CN107984427A - A kind of aero-engine is with disassembling bushing device and application method in blind hole - Google Patents
A kind of aero-engine is with disassembling bushing device and application method in blind hole Download PDFInfo
- Publication number
- CN107984427A CN107984427A CN201711248237.1A CN201711248237A CN107984427A CN 107984427 A CN107984427 A CN 107984427A CN 201711248237 A CN201711248237 A CN 201711248237A CN 107984427 A CN107984427 A CN 107984427A
- Authority
- CN
- China
- Prior art keywords
- hole
- sleeve
- handle
- blind hole
- disassembling
- 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
- 238000000034 method Methods 0.000 title abstract description 11
- 210000000078 claw Anatomy 0.000 claims abstract description 10
- 230000007704 transition Effects 0.000 claims abstract description 8
- 241000446313 Lamella Species 0.000 claims description 6
- 230000008602 contraction Effects 0.000 claims description 3
- 238000012423 maintenance Methods 0.000 description 6
- 230000008569 process Effects 0.000 description 4
- 238000000354 decomposition reaction Methods 0.000 description 2
- 230000003111 delayed effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 239000000284 extract Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
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
- B25B27/06—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 inserting or withdrawing sleeves or bearing races
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Hand Tools For Fitting Together And Separating, Or Other Hand Tools (AREA)
Abstract
Aero-engine belongs to aero-engine technology field with bushing device and application method is disassembled in blind hole.The aero-engine includes mandril, sleeve, swollen valve claw, handle, tightening pin and rotational pin with bushing device is disassembled in blind hole；Mandril is equipped with polished rod portion, thread rod part and termination, polished rod portion is stepped cylindrical, the part that stepped cylindrical is relatively large in diameter is connected with the less part of diameter by the transition conical surface, the part that stepped cylindrical is relatively large in diameter is connected with one end of thread rod part, the other end of thread rod part is connected by tightening pin with handle, and the less part of stepped cylindrical diameter is connected with termination；Internal thread hole and unthreaded hole are equipped with sleeve, the polished rod portion of mandril is located in unthreaded hole, and thread rod part and the internal thread hole of mandril coordinate；The side wall of sleeve is equipped with multiple claw mounting grooves, and claw mounting groove is connected with unthreaded hole, and a swollen valve claw is respectively mounted in each claw mounting groove, and one end of swollen valve claw is equipped with clamp, and the other end is installed in claw mounting groove by rotational pin.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to a device for disassembling a bush in a blind hole for an aero-engine and a using method.
Background
In the aircraft engine assembly and repair process, the installation and the dismantlement of a lot of bushes are designed, and hole and bush generally adopt interference fit, and to the structure of installing the bush in some blind holes very much, it is big to disassemble the degree of difficulty, disassembles for a long time, and the in-process is disassembled and is easily damaged the part, causes the increase of expense and maintenance volume, leads to the fact the delay to assembly and maintenance.
Disclosure of Invention
In order to solve the problems that the bushing in the blind hole of an aeroengine part is difficult to disassemble, the disassembling time is long, parts are easy to damage in the disassembling process, the cost and the maintenance amount are increased, and the assembly and maintenance are delayed, the invention provides a bushing disassembling device in the blind hole for the aeroengine, which comprises a top rod, a sleeve, an expanding jaw, a handle, a fastening pin and a rotating pin;
the ejector rod is provided with a polished rod part, a threaded rod part and an end head, the polished rod part is a stepped cylinder, the part with the larger diameter of the stepped cylinder is connected with the part with the smaller diameter through a transition conical surface, the part with the larger diameter of the stepped cylinder is connected with one end of the threaded rod part, the other end of the threaded rod part is connected with the handle through a fastening pin, and the part with the smaller diameter of the stepped cylinder is connected with the end head;
an internal thread hole and a unthreaded hole are arranged in the sleeve and are communicated, a polished rod part of the ejector rod is positioned in the unthreaded hole, and a threaded rod part of the ejector rod is matched with the internal thread hole;
evenly be equipped with a plurality of jack catch mounting grooves on the telescopic lateral wall, every jack catch mounting groove all with the unthreaded hole intercommunication all installs an expand lamella jack catch in every jack catch mounting groove, and the one end of expanding lamella jack catch is equipped with the dop, and the other end passes through the rotational pin to be installed in the jack catch mounting groove.
And a plurality of wrench mounting holes are formed in the side wall of the handle.
Be equipped with three jack catch mounting grooves on the telescopic lateral wall, three jack catch mounting grooves evenly set up along telescopic circumference.
The sleeve is further provided with a connecting disc, and a through hole is formed in the connecting disc.
The use method of the blind hole inner disassembling lining device for the aeroengine comprises the following steps:
step 1, rotating the handle, wherein the ejector rod slides in a smooth hole of the sleeve until a chuck of the valve expansion claw is in contact with a part with a smaller diameter of the smooth rod part, and the whole device is in an inward contraction state;
step 2, inserting the whole device into an inner hole of a bushing to be disassembled, rotating the handle, driving the threaded rod part to rotate in the inner threaded hole by the handle, moving the ejector rod to the bottom of the blind hole, sliding a chuck of the expanding jaw along the part with the smaller diameter of the smooth rod part until the chuck slides to the part with the larger diameter of the ejector rod along the transition conical surface, expanding the expanding jaw, and clamping the chuck of the expanding jaw on the inner side end surface of the bushing;
and 3, when the end head of the ejector rod props against the bottom of the blind hole, the handle is continuously rotated, and the sleeve drives the expanding jaw to move along the direction far away from the bottom of the blind hole, so that the chuck of the expanding jaw pulls out the bushing.
The blind hole bushing disassembling device for the aero-engine is reasonable and small in structure, convenient to operate and high in practicability, solves the problem of disassembling a bushing in a blind hole, improves the operation efficiency and the use convenience, is fed through threads, adopts mechanical expansion, is free of destructiveness, has the functions of being suitable for small spaces, long strokes and slow operation, has strong reference and reference effects on decomposition and application of similar parts, reduces the labor intensity of workers and the disassembling difficulty, does not damage the parts, and is a high-efficiency and quick using tool. Meanwhile, the device can be made into different series specifications or adjustable modes, and the separation of interference fit forms of different structural specifications is met.
Drawings
FIG. 1 is a schematic structural diagram of a lining disassembling device in a blind hole for an aircraft engine in the using process;
FIG. 2 is a side view of the inside blind hole bushing dismounting device for an aircraft engine in use;
FIG. 3 is a schematic structural view of the carrier rod provided by the present invention;
FIGS. 4 and 5 are schematic structural views of the expanding jaw provided by the present invention;
3 fig. 3 6 3 is 3 a 3 sectional 3 view 3 taken 3 along 3 line 3 a 3- 3 a 3 of 3 the 3 expanding 3 jaw 3 of 3 the 3 present 3 invention 3. 3
Wherein,
the novel screw driver comprises a top rod 1, a sleeve 2, an expansion jaw 3, a handle 4, a fastening pin 5, a rotating pin 6, a smooth rod part 7, a threaded rod part 8, a 9-end head, a smooth hole 10, a jaw mounting groove 11, a chuck 12, a threaded rod connecting part 13, a force application part 14, a wrench mounting hole 15, a connecting disc 16, a through hole 17, a lining 18, a blind hole 19 and a transition conical surface 20.
Detailed Description
In order to solve the problems that the bushing in the blind hole of an aeroengine part is difficult to disassemble, the disassembling time is long, the part is easy to damage in the disassembling process, the cost and the maintenance amount are increased, and the assembly and maintenance are delayed, as shown in figures 1 to 6, the invention provides a bushing disassembling device in the blind hole for the aeroengine, which comprises a top rod 1, a sleeve 2, an expanding jaw 3, a handle 4, a fastening pin 5 and a rotating pin 6;
the ejector rod 1 is provided with a polished rod part 7, a threaded rod part 8 and an end head 9, the polished rod part 7 is a stepped cylinder, the part with the larger diameter of the stepped cylinder is connected with the part with the smaller diameter through a transition conical surface 20, the part with the larger diameter of the stepped cylinder is connected with one end of the threaded rod part 8, the other end of the threaded rod part 8 is connected with the handle 4 through a fastening pin 5, and the part with the smaller diameter of the stepped cylinder is connected with the end head 9;
an internal thread hole and a unthreaded hole 10 are arranged in the sleeve 2, the internal thread hole is communicated with the unthreaded hole 10, a polished rod part 7 of the ejector rod 1 is positioned in the unthreaded hole 10, and a threaded rod part 8 of the ejector rod 1 is matched with the internal thread hole;
evenly be equipped with a plurality of jack catch mounting grooves 11 on sleeve 2's the lateral wall, every jack catch mounting groove 11 all communicates with unthreaded hole 10, all install an bloated lamella jack catch 3 in every jack catch mounting groove 11, the one end of bloated lamella jack catch 3 is equipped with dop 12, the other end passes through kingpin 6 to be installed in jack catch mounting groove 11, preferably, can set up three jack catch mounting groove 11 on sleeve 2's the lateral wall, three jack catch mounting groove 11 evenly sets up along sleeve 2's circumference.
In the invention, the handle 4 comprises a threaded rod connecting part 13 and a force application part 14, the threaded rod connecting part 13 is connected with the force application part 14, the threaded rod connecting part 13 is provided with a threaded rod mounting hole, the other end of the threaded rod part 8 is mounted in the threaded rod mounting hole through a fastening pin 5 to prevent the ejector rod 1 and the handle 4 from rotating relatively, a plurality of wrench mounting holes 15 can be arranged on the side wall of the force application part 14, and in the using process, a wrench can be inserted into the wrench mounting holes 15 to rotate the handle 4 through rotating the wrench.
In the present invention, it is also possible to provide a connection pad 16 for the sleeve 2, the connection pad 16 being connected to a cylindrical portion of the sleeve 2, a plurality of jaw mounting grooves 11 being provided on the cylindrical portion, and a through hole 17 being provided on the connection pad 16, so that when the entire apparatus is not in use, a rope can be passed through the through hole 17 of the connection pad 16 and hung in a workshop.
The use method of the device for disassembling the bush in the blind hole for the aeroengine comprises the following steps:
step 1, rotating the handle 4, inserting a wrench into a wrench mounting hole 15 to rotate the handle 4, sliding the ejector rod 1 in the unthreaded hole 10 of the sleeve 2 until a chuck 12 of the valve expanding jaw 3 is contacted with a part with a smaller diameter of the polished rod part 7, and keeping the whole device in an inward contraction state;
step 2, inserting the whole device into an inner hole of a bushing 18 to be disassembled, rotating a handle 4, driving a threaded rod part 8 to rotate in an inner threaded hole by the handle 4, simultaneously moving an ejector rod 1 to the bottom of a blind hole 19, sliding a chuck 12 of an expanding jaw 3 along a part with a smaller diameter of a smooth rod part 7 until the chuck 12 slides along a transition conical surface 20 to a part with a larger diameter of the ejector rod 1, expanding the expanding jaw 3, and at the moment, keeping the whole device in an expansion state, and clamping the inner side end face of the bushing 18 by the chuck 12 of the expanding jaw 3;
and 3, continuing rotating the handle 4, and when the end head 9 of the ejector rod 1 abuts against the bottom of the blind hole 19, continuing rotating the handle 4, wherein the bottom of the blind hole 19 abuts against the ejector rod 1, so that the sleeve 2 drives the expanding jaw 3 to move in the direction away from the bottom of the blind hole 19, and the chuck 12 of the expanding jaw 3 extracts the bush 18 to separate the bush 18 from the matching surface.
The blind hole bushing disassembling device for the aero-engine is reasonable and small in structure, convenient to operate and high in practicability, solves the problem of disassembling a bushing in a blind hole, improves the operation efficiency and the use convenience, is fed through threads, adopts mechanical expansion, is free of destructiveness, has the functions of being suitable for small spaces, long strokes and slow operation, has strong reference and reference effects on decomposition and application of similar parts, reduces the labor intensity of workers and the disassembling difficulty, does not damage the parts, and is a high-efficiency and quick using tool. Meanwhile, the device can be made into different series specifications or adjustable modes, and the separation of interference fit forms of different structural specifications is met.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (5)
1. The device for disassembling the bush in the blind hole for the aero-engine is characterized by comprising a top rod, a sleeve, an expansion claw, a handle, a fastening pin and a rotating pin, wherein the top rod is connected with the sleeve;
the ejector rod is provided with a polished rod part, a threaded rod part and an end head, the polished rod part is a stepped cylinder, the part with the larger diameter of the stepped cylinder is connected with the part with the smaller diameter through a transition conical surface, the part with the larger diameter of the stepped cylinder is connected with one end of the threaded rod part, the other end of the threaded rod part is connected with the handle through a fastening pin, and the part with the smaller diameter of the stepped cylinder is connected with the end head;
an internal thread hole and a unthreaded hole are arranged in the sleeve and are communicated, a polished rod part of the ejector rod is positioned in the unthreaded hole, and a threaded rod part of the ejector rod is matched with the internal thread hole;
evenly be equipped with a plurality of jack catch mounting grooves on the telescopic lateral wall, every jack catch mounting groove all with the unthreaded hole intercommunication all installs an expand lamella jack catch in every jack catch mounting groove, and the one end of expanding lamella jack catch is equipped with the dop, and the other end passes through the rotational pin to be installed in the jack catch mounting groove.
2. The apparatus for disassembling a bush in a blind hole for an aircraft engine according to claim 1, wherein a plurality of wrench mounting holes are provided on a side wall of the handle.
3. The apparatus for disassembling the bush in the blind hole for the aircraft engine as claimed in claim 1, wherein the side wall of the sleeve is provided with three jaw mounting grooves, and the three jaw mounting grooves are uniformly arranged along the circumference of the sleeve.
4. The apparatus for disassembling a bush in a blind hole for an aircraft engine according to claim 1, wherein the sleeve is further provided with a connecting plate, and the connecting plate is provided with a through hole.
5. The use of an apparatus for disassembling bushings in blind holes for aircraft engines according to claim 1, characterized in that it comprises:
step 1, rotating the handle, wherein the ejector rod slides in a smooth hole of the sleeve until a chuck of the valve expansion claw is in contact with a part with a smaller diameter of the smooth rod part, and the whole device is in an inward contraction state;
step 2, inserting the whole device into an inner hole of a bushing to be disassembled, rotating the handle, driving the threaded rod part to rotate in the inner threaded hole by the handle, moving the ejector rod to the bottom of the blind hole, sliding a chuck of the expanding jaw along the part with the smaller diameter of the smooth rod part until the chuck slides to the part with the larger diameter of the ejector rod along the transition conical surface, expanding the expanding jaw, and clamping the chuck of the expanding jaw on the inner side end surface of the bushing;
and 3, when the end head of the ejector rod props against the bottom of the blind hole, the handle is continuously rotated, and the sleeve drives the expanding jaw to move along the direction far away from the bottom of the blind hole, so that the chuck of the expanding jaw pulls out the bushing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711248237.1A CN107984427A (en) | 2017-12-01 | 2017-12-01 | A kind of aero-engine is with disassembling bushing device and application method in blind hole |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711248237.1A CN107984427A (en) | 2017-12-01 | 2017-12-01 | A kind of aero-engine is with disassembling bushing device and application method in blind hole |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107984427A true CN107984427A (en) | 2018-05-04 |
Family
ID=62035131
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711248237.1A Pending CN107984427A (en) | 2017-12-01 | 2017-12-01 | A kind of aero-engine is with disassembling bushing device and application method in blind hole |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107984427A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111890288A (en) * | 2019-12-20 | 2020-11-06 | 中国航发长春控制科技有限公司 | Decomposition device of thin-wall part |
| CN112091863A (en) * | 2020-09-17 | 2020-12-18 | 中国航发成都发动机有限公司 | Elastic locking device for disassembling turbofan engine rotor |
| CN114425756A (en) * | 2022-02-25 | 2022-05-03 | 万永超 | Bush separator for machining |
| CN114986441A (en) * | 2022-07-13 | 2022-09-02 | 重庆蓝黛传动机械有限公司 | Blind hole shaft sleeve dismounting tool |
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| CN2098998U (en) * | 1991-06-18 | 1992-03-18 | 李蔡清 | Appliance for disassemble air valve port |
| US5406685A (en) * | 1993-10-15 | 1995-04-18 | Harmand; Brice | Pulling tool for extracting ring inserts |
| CN2504028Y (en) * | 2001-10-24 | 2002-08-07 | 程漠贵 | Piston puller |
| CN2838871Y (en) * | 2005-10-10 | 2006-11-22 | 孙奖洪 | Setscrew demountor and setscrew |
| CN2887537Y (en) * | 2006-01-04 | 2007-04-11 | 张银根 | Inner and outer rim puller for bearing |
| CN201143661Y (en) * | 2007-10-17 | 2008-11-05 | 比亚迪股份有限公司 | Bearing outer ring moving-pulling machine |
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| CN103240711A (en) * | 2013-04-25 | 2013-08-14 | 江汉大学 | Expansion unscrew device |
| CN203752080U (en) * | 2014-03-31 | 2014-08-06 | 昌河飞机工业（集团）有限责任公司 | Device for taking out bush |
| CN104015157A (en) * | 2014-06-05 | 2014-09-03 | 中国人民解放军第五七二一工厂 | Tightly-propping pulling type detaching device for bearing neck bush |
| CN203887794U (en) * | 2014-06-23 | 2014-10-22 | 山西平阳重工机械有限责任公司 | Self-positioning blind hole bearing disassembling device |
| CN203901215U (en) * | 2014-06-18 | 2014-10-29 | 中国人民解放军第五七二一工厂 | Tool for disassembling bearing bush in blind hole |
| CN204263073U (en) * | 2014-10-31 | 2015-04-15 | 中国第一汽车股份有限公司 | A kind of bushing dismounting instrument |
| CN104608093A (en) * | 2015-01-13 | 2015-05-13 | 哈尔滨飞机工业集团有限责任公司 | Method for installing locating lining in and taking locating lining out of tool blind hole |
| CN206048078U (en) * | 2016-08-25 | 2017-03-29 | 成都飞机工业（集团）有限责任公司 | A kind of blind hole bushing pulling off device |
-
2017
- 2017-12-01 CN CN201711248237.1A patent/CN107984427A/en active Pending
Patent Citations (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2098998U (en) * | 1991-06-18 | 1992-03-18 | 李蔡清 | Appliance for disassemble air valve port |
| US5406685A (en) * | 1993-10-15 | 1995-04-18 | Harmand; Brice | Pulling tool for extracting ring inserts |
| CN2504028Y (en) * | 2001-10-24 | 2002-08-07 | 程漠贵 | Piston puller |
| CN2838871Y (en) * | 2005-10-10 | 2006-11-22 | 孙奖洪 | Setscrew demountor and setscrew |
| CN2887537Y (en) * | 2006-01-04 | 2007-04-11 | 张银根 | Inner and outer rim puller for bearing |
| CN201143661Y (en) * | 2007-10-17 | 2008-11-05 | 比亚迪股份有限公司 | Bearing outer ring moving-pulling machine |
| CN201261178Y (en) * | 2008-10-07 | 2009-06-24 | 汤志刚 | Bush drawing device |
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| CN103240711A (en) * | 2013-04-25 | 2013-08-14 | 江汉大学 | Expansion unscrew device |
| CN203752080U (en) * | 2014-03-31 | 2014-08-06 | 昌河飞机工业（集团）有限责任公司 | Device for taking out bush |
| CN104015157A (en) * | 2014-06-05 | 2014-09-03 | 中国人民解放军第五七二一工厂 | Tightly-propping pulling type detaching device for bearing neck bush |
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| CN203887794U (en) * | 2014-06-23 | 2014-10-22 | 山西平阳重工机械有限责任公司 | Self-positioning blind hole bearing disassembling device |
| CN204263073U (en) * | 2014-10-31 | 2015-04-15 | 中国第一汽车股份有限公司 | A kind of bushing dismounting instrument |
| CN104608093A (en) * | 2015-01-13 | 2015-05-13 | 哈尔滨飞机工业集团有限责任公司 | Method for installing locating lining in and taking locating lining out of tool blind hole |
| CN206048078U (en) * | 2016-08-25 | 2017-03-29 | 成都飞机工业（集团）有限责任公司 | A kind of blind hole bushing pulling off device |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111890288A (en) * | 2019-12-20 | 2020-11-06 | 中国航发长春控制科技有限公司 | Decomposition device of thin-wall part |
| CN112091863A (en) * | 2020-09-17 | 2020-12-18 | 中国航发成都发动机有限公司 | Elastic locking device for disassembling turbofan engine rotor |
| CN114425756A (en) * | 2022-02-25 | 2022-05-03 | 万永超 | Bush separator for machining |
| CN114986441A (en) * | 2022-07-13 | 2022-09-02 | 重庆蓝黛传动机械有限公司 | Blind hole shaft sleeve dismounting tool |
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Application publication date: 20180504 |