figure 4a and Figure 4b As shown.

[0070] The present invention also provides an assembly method for an aircraft engine turbine baffle, applied to the assembly device for an aircraft engine turbine baffle as described above, comprising:

[0071] The positioning seat, support 2 and spindle assembly 6 are respectively fixedly installed on the frame assembly 1. The turbine disk I is installed on the positioning seat. The turbine disk pressure plate is pressed and fixed on the turbine disk I by the fifth nut 302 on the steel pipe 202.

[0072] The installed chassis assembly with turbine disc is sent to a heating furnace for heating at 200°C for at least 15 minutes. At the same time, the turbine baffle is placed in dry ice for cooling for at least 30 minutes.

[0073] Remove the frame assembly from the heating furnace, install the turbine elastic retaining ring on the baffle assembly of the turbine disk, and then install the retaining ring assembly 8 on the top of the steel pipe 202, so that the bottom end of the retaining plate 403 is located on the outer ring of the turbine elastic retaining ring. By adjusting the adjusting mechanism, reduce the distance between the retaining plate 403 and the support plate 203, so that the bottom end of the retaining plate 403 pushes the turbine elastic retaining ring to quickly retract towards the center, thereby leaving a gap between the turbine elastic retaining ring and the turbine disk for installing the turbine baffle.

[0074] Remove the turbine baffle from the dry ice and quickly install it into the gap;

[0075] Remove the retaining ring assembly 8, install the clamping assembly 28 on the top of the steel pipe 202, press the bottom end of the pressure ring 204 onto the turbine baffle, apply pressure to the turbine baffle through the jack assembly and the pressure ring 204, causing the turbine baffle to deform and create a gap, allowing the turbine elastic retaining ring to spring freely out from the gap and snap into the turbine disk and the turbine baffle, thus completing the assembly of the turbine baffle.

[0076] According to one embodiment of this application, the assembly process of the turbine baffle is further comprising: first completing the assembly process of the turbine rear baffle, and then completing the assembly process of the turbine front baffle; wherein, when assembling the turbine rear baffle, the hub of the turbine disk is placed upward, and when assembling the turbine front baffle, the hub of the turbine disk is placed downward.

[0077] In this embodiment, the structure of the device for assembling the turbine baffle of the aero-engine is as follows: Figure 1 , Figure 2 As shown, the device consists of 29 components, including a frame assembly, support, positioning seat, retaining ring assembly, and clamping assembly. The turbine disk assembly comprises a turbine disk, turbine blades, front and rear turbine baffles, and elastic retaining rings. The assembly structure of the turbine disk and baffles uses a radial and axial bidirectional large interference fit connection. The front and rear baffles are fixed and secured by the spring-loaded elastic retaining rings with an opening structure installed between the baffles and the turbine disk. Figure 3 As shown.

[0078] This device is used to realize a series of functions and actions such as installing and tightening the open elastic retaining ring, installing the front and rear baffles, deforming the baffles, and opening the open elastic retaining ring, so as to complete the rapid assembly of the front and rear baffles of the turbine.

[0079] In specific implementation, (1) the first positioning seat 4 and the spindle assembly 6 are first installed on the frame assembly 1. The positioning seat is fixed with the first nut 11, the double-ended bolt 12 and the set screw 13. The spindle assembly 6 is fixed with the quick-release pin 14, the support 2 and the frame. The quick-release pin 14 is tied with a thin steel wire rope 16. The other end of the thin steel wire rope 16 is tied to the frame assembly 1 to prevent the quick-release pin 14 from being lost.

[0080] (2) Then install the turbine disk I onto the positioning seat. Since the assembly of the end baffle is required beforehand according to process needs in this embodiment, the turbine disk should be placed upwards. Figure 1 As shown. The turbine disk I is positioned and secured using the first pressure plate 5 and the fifth nut 302 on the spindle assembly 6;

[0081] (3) Push the chassis assembly with turbine disc into the heating furnace for heating at 200°C and keep it warm for no less than 15 minutes. At the same time, put the turbine rear baffle into dry ice for cooling for no less than 30 minutes.

[0082] (4) Remove the frame assembly with turbine disc from the heating furnace, and install the elastic retaining ring II at the rear baffle onto the turbine disc. According to process requirements, the opening position of the elastic retaining ring coincides with the 0 position of the turbine disc. Install the retaining ring assembly 8 on the frame assembly, and then manually move the 12 third nuts 603. Through the sliding of the retaining plate 403, the elastic retaining ring is quickly retracted towards the center, so that the outer diameter of the elastic retaining ring is flush with the boss that mates with the upper baffle of the turbine disc, thus allowing for the assembly space of the turbine rear baffle. The retaining plate with a sliding structure makes the operation quick and easy.

[0083] (5) Remove the turbine backplate from the dry ice and quickly install it onto the turbine disc;

[0084] (6) Remove the retaining ring assembly 8, and install the adapter shaft 26, the clamping assembly 28, the shim ring 27, the jack 29 and the fourth nut 25 in sequence;

[0085] (7) Apply a pressure of (12-15)T to deform the rear baffle, ensuring sufficient space for the elastic retaining ring to spring open freely. After the elastic retaining ring springs open, release the hydraulic pressure of the jack. The elastic retaining ring will then be locked between the turbine disc and the rear baffle, serving to fix and secure the rear baffle. In this embodiment, the jack used is an RCH-302 hollow hydraulic jack, which is used in conjunction with a manual hydraulic pump (model and specifications are not limited). It can provide a continuously adjustable pressure of (0-30)T. The hollow structure is beneficial for improving and optimizing the structural layout of the pressure application device.

[0086] (8) After the baffle is assembled, the front baffle is then assembled. To do this, the fourth nut 25, jack 29, shim ring 27, clamping assembly 28, adapter shaft 26 and spindle assembly 6 must be removed first.

[0087] (9) Lift the turbine disk by lifting eye bolt 24, remove the first positioning seat 4, replace it with the second positioning seat 10, rotate the turbine disk with the rear baffle 180° and install it on the assembly clamp, with the hub facing down, and use the second pressure plate 9 to fasten the turbine disk.

[0088] Install the elastic retaining ring III and the turbine front baffle according to the methods described in (3) to (9) above.

[0089] The assembly device and method of this invention solve the technical problem of rapid tightening of retaining rings in confined spaces, achieving rapid tightening of retaining rings within 30 seconds, thus improving effective assembly time and achieving a 100% assembly success rate. This invention employs a jack structure, overcoming the technical challenge of difficult elastic deformation of rigid structures. It achieves continuously adjustable pressure from 0 to 30 tons, reducing labor intensity by over 90% and increasing assembly efficiency by over 70%. This invention integrates multiple functions of the device, reducing the number of repetitive installation and positioning steps and the number of parts installations, saving operation waiting time and significantly improving work efficiency.

[0090] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An assembly device for an aircraft engine turbine baffle, characterized in that, include: A frame assembly, the frame assembly including a base plate, uprights fixed on the base plate, long crossbeams arranged between the uprights, and a support plate arranged at the top of the uprights; A mandrel assembly and a tubular support, the support being fixed to the long crossbeam, the mandrel assembly including a steel pipe, the bottom end of the steel pipe being fixed in the support, and the top end of the steel pipe passing through the support plate; It also includes a circular positioning seat and a circular turbine disk pressure plate. The positioning seat is sleeved on the steel pipe and fixedly assembled on the support plate. The positioning seat has a positioning groove for assembling the turbine disk. The turbine disk pressure plate is sleeved on the steel pipe and is pressed and fixed on the turbine disk by a nut on the steel pipe. It also includes a retaining ring assembly, which includes a disc-shaped support sleeve that is detachably fixed to the top of the steel pipe. The support sleeve has multiple L-shaped support plates evenly arranged radially from the center to the edge. The retaining ring assembly also includes a retaining plate, which is movably connected to the vertical section of the support plate through an adjustment mechanism, allowing the retaining plate to move relative to the support plate. The bottom end of the retaining plate is conical. It also includes a turbine elastic retaining ring, which is installed at the baffle assembly of the turbine disk. The bottom end of the retaining plate is located on the outer ring of the turbine elastic retaining ring. The distance between the retaining plate and the support plate is reduced by the adjustment mechanism, so that the bottom end of the retaining plate pushes the turbine elastic retaining ring to quickly retract towards the center, thereby leaving a gap between the turbine elastic retaining ring and the turbine disk for installing the turbine baffle. It also includes a clamping assembly, which includes a pressure plate detachably fixed to the top of the steel pipe. A pressure ring is vertically fixed to the edge of the pressure plate, and the bottom end of the pressure ring presses against the turbine baffle. The clamping assembly also includes a jack assembly, which is mounted above the pressure plate and is used to apply pressure to the turbine baffle through the pressure ring. This causes the turbine baffle to deform and create a gap, allowing the turbine elastic retaining ring to spring open freely from the gap and engage between the turbine disk and the turbine baffle, thus completing the assembly of the turbine baffle.

2. The assembly device for an aircraft engine turbine baffle according to claim 1, characterized in that, The opening position of the turbine elastic retaining ring coincides with the 0 position of the turbine disk.

3. The assembly device for an aircraft engine turbine baffle according to claim 1, characterized in that, The adjustment mechanism includes a screw and a nut that cooperate with each other. The vertical section of the support plate is movably connected to the clamping plate through the screw to adjust the distance between the clamping plate and the support plate.

4. The assembly device for an aircraft engine turbine baffle according to claim 1, characterized in that, The support includes a tubular fixing seat, the bottom edge of which extends outward to form a fixing outer ring, which is fixed to the long crossbeam to fix the support.

5. The assembly device for an aircraft engine turbine baffle according to claim 1, characterized in that, The jack assembly includes a shim ring mounted on the top of the steel pipe above the pressure plate, an adapter shaft sleeved inside the shim ring, a jack mounted on the top of the adapter shaft, and a nut mounted on the top of the jack for fixation.

6. The assembly device for an aircraft engine turbine baffle according to claim 5, characterized in that, The jack is a hollow hydraulic jack and is used in conjunction with a manual hydraulic pump.

7. The assembly device for an aircraft engine turbine baffle according to claim 1, characterized in that, The frame assembly also includes rollers and locking devices, which are respectively mounted on the base plate to enable movement and locking of the frame assembly.

8. The assembly device for an aircraft engine turbine baffle according to claim 1, characterized in that, The frame assembly also includes a handrail fixed to the upright and a pad fixed to the long crossbeam. The support is fixed to the pad, and a storage box is also provided on the long crossbeam.

9. A method for assembling a turbine baffle for an aircraft engine, applied to the assembly apparatus for an aircraft engine turbine baffle as described in any one of claims 1 to 8, characterized in that, include: The positioning seat, support and spindle assembly are fixedly installed on the frame assembly, the turbine disk is installed on the positioning seat, and the turbine disk pressure plate is pressed and fixed on the turbine disk by the nut on the steel pipe; The installed chassis assembly with turbine disc is sent to a heating furnace for heating at 200°C for at least 15 minutes. At the same time, the turbine baffle is placed in dry ice for cooling for at least 30 minutes. Remove the frame assembly from the heating furnace, install the turbine elastic retaining ring on the baffle assembly of the turbine disk, and then install the retaining ring assembly on the top of the steel pipe, so that the bottom end of the retaining plate is located on the outer ring of the turbine elastic retaining ring. By adjusting the adjustment mechanism, reduce the distance between the retaining plate and the support plate, so that the bottom end of the retaining plate pushes the turbine elastic retaining ring to quickly retract towards the center, thereby leaving a gap between the turbine elastic retaining ring and the turbine disk for installing the turbine baffle. Remove the turbine baffle from the dry ice and quickly install it into the gap; Remove the retaining ring assembly and install the clamping assembly at the top of the steel pipe, so that the bottom end of the pressure ring presses against the turbine baffle. Apply pressure to the turbine baffle through the jack assembly and the pressure ring, so that the turbine baffle deforms and creates a gap, allowing the turbine elastic retaining ring to spring freely out from the gap and snap into the turbine disk and the turbine baffle, thus completing the assembly of the turbine baffle.

10. The assembly method for an aero-engine turbine baffle according to claim 9, characterized in that, Also includes: During the assembly of the turbine baffle, the assembly of the turbine rear baffle is completed first, followed by the assembly of the turbine front baffle. When assembling the turbine rear baffle, the hub of the turbine disk is placed upwards, and when assembling the turbine front baffle, the hub of the turbine disk is placed downwards.

Images