CN106392957A - Assembly clamp and assembly method for front baffle plate of gas turbine disc - Google Patents
Assembly clamp and assembly method for front baffle plate of gas turbine disc Download PDFInfo
- Publication number
- CN106392957A CN106392957A CN201611189640.7A CN201611189640A CN106392957A CN 106392957 A CN106392957 A CN 106392957A CN 201611189640 A CN201611189640 A CN 201611189640A CN 106392957 A CN106392957 A CN 106392957A
- Authority
- CN
- China
- Prior art keywords
- front apron
- pressure ring
- turbine disk
- assembly
- gas turbine
- 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
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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
- 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
-
- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses an assembly clamp and an assembly method for a front baffle plate of a gas turbine disc. The front baffle plate is arranged on the installation end surface of the turbine disc, an installation convex part is arranged on the installation end surface along the circumference, and a hook part is arranged on the inner circular surface of the front baffle plate and is engaged with the installation convex part. The assembly clamp comprises a base, a pull rod and a press ring assembly, wherein the pull rod is fixedly connected with the base and is used for positioning and supporting the turbine disc in the assembly process; the press ring assembly is matched with the pull rod, and is used for applying circumferential action force to the front baffle plate on the turbine disc to drive the front baffle plate and the turbine disc to be engaged and matched. The assembly clamp has the advantages that by designing the special assembly clamp for installing the front baffle plate on the turbine disc, the defect of complicated installation of the front baffle plate due to no force applying point and failure to apply circumferential action force in the installation process is overcome; by adopting the method, the requirement of one-time assembly is met, the installation cycle is effectively shortened, the installation cost is reduced, the installation is reliable, and the qualified rate of a product is effectively guaranteed.
Description
Technical field
The present invention relates to aero-engine assembling field, especially, it is related to a kind of gas turbine disk front apron assembling jig
And assembly method.
Background technology
During the assembling of aero-engine reaction wheel, extremely strict to matching requirements, if reaction wheel assembling
Unqualified, it is bad to be easily caused engine performance, has a strong impact on engine assembly progress and engine performance index.Rotor assembles
Unqualified electromotor may be caused with severe compromise, affect engine health, or even cause sending out of aircraft flight accident
Raw.Therefore improve engine gas turbine rotor matching requirements, engine health functional reliability can be effectively improved.Certain model is sent out
During the assembling of motivation reaction wheel front apron, the turbine disk adopts non-bolted joint structure with front apron, therebetween through hook
Intermesh, engagement place interference fits, due to impetus no any on front apron, cannot stress, additionally, empty at front apron hook
Between narrow according at each hook, front apron can only be installed it is impossible to be installed using general tool, have during repetitive operation send out
Raw, seriously delay part and the final assembly demand of electromotor, be delayed the progress that is delivered for use of whole machine.
Content of the invention
The invention provides a kind of gas turbine disk front apron assembling jig and assembly method, to solve existing combustion gas whirlpool
Wheel front apron installs the technical problem of inconvenience.
The technical solution used in the present invention is as follows：
According to an aspect of the present invention, provide a kind of gas turbine disk front apron assembling jig, in the turbine disk
Install, on end face, front apron be installed, end face is installed circumferentially arranged with installing protuberance, the inner ring surface of front apron be provided with install convex
The hook portion of portion's engagement；Assembling jig of the present invention includes：Base and be fixed on base when being used for assembling position and support turbine
The pull bar of disk, assembling jig also includes coordinating for the front apron being arranged on the turbine disk is applied with circumferential active force with pull bar
To drive front apron to engage the pressure ring assembly of cooperation with the turbine disk.
Further, pressure ring assembly includes：It is sheathed on the pressure ring on pull bar, circumferentially arranged multiple use on the side wall of pressure ring
In the slide block of the inner ring surface abutting front apron, the latch through the radially displaceable locking along pressure ring for the slide block lock onto on pressure ring；Pressure
Ring is provided with the force section for pressure ring is applied with circumferential active force.
Further, end slide block being abutted with front apron is provided with the chimb of the hook portion being convex on front apron.
Further, it is provided between pressure ring and pull bar and be connected through bearing.
Further, the bottom of bearing is through the first bushing positioning, the top of bearing and bearing and the pull bar in pressure ring
Cooperation at through second bushing position.
Further, it is provided with the cover plate of the top outer rim of compression positioning bearing on pressure ring, cover plate is fixed to through securing member
On pressure ring.
Further, pressure ring sets gradually open washer and nut on the second bushing, through nut and pull bar cooperation lock
Only the second bushing.
Further, force section is the multiple force handles or indent being fixed on pressure ring in the outside wall surface of pressure ring
Multiple force female part.
According to a further aspect in the invention, also provide a kind of gas turbine disk front apron assembly method, using above-mentioned dress
Join fixture, assembly method of the present invention includes：
The turbine disk is fastened on base and pull bar；
Front apron is installed on the stop portion of the installation end face of the turbine disk；
Pressure ring assembly is installed, and drives front apron to rotate in a circumferential direction relative to the turbine disk through pressure ring assembly, until install having coordinated
Finish.
Further, the turbine disk is after heat treatment installed on pull bar.
The invention has the advantages that：
Gas turbine disk front apron assembling jig of the present invention and assembly method, by design specialized in the front apron of the turbine disk
The assembling jig installed, it is to avoid traditional front apron is due to no impetus, cannot to apply the installation that circumferential active force leads to numerous
Trivial defect, can meet once assembling demand using the inventive method, and then effectively shortens installation period, and reduction is mounted to
This, and reliability is installed, conforming product rate obtains effective guarantee.
In addition to objects, features and advantages described above, the present invention also has other objects, features and advantages.
Below with reference to accompanying drawings, the present invention is further detailed explanation.
Brief description
The accompanying drawing constituting the part of the application is used for providing a further understanding of the present invention, the schematic reality of the present invention
Apply example and its illustrate, for explaining the present invention, not constituting inappropriate limitation of the present invention.In the accompanying drawings：
Fig. 1 is the structural representation of preferred embodiment of the present invention gas turbine disk front apron assembling jig.
Description of reference numerals：
1st, base；2nd, pull bar；3rd, slide block；4th, latch；5th, knurled nut with holes；
6th, pressure ring；7th, the first bushing；8th, single direction thrust ball bearing；9th, cover plate；
10th, exert a force handle；11st, sleeve；12nd, open washer；13rd, nut；
14th, the second bushing；15th, screw；16th, straight pin；
20th, the turbine disk；30th, front apron.
Specific embodiment
It should be noted that in the case of not conflicting, the embodiment in the application and the feature in embodiment can phases
Mutually combine.To describe the present invention below with reference to the accompanying drawings and in conjunction with the embodiments in detail.
With reference to Fig. 1, the preferred embodiments of the present invention provide a kind of gas turbine disk front apron assembling jig, in whirlpool
On the installation end face of wheel disc 20, front apron 30 is installed, in the present embodiment, the turbine disk 20 installs end face circumferentially arranged with installation protuberance,
The inner ring surface of front apron 30 is provided with and installs the hook portion that protuberance engages, and that is, the front apron on the turbine disk adopts non-bolted joint
Assembling structure, be prevented effectively from the stress concentration on the turbine disk, the present embodiment assembling jig includes：Base 1 and be fixed in base 1
Upper positioning and the pull bar 2 supporting the turbine disk 20 when being used for assembling, assembling jig also includes coordinating for being arranged at whirlpool with pull bar 2
Front apron on wheel disc applies circumferential active force to drive the pressure ring assembly that front apron engages cooperation with the turbine disk.
In the present embodiment, pressure ring assembly includes：It is sheathed on the pressure ring 6 on pull bar 2, circumferentially arranged on the side wall of pressure ring 6
The slide block 3 of multiple inner ring surfaces for abutting front apron 30, the latch 4 through the radially displaceable locking along pressure ring 6 for the slide block 3 is locked
On pressure ring 6；Pressure ring 6 is provided with the force section for pressure ring 6 is applied with circumferential active force.In the present embodiment, force section includes
It is arranged at the multiple force handles 10 on the side wall of pressure ring 6, and the handle 10 that exerts a force is provided with and its mating sleeve 11, during use, outward
Power is conducted to pressure ring 6 through sleeve 11 and force handle 10, and then with movable slider 3 and the front apron 30 that abuts with slide block 3 is along week
To motion so that the hook portion on front apron 30 engages tight fit with the installation protuberance on the turbine disk 20, complete to assemble.Using this
The assembling process of embodiment assembling jig, 1 time till now by 5-6 time original minimizing of its assembling number of times, it is prevented effectively from part
Change a job number of rewelding；And separate unit engine gas turbine rotor payment subsequent processing cycle obvious reduction shortens to original 1/6；
Reduce cost of labor simultaneously；Conforming product rate is made to obtain effective guarantee.
In the present embodiment, the end that slide block 3 is abutted with front apron 30 is provided with the chimb of the hook portion being convex on front apron.
Due to the hook portion narrow space on front apron, the present embodiment coordinates with it through the chimb on slide block 3 it is ensured that front apron and slide block
Between shape abut reliably secure.
In the present embodiment, it is provided between pressure ring 6 and pull bar 2 and is connected through bearing.With reference to Fig. 1, in the present embodiment, this bearing is excellent
Elect single direction thrust ball bearing 8 as.Preferably, the bottom of single direction thrust ball bearing 8 positions through the first bushing 7 in pressure ring 6,
The top of single direction thrust ball bearing 8 and its with the cooperation of pull bar 2 at position through the second bushing 14.The present embodiment adopts the first bushing
7 and the mode of the second bushing 14 cooperation realize the positioning to bearing and protection, it is to avoid bearing bears radial forces, extends this
The service life of embodiment assembling jig.
In the present embodiment, it is provided with the cover plate 9 of the top outer rim of compression positioning bearing on pressure ring 6, cover plate 9 is solid through securing member
Determine to pressure ring.With reference to Fig. 1, cover plate 9 is anchored on pressure ring 6 through draw-in groove fillister head screw 15.Preferably, pressure ring 6 is in the second lining
Set gradually open washer 12 and nut 13 on set 14, coordinate locking the second bushing 14 through nut 13 with pull bar 2.
When assembling front apron 30 shown in Fig. 1 and the turbine disk 20, first front apron 30 is arranged on above the turbine disk 20, right
Positive position；Afterwards pressure ring assembly is arranged on above front apron 30, outwards pulls locking sliding block and tighten splined nut 5 with holes；
Last construction opening packing ring 12 and nut 13, and tighten nut with adjustable wrench.After the completion for the treatment of above-mentioned work, sleeve 11 is inserted
Force handle 10 simultaneously rotates both sides sleeve.Now, pressure ring 6 can drive front apron 30 and the turbine disk 20 relative rotary motion, works as gear
During plate rotation, go to certain angle, visual observations specified location, now the turbine disk 20 and front apron 30 install.
In other embodiments, force section can multiple force female part in the outside wall surface of pressure ring for the indent, such as with six sides
The interior hexagonal hole of screw rod cooperation.
According to a further aspect in the invention, also provide a kind of gas turbine disk front apron assembly method, using above-mentioned enforcement
The assembling jig of example, assembly method of the present invention includes：
The turbine disk is fastened on base and pull bar；
Front apron is installed on the stop portion of the installation end face of the turbine disk；
Pressure ring assembly is installed, and drives front apron to rotate in a circumferential direction relative to the turbine disk through pressure ring assembly, until install having coordinated
Finish.
Preferably, the turbine disk is after heat treatment installed on pull bar.
When certain type turbine shaft type engine gas rotor assembles, it is warmed to 200 degrees Celsius using by the turbine disk, be incubated 10
After minute, the turbine disk is arranged on base；Quickly front apron is arranged on stop portion above the turbine disk afterwards, and turbine relatively
Disc spins baffle plate certain angle；Then pressure ring assembly is installed successively；Hand taut the slide block of pressure ring four direction, and tighten relatively
The knurled nut with holes answering；Last construction opening packing ring and nut above pressure ring, is tightened with adjustable wrench；With two sleeve handss
Handle rotates pressure ring at handle.Baffle plate and the turbine disk are rotated to specified location.Now, the turbine disk and baffle plate install, and treat
After part is cooled to normal temperature state, subsequently assembled.
From above description it is known that the present embodiment gas turbine disk front apron assembling jig and assembly method, pass through
Design specialized is in the assembling jig installed of front apron of the turbine disk, it is to avoid traditional front apron is due to no impetus, Wu Fashi
Plus the defect that the installation that leads to of circumferential active force is loaded down with trivial details, once assembling demand can be met using the inventive method, and then effectively
Shorten installation period, reduce installation cost, and reliability is installed, conforming product rate obtains effective guarantee.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for the skill of this area
For art personnel, the present invention can have various modifications and variations.All within the spirit and principles in the present invention, made any repair
Change, equivalent, improvement etc., should be included within the scope of the present invention.
Claims (10)
1. a kind of gas turbine disk front apron assembling jig, for installing front apron, described peace on the installation end face of the turbine disk
Circumferentially arranged with installing protuberance, the inner ring surface of described front apron is provided with installs, with described, the hook portion that protuberance engages to dress end face；
It is characterized in that, described assembling jig includes：Base and be fixed in when being used for assembling on described base position and support described whirlpool
The pull bar of wheel disc, described assembling jig also includes coordinating for the front apron being arranged on the described turbine disk with described pull bar
Apply circumferential active force to drive the pressure ring assembly that described front apron engages cooperation with the described turbine disk.
2. gas turbine disk front apron assembling jig according to claim 1 it is characterised in that
Described pressure ring assembly includes：It is sheathed on the pressure ring on described pull bar, circumferentially arranged multiple use on the side wall of described pressure ring
In the slide block of the inner ring surface abutting described front apron, the latch through the radially displaceable locking along described pressure ring for the described slide block is locked
On described pressure ring；Described pressure ring is provided with the force section for described pressure ring is applied with circumferential active force.
3. gas turbine disk front apron assembling jig according to claim 2 it is characterised in that
The end abutting with described front apron on described slide block is provided with the chimb of the hook portion being convex on described front apron.
4. gas turbine disk front apron assembling jig according to claim 2 it is characterised in that
It is provided between described pressure ring and described pull bar and be connected through bearing.
5. gas turbine disk front apron assembling jig according to claim 4 it is characterised in that
The bottom of described bearing is through the first bushing positioning, the top of described bearing and described bearing and the institute in described pressure ring
State and position through the second bushing at the cooperation of pull bar.
6. gas turbine disk front apron assembling jig according to claim 5 it is characterised in that
It is provided with the cover plate that compression positions the top outer rim of described bearing, described cover plate is fixed to institute through securing member on described pressure ring
State on pressure ring.
7. gas turbine disk front apron assembling jig according to claim 6 it is characterised in that
Described pressure ring sets gradually open washer and nut on described second bushing, through described nut and described pull bar cooperation
Second bushing described in locking.
8. according to the arbitrary described gas turbine disk front apron assembling jig of claim 2 to 7 it is characterised in that
Described force section is the multiple force handles or indent being fixed on described pressure ring in the outside wall surface of described pressure ring
Multiple force female part.
9. a kind of gas turbine disk front apron assembly method is it is characterised in that adopt described dress as arbitrary in claim 1 to 8
Join fixture, described assembly method includes：
The turbine disk is fastened on described base and described pull bar；
Front apron is installed on the stop portion of the installation end face of the described turbine disk；
Pressure ring assembly is installed, and drives the relatively described turbine disk of described front apron to rotate in a circumferential direction through described pressure ring assembly, until peace
Assembling conjunction finishes.
10. gas turbine disk front apron assembly method according to claim 9 it is characterised in that
The described turbine disk is after heat treatment installed on described pull bar.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611189640.7A CN106392957A (en) | 2016-12-21 | 2016-12-21 | Assembly clamp and assembly method for front baffle plate of gas turbine disc |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611189640.7A CN106392957A (en) | 2016-12-21 | 2016-12-21 | Assembly clamp and assembly method for front baffle plate of gas turbine disc |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106392957A true CN106392957A (en) | 2017-02-15 |
Family
ID=58087898
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611189640.7A Pending CN106392957A (en) | 2016-12-21 | 2016-12-21 | Assembly clamp and assembly method for front baffle plate of gas turbine disc |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106392957A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107363779A (en) * | 2017-09-04 | 2017-11-21 | 中国航发南方工业有限公司 | The attaching/detaching apparatus of aero-engine high pressure joint rotor |
| CN107932060A (en) * | 2017-11-23 | 2018-04-20 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of method for controlling combustion engine low-pressure first-stage turbine mill damage |
| CN108098673A (en) * | 2017-12-11 | 2018-06-01 | 中国航发沈阳发动机研究所 | Low-pressure turbine blade baffle assembling and disassembling device |
| CN109184807A (en) * | 2018-09-05 | 2019-01-11 | 中国航发动力股份有限公司 | A kind of decomposition method of two-restriction degree chuck |
| CN109352582A (en) * | 2018-11-29 | 2019-02-19 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of aero-engine calotte assembling jig and application method |
| CN110788768A (en) * | 2019-09-27 | 2020-02-14 | 中国航发南方工业有限公司 | Lock ring auxiliary assembly device and engine power turbine assembly method with lock ring |
| CN112045615A (en) * | 2019-06-06 | 2020-12-08 | 中国航发商用航空发动机有限责任公司 | Assembly tool for inner guide pipe of turbine shaft |
| CN112228159A (en) * | 2020-08-31 | 2021-01-15 | 中国航发南方工业有限公司 | Safety structure of locking ring |
| CN114083396A (en) * | 2020-08-24 | 2022-02-25 | 中国航发商用航空发动机有限责任公司 | Turbine rotor blade tip grinding adapter clamp and mounting method thereof |
| CN117697692A (en) * | 2024-02-06 | 2024-03-15 | 成都中科翼能科技有限公司 | Special loading and unloading tool for gas turbine locking connection device |
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| CN204366894U (en) * | 2014-12-23 | 2015-06-03 | 株洲高精传动技术有限公司 | Stripped nut pre-tightening apparatus |
| CN106217298A (en) * | 2016-08-18 | 2016-12-14 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of attaching/detaching apparatus of high-pressure turbine front apron |
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| DE202010012741U1 (en) * | 2010-09-17 | 2010-12-02 | Schaeffler Technologies Gmbh & Co. Kg | Puller for bearing rings |
| CN102371566A (en) * | 2011-08-31 | 2012-03-14 | 无锡先锋电机有限公司 | Disassembling device of motor coupler |
| CN102922471A (en) * | 2012-10-31 | 2013-02-13 | 沈阳黎明航空发动机(集团)有限责任公司 | Device for mounting and decomposing bolt-free connecting baffle plate |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107363779A (en) * | 2017-09-04 | 2017-11-21 | 中国航发南方工业有限公司 | The attaching/detaching apparatus of aero-engine high pressure joint rotor |
| CN107932060A (en) * | 2017-11-23 | 2018-04-20 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of method for controlling combustion engine low-pressure first-stage turbine mill damage |
| CN108098673A (en) * | 2017-12-11 | 2018-06-01 | 中国航发沈阳发动机研究所 | Low-pressure turbine blade baffle assembling and disassembling device |
| CN109184807A (en) * | 2018-09-05 | 2019-01-11 | 中国航发动力股份有限公司 | A kind of decomposition method of two-restriction degree chuck |
| CN109184807B (en) * | 2018-09-05 | 2021-09-28 | 中国航发动力股份有限公司 | Decomposition method of double-tightness chuck |
| CN109352582A (en) * | 2018-11-29 | 2019-02-19 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of aero-engine calotte assembling jig and application method |
| CN112045615A (en) * | 2019-06-06 | 2020-12-08 | 中国航发商用航空发动机有限责任公司 | Assembly tool for inner guide pipe of turbine shaft |
| CN112045615B (en) * | 2019-06-06 | 2021-09-24 | 中国航发商用航空发动机有限责任公司 | Breather pipe assembly fixture in turbine shaft |
| CN110788768B (en) * | 2019-09-27 | 2021-04-13 | 中国航发南方工业有限公司 | Lock ring auxiliary assembly device and engine power turbine assembly method with lock ring |
| CN110788768A (en) * | 2019-09-27 | 2020-02-14 | 中国航发南方工业有限公司 | Lock ring auxiliary assembly device and engine power turbine assembly method with lock ring |
| CN114083396A (en) * | 2020-08-24 | 2022-02-25 | 中国航发商用航空发动机有限责任公司 | Turbine rotor blade tip grinding adapter clamp and mounting method thereof |
| CN114083396B (en) * | 2020-08-24 | 2022-10-18 | 中国航发商用航空发动机有限责任公司 | Mounting method of turbine rotor blade tip grinding adapter clamp |
| CN112228159A (en) * | 2020-08-31 | 2021-01-15 | 中国航发南方工业有限公司 | Safety structure of locking ring |
| CN117697692A (en) * | 2024-02-06 | 2024-03-15 | 成都中科翼能科技有限公司 | Special loading and unloading tool for gas turbine locking connection device |
| CN117697692B (en) * | 2024-02-06 | 2024-04-23 | 成都中科翼能科技有限公司 | Special loading and unloading tool for gas turbine locking connection device |
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| PB01 | Publication | ||
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Application publication date: 20170215 |