CN102554825A - Turbine blade assembling insurance clamp and method for performing impeller clamping thereof - Google Patents
Turbine blade assembling insurance clamp and method for performing impeller clamping thereof Download PDFInfo
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- CN102554825A CN102554825A CN2011104376833A CN201110437683A CN102554825A CN 102554825 A CN102554825 A CN 102554825A CN 2011104376833 A CN2011104376833 A CN 2011104376833A CN 201110437683 A CN201110437683 A CN 201110437683A CN 102554825 A CN102554825 A CN 102554825A
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- positioning seat
- leading edge
- turbine disk
- blade
- exhaust limit
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Abstract
The invention discloses a turbine blade assembling insurance clamp and a method for performing impeller clamping thereof, which belong to the technical field of aircraft engine gas turbine blade assembling. Bosses are evenly distributed on the edge portion of an air inlet edge positioning seat of a turbine disc of the turbine blade assembling insurance clamp, a screw penetrates through the air inlet edge positioning seat of the turbine disc to be fixed with an air discharging edge positioning seat of the turbine disc, and in use, turbine blades are fixed. The method for performing impeller clamping includes the following steps: step 1 assembling the air inlet edge positioning seat and an impeller; step 2 installing the impeller in an air inlet edge positioning seat assembly; step 3 installing a gasket; and step 4 installing an air discharging edge positioning seat assembly. The turbine blade assembling insurance clamp leads insured blades to meet requirements for dimensions of 3.4+/-0.5mm, avoids the blades from being ejected to be loose and improves turbine blade assembling yield rate. The method for performing blade clamping can perform turbine positioning fast and conveniently and reduces labor intensity and maintenance cost.
Description
Technical field
The present invention relates to aero-engine gas-turbine blade mounting technology, particularly a kind of turbine disk and blade adopt the mounting technology of the connected mode of locking plate.
Background technology
The turbine disk and the blade that adopt locking plate to connect, the qualified acceptance criteria of its turbo blade assembling is: do not allow any becoming flexible after the blade insurance, and the blade inlet edge boss exceeds turbine disk leading edge face size 3.4 ± 0.05mm.In the process of engine turbine blade assembling insurance, because the design defect of former assembler dress often causes insuring good blade by frock top pine, make blade loosening, more can not satisfy the dimensional requirement of 3.4 ± 0.05mm.To pull down and scrap locking plate thus, again blade insured, make that all blades satisfy dimensional requirement on the whole turbine disk, need repeatedly do over again.Waste time and energy, have a strong impact on repair progress, and wasted many locking plates, increased cost virtually.
Summary of the invention
Goal of the invention of the present invention is: to the problem of above-mentioned existence; Provide a kind of simple in structure, easy and simple to handle, the turbo blade that satisfies engine turbine rotor blade assembling use assembles the method for insuring anchor clamps and carrying out the impeller clamping; Should insure anchor clamps through using; Can make the blade after the insurance satisfy the requirement of size 3.4 ± 0.05mm, and the top pine has been insured qualified blade can effectively avoid insuring other blades the time, improves the qualification rate of turbo blade assembling; Through using this furniture to carry out the method for impeller clamping, can carry out the location of turbine quickly and easily, reduce labour intensity, reduce the locking plate scrappage, improve repair progress, reduce maintenance cost.
The technical scheme that the present invention adopts is following:
Turbo blade assembling insurance anchor clamps of the present invention; Comprise turbine disk leading edge positioning seat, turbine disk exhaust limit positioning seat and screw rod; Limit portion at turbine disk leading edge positioning seat inner face is evenly equipped with at least three boss; Screw rod passes the middle part of turbine disk leading edge positioning seat and turbine disk exhaust limit positioning seat and fixes; During use, turbo blade is between turbine disk leading edge positioning seat and turbine disk exhaust limit positioning seat, and turbine disk leading edge positioning seat and boss cooperate with turbine disk exhaust limit positioning seat fixes turbo blade.
Owing to adopted said structure, impeller can be by turbine disk leading edge positioning seat between the fixing and turbine disk exhaust limit positioning seat, and fixes through the middle part that screw rod passes turbine disk leading edge positioning seat and turbine disk exhaust limit positioning seat; Guarantee that its structure surely leans on; Avoid in the process of assembling, taking place to become flexible and be out of shape, thereby guarantee the qualification rate that impeller is installed, especially when needs assemble impeller; Need impeller be placed between turbine disk leading edge positioning seat and turbine disk exhaust limit positioning seat and fix; Make turbine disk leading edge positioning seat and boss cooperate turbo blade is fixed, can effectively impeller be positioned and fixing, not only can make blade after the insurance satisfy the requirement of size 3.4 ± 0.05mm with turbine disk exhaust limit positioning seat; And can effectively avoid insuring other blades time top pine to insure qualified blade; Improve the qualification rate of turbo blade assembling, thereby can reduce maintenance cost effectively, be fit to apply.
Turbo blade assembling insurance anchor clamps of the present invention, said boss is three, and is distributed in the limit portion of the inner face of turbine disk leading edge positioning seat, is provided with turbine disk leading edge positioning seat boss on each boss.
Owing to adopted said structure; Boss is three; And be distributed in the limit portion of the inner face of turbine disk leading edge positioning seat, and turbine disk leading edge positioning seat boss is set on each boss, because leading edge adopts 3 point types to support locating ring; Blade exhaust limit locating ring only contacts the blade boss, for the intensive very large raising of locking plate insurance operability of circle distribution; Leading edge positioning seat 3 point types contacts turbine disk tenon tooth end face does not contact blade tenon fully, does not receive the rest blade insurance and becomes flexible with having insured qualified blade on the turbine disk.
Turbo blade assembling insurance anchor clamps of the present invention; The inner face of said turbine disk leading edge positioning seat is provided with blade leading edge locating ring; The inner face of said turbine disk exhaust limit positioning seat is provided with blade exhaust limit locating ring; During use, said blade leading edge locating ring is relative with blade exhaust limit locating ring, and turbo blade is located.
Owing to adopted said structure, blade leading edge locating ring is set on the inner face of turbine disk leading edge positioning seat, blade exhaust limit locating ring is set on the inner face of turbine disk exhaust limit positioning seat; Two locating rings are used for cooperatively interacting in the process of using, and promptly blade leading edge locating ring is relative with blade exhaust limit locating ring, thereby impeller is had good positioning; Avoid impeller in the process of assembling; Loosening distortion taking place, can protect impeller effectively, thereby can make blade after the insurance satisfy the requirement of size 3.4 ± 0.05mm; And the top pine has been insured qualified blade in the time of can effectively avoiding insuring other blades; Improve the qualification rate of turbo blade assembling, thereby can reduce cost, be fit to apply.
Turbo blade assembling insurance anchor clamps of the present invention, said turbine disk leading edge positioning seat boss exceeds 3.4 ± 0.02mm than blade leading edge locating ring.
Owing to adopted said structure; Turbine disk leading edge positioning seat boss exceeds locating ring 3.4 ± 0.02mm; Guarantee to insure rear blade leading edge boss and exceed turbine disk leading edge face size 3.4 ± 0.05mm; Thereby the top pine has been insured qualified blade in the time of can effectively avoiding insuring other blades, improves the qualification rate of turbo blade assembling, thereby reduces maintenance cost.
Turbo blade assembling insurance anchor clamps of the present invention; The two ends of said screw rod are equipped with screw thread; And screw rod has the leading edge locking nut in the fit on of turbine disk leading edge positioning seat; Screw rod has exhaust limit locking nut in the positioning seat fit on of wheel disc exhaust limit, is with packing ring on the screw rod between said turbine disk leading edge positioning seat and the wheel disc exhaust limit positioning seat.
Owing to adopted said structure, whole insurance harness is fixed through screw rod, wherein at an end of turbine disk leading edge positioning seat; Leading edge locking nut through cooperating with screw rod is fixed, and at an end of wheel disc exhaust limit positioning seat, fixes through the exhaust limit locking nut that cooperates with screw rod; Make the two ends of furniture all can fix through screw rod, turbine is placed between turbine disk leading edge positioning seat and the wheel disc exhaust limit positioning seat, and on screw rod, is with second packing ring; Can turbine be fixed, and have good positioning, avoid it loosening; And the quality of qualified blade has been insured in influence, and then improves the qualification rate of turbo blade assembling.
Employing turbo blade assembling insurance anchor clamps of the present invention carry out the method for impeller clamping, may further comprise the steps:
Step 1. is assembled into leading edge positioning seat assembly with turbine disk leading edge positioning seat and blade leading edge locating ring, and locking plate and blade composition impeller are installed on the turbine disk;
Step 2. is installed to impeller in the leading edge positioning seat assembly; Make turbine disk leading edge positioning seat, boss and turbine disk leading edge positioning seat boss contact turbine disk leading edge end face; But can not contact with blade tenon, the blade inlet edge boss contacts with blade leading edge locating ring simultaneously;
Step 4. is assembled into exhaust limit positioning seat assembly with blade exhaust limit locating ring and turbine disk exhaust limit positioning seat, and exhaust limit positioning seat assembly is installed, and the trailing edge boss is contacted with blade exhaust limit locating ring, and second packing ring is installed, and tightens exhaust limit locking nut.
Owing to adopted said method, assemble leading edge positioning seat assembly and impeller respectively, for early-stage preparations are carried out in follow-up production assembling; When assembling, impeller is installed in the leading edge positioning seat assembly, make that turbine disk leading edge positioning seat, boss and the turbine disk leading edge positioning seat boss in the whole anchor clamps can contact with turbine disk leading edge end face; But special demands can not contact with blade tenon, avoid impeller is caused the infringement of collision, avoid its distortion; Also require the blade inlet edge boss to contact simultaneously, can effectively impeller be fixed, make whole anchor clamps can protect whole impeller well with blade leading edge locating ring; Improve the qualification rate of turbo blade assembling, can anchor clamps be locked through being equipped with packing ring and nut on the screw rod again, impeller is fixed in the anchor clamps; And can pass through the special construction of the boss in the anchor clamps, thereby guarantee that blade satisfies the requirement of size 3.4 ± 0.05mm, again the exhaust limit positioning seat assembly that assembles assembled cooperation; And guarantee that the trailing edge boss contacts with blade exhaust limit locating ring; Make whole anchor clamps to play a very good protection, avoid it loosening, guarantee its life-span impeller.Employing turbo blade assembling insurance anchor clamps therefore of the present invention carry out the method for impeller clamping, can carry out the location of turbine quickly and easily, reduce labour intensity, reduce the locking plate scrappage, improve repair progress, reduce maintenance cost.
In sum, owing to adopted technique scheme, the invention has the beneficial effects as follows:
1, turbo blade assembling insurance anchor clamps of the present invention are simple in structure, easy and simple to handle, satisfy the assembling of engine turbine rotor blade and use;
2, turbo blade of the present invention assembling insurance anchor clamps can make the blade after the insurance satisfy the requirement of size 3.4 ± 0.05mm, and the top pine has been insured qualified blade can effectively avoid insuring other blades the time, improves the qualification rate of turbo blade assembling;
3, employing turbo blade assembling insurance anchor clamps of the present invention carry out the method for impeller clamping, can carry out the location of turbine quickly and easily, reduce labour intensity, reduce the locking plate scrappage, improve repair progress, reduce maintenance cost.
Description of drawings
The present invention will explain through example and with reference to the mode of accompanying drawing, wherein:
Fig. 1 is the structural representation of turbo blade assembling insurance anchor clamps of the present invention;
Fig. 2 is a turbine disk leading edge positioning seat structural representation among the present invention;
Fig. 3 is the left view of Fig. 2;
Fig. 4 is the blade wheel structure sketch map that needs insurance among the present invention.
Mark among the figure: 1-leading edge locking nut; 2-first packing ring; 3-turbine disk leading edge positioning seat; 4-blade leading edge locating ring; 5-blade exhaust limit locating ring; 6-turbine disk exhaust limit positioning seat; The 7-boss; 8-second packing ring; The 9-screw rod; 10-exhaust limit locking nut; 11-turbine disk leading edge positioning seat boss; 12-blade inlet edge boss; 13-turbine disk leading edge end face; 14-trailing edge boss; The 15-turbo blade; The 16-locking plate; The 17-turbine disk; 18-turbine disk exhaust limit boss; The 19-hole.
The specific embodiment
Disclosed all characteristics in this specification, or the step in disclosed all methods or the process except mutually exclusive characteristic and/or the step, all can make up by any way.
Disclosed arbitrary characteristic in this specification (comprising any accessory claim, summary and accompanying drawing) is only if special narration all can be replaced by other equivalences or the alternative features with similar purpose.That is, only if special narration, each characteristic is an example in a series of equivalences or the similar characteristics.
As shown in Figure 4, its blade wheel structure for insuring; Fig. 1 to Fig. 3 is the structural representation of turbo blade of the present invention assembling insurance anchor clamps, is example with above-mentioned four accompanying drawings, to these anchor clamps with and clamping method tell about.Among the present invention; With Fig. 1 is example; Turbine disk leading edge positioning seat 3 inner faces are the right side of turbine disk leading edge positioning seat 3, and the outer face is the left side of turbine disk leading edge positioning seat 3, same principle; The inner face of turbine disk exhaust limit positioning seat 6 is the left side, and the outer face of turbine disk exhaust limit positioning seat 6 is the right side.
Turbo blade assembling insurance anchor clamps of the present invention; Comprise turbine disk leading edge positioning seat 3, turbine disk exhaust limit positioning seat 6 and screw rod 9; Limit portion at turbine disk leading edge positioning seat 3 inner faces is evenly equipped with three boss 7; This example adopts three boss 7, and four boss 7 or five boss 7 can certainly be set according to actual needs, is at least three.Adopt 3 point types to support locating ring at turbine disk leading edge, 4 contacts of blade exhaust limit locating ring blade boss 7 is for the intensive very large raising of locking plate insurance operability of circle distribution.Boss 7 is distributed in the limit portion of the inner face of turbine disk leading edge positioning seat 3; Be provided with turbine disk leading edge positioning seat boss 11 on each boss 7; The inner face of said turbine disk leading edge positioning seat 3 is provided with blade leading edge locating ring 4; And said turbine disk leading edge positioning seat boss 11 exceeds 3.38mm than blade leading edge locating ring 4; Can certainly adopt turbine disk leading edge positioning seat boss 11 to exceed 3.42mm, and also can design and adopt turbine disk leading edge positioning seat boss 11 to exceed 3.40mm, according to above-mentioned principle than blade leading edge locating ring 4 than blade leading edge locating ring 4; Can design turbine disk leading edge positioning seat boss 11 and exceed 3.4 ± 0.02mm, exceed turbine disk leading edge face size 3.4 ± 0.05mm thereby guarantee to insure rear blade leading edge boss than blade leading edge locating ring 4.The inner face of said turbine disk exhaust limit positioning seat 6 is provided with blade exhaust limit locating ring 5, and during use, said blade leading edge locating ring 4 is relative with blade exhaust limit locating ring 5, and turbo blade is located.The two ends of said screw rod 9 are equipped with screw thread; And screw rod 9 has leading edge locking nut 1 in 3 fit ons of turbine disk leading edge positioning seat; Positioning seat 6 fit ons have exhaust limit locking nut 10 to screw rod 9 on wheel disc exhaust limit; Be with second packing ring 8 on the screw rod 9 between said turbine disk leading edge positioning seat 3 and the wheel disc exhaust limit positioning seat 6, it is also fixing with the middle part of turbine disk exhaust limit positioning seat 6 that screw rod 9 passes turbine disk leading edge positioning seat 3.During use, turbo blade is between turbine disk leading edge positioning seat 3 and turbine disk exhaust limit positioning seat 6, and turbine disk leading edge positioning seat 3 cooperates with turbine disk exhaust limit positioning seat 6 with boss 7 fixes turbo blade.
The turbo blade assembling insurance anchor clamps of employing of the present invention carry out the method for impeller clamping, and it may further comprise the steps:
Step 1. is assembled into leading edge positioning seat assembly with turbine disk leading edge positioning seat 3 and blade leading edge locating ring 4, and locking plate 16 is installed on the turbine disk 17 is formed impeller with blade 15;
Step 2. is installed to impeller in the leading edge positioning seat assembly; Make turbine disk leading edge positioning seat 3, boss 7 and turbine disk leading edge positioning seat boss 11 contact turbine disk leading edge end face 13; But can not contact with blade tenon, blade inlet edge boss 12 contacts with blade leading edge locating ring 4 simultaneously;
Step 4. is assembled into exhaust limit positioning seat assembly with blade exhaust limit locating ring 5 and turbine disk exhaust limit positioning seat 6; Exhaust limit positioning seat assembly is installed; Make trailing edge boss 14 contact blade exhaust limit locating rings 5; Second packing ring 8 is installed, is tightened exhaust limit locking nut 10, accomplish the work of impeller clamping.
In the above-mentioned steps 4, can the number of assembling steps of exhaust limit positioning seat assembly be carried out in step 1, be good to accomplish the work of impeller clamping, and need not consider the order of this method.With the good impeller of vice attachment clamping, can carry out the insurance of locking plate, accomplish the one side insurance after, another side is insured after turning 180 °.
Turbo blade assembling insurance anchor clamps of the present invention can support turbine disk exhaust limit through on screw rod 9 six square toes, packing ring being installed, and blade exhaust limit locating ring 5 and positioning seat assembly support blade trailing edge boss 14 prevent that blade from falling; 3 of turbine disk leading edge positioning seat 3 circumference compress turbine disk leading edge; Make all contact blade leading edge locating rings 4 of blade inlet edge boss 12; Trailing edge boss 14 is in free state, tightens leading edge locking nut 1, adjustment blade exhaust limit locating ring 5 and positioning seat assembly; Make it compress trailing edge boss 14, tighten leading edge locking nut 1.Through compressing the turbine disk and turbo blade simultaneously, make it loosening invariably; Turbine disk leading edge positioning seat boss 14 exceeds blade exhaust limit locating ring 3.4 ± 0.02mm, guarantees to insure rear blade leading edge boss 12 and exceeds turbine disk leading edge face size 3.4 ± 0.05mm.Because leading edge adopts 3 point types to support locating ring, blade exhaust limit locating ring only contacts blade boss 7, makes all locking plates, and the tongue-and-groove junction is exposed outside fully, guarantees sufficient insurance operating space.Through leading edge positioning seat 3 point types contacts turbine disk tenon tooth end face, do not contact blade tenon fully, guarantee not receive the rest blade insurance and become flexible with having insured qualified blade on the turbine disk.
The invention has the beneficial effects as follows: these turbo blade assembling insurance anchor clamps, because leading edge adopts 3 point types to support locating ring, blade exhaust limit locating ring only contacts the blade boss, for the intensive very large raising of locking plate insurance operability of circle distribution; Leading edge positioning seat 3 point types contacts turbine disk tenon tooth end face does not contact blade tenon fully, does not receive the rest blade insurance and becomes flexible with having insured qualified blade on the turbine disk; Workable, reduce labour intensity, reduce the locking plate scrappage; Improve repair progress, reduce maintenance cost.Anchor clamps are workable, reduce labour intensity, reduce the locking plate scrappage, improve repair progress, reduce maintenance cost.
The present invention is not limited to the aforesaid specific embodiment.The present invention expands to any new feature or any new combination that discloses in this manual, and the arbitrary new method that discloses or step or any new combination of process.
Claims (7)
1. anchor clamps are insured in the turbo blade assembling; It is characterized in that: it comprises turbine disk leading edge positioning seat (3), turbine disk exhaust limit positioning seat (6) and screw rod (9); Limit portion at turbine disk leading edge positioning seat (3) inner face is evenly equipped with at least three boss (7); It is also fixing with the middle part of turbine disk exhaust limit positioning seat (6) that screw rod (9) passes turbine disk leading edge positioning seat (3); During use, turbo blade is positioned between turbine disk leading edge positioning seat (3) and the turbine disk exhaust limit positioning seat (6), and turbine disk leading edge positioning seat (3) and boss (7) cooperate with turbine disk exhaust limit positioning seat (6) fixes turbo blade.
2. turbo blade assembling insurance anchor clamps as claimed in claim 1, it is characterized in that: said boss (7) is three, is provided with turbine disk leading edge positioning seat boss (11) on each boss (7).
3. according to claim 1 or claim 2 turbo blade assembling insurance anchor clamps; It is characterized in that: the inner face of said turbine disk leading edge positioning seat (3) is provided with blade leading edge locating ring (4); The inner face of said turbine disk exhaust limit positioning seat (6) is provided with blade exhaust limit locating ring (5); During use, said blade leading edge locating ring (4) is relative with blade exhaust limit locating ring (5), and turbo blade is located.
4. turbo blade assembling insurance anchor clamps as claimed in claim 3, it is characterized in that: said turbine disk leading edge positioning seat boss (11) exceeds 3.4 ± 0.02mm than blade leading edge locating ring (4).
5. turbo blade assembling insurance anchor clamps as claimed in claim 3; It is characterized in that: the two ends of said screw rod (9) are equipped with screw thread; And screw rod (9) has leading edge locking nut (1) in turbine disk leading edge positioning seat (3) fit on; Screw rod (9) has exhaust limit locking nut (10) in wheel disc exhaust limit positioning seat (6) fit on, is with packing ring (8) on the screw rod (9) between said turbine disk leading edge positioning seat (3) and the wheel disc exhaust limit positioning seat (6).
6. like claim 1 or 2 or 4 described turbo blade assembling insurance anchor clamps; It is characterized in that: the two ends of said screw rod (9) are equipped with screw thread; And screw rod (9) has leading edge locking nut (1) in turbine disk leading edge positioning seat (3) fit on; Screw rod (9) has exhaust limit locking nut (10) in wheel disc exhaust limit positioning seat (6) fit on, is with second packing ring (8) on the screw rod (9) between said turbine disk leading edge positioning seat (3) and the wheel disc exhaust limit positioning seat (6).
7. method that adopts in the claim 1 to 6 each described turbo blade assembling insurance anchor clamps to carry out the impeller clamping, be characterised in that: it may further comprise the steps:
Step 1. is assembled into leading edge positioning seat assembly with turbine disk leading edge positioning seat (3) and blade leading edge locating ring (4), and in the turbine disk (17)
OnLocking plate (16) and blade (15) are installed are formed impeller;
Step 2. is installed to impeller in the leading edge positioning seat assembly; Make turbine disk leading edge positioning seat (3), boss (7) and turbine disk leading edge positioning seat boss (11) contact turbine disk leading edge end face (13); But can not contact with blade tenon, blade inlet edge boss (12) contacts with blade leading edge locating ring (4) simultaneously;
Step 3. is installed second packing ring (8) to turbine disk exhaust limit boss (18), and aims at installing hole (19), and the screw rod of packing into (9) makes screw rod six square toes contact second packing ring (8), and first packing ring (2) is installed, and tightens leading edge locking nut (1);
Step 4. is assembled into exhaust limit positioning seat assembly with blade exhaust limit locating ring (5) and turbine disk exhaust limit positioning seat (6); Exhaust limit positioning seat assembly is installed; Make trailing edge boss (14) contact blade exhaust limit locating ring (5); Second packing ring (8) is installed, is tightened exhaust limit locking nut (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110437683.3A CN102554825B (en) | 2011-12-23 | 2011-12-23 | Turbine blade assembling insurance clamp and method for performing impeller clamping thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110437683.3A CN102554825B (en) | 2011-12-23 | 2011-12-23 | Turbine blade assembling insurance clamp and method for performing impeller clamping thereof |
Publications (2)
| Publication Number | Publication Date |
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| CN102554825A true CN102554825A (en) | 2012-07-11 |
| CN102554825B CN102554825B (en) | 2014-07-16 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201110437683.3A Active CN102554825B (en) | 2011-12-23 | 2011-12-23 | Turbine blade assembling insurance clamp and method for performing impeller clamping thereof |
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| CN (1) | CN102554825B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| CN105014574A (en) * | 2015-07-27 | 2015-11-04 | 中煤第一建设有限公司 | Clamping device for quick separation of fluid coupling |
| CN112129476A (en) * | 2019-06-24 | 2020-12-25 | 中国航发商用航空发动机有限责任公司 | Interstage sealing plate test fixture |
| CN115351563A (en) * | 2022-07-26 | 2022-11-18 | 中国航发航空科技股份有限公司 | Clamp for milling blisk |
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| CN202480003U (en) * | 2011-12-23 | 2012-10-10 | 四川亚美动力技术有限公司 | Secutity clamp for assembly of turbine vanes |
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| CN2322742Y (en) * | 1998-01-19 | 1999-06-09 | 黄南平 | Clamp for precision machining brake disk parts |
| US20110030183A1 (en) * | 2007-09-13 | 2011-02-10 | General Electric Company | Jig and fixture for wind turbine blade |
| GB2463392A (en) * | 2008-12-24 | 2010-03-17 | Benjamin John Ridehough | Hydraulic clamping device |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| CN102922471B (en) * | 2012-10-31 | 2014-11-19 | 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 |
| CN105014574A (en) * | 2015-07-27 | 2015-11-04 | 中煤第一建设有限公司 | Clamping device for quick separation of fluid coupling |
| CN105014574B (en) * | 2015-07-27 | 2017-07-25 | 中煤第一建设有限公司 | A kind of clamping device of fluid-flywheel clutch quick separating |
| CN112129476A (en) * | 2019-06-24 | 2020-12-25 | 中国航发商用航空发动机有限责任公司 | Interstage sealing plate test fixture |
| CN112129476B (en) * | 2019-06-24 | 2022-08-02 | 中国航发商用航空发动机有限责任公司 | Interstage sealing plate test fixture |
| CN115351563A (en) * | 2022-07-26 | 2022-11-18 | 中国航发航空科技股份有限公司 | Clamp for milling blisk |
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|---|---|
| CN102554825B (en) | 2014-07-16 |
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Effective date of registration: 20171107 Address after: No. 21 high tech Zone Gaopeng road in Chengdu city of Sichuan Province in 610000 Patentee after: Sichuan Haite High-tech Co.,Ltd. Address before: 610041 No. 4 South Road, Chengdu hi tech Development Zone, Chengdu, Sichuan Patentee before: Sichuan Yamei Power Technology Co., Ltd. |
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Effective date of registration: 20190202 Address after: 610000 No. 4 South Keyuan Road, Chengdu High-tech Zone, Sichuan Province Patentee after: Sichuan Yamei Power Technology Co., Ltd. Address before: 610000 Gaopeng Avenue, Chengdu High-tech Zone, Sichuan Province Patentee before: Sichuan Haite High-tech Co.,Ltd. |