CN107738223B - Auxiliary assembly and disassembly tool for fairing of first-stage stator blade of aircraft engine - Google Patents
Auxiliary assembly and disassembly tool for fairing of first-stage stator blade of aircraft engine Download PDFInfo
- Publication number
- CN107738223B CN107738223B CN201711111848.1A CN201711111848A CN107738223B CN 107738223 B CN107738223 B CN 107738223B CN 201711111848 A CN201711111848 A CN 201711111848A CN 107738223 B CN107738223 B CN 107738223B
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- China
- Prior art keywords
- fairing
- stage stator
- head
- auxiliary fixture
- aircraft engine
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- 239000000463 material Substances 0.000 claims description 4
- 230000006378 damage Effects 0.000 description 5
- 210000004907 gland Anatomy 0.000 description 4
- 230000003139 buffering effect Effects 0.000 description 3
- 230000002411 adverse Effects 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 208000027418 Wounds and injury Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 208000014674 injury Diseases 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 230000017105 transposition 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
- B25B27/14—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for assembling objects other than by press fit or detaching same
-
- 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
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
- B25B11/02—Assembly jigs
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Details Of Aerials (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
An auxiliary assembly for disassembly and assembly of a first stage stator vane fairing of an aircraft engine, comprising: the clamping device comprises a support, N connecting rods, a supporting block, a swivel base, a rotating rod and M clamping jaws. And each clamping jaw surrounds the periphery of the fairing of the first-stage stator blade, the clamping head is hooked on the outer edge of the fairing, and the arc-shaped grooves on each supporting block are aligned with the front lip of the engine and are contacted with the front lip of the engine, so that the whole tool is supported. The swivel mount is then rotated and moved down the screw head to drive the jaws down to remove the first stage stator vane fairing. And similarly, when the rotary seat is reversely rotated to enable the rotary seat to upwards move along the thread head, each clamping jaw moves upwards, so that the first-stage stator blade fairing is installed. The disassembly and assembly efficiency and the disassembly and assembly precision of the first-stage stator blade fairing are improved.
Description
Technical Field
The invention relates to the field of aircraft maintenance, in particular to an auxiliary tool for dismounting a fairing of a first-stage stator blade of an aircraft engine.
Background
The engine is a core part of the aircraft and is a main power source for the aircraft to fly. The engine has a very harsh structure and parts in a working environment, and is surrounded by various adverse factors which are easy to cause structural corrosion, fatigue, part damage and damage, such as high temperature, low temperature, high-low temperature alternation, high vibration, various corrosive gases, liquid, foreign matters, wind erosion and the like. Due to the fact that the first-stage stator blade assembly of the engine is corroded, layered and structurally damaged due to the adverse factors, when the first-stage guide blade fairing is dismounted, due to the fact that the component is subjected to high vibration, high-low temperature alternation and the influence of various corrosive gas liquids for a long time, the fairing is tightly attached to the engine structure, when an existing special tool is used in combination with a PULL clamp, the fairing is difficult to dismount, damage to a special opening for dismounting the fairing is easily caused, and even due to the fact that a worker forcefully breaks hard to enable the PULL clamp to separate from the special tool, an air inlet is injured or injury to the worker is caused. When the first-stage guide vane fairing is installed, the fairing must be adjusted to the required position, but accurate fine adjustment is difficult to achieve by manpower, and the existing process has no special tool for adjusting the position and can only be adjusted by hands, so that the work is very difficult. Not only wasting a large amount of time and manpower, influencing the aircraft cycle, possibly even causing the potential safety hazard of aircraft.
Disclosure of Invention
In order to overcome the defects of the technology, the invention provides a tool for improving the precision of the disassembly and assembly efficiency of the first-stage stator blade fairing of the aircraft engine.
The technical scheme adopted for overcoming the technical problems is as follows:
an auxiliary assembly for disassembly and assembly of a first stage stator vane fairing of an aircraft engine, comprising:
the support is vertically provided with a thread head;
n connecting rods are uniformly arranged at intervals along the circumferential direction of the support, and N is a natural number approximately equal to 2;
the support block is arranged at the head end of the connecting rod and is provided with an arc-shaped groove matched with the front lip of the engine;
the rotary seat is screwed on the thread head through threaded connection;
the rotating rod is rotatably arranged on the swivel base; and
m clamping jaws are uniformly arranged at intervals on the head end of the rotating rod along the circumferential direction, M is a natural number greater than or equal to 3, and clamping heads are arranged on the inner sides of the head ends of the clamping jaws;
each clamping jaw surrounds the periphery of the fairing of the first-stage stator blade, and the clamping head is hooked on the outer edge of the fairing.
In order to play a role of buffering, the supporting block is made of rubber materials.
For convenient operation, the rotary seat is provided with a plurality of handle bars at intervals along the circumferential direction.
In order to realize angle matching, the tail end of the rotating rod is provided with a ball head, a ball groove matched with the ball head is formed in the rotating base, a round hole with the inner diameter larger than the outer diameter of the rotating rod and smaller than the outer diameter of the ball head is formed in the pressing cover, and the pressing cover penetrates through the rotating rod and is fixed to the head end of the rotating base, so that the ball head is clamped between the rotating base and the pressing cover.
In order to further improve the supportability, the engine air inlet pipe further comprises a supporting rod, a supporting disc and a tension spring, wherein the supporting rod is hinged to the connecting rod through a pin shaft I, the supporting disc is hinged to the head end of the supporting rod through a pin shaft II, one end of the tension spring is connected to the supporting rod, the other end of the tension spring is connected to the connecting rod, and the supporting disc is in contact with the inner wall of the engine air inlet pipe.
In order to firmly clamp the fairing by the clamping jaw, the device further comprises a sliding rod arranged at the head end of the rotating rod along the axial direction of the rotating rod, a sliding ring slidably arranged on the sliding rod, a hinging seat hinged on the clamping jaw and M screws arranged at equal intervals along the circumferential direction, one end of the connecting rod is screwed on the hinging seat through threads, and the other end of the connecting rod is screwed on the screws through threads.
For skid prevention and buffering, a rubber pad is arranged on the supporting disc.
The beneficial effects of the invention are as follows: and each clamping jaw surrounds the periphery of the fairing of the first-stage stator blade, the clamping head is hooked on the outer edge of the fairing, and the arc-shaped grooves on each supporting block are aligned with the front lip of the engine and are contacted with the front lip of the engine, so that the whole tool is supported. The swivel mount is then rotated and moved down the screw head to drive the jaws down to remove the first stage stator vane fairing. And similarly, when the rotary seat is reversely rotated to enable the rotary seat to upwards move along the thread head, each clamping jaw moves upwards, so that the first-stage stator blade fairing is installed. The disassembly and assembly efficiency and the disassembly and assembly precision of the first-stage stator blade fairing are improved.
Drawings
FIG. 1 is a schematic perspective view of the present invention;
FIG. 2 is an exploded view of a three-dimensional structure of a transposition portion according to the present invention;
in the figure, 1, a support 2, a connecting rod 3, a supporting block 4, an arc-shaped groove 5, a pin shaft I6, a supporting rod 7, a pin shaft II 8, a supporting disc 9, a tension spring 10, a threaded head 11, a swivel seat 12, a handle rod 13, a gland 14, a rotary rod 15, a ball head 16, a clamping jaw 17, a clamping head 18, a sliding rod 19, a sliding ring 20, a screw rod 21, a hinge seat.
Detailed Description
The invention is further described with reference to fig. 1 and 2.
An auxiliary assembly for disassembly and assembly of a first stage stator vane fairing of an aircraft engine, comprising: a support 1, which is vertically mounted with a screw head 10; n connecting rods 2 which are uniformly spaced along the circumferential direction of the support 1, wherein N is a natural number approximately equal to 2; the support block 3 is arranged at the head end of the connecting rod 2, and an arc-shaped groove 4 matched with the front lip of the engine is arranged on the support block 3; the rotary seat 11 is screwed on the thread head 10 through threaded connection; the rotating rod 14 is rotatably arranged on the swivel seat 11; and M clamping jaws 16 which are uniformly arranged at intervals along the circumferential direction at the head end of the rotating rod 14, wherein M is a natural number greater than or equal to 3, and clamping heads 17 are arranged at the inner sides of the head ends of the clamping jaws 15. When the tool is used, the clamping jaws 15 encircle the periphery of the fairing of the first-stage stator blade, the clamping heads 17 are hooked on the outer edge of the fairing, the arc-shaped grooves 4 on the supporting blocks 3 are aligned with the front lip of the engine and are contacted with the front lip of the engine, and the whole tool is supported. The swivel mount 11 is then rotated and moved down the screw head 10 to drive the respective jaws 15 down to remove the first stage stator vane fairing. Similarly, when the swivel mount 11 is rotated reversely to move upward along the screw head 10, the respective clamping jaws 15 are moved upward, thereby realizing the mounting of the first-stage stator vane fairing. The disassembly and assembly efficiency and the disassembly and assembly precision of the first-stage stator blade fairing are improved.
Preferably, the support block 3 is made of a rubber material. The rubber material support block 3 can play a role of stress buffering when contacting with the engine front lip, and prevent the engine front lip from being damaged. The swivel seat 11 is provided with a plurality of handle bars 12 at intervals along the circumferential direction. The swivel seat 11 can be driven to rotate by the handle bar 12, thereby further improving the convenience of operation.
Further, the tail end of the rotating rod 14 is provided with a ball head 15, the rotating seat 11 is provided with a ball groove matched with the ball head 15, the gland 13 is provided with a round hole with an inner diameter larger than the outer diameter of the rotating rod 14 and smaller than the outer diameter of the ball head 15, and the gland 13 penetrates through the rotating rod 14 and then is fixed at the head end of the rotating seat 11, so that the ball head 15 is clamped between the rotating seat 11 and the gland 13. Because the ball head 15 is rotationally connected with the swivel seat 11, the rotating rod 14 can deflect towards any angle, and the device is convenient for adapting to the use environment with inconsistent inner gradient of the engine.
Further, the engine air inlet is characterized by further comprising a supporting rod 6, a supporting disc 8 and a tension spring 9, wherein the bottom of the supporting rod 6 is hinged to the connecting rod 2 through a pin shaft I5, the supporting disc 8 is hinged to the head end of the supporting rod 6 through a pin shaft II 7, one end of the tension spring 9 is connected to the supporting rod 6, the other end of the tension spring is connected to the connecting rod 2, and the supporting disc 8 is in contact with the inner wall of the engine air inlet channel. When the front lip of the engine contacts with the supporting block 3, the supporting rod 6 can deflect and the supporting disc 8 can deflect, so that the supporting disc 8 is attached to the inner wall of the engine air inlet, and the supporting disc 8 is tightly attached to the inner wall of the engine air inlet under the tension of the tension spring 9, so that the support of the inside of the engine is realized. The stability of the support is improved. Preferably, be provided with the rubber pad on the supporting disk 8, laminate with engine intake inner wall through the rubber pad not only improved frictional force, can also cushion pressure, prevent to damage the engine intake.
Further, the device also comprises a sliding rod 18 arranged at the head end of the rotating rod 14 along the axial direction of the rotating rod 14, a sliding ring 19 slidably arranged on the sliding rod 18, a hinging seat 22 hinged on the clamping jaw 16, and M screws 20 uniformly arranged at intervals along the circumferential direction, wherein one end of the connecting rod 21 is screwed on the hinging seat 22 through threads, and the other end of the connecting rod is screwed on the screws 20 through threads. After the clamping jaw 15 surrounds the periphery of the fairing of the first-stage stator blade and the clamping head 17 is hooked on the outer edge of the fairing, each clamping jaw 15 can be closed inwards by rotating each connecting rod 21, so that the fairing is clamped by the clamping jaw, falling off during disassembly is prevented, and the use safety is improved.
Claims (7)
1. The utility model provides an dismouting auxiliary fixtures of aircraft engine first level stator blade radome, its characterized in that includes:
a support (1) vertically mounted with a screw head (10);
n connecting rods (2) which are uniformly arranged at intervals along the circumferential direction of the support (1), wherein N is a natural number approximately equal to 2;
the support block (3) is arranged at the head end of the connecting rod (2), and an arc-shaped groove (4) matched with the front lip of the engine is arranged on the support block (3);
the rotary seat (11) is screwed on the thread head (10) through threaded connection;
the rotating rod (14) is rotatably arranged on the swivel base (11); and
m clamping jaws (16) are uniformly arranged at intervals at the head end of the rotating rod (14) along the circumferential direction, M is a natural number which is more than or equal to 3, and clamping heads (17) are arranged at the inner side of the head end of each clamping jaw (15);
each clamping jaw (15) surrounds the periphery of the fairing of the first-stage stator blade, and the clamping head (17) is hooked on the outer edge of the fairing.
2. The auxiliary fixture for assembling and disassembling the first-stage stator vane fairing of the aircraft engine according to claim 1, wherein the auxiliary fixture is characterized in that: the supporting block (3) is made of rubber material.
3. The auxiliary fixture for assembling and disassembling the first-stage stator vane fairing of the aircraft engine according to claim 1, wherein the auxiliary fixture is characterized in that: the rotary seat (11) is provided with a plurality of handle bars (12) at intervals along the circumferential direction.
4. The auxiliary fixture for assembling and disassembling the first-stage stator vane fairing of the aircraft engine according to claim 1, wherein the auxiliary fixture is characterized in that: the tail end of the rotating rod (14) is provided with a ball head (15), a ball groove matched with the ball head (15) is formed in the rotating base (11), a round hole with the inner diameter larger than the outer diameter of the rotating rod (14) and smaller than the outer diameter of the ball head (15) is formed in the pressing cover (13), the pressing cover (13) penetrates through the rotating rod (14) and then is fixed to the head end of the rotating base (11), and the ball head (15) is clamped between the rotating base (11) and the pressing cover (13).
5. The auxiliary fixture for assembling and disassembling the first-stage stator vane fairing of the aircraft engine according to claim 1, wherein the auxiliary fixture is characterized in that: still include bottom through round pin axle I (5) articulated bracing piece (6) of installing on connecting rod (2), install in supporting disk (8) and extension spring (9) of bracing piece (6) head end through round pin axle II (7) articulated, extension spring (9) one end is connected in bracing piece (6), and its other end is connected in connecting rod (2), supporting disk (8) are contacted with engine intake duct inner wall.
6. The auxiliary fixture for assembling and disassembling the first-stage stator vane fairing of the aircraft engine according to claim 1, wherein the auxiliary fixture is characterized in that: the novel rotary clamping device is characterized by further comprising a sliding rod (18) arranged at the head end of the rotating rod (14) along the axial direction of the rotating rod (14), a sliding ring (19) slidably mounted on the sliding rod (18), a hinging seat (22) hinged on the clamping jaw (16) and M screws (20) uniformly arranged at intervals along the circumferential direction, wherein one end of the connecting rod (21) is screwed on the hinging seat (22) through threads, and the other end of the connecting rod is screwed on the screws (20) through threads.
7. The auxiliary fixture for assembling and disassembling the first-stage stator vane fairing of the aircraft engine according to claim 5, wherein the auxiliary fixture comprises: and a rubber pad is arranged on the supporting disc (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711111848.1A CN107738223B (en) | 2017-11-13 | 2017-11-13 | Auxiliary assembly and disassembly tool for fairing of first-stage stator blade of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711111848.1A CN107738223B (en) | 2017-11-13 | 2017-11-13 | Auxiliary assembly and disassembly tool for fairing of first-stage stator blade of aircraft engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107738223A CN107738223A (en) | 2018-02-27 |
| CN107738223B true CN107738223B (en) | 2023-11-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711111848.1A Active CN107738223B (en) | 2017-11-13 | 2017-11-13 | Auxiliary assembly and disassembly tool for fairing of first-stage stator blade of aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107738223B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109600003B (en) * | 2018-12-18 | 2020-11-06 | 中国航发沈阳发动机研究所 | Engine rotor blade dismounting device |
| CN109676562A (en) * | 2018-12-19 | 2019-04-26 | 中国航发沈阳发动机研究所 | A kind of aero-engine low-pressure turbine guide vane mounting device |
| CN110576414B (en) * | 2019-08-12 | 2020-12-25 | 江苏恒丰橡胶制品有限公司 | Sealing washer cup joints device and equipment thereof |
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| CN107738223A (en) | 2018-02-27 |
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