CN113829294A - Puller for turbine disc of aircraft engine - Google Patents
Puller for turbine disc of aircraft engine Download PDFInfo
- Publication number
- CN113829294A CN113829294A CN202111250750.0A CN202111250750A CN113829294A CN 113829294 A CN113829294 A CN 113829294A CN 202111250750 A CN202111250750 A CN 202111250750A CN 113829294 A CN113829294 A CN 113829294A
- Authority
- CN
- China
- Prior art keywords
- engine turbine
- puller
- turbine disc
- claw
- aircraft engine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 210000000078 claw Anatomy 0.000 claims abstract description 34
- 210000004907 gland Anatomy 0.000 claims abstract description 19
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- 238000009826 distribution Methods 0.000 claims description 2
- 239000000463 material Substances 0.000 claims description 2
- 238000003466 welding Methods 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 8
- 230000002035 prolonged effect Effects 0.000 abstract description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 229910003460 diamond Inorganic materials 0.000 description 1
- 239000010432 diamond Substances 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
Images
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A puller for an aircraft engine turbine disc comprises claws, a shaft sleeve, a gland, a bracket, a handle and screws, wherein the shaft sleeve is fixedly connected to the center of a base where the engine turbine disc is located; one end of the screw penetrates through a threaded hole formed in the middle of the support and then is propped against the top of the gland, the handle penetrates through the other end of the screw, and the screw can be rotated by rotating the handle; the claw is a plurality of, and one end is connected on the support, and the other end card is on engine turbine dish. By implementing the invention, the engine turbine disc is lifted up in the direction vertical to the base in the dismounting process, the engine turbine disc can be pulled up in the direction vertical to the clamp, the diamond-shaped pin is prevented from being broken, the engine turbine disc can be easily pulled out, meanwhile, the puller has the advantages of simple structure, convenience for dismounting and high working efficiency, and the dismounting time required by the aeroengine parts during processing can be greatly prolonged.
Description
Technical Field
The invention belongs to the technical field of manufacturing of aero-engines, and particularly relates to a puller for a turbine disc of an aero-engine.
Background
In the manufacturing process of an aircraft engine, a high-pressure turbine disc after finish machining needs to be installed in a base through an inner hole in a positioning mode, the inner hole is in clearance fit with a clamp by 0.05, a diamond-shaped pin falls into the bottom of the turbine disc to prevent the disc from rotating axially, the diamond-shaped pin is in interference fit, a manual pulling-out method is generally adopted at present, the direction of the manual method is not easy to grasp, a part cannot be lifted in the direction perpendicular to the base of the clamp in the disassembling process, and the situation that the pin is broken off due to the fact that the weight of the part impacts the pin is often caused. Therefore, it is desirable to provide a pin puller that can pull out a part in the vertical direction to prevent the weight of the part from striking the pin and causing the pin to break.
Disclosure of Invention
In order to solve the technical problem, the invention provides a puller for a turbine disc of an aeroengine.
The invention is realized by the following technical scheme.
The invention provides a puller for an aircraft engine turbine disc, which comprises claws, a shaft sleeve, a gland, a bracket, a handle and screws, wherein the shaft sleeve is fixedly connected to the center of a base where the engine turbine disc is located; the middle part of the bracket is provided with a threaded hole matched with the screw, one end of the screw penetrates through the threaded hole arranged in the middle part of the bracket and then is propped against the top of the gland, the handle penetrates through the other end of the screw, and the screw can be rotated by rotating the handle; the claw is a plurality of, and one end is connected on the support to be circular distribution along engine turbine dish on the support, the other end of claw is equipped with interior bulge, blocks on engine turbine dish.
Furthermore, a circular groove is formed in the center of the top of the gland, and the screw penetrates through one end of the support and is inserted into the circular groove.
Furthermore, the clamping device further comprises a positioning ring, wherein the plurality of claws are provided with outer convex parts at one end of the engine turbine disc, and the positioning ring is clamped on a circle formed by the outer convex parts of the plurality of claws.
Furthermore, the claw is connected with the support through a pin, and the claw can rotate on the support by taking the pin as a circle center.
Further, the outer protruding part of the claw has a height of 6mm and a width of 3 mm.
Further, the sleeve and the gland are in welded connection.
Furthermore, the circular groove at the top end of the gland is of a conical structure with a narrow upper part and a wide lower part.
Furthermore, the shape of support is three claw formula star structures, 3 claws, the equipartition is in the terminal of support star roof beam.
Further, the shaft sleeve is made of aluminum materials.
Furthermore, 4 holes with the diameter of 25mm are uniformly distributed on the shaft sleeve.
The invention has the beneficial effects that: by implementing the invention, the engine turbine disc is lifted up in the direction vertical to the base of the clamp in the dismounting process, the engine turbine disc can be pulled up in the direction vertical to the clamp, the diamond-shaped pin is prevented from being broken, the engine turbine disc can be easily pulled out, meanwhile, the puller has the advantages of simple structure, convenience for dismounting and high working efficiency, and the dismounting time required by the parts of the aero-engine during processing can be greatly prolonged.
Drawings
FIG. 1 is a schematic structural composition of the present invention;
FIG. 2 is a schematic view of the retaining ring of the present invention;
FIG. 3 is a schematic view of the jaw configuration of the present invention;
FIG. 4 is a schematic view of the bushing configuration of the present invention;
FIG. 5 is a schematic view of the sleeve construction of the present invention;
FIG. 6 is a schematic view of the gland structure of the present invention;
FIG. 7 is a schematic view of the stent structure of the present invention;
FIG. 8 is a schematic view of the handle structure of the present invention;
in the figure: 1-positioning ring, 2-claw, 3-shaft sleeve, 4-sleeve, 5-gland, 6-bracket, 7-handle, 8-screw and 9-pin.
Detailed Description
The technical solution of the present invention is further described below, but the scope of the claimed invention is not limited to the described.
As shown in fig. 1, the puller for the turbine disc of the aircraft engine is mainly used for conveniently detaching the turbine disc. The novel clamp comprises a positioning ring 1, a claw 2, a shaft sleeve 3, a sleeve 4, a gland 5, a support 6, a handle 7, a screw 8 and a pin 9. The structure of the positioning ring 1 is shown in fig. 2, the structure of the claw 2 is shown in fig. 3, the structure of the sleeve 3 is shown in fig. 4, the structure of the sleeve 4 is shown in fig. 5, the structure of the gland 5 is shown in fig. 6, the structure of the bracket 6 is shown in fig. 7, and the structure of the handle 7 is shown in fig. 8.
The aeroengine turbine disk part has the characteristics that: the turbine disc is basically designed to be in the final size in the broaching and mortise process, and the surface finish of parts is high. In order to provide an acting point for pulling out the part in the process, allowance is reserved at the end face grate, grate turning is not carried out, and allowance of 2mm is reserved at the maximum excircle diameter of the grate. The right angle processing is carried out at the allowance of the grid teeth, and the right angle processing is provided for the acting point of the claw 2.
The base is characterized in that: the base supporting surface is the broaching mortise end surface of the high-pressure turbine disc; the base is in clearance fit with the inner hole of the high-pressure turbine disc through the inner hole; the base is provided with a diamond pin which is inserted into the end face hole of the high-pressure turbine disc to limit the radial rotation of the high-pressure turbine disc.
When in use, the shaft sleeve 3 is connected with the base through the central threaded rod of the base. The shaft sleeve is made of aluminum. 4 holes with the diameter of 25 are formed in the shaft sleeve step by step, so that the weight of the shaft sleeve can be reduced. Then, the sleeve 4 and the gland 5 are welded together to ensure that the sleeve does not fall off; the sleeve 4 and the gland 5 are arranged on the shaft sleeve 3, the top of the gland 5 adopts a circular groove with a convex structure, and the upper part is narrow and the lower part is wide; a screw 8 is placed in a circular groove on the sleeve 5, the screw 8 is screwed into the bracket 6, and the bracket 6 adopts a three-claw structure and is star-shaped; the support 6 is connected with the claw 2 through a pin 9, the claw 2 can be opened and axially rotated, and the pin connection structure can enable the claw 2 to rotate along the diameter direction of the pin; subsequently, the inner convex part of the claw 2 is placed at the grate end face with allowance reserved on the turbine disc, the positioning ring 1 is sleeved at the outer circle of the claw 2, the positioning ring 1 can prevent the claw 2 from axially rotating and simultaneously plays a role in fixing, the outer convex part is arranged on the outer side of the outer circle of the claw 2, the height is 6mm, the width is 3mm, and the positioning ring 1 is limited by the outer convex part of the claw 2 in displacement. Rotating the handle 7 rotates the screw 8 and drives the bracket 6 to move along the vertical direction of the base, and drives the claw 2 to pull the high-pressure turbine disc out of the base.
The puller can pull the part in the direction vertical to the clamp, so that the problem of breakage of the diamond-shaped pin is prevented, and the part can be easily pulled out of the clamp. At present, parts are generally pulled out manually, the direction of the manual method is not easy to grasp, and the diamond-shaped pin is broken.
Claims (10)
1. The utility model provides a puller for aeroengine turbine dish which characterized in that: comprises claws, a shaft sleeve, a gland, a bracket, a handle and a screw,
the shaft sleeve is fixedly connected to the center of the base where the engine turbine disc is located, and the sleeve and the gland are sequentially arranged on the shaft sleeve in an overlapping mode; the middle part of the bracket is provided with a threaded hole matched with the screw, one end of the screw penetrates through the threaded hole arranged in the middle part of the bracket and then is propped against the top of the gland, the handle penetrates through the other end of the screw, and the screw can be rotated by rotating the handle; the claw is a plurality of, and one end is connected on the support to be circular distribution along engine turbine dish on the support, the other end of claw is equipped with interior bulge, blocks on engine turbine dish.
2. A puller for an aircraft engine turbine disc as claimed in claim 1, wherein: a circular groove is formed in the center of the top of the gland, and the screw penetrates through one end of the support and is inserted into the circular groove.
3. A puller for an aircraft engine turbine disc as claimed in claim 1, wherein: still include the holding ring, a plurality of claws still are equipped with outer bulge in engine turbine dish one end, the holding ring card is on the circle that the outer bulge of a plurality of claws formed.
4. A puller for an aircraft engine turbine disc as claimed in claim 1, wherein: the claw is connected with the support through a pin, and the claw can rotate on the support by taking the pin as a circle center.
5. A puller for an aircraft engine turbine disc as claimed in claim 3, wherein: the outer protruding part of the claw is 6mm in height and 3mm in width.
6. A puller for an aircraft engine turbine disc as claimed in claim 1, wherein: the sleeve is connected with the gland in a welding mode.
7. A puller for an aircraft engine turbine disc as claimed in claim 2, wherein: the circular groove at the top end of the gland is of a conical structure with a narrow upper part and a wide lower part.
8. A puller for an aircraft engine turbine disc as claimed in claim 1, wherein: the shape of support is three claw formula star type structures, 3 claws, the equipartition is in the terminal of support star type roof beam.
9. A puller for an aircraft engine turbine disc as claimed in claim 1, wherein: the shaft sleeve is made of aluminum materials.
10. A puller for an aircraft engine turbine disc as claimed in claim 1, wherein: 4 holes with the diameter of 25mm are uniformly distributed on the shaft sleeve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111250750.0A CN113829294A (en) | 2021-10-26 | 2021-10-26 | Puller for turbine disc of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111250750.0A CN113829294A (en) | 2021-10-26 | 2021-10-26 | Puller for turbine disc of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113829294A true CN113829294A (en) | 2021-12-24 |
Family
ID=78966368
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111250750.0A Pending CN113829294A (en) | 2021-10-26 | 2021-10-26 | Puller for turbine disc of aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113829294A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150246436A1 (en) * | 2014-03-03 | 2015-09-03 | Puller Structure | Puller structure |
| CN204800245U (en) * | 2015-06-29 | 2015-11-25 | 珠海保税区摩天宇航空发动机维修有限公司 | Hydraulic pressure puller is dismantled to CFM56 engine high pressure compressor poising tool axle sleeve |
| CN204868737U (en) * | 2015-08-10 | 2015-12-16 | 常州市惠涛纺织有限公司 | Supplementary type draws horse |
| CN207309845U (en) * | 2017-09-27 | 2018-05-04 | 中国人民解放军第五七二一工厂 | A kind of instrument of not damaged dismounting pulley assembly |
| US20200338705A1 (en) * | 2019-04-29 | 2020-10-29 | Julio Sampedro Martinez | Mechanical Device Self-Centering Gear Extractor |
-
2021
- 2021-10-26 CN CN202111250750.0A patent/CN113829294A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150246436A1 (en) * | 2014-03-03 | 2015-09-03 | Puller Structure | Puller structure |
| CN204800245U (en) * | 2015-06-29 | 2015-11-25 | 珠海保税区摩天宇航空发动机维修有限公司 | Hydraulic pressure puller is dismantled to CFM56 engine high pressure compressor poising tool axle sleeve |
| CN204868737U (en) * | 2015-08-10 | 2015-12-16 | 常州市惠涛纺织有限公司 | Supplementary type draws horse |
| CN207309845U (en) * | 2017-09-27 | 2018-05-04 | 中国人民解放军第五七二一工厂 | A kind of instrument of not damaged dismounting pulley assembly |
| US20200338705A1 (en) * | 2019-04-29 | 2020-10-29 | Julio Sampedro Martinez | Mechanical Device Self-Centering Gear Extractor |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20211224 |
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| RJ01 | Rejection of invention patent application after publication |