CN221048342U - Turbine disk shaft disassembling tool for aviation auxiliary power device - Google Patents
Turbine disk shaft disassembling tool for aviation auxiliary power device Download PDFInfo
- Publication number
- CN221048342U CN221048342U CN202323067688.9U CN202323067688U CN221048342U CN 221048342 U CN221048342 U CN 221048342U CN 202323067688 U CN202323067688 U CN 202323067688U CN 221048342 U CN221048342 U CN 221048342U
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- turbine
- shaft
- auxiliary power
- transmission structure
- turbine disc
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- 230000005540 biological transmission Effects 0.000 claims abstract description 76
- 230000002093 peripheral effect Effects 0.000 claims description 5
- 238000000746 purification Methods 0.000 abstract 1
- 239000002184 metal Substances 0.000 description 6
- 238000000034 method Methods 0.000 description 6
- 230000000694 effects Effects 0.000 description 5
- 238000013461 design Methods 0.000 description 4
- 238000009434 installation Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model discloses a turbine disc shaft disassembling tool for an aviation auxiliary power device, relates to the technical field of plate purification, and can solve the problem that parts are easy to damage when a primary turbine disc and a turbine shaft are directly disassembled in a knocking mode at present. The utility model discloses a turbine disc shaft disassembling tool for an aviation auxiliary power device, which comprises a lock shaft component for locking and fixing a turbine shaft and a transmission structure for driving the lock shaft component to rotate; the device also comprises a limiting structure for limiting the rotation of the turbine disk, wherein the limiting structure is sleeved on the transmission structure and is in spiral connection with the transmission structure; the lock shaft member is detachably and fixedly connected with the transmission structure.
Description
Technical Field
The utility model relates to the technical field of aviation auxiliary power devices, in particular to a turbine disc shaft disassembling tool for an aviation auxiliary power device.
Background
The aviation auxiliary power device consists of a power section, a load compressor and an accessory gearbox. Because of the importance of aviation products, the aviation products need to be issued for cleaning, disassembly, repair, testing and other procedures every time a certain period of operation or unqualified performance is achieved. Only after finishing various maintenance works and confirming that the performance of the APU meets the continuous navigable requirements, the APU can be reinstalled on the aircraft and then put into use.
In the maintenance process of the whole auxiliary power device, the situation that two matched parts are difficult to disassemble frequently occurs in the disassembly process. When the hot end component of the power section is decomposed, the condition that the primary turbine disc and the turbine shaft are difficult to disassemble by using a conventional method due to metal adhesion caused by long-time high temperature often occurs. If a knocking mode is used, the part is easy to deform or crack.
Based on the background, the inventor designs a turbine disk shaft disassembly tool for an aviation auxiliary power device, which can solve the problem that the first-stage turbine disk and the turbine shaft are easy to deform or crack in the disassembly process due to metal adhesion at high temperature, thereby bringing forward the application.
Disclosure of utility model
The application aims to provide a turbine disc shaft disassembling tool for an aviation auxiliary power device, which is used for solving the problem that parts are easy to damage when a primary turbine disc and a turbine shaft are directly disassembled in a knocking mode and the like at present.
In order to solve the technical problems, the invention adopts the following scheme:
The application relates to a turbine disc shaft disassembling tool for an aviation auxiliary power device, which comprises a lock shaft component for locking and fixing a turbine shaft and a transmission structure for driving the lock shaft component to rotate;
the device also comprises a limiting structure for limiting the rotation of the turbine disk, wherein the limiting structure is sleeved on the transmission structure and is in spiral connection with the transmission structure;
the lock shaft member is detachably and fixedly connected with the transmission structure.
The conception of the application is as follows: through setting up lock axle member, transmission structure and limit structure, and lock axle member and transmission structure fixed connection, limit structure and transmission structure screwed connection, can realize utilizing lock axle member to lock fixed back with the turbine axle, drive transmission structure is rotatory to drive the turbine axle rotation of lock axle member and lock axle member locking, after fixing limit structure, along with transmission structure's rotation, can make limit structure's terminal surface support the pressure turbine dish, realize restricting turbine dish pivoted effect, and along with transmission structure continues to drive the turbine axle rotation, can make appear relative pivoted design conception between turbine dish and the turbine axle, realize the effect that metal adhesion area between turbine dish and the turbine axle is not hard up, solve at present and directly disassemble one-level turbine dish and the problem that the turbine axle damages the part easily with mode such as knocks.
The concept of the application is as follows, and some preferred schemes are as follows:
preferably, the transmission structure comprises a transmission rod for passing through the turbine disc and the turbine shaft;
The transmission rod is provided with external threads matched with the limiting structure.
Preferably, the transmission rod is further provided with a screwing piece for transmitting screwing force, and the screwing piece is located at one side, far away from the lock shaft member, of the limiting structure and is fixedly connected with the transmission rod.
Preferably, the screw comprises a screw nut screwed or welded to an end of the transmission rod remote from the lock shaft member.
Preferably, the limiting structure comprises a limiting sleeve, and an internal thread matched with the transmission structure is arranged in the limiting sleeve.
Preferably, the outer peripheral wall of the limit sleeve is sleeved and fixed with an anti-skid sleeve or carved with anti-skid patterns.
Preferably, the lock shaft member comprises a hoop component for locking and fixing a turbine shaft away from a step on one side of the turbine disc and a mounting seat for mounting the hoop component, and the hoop component is detachably connected with the mounting seat;
the mounting seat is coaxially arranged with the transmission structure and is detachably and fixedly connected with the transmission structure.
Preferably, the hoop assembly comprises two C-shaped hoops which are arranged in a buckling manner, and a slipknot bolt for adjusting the locking force of the hoop assembly on the turbine shaft;
both ends of the two C-shaped hoops are detachably connected and fixed through a slipknot bolt.
Preferably, the mounting seat is disc-shaped;
a semicircular groove matched with the disc-shaped mounting seat is formed in the inner side surface of the C-shaped hoop;
the mounting seat is coaxially arranged with the transmission structure and is detachably and fixedly connected with the transmission structure.
Preferably, the nut of the slipknot bolt adopts a butterfly nut.
The utility model has the beneficial effects that:
According to the application, through the mutual coordination among the lock shaft component, the transmission structure and the limiting structure, one rotation is realized between the turbine shaft and the turbine disc, so that the design concept of relative rotation of the turbine shaft and the turbine disc can be realized, the technical effect that the metal adhesion area of the turbine disc and the turbine shaft is loosened due to slight relative rotation is achieved, and the problem that parts are easy to damage when the first-stage turbine disc and the turbine shaft are directly disassembled by means of knocking and the like in the prior art is effectively solved.
Drawings
FIG. 1 is a schematic diagram of a front view structure of an embodiment of the present application;
FIG. 2 is a schematic perspective view of an embodiment of the present application;
fig. 3 is a schematic front view of the embodiment of the present application in use.
Reference numerals illustrate:
The device comprises a 1-transmission structure, 11-external threads, 12-screwing pieces, 2-lock shaft members, 21-C-shaped hoop surfaces, 22-slipknot bolts, 23-installation seats, 3-limiting structures, 4-turbine discs and 5-turbine shafts.
Detailed Description
The present invention will be described in further detail with reference to examples and drawings, but embodiments of the present invention are not limited thereto.
In the description of the present invention, it should be noted that, directions or positional relationships indicated by terms such as "center", "upper", "lower", "left", "right", "vertical", "longitudinal", "lateral", "horizontal", "inner", "outer", "front", "rear", "top", "bottom", etc., are directions or positional relationships based on those shown in the drawings, or are directions or positional relationships conventionally put in use of the inventive product, are merely for convenience of describing the present invention and for simplifying the description, and are not indicative or implying that the apparatus or element to be referred to must have a specific direction, be constructed and operated in a specific direction, and therefore should not be construed as limiting the present invention.
In the description of the present invention, it should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed," "configured," "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
The invention is described in detail below by reference to the attached drawings and in connection with the embodiments:
As shown in fig. 1 to 3, the present embodiment provides: the utility model provides a turbine disc 4 axle disassemble frock that aviation auxiliary power device used, includes the lock axle component 2 that is used for locking fixed turbine axle 5, and is used for driving the transmission structure 1 that lock axle component 2 rotated;
The device also comprises a limiting structure 3 for limiting the rotation of the turbine disk 4, wherein the limiting structure 3 is sleeved on the transmission structure 1 and is in spiral connection with the transmission structure;
the lock shaft member 2 is detachably and fixedly connected with the transmission structure 1.
The conception of the application is as follows: through setting up lock axle member 2, transmission structure 1 and limit structure 3, and lock axle member 2 and transmission structure 1 fixed connection, limit structure 3 and transmission structure 1 screwed connection, can realize utilizing lock axle member 2 to lock fixed back with turbine axle 5, drive transmission structure 1 rotatory carry out the turbine axle 5 rotation that drives lock axle member 2 and lock axle member 2 locking, after fixing limit structure 3, along with transmission structure 1's rotation, can make limit structure 3's terminal surface press turbine disk 4, realize restricting turbine disk 4 pivoted effect, and along with transmission structure 1 continues to drive turbine axle 5 rotation, can make the design conception of relative rotation appear between turbine disk 4 and the turbine axle 5, realize the effect that the metal adhesion area between turbine disk 4 and the turbine axle 5 is not hard up, solve the problem that the mode such as utilization is knocked down at present directly disassembles one-level turbine disk 4 and turbine axle 5 and damages the part easily.
When the embodiment is used, firstly, the lock shaft member 2 is detached from the transmission structure 1, the lock shaft member 2 is fixed on the step surface of the turbine shaft 5, the connection and fixation of the turbine shaft 5 and the lock shaft member 2 are realized, then, one end of the transmission structure 1, which is close to the lock shaft member 2, passes through the turbine disc 4 and the turbine shaft 5 and is reconnected and fixed with the lock shaft member 2, at the moment, the limit structure 3 or the transmission structure 1 is rotated, the limit structure 3 is pressed on one side, which is far away from the turbine shaft 5, of the turbine disc 4, then, the transmission structure 1 is fixed, the turbine shaft 5 is driven to rotate by screwing the transmission structure 1 by using a spanner, so that relative rotation occurs between the turbine shaft 5 and the turbine disc 4, a metal area between the turbine disc 4 and the turbine shaft 5 is loosened, and then, the turbine disc 4 and the turbine shaft 5 can be easily separated.
The concept of the application is as follows, and some preferred schemes are as follows:
In some preferred exemplary embodiments, the transmission 1 comprises a transmission rod for passing through the turbine disc 4 and the turbine shaft 5;
The transmission rod is provided with external threads 11 which are matched with the limiting structure 3. The transmission rod is connected with the limit structure 3 in a spiral way through an external thread 11 arranged on the transmission rod.
In some preferred exemplary embodiments, the transmission rod is further provided with a screwing piece 12 for transmitting screwing force, and the screwing piece 12 is located on the side of the limiting structure 3 away from the lock shaft member 2 and fixedly connected with the transmission rod. In this embodiment, the screwing part 12 is detachably and fixedly connected with the transmission rod, so that the screwing part 12 can be conveniently replaced after deformation in the screwing process, and in some embodiments, the screwing part 12 and the transmission rod can be fixed by welding.
In some preferred exemplary embodiments, the screw 12 comprises a screw nut screwed or welded to the end of the transmission rod remote from the lock shaft member 2. The screw nut is arranged, so that an operator can conveniently drive the transmission rod to rotate by using tools such as a manual wrench or an electric wrench.
In some preferred exemplary embodiments, the limit structure 3 comprises a limit sleeve, in which an internal thread is provided, adapted to the transmission structure 1. The limit sleeve is in threaded connection with the transmission structure 1, so that the transmission structure 1 is in the rotation process, after the limit sleeve is held, the distance between the limit sleeve and the turbine disc 4 is continuously close until the end part of the limit sleeve is propped against the turbine disc 4, and the rotation of the turbine disc 4 is limited.
In some preferred example embodiments, the outer peripheral wall of the limit sleeve is sleeved and fixed with an anti-slip sleeve or carved with anti-slip patterns. The anti-skid sleeve is provided with the anti-skid sleeve or the anti-skid lines are arranged on the peripheral wall, so that slipping can be avoided when the limit sleeve is held.
In some preferred exemplary embodiments, the lock shaft member 2 includes a hoop assembly for locking and fixing the step of the turbine shaft 5 away from the side of the turbine disc 4, and a mounting seat 23 for mounting the hoop assembly, and the hoop assembly is detachably connected with the mounting seat 23;
The mounting seat 23 is arranged coaxially with the transmission structure 1 and is detachably and fixedly connected with the transmission structure. In this embodiment, the mounting seat 23 and the transmission structure 1 may be connected and fixed in a threaded connection manner, and the mounting seat 23 and the transmission structure 1 may be detachably connected, so that the turbine disk 4 is conveniently mounted between the mounting seat 23 and the limiting structure 3.
In some preferred exemplary embodiments, the hoop assembly comprises two C-shaped hoops 21 arranged in a butt-buckling manner, and a slipknot bolt 22 for adjusting the locking force of the hoop assembly to the turbine shaft 5;
Both ends of the two C-shaped hoops 21 are detachably connected and fixed through a slipknot bolt 22. In this embodiment, two C type staple bolts 21 set up and through the detachable connection of slipknot bolt 22 fixed, can make things convenient for the installation locking of turbine axle 5, the interior perisporium of two C type staple bolts 21 and the circular step looks adaptation of turbine axle 5, and two C type staple bolts 21 are locked through the circular step of turbine axle 5.
In some preferred exemplary embodiments, the mounting base 23 is disc-shaped;
A semicircular groove matched with the disc-shaped mounting seat 23 is formed in the inner side surface of the C-shaped hoop 21;
The mounting seat 23 is arranged coaxially with the transmission structure 1 and is detachably and fixedly connected with the transmission structure. In this embodiment, the two C-shaped hoops 21 are fastened to the disc-shaped mounting seat 23, and the turbine shaft 5 is pressed between the two C-shaped hoops 21, so that the turbine shaft 5 rotates along with the rotation of the two C-shaped hoops 21.
In some preferred example embodiments, the nut of the slip-knot bolt 22 is a wing nut. And the butterfly nut is adopted, so that the C-shaped anchor ear 21 anchor ear is convenient to assemble and disassemble.
It is to be understood that the above embodiments are merely illustrative of the application of the principles of the present invention, but not in limitation thereof. Various modifications and improvements may be made by those skilled in the art without departing from the spirit and substance of the invention, and are also considered to be within the scope of the invention.
Claims (10)
1. The turbine disc (4) shaft disassembling tool for the aviation auxiliary power device is characterized by comprising a lock shaft member (2) for locking and fixing a turbine shaft (5), and a transmission structure (1) for driving the lock shaft member (2) to rotate;
The device also comprises a limiting structure (3) for limiting the rotation of the turbine disk (4), wherein the limiting structure (3) is sleeved on the transmission structure (1) and is in spiral connection with the transmission structure;
the lock shaft member (2) is detachably and fixedly connected with the transmission structure (1).
2. A turbine disc (4) shaft dismantling tool for an aero auxiliary power device according to claim 1, wherein the transmission structure (1) comprises a transmission rod for passing through the turbine disc (4) and the turbine shaft (5);
The transmission rod is provided with external threads (11) which are matched with the limiting structure (3).
3. The turbine disc (4) shaft disassembling tool for the aviation auxiliary power device according to claim 2, wherein a screwing piece (12) for transmitting screwing force is further arranged on the transmission rod, and the screwing piece (12) is located on one side, away from the lock shaft member (2), of the limiting structure (3) and fixedly connected with the transmission rod.
4. A turbine disc (4) shaft dismantling tool for an aeronautical auxiliary power device according to claim 3, wherein the screwing piece (12) comprises a screwing nut screwed or welded to the end of the transmission rod remote from the lock shaft member (2).
5. The turbine disc (4) shaft disassembly tool for the aviation auxiliary power device according to claim 1, wherein the limiting structure (3) comprises a limiting sleeve, and an internal thread matched with the transmission structure (1) is arranged in the limiting sleeve.
6. The tool for disassembling the shaft of the turbine disc (4) for the aviation auxiliary power device according to claim 5, wherein an anti-skid sleeve is sleeved and fixed on the peripheral wall of the limiting sleeve or anti-skid patterns are carved on the peripheral wall of the limiting sleeve.
7. The turbine disc (4) shaft disassembly tool for the aviation auxiliary power device according to claim 1, wherein the lock shaft member (2) comprises a hoop assembly used for locking and fixing a step on one side of a turbine shaft (5) far away from the turbine disc (4), and a mounting seat (23) used for mounting the hoop assembly, and the hoop assembly is detachably connected with the mounting seat (23);
The mounting seat (23) is coaxially arranged with the transmission structure (1) and is detachably and fixedly connected with the transmission structure.
8. The turbine disc (4) shaft disassembly tool for an aviation auxiliary power unit according to claim 7, wherein the hoop assembly comprises two C-shaped hoops (21) which are arranged in a buckling manner, and a slipknot bolt (22) for adjusting the locking force of the hoop assembly on the turbine shaft (5);
Both ends of the two C-shaped hoops (21) are detachably connected and fixed through a slipknot bolt (22).
9. The tool for disassembling a shaft of a turbine disc (4) for an aeronautical auxiliary power unit according to claim 8, wherein the shape of the mounting seat (23) is disc-shaped;
a semicircular groove matched with the disc-shaped mounting seat (23) is formed in the inner side surface of the C-shaped hoop (21);
The mounting seat (23) is coaxially arranged with the transmission structure (1) and is detachably and fixedly connected with the transmission structure.
10. The turbine disc (4) shaft disassembly tool for an aviation auxiliary power unit according to claim 8, wherein the nut of the slip-joint bolt (22) is a butterfly nut.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323067688.9U CN221048342U (en) | 2023-11-14 | 2023-11-14 | Turbine disk shaft disassembling tool for aviation auxiliary power device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323067688.9U CN221048342U (en) | 2023-11-14 | 2023-11-14 | Turbine disk shaft disassembling tool for aviation auxiliary power device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN221048342U true CN221048342U (en) | 2024-05-31 |
Family
ID=91203452
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202323067688.9U Active CN221048342U (en) | 2023-11-14 | 2023-11-14 | Turbine disk shaft disassembling tool for aviation auxiliary power device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN221048342U (en) |
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2023
- 2023-11-14 CN CN202323067688.9U patent/CN221048342U/en active Active
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