CN112497147A - Mechanism for disassembling disk type parts of aircraft engine - Google Patents
Mechanism for disassembling disk type parts of aircraft engine Download PDFInfo
- Publication number
- CN112497147A CN112497147A CN202011302008.5A CN202011302008A CN112497147A CN 112497147 A CN112497147 A CN 112497147A CN 202011302008 A CN202011302008 A CN 202011302008A CN 112497147 A CN112497147 A CN 112497147A
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- tray
- clamping jaw
- pull rod
- disc
- shaped
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B27/00—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for
- B25B27/02—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for connecting objects by press fit or detaching same
- B25B27/023—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for connecting objects by press fit or detaching same using screws
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- Mechanical Engineering (AREA)
- Jigs For Machine Tools (AREA)
Abstract
The invention discloses a mechanism for disassembling disk parts of an aircraft engine, wherein a plurality of mounting teeth are distributed on the circumference of a tray; one end of the clamping jaw is connected to the mounting teeth of the tray; the other end of the clamping jaw is provided with a step-shaped clamping table matched with the limiting ring; one end of the pull rod is connected to the wall of the clamping jaw, the other end of the pull rod is connected to the strip-shaped groove of the mounting tooth, a spring mandrel is arranged on the pull rod, the spring is sleeved on the spring mandrel, and the pull rod is clamped on the strip-shaped groove through an R-shaped nut; the jacking bolt penetrates through the tray, the middle position of the jacking bolt is connected with a threaded bushing arranged on the tray, the jacking bolt jacks in a threaded blind hole arranged on the jacking tray, and the jacking bolt receives downward force of the threaded bushing of the tray and applies the force to the jacking tray; the spacing ring is arranged at the other end of the clamping jaw. The invention adopts the clamping jaw which can rotate and swing, meets the requirements that the clamping jaw can extend into the rear end of a disc part to pull the disc part to be decomposed, and is convenient for flexibly adjusting the position of the clamping jaw of the mechanism.
Description
Technical Field
The invention relates to the technical field of disc part decomposition, in particular to a mechanism for disassembling disc parts of an aircraft engine.
Background
The connection of various disc parts in the aircraft engine mostly adopts interference fit, and certain complexity exists in the assembling and disassembling processes. But often require multiple disassembly during manufacture and repair to adjust the engine to optimum conditions.
Disclosure of Invention
In order to solve the technical problem, the specific technical scheme of the mechanism for disassembling the disk parts of the aircraft engine is as follows:
a mechanism for disassembling disk parts of an aircraft engine comprises a tray, a puller bolt, a puller disk, an R-shaped nut, a spring mandrel, a pull rod, a clamping jaw and a limiting ring;
the tray is disc-shaped, and a plurality of mounting teeth are circumferentially distributed on the tray; and the mounting teeth are provided with strip-shaped grooves;
one end of the clamping jaw is connected to the mounting teeth of the tray;
the other end of the clamping jaw is provided with a step-shaped clamping table matched with the limiting ring;
one end of the pull rod is connected to the wall of the clamping jaw, the other end of the pull rod is connected to the strip-shaped groove of the mounting tooth, a spring mandrel is arranged on the pull rod, the spring is sleeved on the spring mandrel, and the pull rod is clamped on the strip-shaped groove through an R-shaped nut;
the jacking bolt penetrates through the tray, the middle position of the jacking bolt is connected with a threaded bushing arranged on the tray, the jacking bolt jacks in a threaded blind hole arranged on the jacking tray, and the jacking bolt receives downward force of the threaded bushing of the tray and applies the force to the jacking tray;
the limiting ring is arranged at the other end of the clamping jaw;
when the clamping jaws are clamped below the disc to be decomposed and hook the edge of the disc, the condition for decomposing the disc in the next step is met.
The mechanism for disassembling the disc parts of the aircraft engine has the preferable scheme that the limiting ring is at the minimum position where the clamping jaw retracts to the diameter around the rotating shaft when the clamping jaw is arranged at the lowest end of the clamping table;
the limiting ring is used for limiting the clamping jaw to extend to the position with the maximum diameter around the rotating shaft under the action of the elastic force of the spring when the upper end of the clamping jaw clamping table is arranged.
The mechanism for disassembling the disk parts of the aircraft engine has the preferable scheme that the number of the installation teeth is eleven, and the number of the installation teeth is properly adjusted according to the diameter of a disk to be disassembled.
According to the preferable scheme, when the inclined degree and the size of the inclined plane on the clamping jaws determine that the outer ring rises for a certain distance, the contraction distance of each clamping jaw towards the center is set according to specific use conditions, when the contraction distance of the clamping jaw towards the center is larger, the inclined plane inclination angle can be designed to be larger, and vice versa.
The mechanism for disassembling the disc parts of the aircraft engine has the advantages that the clamping table is designed according to the disc parts to be disassembled in the engine, and therefore the diameter of the clamping table is slightly smaller than that of the edge of the disc.
The mechanism for disassembling the disc parts of the aircraft engine has the preferable scheme that the upper end face of the R-shaped nut is a plane, and the lower end face of the R-shaped nut is an R arc, so that the R-shaped nut can stably feed back the spring force to the clamping jaws when the pull rod is at any angle; the lower end face of the R-shaped nut is a half circular arc R.
The working principle of a mechanism for disassembling disk type parts of an aircraft engine is as follows:
1. moving the limiting ring to the lowest end of the clamping jaw, so that the clamping jaw retracts to the position with the minimum diameter around the rotating shaft, and at the moment, eleven clamping jaws can be deeply inserted into the bottom of the pre-disassembly disc;
2. moving the position of the limit ring upwards, and extending the clamping jaws to the position with the maximum diameter at the center of the disk to be decomposed around the rotating shaft under the action of the elastic force of the spring; the step at the bottom of the claw hook hooks the bottom of the pre-detaching disc. In the process that the clamping jaws rotate around the rotating shafts, the angles of the pull rods and the tray are changed constantly, and the R-shaped nuts ensure that the acting force of the springs is transmitted to the clamping jaws through the pull rods; the spring mandrel ensures the position of the spring center, so that the spring force of each part is basically consistent;
3. rotating the puller bolt to drive the puller disc to move downwards to jack the end face of the engine journal, and continuously rotating the puller bolt to move the pre-decomposed disc and the engine journal relatively to each other, so as to realize the purpose of detaching the disc;
4. after the disc is disassembled, the limiting ring is used for moving upwards, so that the clamping jaws are all retracted to the position with the minimum diameter around the rotating shaft, the clamping jaws are separated from the disc to be disassembled, and the whole disassembling process is completed.
The invention has the beneficial effects that: the invention adopts the clamping jaw which can rotate and swing, meets the requirements that the clamping jaw can extend into the rear end of a disc part to pull the disc part to be decomposed and is convenient for flexibly adjusting the position of the clamping jaw of the mechanism; the problem of demolish of aeroengine dish class part is solved, the production user demand has been satisfied, its operation process is simple special-shaped, has improved engine assembly production benefit.
Drawings
FIG. 1 is a perspective view of a mechanism for removing disk type parts of an aircraft engine;
FIG. 2 is a front view of an arrangement for removing disk type parts from an aircraft engine;
fig. 3 is a top view of a mechanism for removing disk type parts of an aircraft engine.
In the figure, 1-tray, 2-tightening bolt, 3-tightening tray, 4-R type nut, 5-spring, 6-spring mandrel, 7-pull rod, 8-claw, 9-spacing ring, 10-mounting tooth and 11-clamping table.
Detailed Description
As shown in fig. 1-3, the mechanism for disassembling disk parts of an aircraft engine is characterized by comprising a tray 1, a puller bolt 2, a puller disk 3, an R-shaped nut 4, a spring 5, a spring mandrel 6, a pull rod 7, a jaw 8 and a limit ring 9;
the tray 1 is disc-shaped, and eleven mounting teeth 10 are circumferentially distributed; and the mounting teeth are provided with strip-shaped grooves;
one end of the claw 8 is connected to the mounting tooth 10 of the tray;
the other end of the clamping jaw 8 is provided with a step-shaped clamping table 11 matched with the limiting ring 9;
one end of the pull rod 7 is connected to the wall of the clamping jaw 8, the other end of the pull rod 7 is connected to the strip-shaped groove of the mounting tooth 10, a spring mandrel 6 is arranged on the pull rod 7, the spring 5 is sleeved on the spring mandrel 6, and the pull rod 7 is clamped on the strip-shaped groove through an R-shaped nut 4;
the jacking bolt 2 penetrates through the tray 1, the middle position of the jacking bolt is connected with a threaded bushing arranged on the tray 1, the jacking bolt jack 2 receives downward force of the threaded bushing of the tray 1 through the jacking bolt 2 in a threaded blind hole arranged on the jacking tray 3, and the force is applied to the jacking tray 3;
the limiting ring 9 is arranged at the other end of the clamping jaw;
when the claw 8 is clamped below the disk to be disassembled and hooks the edge of the disk, the condition for disassembling the disk in the next step is met.
The limiting ring 9 is the minimum position of the diameter of the clamping jaw 8 retracted around the rotating shaft when the clamping jaw 8 is positioned at the lowest end of the clamping table 11;
when the limiting ring 9 is arranged at the upper end of the clamping table 11 of the clamping jaw 8, the clamping jaw 8 extends to the position with the maximum diameter around the rotating shaft under the action of the elastic force of the spring.
The number of the mounting teeth 10 is eleven.
When the inclined degree and the size of the upper inclined plane of each clamping jaw 8 determine that the outer ring rises for a certain distance, the distance of each clamping jaw 8 shrinking towards the center is given according to specific use conditions, and when each clamping jaw 8 shrinks towards the center for a longer distance, the inclined plane inclined angle can be designed to be larger, otherwise, the inclined plane inclined angle is designed to be smaller.
The design of the clamping table 11 is according to the disk parts to be decomposed in the engine, so the diameter of the clamping table is slightly smaller than the edge diameter of the disk.
The upper end face of the R-shaped nut 4 is a plane, and the lower end face of the R-shaped nut 4 is an R arc, so that the R-shaped nut 4 can stably feed back the spring force to the clamping jaw 8 at any angle when the pull rod 7 is at any angle; the lower end surface of the R-shaped nut 4 is a half circular arc R.
The working principle of a mechanism for disassembling disk type parts of an aircraft engine is as follows:
1. moving the limiting ring to the lowest end of the clamping jaw 8 to enable the clamping jaw 8 to retract to the position with the minimum diameter around the rotating shaft, and enabling eleven clamping jaws 8 to penetrate into the bottom of the pre-disassembly disc;
2. the position of the limiting ring 9 is moved upwards, and the claw 8 extends to the position with the maximum diameter around the rotating shaft under the action of the elastic force of the spring 6; the step at the bottom of the claw 8 will hook the bottom of the pre-dissembling disk. In the process that the clamping jaws 8 rotate around the rotating shafts, the angles of the pull rods 7 and the tray 1 are changed at all times, and the R-shaped nuts 4 ensure that the acting force of the springs 6 is transmitted to the clamping jaws 8 through the pull rods 7; the spring mandrel 6 ensures the position of the center of the spring 6, so that the spring force is basically consistent everywhere;
3. rotating the puller bolt 2 to drive the puller disc 3 to move downwards to jack the end face of the engine journal, and continuously rotating the puller bolt 2 to enable the pre-decomposed disc and the engine journal to move relatively, so that the aim of disassembling the disc is fulfilled;
4. after the disc is disassembled, the limiting ring 9 is used for moving upwards, so that the clamping jaws 8 are all retracted to the position with the minimum diameter around the rotating shaft, the clamping jaws 8 are separated from the disc to be disassembled, and the whole disassembling process is completed.
Claims (6)
1. A mechanism for disassembling disk type parts of an aircraft engine is characterized by comprising a tray, a puller bolt, a puller disk, an R-shaped nut, a spring mandrel, a pull rod, a clamping jaw and a limiting ring;
the tray is disc-shaped, and a plurality of mounting teeth are circumferentially distributed on the tray; and the mounting teeth are provided with strip-shaped grooves;
one end of the clamping jaw is connected to the mounting teeth of the tray;
the other end of the clamping jaw is provided with a step-shaped clamping table matched with the limiting ring;
one end of the pull rod is connected to the wall of the clamping jaw, the other end of the pull rod is connected to the strip-shaped groove of the mounting tooth, a spring mandrel is arranged on the pull rod, the spring is sleeved on the spring mandrel, and the pull rod is clamped on the strip-shaped groove through an R-shaped nut;
the jacking bolt penetrates through the tray, the middle position of the jacking bolt is connected with a threaded bushing arranged on the tray, the jacking bolt jacks in a threaded blind hole arranged on the jacking tray, and the jacking bolt receives downward force of the threaded bushing of the tray and applies the force to the jacking tray;
the limiting ring is arranged at the other end of the clamping jaw;
when the claw is clamped below the disk to be disassembled and hooks the edge of the disk, the condition of pulling out the disk in the next step is met.
2. A mechanism for disassembly of an aircraft engine disc-like part according to claim 1, wherein the stop collar is a minimum position of diameter retraction of the jaws about the axis of rotation when the jaw chuck is lowermost;
the limiting ring is used for limiting the clamping jaw to extend to the position with the maximum diameter around the rotating shaft under the action of the elastic force of the spring when the upper end of the clamping jaw clamping table is arranged.
3. A mechanism for disassembly of an aircraft engine disc-like part according to claim 1, wherein the number of mounting teeth is eleven.
4. The mechanism for disassembling disk type parts of aircraft engine according to claim 1, characterized in that the inclined degree and size of the inclined plane on the jaws determine the distance of contraction of each jaw towards the center when the outer ring rises for a certain distance, and the inclined angle of the inclined plane can be designed to be larger when the distance of contraction of the jaw towards the center is larger, and vice versa according to the specific use conditions.
5. A mechanism for removing disc-like components from an aircraft engine according to claim 1, characterised in that the design of the cassette is such that the cassette is slightly smaller than the diameter of the edge of the disc, in accordance with the disc-like component to be removed from the engine.
6. The mechanism for disassembling the disc parts of the aircraft engine as claimed in claim 1, wherein the upper end surface of the R-shaped nut is a plane, and the lower end surface of the R-shaped nut is an R-arc, so as to ensure that the R-shaped nut can stably feed back the spring force to the clamping jaws when the pull rod is at any angle; the lower end face of the R-shaped nut is a half circular arc R.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011302008.5A CN112497147A (en) | 2020-11-19 | 2020-11-19 | Mechanism for disassembling disk type parts of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011302008.5A CN112497147A (en) | 2020-11-19 | 2020-11-19 | Mechanism for disassembling disk type parts of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112497147A true CN112497147A (en) | 2021-03-16 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011302008.5A Pending CN112497147A (en) | 2020-11-19 | 2020-11-19 | Mechanism for disassembling disk type parts of aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112497147A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113787489A (en) * | 2021-09-08 | 2021-12-14 | 陕西法士特齿轮有限责任公司 | Dual-purpose bearing frock of dismouting |
| CN113985076A (en) * | 2021-10-26 | 2022-01-28 | 西安高压电器研究院有限责任公司 | Arc extinguish chamber opening distance changing device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0397405A1 (en) * | 1989-05-08 | 1990-11-14 | Posi Lock Puller, Inc. | Hydraulic puller |
| CN207432117U (en) * | 2017-11-10 | 2018-06-01 | 中航飞机起落架有限责任公司 | A kind of airplane wheel bearing extractor |
| CN207807612U (en) * | 2017-12-29 | 2018-09-04 | 中核检修有限公司 | The extracting tool of steel skeleton gasket |
| CN209425356U (en) * | 2018-11-28 | 2019-09-24 | 上海天永智能装备股份有限公司 | A kind of extracting tool for ring set type part |
| CN110340848A (en) * | 2019-08-21 | 2019-10-18 | 无锡市润和机械有限公司 | Puller is used in a kind of assembly of aeroengine rotor component |
-
2020
- 2020-11-19 CN CN202011302008.5A patent/CN112497147A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0397405A1 (en) * | 1989-05-08 | 1990-11-14 | Posi Lock Puller, Inc. | Hydraulic puller |
| CN207432117U (en) * | 2017-11-10 | 2018-06-01 | 中航飞机起落架有限责任公司 | A kind of airplane wheel bearing extractor |
| CN207807612U (en) * | 2017-12-29 | 2018-09-04 | 中核检修有限公司 | The extracting tool of steel skeleton gasket |
| CN209425356U (en) * | 2018-11-28 | 2019-09-24 | 上海天永智能装备股份有限公司 | A kind of extracting tool for ring set type part |
| CN110340848A (en) * | 2019-08-21 | 2019-10-18 | 无锡市润和机械有限公司 | Puller is used in a kind of assembly of aeroengine rotor component |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113787489A (en) * | 2021-09-08 | 2021-12-14 | 陕西法士特齿轮有限责任公司 | Dual-purpose bearing frock of dismouting |
| CN113787489B (en) * | 2021-09-08 | 2023-03-10 | 陕西法士特齿轮有限责任公司 | Dual-purpose bearing frock of dismouting |
| CN113985076A (en) * | 2021-10-26 | 2022-01-28 | 西安高压电器研究院有限责任公司 | Arc extinguish chamber opening distance changing device |
| CN113985076B (en) * | 2021-10-26 | 2024-01-30 | 西安高压电器研究院股份有限公司 | Arc extinguishing chamber variable-spacing device |
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Application publication date: 20210316 |
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| RJ01 | Rejection of invention patent application after publication |