CN107738223A - The dismounting auxiliary mould of aircraft engine first order stator blade radome fairing - Google Patents
The dismounting auxiliary mould of aircraft engine first order stator blade radome fairing Download PDFInfo
- Publication number
- CN107738223A CN107738223A CN201711111848.1A CN201711111848A CN107738223A CN 107738223 A CN107738223 A CN 107738223A CN 201711111848 A CN201711111848 A CN 201711111848A CN 107738223 A CN107738223 A CN 107738223A
- Authority
- CN
- China
- Prior art keywords
- radome fairing
- stator blade
- order stator
- clamping jaw
- bull stick
- 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.)
- Granted
Links
- 244000309464 bull Species 0.000 claims abstract description 24
- 210000004907 gland Anatomy 0.000 claims description 9
- 239000013536 elastomeric material Substances 0.000 claims description 4
- 102000008579 Transposases Human genes 0.000 description 11
- 108010020764 Transposases Proteins 0.000 description 11
- 230000006378 damage Effects 0.000 description 4
- 230000003139 buffering effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000003628 erosive effect Effects 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
- 238000010586 diagram Methods 0.000 description 1
- 239000002360 explosive Substances 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
- 230000003319 supportive effect Effects 0.000 description 1
- 239000002699 waste material Substances 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
A kind of dismounting auxiliary mould of aircraft engine first order stator blade radome fairing, including：Bearing, N number of connecting rod, support block, swivel base, bull stick and M clamping jaw.Each clamping jaw is surrounded on first order stator blade radome fairing periphery, dop is hooked in the outer rim of radome fairing, and the deep-slotted chip breaker in each support block is aligned into engine anterior lip, and is allowed to be in contact with it, and realizes the support to whole frock.Swivel base is rotated afterwards, and threadingly head moves downward for it, so as to drive each clamping jaw to move down, so as to which first order stator blade radome fairing be pulled down.With should rotate backward swivel base, when making it threadingly head moving upwards, each clamping jaw moves up, and installs first order stator blade radome fairing so as to realize.Improve first order stator blade radome fairing disassembly efficiency and dismounting precision.
Description
Technical field
The present invention relates to aircraft maintenance field, and in particular to a kind of aircraft engine first order stator blade radome fairing is torn open
Fill auxiliary mould.
Background technology
Engine is the core of aircraft, is the main power source of aircraft flight.Residing for the structure and part of engine
Working environment it is very severe, more in high temperature, low temperature, high and low temperature alternative, high vibrations, various corrosivity air-liquid bodies, foreign matter,
Wind erosion etc. is a variety of to easily cause structure erosion, fatigue, components damage, the unfavorable factor of damage encirclement among.Due to above-mentioned unfavorable
Factor causes engine first order stator vane assembly that burn into layering and structural failure occurs, and is removing first order directing vane
During piece radome fairing, because the part is chronically at the influence of high vibrations, high and low temperature alternative and all kinds of etchant gas liquid so that
Radome fairing is bonded very tight with engine structure, is coordinating PULL- draw vices in use, it is difficult to will be whole using existing specific purpose tool
Stream cover is removed, but also is easily caused radome fairing and removed the damage that goes out of dedicated port, in addition due to when removing staff exert oneself
It is too quickly so that PULL- draw vices depart from specific purpose tool, injure air intake duct by a crashing object or cause the injury of staff.The first order is installed to be oriented to
During blade radome fairing, it is necessary to radome fairing is adjusted to the position of its requirement, but is difficult to accomplish precise vernier adjustment by manpower, Er Qiexian
Some technique does not have the specific purpose tool of adjustment position, is only capable of armrest and goes to adjust, therefore it is very difficult to work.Not only waste substantial amounts of
Time and manpower, the aircraft cycle is influenceed, it could even be possible to causing the potential safety hazard of aircraft.
The content of the invention
The present invention is in order to overcome the shortcomings of above technology, there is provided it is whole that one kind improves aircraft engine first order stator blade
Flow the frock of the disassembly efficiency essence precision of cover.
Technical scheme is used by the present invention overcomes its technical problem：
A kind of dismounting auxiliary mould of aircraft engine first order stator blade radome fairing, including：
Bearing, its is vertically-mounted thread head；
N number of connecting rod, it is set along seating circumference direction uniform intervals, and N is approximately equal to 2 natural number；
Support block, the head end of connecting rod is installed on, the deep-slotted chip breaker to match with engine anterior lip is provided with the support block；
Swivel base, it is connected through a screw thread and is combined on thread head；
Bull stick, it is rotatablely installed on swivel base；And
M clamping jaw, along the circumferential direction uniform intervals be arranged at the head end of bull stick, M is the natural number more than or equal to 3, the clamping jaw
Head end on the inside of be provided with dop；
Each clamping jaw is surrounded on first order stator blade radome fairing periphery, and the dop is hooked in the outer rim of radome fairing.
In order to play cushioning effect, above-mentioned support block is made up of elastomeric material.
In order to facilitate operation, above-mentioned swivel base is circumferentially spaced to be provided with some handlebar stems.
In order to realize angle automatching, the tail end of above-mentioned bull stick is provided with bulb, is provided with the swivel base and matches with bulb
Ball groove, internal diameter is provided with gland more than bull stick external diameter and is fixed on less than the circular hole of bulb external diameter, gland after passing through bull stick
The head end of swivel base, bulb is clipped between swivel base and gland by it.
In order to further improve supportive, in addition to bottom is hinged the support bar being installed on connecting rod by bearing pin I, passed through
The be hinged support plate for being installed on support rod head end of pin shaft II and extension spring, described extension spring one end are connected to support bar, its other end
Connecting rod is connected to, the support plate is in contact with engine inlets inwall.
In order to which clamping jaw firmly clamps radome fairing, in addition to along bull stick the slide bar for being axially set in bull stick head end, slide
M spiral shell of the slip ring, the be hinged hinged seat being installed on clamping jaw and the along the circumferential direction uniform intervals setting that are installed on slide bar
Bar, connecting rod one end is by threaded engagement on hinged seat, and its other end is by threaded engagement on screw rod.
For anti-skidding and buffering, rubber blanket is provided with above-mentioned support plate.
The beneficial effects of the invention are as follows：Each clamping jaw is surrounded on first order stator blade radome fairing periphery, dop hooks
In in the outer rim of radome fairing, the deep-slotted chip breaker in each support block is directed at engine anterior lip, and is allowed to be in contact with it, is realized to whole
The support of individual frock.Swivel base is rotated afterwards, and threadingly head moves downward for it, so as to drive each clamping jaw to move down, so as to by first
Level stator blade radome fairing is pulled down.With should rotate backward swivel base, when making it threadingly head moving upwards, each clamping jaw moves up,
First order stator blade radome fairing is installed so as to realize.Improve first order stator blade radome fairing disassembly efficiency and dismounting essence
Degree.
Brief description of the drawings
Fig. 1 is the dimensional structure diagram of the present invention；
Fig. 2 is the swivel base position stereochemical structure explosive view of the present invention；
In figure, the support plate of 1. bearing, 2. connecting rod, 3. support block, 4. deep-slotted chip breaker, 5. bearing pin, I 6. support bar, 7. pin shaft II 8.
9. the dop of 16. clamping jaw of extension spring 10. thread head, 11. transposase 11,2. handlebar stem, 13. gland, 14. bull stick, 15. bulb 17.
18. the hinged seat of 21. connecting rod of slide bar 19. slip ring, 20. screw rod 22..
Embodiment
Below in conjunction with the accompanying drawings 1, the present invention will be further described for accompanying drawing 2.
A kind of dismounting auxiliary mould of aircraft engine first order stator blade radome fairing, including：Bearing 1, its vertical peace
Equipped with thread head 10；N number of connecting rod 2, it is set along the circumferencial direction uniform intervals of bearing 1, and N is approximately equal to 2 natural number；Support
Block 3, the head end of connecting rod 2 is installed on, the deep-slotted chip breaker 4 to match with engine anterior lip is provided with support block 3；Transposase 11 1, passes through
Threaded connection is combined on thread head 10；Bull stick 14, it is rotatablely installed on transposase 11 1；And M clamping jaw 16, along the circumferential direction
The even head end for being arranged at intervals at bull stick 14, M are the natural number more than or equal to 3, and dop 17 is provided with the inside of the head end of clamping jaw 15.Make
Used time, each clamping jaw 15 is surrounded on first order stator blade radome fairing periphery, dop 17 is hooked in the outer rim of radome fairing, will
Deep-slotted chip breaker 4 in each support block 3 is directed at engine anterior lip, and is allowed to be in contact with it, and realizes the support to whole frock.Afterwards
Transposase 11 1 is rotated, threadingly first 10 move downward for it, so as to drive each clamping jaw 15 to move down, so as to which first order stator blade is whole
Stream cover is pulled down.With transposase 11 1 should be rotated backward, make its threadingly first 10 upwards motion when, each clamping jaw 15 moves up, so as to real
Now first order stator blade radome fairing is installed.Improve first order stator blade radome fairing disassembly efficiency and dismounting precision.
Preferably, support block 3 is made up of elastomeric material.The support block 3 of elastomeric material can contact with engine anterior lip
When, stress cushioning effect is played, prevents from damaging engine anterior lip.Transposase 11 1 is circumferentially spaced to be provided with some handlebar stems
12.By handlebar stem 12 transposase 11 1 can be driven to rotate, so as to further increase the convenience of operation.
Further, the tail end of bull stick 14 is provided with bulb 15, and the ball groove to match with bulb 15, pressure are provided with transposase 11 1
Internal diameter is provided with lid 13 more than the external diameter of bull stick 14 and is fixed on less than the circular hole of the external diameter of bulb 15, gland 13 after passing through bull stick 14
The head end of transposase 11 1, bulb 15 is clipped between transposase 11 1 and gland 13 by it.Connect due to being rotated by bulb 15 and transposase 11 1
Connect, therefore bull stick 14 can deflect towards any angle, it is convenient to be adapted to the use environment that the gradient is inconsistent in engine.
Further, in addition to bottom is hinged the support bar 6 being installed on connecting rod 2, by pin shaft II 7 by bearing pin I 5
Be hinged support plate 8 and the extension spring 9 for being installed on the head end of support bar 6, the one end of extension spring 9 are connected to support bar 6, and its other end is connected to
Connecting rod 2, support plate 8 are in contact with engine inlets inwall.When engine anterior lip contacts with support block 3, due to support bar 6
It can deflect and support plate 8 can deflect, support plate 8 can be made to be bonded with engine inlets inwall, in the drawing of extension spring 9
Under power, support plate 8 is bonded the support closely, realized to engine interior with engine inlets inwall.Improve support
Stability.Preferably, rubber blanket is provided with support plate 8, is bonded not only with engine inlets inwall by rubber blanket
Frictional force is improved, row buffering can also be entered to pressure, prevents from damaging engine inlets.
Further, in addition to along bull stick 14 the slide bar 18 for being axially set in the head end of bull stick 14, be slidably mounted on slide bar
M screw rod of slip ring 19, the be hinged hinged seat 22 being installed on clamping jaw 16 and along the circumferential direction uniform intervals setting on 18
20, the one end of connecting rod 21 is by threaded engagement on hinged seat 22, and its other end is by threaded engagement on screw rod 20.When individual folder
Pawl 15 is surrounded on first order stator blade radome fairing periphery and after dop 17 is hooked in the outer rim of radome fairing, each by rotating
Connecting rod 21, each clamping jaw 15 can be made to be drawn close to inner side, so as to be that it clamps radome fairing, prevent from falling off during dismounting,
Improve the security used.
Claims (7)
- A kind of 1. dismounting auxiliary mould of aircraft engine first order stator blade radome fairing, it is characterised in that including：Bearing（1）, its is vertically-mounted thread head（10）；N number of connecting rod（2）, it is along bearing（1）Circumferencial direction uniform intervals are set, and N is approximately equal to 2 natural number；Support block（3）, it is installed on connecting rod（2）Head end, the support block（3）On be provided with the arc to match with engine anterior lip Shape groove（4）；Swivel base（11）, it is connected through a screw thread and is combined on thread head（10）On；Bull stick（14）, it is rotatablely installed in swivel base（11）On；AndM clamping jaw（16）, along the circumferential direction uniform intervals be arranged at bull stick（14）Head end, M is natural number more than or equal to 3, The clamping jaw（15）Head end on the inside of be provided with dop（17）；Each clamping jaw（15）It is surrounded on first order stator blade radome fairing periphery, the dop（17）It is hooked in the outer rim of radome fairing On.
- 2. the dismounting auxiliary mould of aircraft engine first order stator blade radome fairing according to claim 1, its feature It is：The support block（3）It is made up of elastomeric material.
- 3. the dismounting auxiliary mould of aircraft engine first order stator blade radome fairing according to claim 1, its feature It is：The swivel base（11）It is circumferentially spaced to be provided with some handlebar stems（12）.
- 4. the dismounting auxiliary mould of aircraft engine first order stator blade radome fairing according to claim 1, its feature It is：The bull stick（14）Tail end be provided with bulb（15）, the swivel base（11）On be provided with and bulb（15）The ball of matching Groove, gland（13）On be provided with internal diameter and be more than bull stick（14）External diameter and it is less than bulb（15）The circular hole of external diameter, gland（13）Pass through Bull stick（14）After be fixed on swivel base（11）Head end, it is by bulb（15）It is clipped on swivel base（11）With gland（13）Between.
- 5. the dismounting auxiliary mould of aircraft engine first order stator blade radome fairing according to claim 1, its feature It is：Also pass through bearing pin I including bottom（5）It is be hinged to be installed on connecting rod（2）On support bar（6）, pass through pin shaft II（7）Be hinged peace Loaded on support bar（6）The support plate of head end（8）And extension spring（9）, the extension spring（9）One end is connected to support bar（6）, its is another End is connected to connecting rod（2）, the support plate（8）It is in contact with engine inlets inwall.
- 6. the dismounting auxiliary mould of aircraft engine first order stator blade radome fairing according to claim 1, its feature It is：Also include along bull stick（14）Be axially set in bull stick（14）The slide bar of head end（18）, be slidably mounted on slide bar（18）On Slip ring（19）, be hinged be installed on clamping jaw（16）On hinged seat（22）And the M spiral shell that along the circumferential direction uniform intervals are set Bar（20）, connecting rod（21）One end is by threaded engagement in hinged seat（22）On, its other end is by threaded engagement in screw rod （20）On.
- 7. the dismounting auxiliary mould of aircraft engine first order stator blade radome fairing according to claim 5, its feature It is：The support plate（8）On be provided with rubber blanket.
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 true CN107738223A (en) | 2018-02-27 |
| CN107738223B CN107738223B (en) | 2023-11-10 |
Family
ID=61234386
Family Applications (1)
| 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) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109600003A (en) * | 2018-12-18 | 2019-04-09 | 中国航发沈阳发动机研究所 | Engine rotor blade disassemblerassembler |
| 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 |
| CN110576414A (en) * | 2019-08-12 | 2019-12-17 | 王远伦 | Sealing washer cup joints device and equipment thereof |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109600003A (en) * | 2018-12-18 | 2019-04-09 | 中国航发沈阳发动机研究所 | Engine rotor blade disassemblerassembler |
| 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 |
| CN110576414A (en) * | 2019-08-12 | 2019-12-17 | 王远伦 | Sealing washer cup joints device and equipment thereof |
| 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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| Publication number | Publication date |
|---|---|
| CN107738223B (en) | 2023-11-10 |
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