CN102554825B - 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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- CN102554825B CN102554825B CN201110437683.3A CN201110437683A CN102554825B CN 102554825 B CN102554825 B CN 102554825B CN 201110437683 A CN201110437683 A CN 201110437683A CN 102554825 B CN102554825 B CN 102554825B
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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 the mounting technology that aero-engine gas-turbine blade mounting technology, particularly a kind of turbine disk and blade adopt the connected mode of locking plate.
Background technology
The turbine disk and the blade that adopt locking plate to connect, its turbo blade assembles qualified acceptance criteria and is: after blade insurance, do not allowed any becoming flexible, and blade inlet edge boss exceeds turbine disk leading edge face size 3.4 ± 0.05mm.In the process of engine turbine blade assembling insurance, due to the design defect of former assembly tooling, often cause the blade having insured by frock top pine, make blade loosening, more can not meet the dimensional requirement of 3.4 ± 0.05mm.To pull down and scrap locking plate thus, again blade be insured, make all blades on the whole turbine disk meet dimensional requirement, need repeatedly do over again.Waste time and energy, have a strong impact on repair progress, and wasted many locking plates, virtually increased cost.
Summary of the invention
Goal of the invention of the present invention is: for the problem of above-mentioned existence, provide a kind of simple in structure, easy and simple to handle, meet the method that engine turbine rotor blade assembles the turbine blade assembling insurance clamp using and carries out impeller clamping, by using this insurance clamp, can make the blade after insurance meet the requirement of size 3.4 ± 0.05mm, and can effectively avoid insuring other blades time top pine to insure qualified blade, improve the qualification rate of turbo blade assembling; By using this furniture to carry out the method for impeller clamping, can carry out quickly and easily the location of turbine, reduce labour intensity, reduce locking plate scrappage, improve repair progress, reduce maintenance cost.
The technical solution used in the present invention is as follows:
Turbine blade assembling insurance clamp 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 is also fixing through the middle part of turbine disk leading edge positioning seat and turbine disk exhaust limit positioning seat, when 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 coordinate turbo blade is fixed with turbine disk exhaust limit positioning seat.
Owing to having adopted said structure, impeller can be fixed between the positioning seat of turbine disk exhaust limit by turbine disk leading edge positioning seat, and the middle part of passing turbine disk leading edge positioning seat and turbine disk exhaust limit positioning seat by screw rod is fixed, ensure that its structure surely leans on, avoid occurring in the process of assembling loosening and be out of shape, thereby ensure the qualification rate that impeller is installed, especially in the time that needs assemble impeller, impeller need to be placed between turbine disk leading edge positioning seat and turbine disk exhaust limit positioning seat and be fixed, make turbine disk leading edge positioning seat and boss coordinate turbo blade is fixed with turbine disk exhaust limit positioning seat, can effectively impeller be positioned and be fixed, not only can make the blade after insurance meet the requirement of size 3.4 ± 0.05mm, and can effectively avoid insuring other blades time top pine to insure qualified blade, improve the qualification rate of turbo blade assembling, thereby can effectively reduce maintenance cost, be applicable to applying.
Turbine blade assembling insurance clamp of the present invention, described 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 having 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 type supporting and location rings, blade exhaust limit locating ring only contacts blade boss, for the intensive very large raising of locking plate insurance operability of circle distribution; Leading edge positioning seat 3 point type contact turbine disk tenon tooth end faces, do not contact blade tenon completely, are not subject to rest blade insurance and become flexible with having insured qualified blade on a turbine disk.
Turbine blade assembling insurance clamp of the present invention, on the inner face of described turbine disk leading edge positioning seat, be provided with blade leading edge locating ring, on the inner face of described turbine disk exhaust limit positioning seat, be provided with blade exhaust limit locating ring, when use, described blade leading edge locating ring is relative with blade exhaust limit locating ring, and turbo blade is located.
Owing to having 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 for cooperatively interacting in the process using, be that 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, there is loosening distortion, can effectively protect impeller, thereby can make the blade after insurance meet the requirement of size 3.4 ± 0.05mm, and can effectively avoid insuring other blades time, top pine have been insured qualified blade, improve the qualification rate of turbo blade assembling, thereby can reduce costs, be applicable to applying.
Turbine blade assembling insurance clamp of the present invention, described turbine disk leading edge positioning seat boss exceeds 3.4 ± 0.02mm than blade leading edge locating ring.
Owing to having 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 can effectively avoid insuring other blades time, top pine have been insured qualified blade, improve the qualification rate of turbo blade assembling, thereby reduce maintenance cost.
Turbine blade assembling insurance clamp of the present invention, the two ends of described screw rod are equipped with screw thread, and screw rod has 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 turbine disk exhaust limit, and on the screw rod between described turbine disk leading edge positioning seat and turbine disk exhaust limit positioning seat, cover has packing ring two.
Owing to having adopted said structure, whole insurance harness is fixed by screw rod, wherein in one end of turbine disk leading edge positioning seat, be fixed by the leading edge locking nut coordinating with screw rod, and in one end of turbine disk exhaust limit positioning seat, be fixed by the exhaust limit locking nut coordinating with screw rod, the two ends of furniture all can be fixed by screw rod, turbine is placed between turbine disk leading edge positioning seat and turbine disk exhaust limit positioning seat, and cover has packing ring two on screw rod, turbine can be fixed, and have good positioning, avoid it loosening, and the quality of qualified blade has been insured in impact, and then the qualification rate of raising turbo blade assembling.
Employing turbine blade assembling insurance clamp of the present invention carries out the method for impeller clamping, comprises the following steps:
Turbine disk leading edge positioning seat and blade leading edge locating ring are assembled into leading edge positioning seat assembly by step 1., and locking plate and blade composition impeller are installed on the turbine disk;
Step 2. is installed to impeller in 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, blade inlet edge boss contacts with blade leading edge locating ring simultaneously;
Step 3. is installed packing ring two to the boss of turbine disk exhaust limit, and aims at installing hole, packs screw rod into and makes screw rod six square toes contact packing rings two, and packing ring one is installed, and tightens leading edge locking nut;
Blade exhaust limit locating ring and turbine disk exhaust limit positioning seat are assembled into exhaust limit positioning seat assembly by step 4., and exhaust limit positioning seat assembly is installed, and trailing edge boss is contacted with blade exhaust limit locating ring, and the 3rd packing ring is installed, and tightens exhaust limit locking nut.
Owing to having adopted said method, assemble respectively leading edge positioning seat assembly and impeller, for early-stage preparations are carried out in follow-up production assembling, in the time assembling, impeller is installed in leading edge positioning seat assembly, make the turbine disk leading edge positioning seat in whole fixture, boss and turbine disk leading edge positioning seat boss can contact with turbine disk leading edge end face, but special requirement can not contact with blade tenon, avoid impeller to cause the infringement of collision, avoid its distortion, also require blade inlet edge boss to contact with blade leading edge locating ring simultaneously, can effectively impeller be fixed, make whole fixture can protect well whole impeller, improve the qualification rate of turbo blade assembling, again can be by fixture locking by being equipped with packing ring and nut on screw rod, impeller is fixed in fixture, and can be by the special construction of the boss in fixture, thereby ensure that blade meets the requirement of size 3.4 ± 0.05mm, again the exhaust limit positioning seat assembly assembling is assembled to cooperation, and ensure that trailing edge boss contacts with blade exhaust limit locating ring, whole fixture can be played a very good protection to impeller, avoid it loosening, ensure its life-span.Therefore employing turbine blade assembling insurance clamp of the present invention carries out the method for impeller clamping, can carry out quickly and easily the location of turbine, reduces labour intensity, reduces locking plate scrappage, improves repair progress, reduces maintenance cost.
In sum, owing to having adopted technique scheme, the invention has the beneficial effects as follows:
1, turbine blade assembling insurance clamp of the present invention, simple in structure, easy and simple to handle, meets the assembling of engine turbine rotor blade and use;
2, turbine blade assembling insurance clamp of the present invention, can make the blade after insurance meet the requirement of size 3.4 ± 0.05mm, and can effectively avoid insuring other blades time top pine to insure qualified blade, improves the qualification rate of turbo blade assembling;
3, employing turbine blade assembling insurance clamp of the present invention carries out the method for impeller clamping, can carry out quickly and easily the location of turbine, reduces labour intensity, reduces locking plate scrappage, improves repair progress, reduces maintenance cost.
Brief description of the drawings
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein:
Fig. 1 is the structural representation of turbine blade assembling insurance clamp of the present invention;
Fig. 2 is turbine disk leading edge location seat structure schematic diagram in the present invention;
Fig. 3 is the left view of Fig. 2;
Fig. 4 is the blade wheel structure schematic diagram that needs insurance in the present invention.
Mark in figure: 1-leading edge locking nut, 2-packing ring one, 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, 7-boss, 8-packing ring two, 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, 15-turbo blade, 16-locking plate, the 17-turbine disk, 18-turbine disk exhaust limit boss, 19-hole.
Detailed description of the invention
Disclosed all features in this description, or step in disclosed all methods or process, except mutually exclusive feature and/or step, all can combine by any way.
Disclosed arbitrary feature in this description (comprising any accessory claim, summary and accompanying drawing), unless narration especially all can be replaced by other equivalences or the alternative features with similar object.,, unless narration especially, each feature is an example in a series of equivalences or similar characteristics.
As shown in Figure 4, its blade wheel structure for insuring; Fig. 1 to Fig. 3 is the structural representation of turbine blade assembling insurance clamp of the present invention, taking above-mentioned four accompanying drawings as example, to this fixture with and clamping method tell about.In the present invention, taking Fig. 1 as example, turbine disk leading edge positioning seat 3 inner faces are the right side of turbine disk leading edge positioning seat 3, 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 left side, and the outer face of turbine disk exhaust limit positioning seat 6 is right side.
Turbine blade assembling insurance clamp 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, four boss 7 or five boss 7 can certainly be set according to actual needs, be at least three.Adopt 3 point type supporting and location rings at turbine disk leading edge, 4 contact blade boss 7 of blade exhaust limit locating ring, 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, on each boss 7, be provided with turbine disk leading edge positioning seat boss 11, on the inner face of described turbine disk leading edge positioning seat 3, be provided with blade leading edge locating ring 4, and described 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 than blade leading edge locating ring 4, and also can design and adopt turbine disk leading edge positioning seat boss 11 to exceed 3.40mm than blade leading edge locating ring 4, according to above-mentioned principle, can design turbine disk leading edge positioning seat boss 11 and exceed 3.4 ± 0.02mm than blade leading edge locating ring 4, thereby guarantee to insure rear blade leading edge boss and exceed turbine disk leading edge face size 3.4 ± 0.05mm.On the inner face of described turbine disk exhaust limit positioning seat 6, be provided with blade exhaust limit locating ring 5, when use, described blade leading edge locating ring 4 is relative with blade exhaust limit locating ring 5, and turbo blade is located.The two ends of described 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, on turbine disk exhaust limit, positioning seat 6 fit ons have exhaust limit locking nut 10 to screw rod 9, on screw rod 9 between described turbine disk leading edge positioning seat 3 and turbine disk exhaust limit positioning seat 6, cover has packing ring 28, and screw rod 9 is also fixing with the middle part of turbine disk exhaust limit positioning seat 6 through turbine disk leading edge positioning seat 3.When 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 and boss 7 coordinate turbo blade is fixed with turbine disk exhaust limit positioning seat 6.
The turbine blade assembling insurance clamp of employing of the present invention carries out the method for impeller clamping, and it comprises the following steps:
Turbine disk leading edge positioning seat 3 and blade leading edge locating ring 4 are assembled into leading edge positioning seat assembly by step 1., and on the turbine disk 17, locking plate 16 is installed and blade 15 forms impeller;
Step 2. is installed to impeller in 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 packing ring 28 to turbine disk exhaust limit boss 18, and aims at installing hole 19, packs screw rod 9 into and makes screw rod six square toes contact packing rings 28, and packing ring 1 is installed, and tightens leading edge locking nut 1;
Blade exhaust limit locating ring 5 and turbine disk exhaust limit positioning seat 6 are assembled into exhaust limit positioning seat assembly by step 4., exhaust limit positioning seat assembly is installed, make trailing edge boss 14 contact blade exhaust limit locating ring 5, the 3rd packing ring is installed, tighten exhaust limit locking nut 10, complete impeller clamping work.
In above-mentioned steps 4, can, by the number of assembling steps of exhaust limit positioning seat assembly, in step 1, carry out, to complete impeller clamping work as good, and need not consider the order of the method.With the fixing clamping impeller of vice, can carry out the insurance of locking plate, complete after one side insurance, another side is insured after turning 180 °.
Turbine blade assembling insurance clamp of the present invention, can, by screw rod 9 six square toes, packing ring being installed, support turbine disk exhaust limit, 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, tighten leading edge locking nut 1, adjust blade exhaust limit locating ring 5 and positioning seat assembly, make it compress trailing edge boss 14, tighten leading edge locking nut 1.By compress the turbine disk and turbo blade simultaneously, make it invariably loosening; 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 type supporting and location rings, blade exhaust limit locating ring only contacts blade boss 7, makes all locking plates, and tongue-and-groove junction is exposed outside completely, ensures sufficient insurance operating space.By leading edge positioning seat 3 point type contact turbine disk tenon tooth end faces, do not contact blade tenon completely, guarantee be not subject to rest blade insurance and become flexible with having insured qualified blade on a turbine disk.
The invention has the beneficial effects as follows: this turbine blade assembling insurance clamp, because leading edge adopts 3 point type supporting and location rings, blade exhaust limit locating ring only contacts blade boss, for the intensive very large raising of locking plate insurance operability of circle distribution; Leading edge positioning seat 3 point type contact turbine disk tenon tooth end faces, do not contact blade tenon completely, are not subject to rest blade insurance and become flexible with having insured qualified blade on a turbine disk, workable, reduce labour intensity, reduce locking plate scrappage, improve repair progress, reduce maintenance cost.Fixture is workable, reduces labour intensity, reduces locking plate scrappage, improves repair progress, reduces maintenance cost.
The present invention is not limited to aforesaid detailed description of the invention.The present invention expands to any new feature or any new combination disclosing in this manual, and the arbitrary new method disclosing or step or any new combination of process.
Claims (7)
1. turbine blade assembling insurance clamp, 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), screw rod (9) is also fixing with the middle part of turbine disk exhaust limit positioning seat (6) through turbine disk leading edge positioning seat (3), when use, turbo blade is positioned between turbine disk leading edge positioning seat (3) and turbine disk exhaust limit positioning seat (6), turbine disk leading edge positioning seat (3) and boss (7) coordinate turbo blade are fixed with turbine disk exhaust limit positioning seat (6).
2. turbine blade assembling insurance clamp as claimed in claim 1, is characterized in that: described boss (7) is three, is provided with turbine disk leading edge positioning seat boss (11) on each boss (7).
3. turbine blade assembling insurance clamp as claimed in claim 1 or 2, it is characterized in that: on the inner face of described turbine disk leading edge positioning seat (3), be provided with blade leading edge locating ring (4), on the inner face of described turbine disk exhaust limit positioning seat (6), be provided with blade exhaust limit locating ring (5), when use, described blade leading edge locating ring (4) is relative with blade exhaust limit locating ring (5), and turbo blade is located.
4. turbine blade assembling insurance clamp as claimed in claim 3, is characterized in that: described turbine disk leading edge positioning seat boss (11) exceeds 3.4 ± 0.02mm than blade leading edge locating ring (4).
5. turbine blade assembling insurance clamp as claimed in claim 3, it is characterized in that: the two ends of described 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 turbine disk exhaust limit positioning seat (6) fit on, and the upper cover of screw rod (9) between described turbine disk leading edge positioning seat (3) and turbine disk exhaust limit positioning seat (6) has packing ring (8).
6. turbine blade assembling insurance clamp as claimed in claim 4, it is characterized in that: the two ends of described 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 turbine disk exhaust limit positioning seat (6) fit on, and the upper cover of screw rod (9) between described turbine disk leading edge positioning seat (3) and turbine disk exhaust limit positioning seat (6) has packing ring two (8).
7. adopt the turbine blade assembling insurance clamp described in any one in claim 1 to 6 to carry out a method for impeller clamping, be characterised in that: it comprises the following steps:
Turbine disk leading edge positioning seat (3) and blade leading edge locating ring (4) are assembled into leading edge positioning seat assembly by step 1., and in the turbine disk (17)
onlocking plate (16) and blade (15) composition impeller are installed;
Step 2. is installed to impeller in 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;
It is upper to turbine disk exhaust limit boss (18) that step 3. is installed packing ring two (8), and aim at installing hole (19), packs screw rod (9) into and make screw rod six square toes contact packing rings two (8), and packing ring one (2) is installed, and tightens leading edge locking nut (1);
Blade exhaust limit locating ring (5) and turbine disk exhaust limit positioning seat (6) are assembled into exhaust limit positioning seat assembly by step 4., exhaust limit positioning seat assembly is installed, make trailing edge boss (14) contact blade exhaust limit locating ring (5), the 3rd packing ring 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 |
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| Publication Number | Publication Date |
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| CN102554825A CN102554825A (en) | 2012-07-11 |
| CN102554825B true 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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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| 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 |
| CN112476255A (en) * | 2020-12-09 | 2021-03-12 | 安徽应流航源动力科技有限公司 | Sand blasting protection device for air inlet edge and air exhaust edge of blade |
| CN113146471A (en) * | 2021-05-31 | 2021-07-23 | 四川亚美动力技术有限公司 | Device for precisely grinding turbine disc blade assembly |
| 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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| CN2322742Y (en) * | 1998-01-19 | 1999-06-09 | 黄南平 | Clamp for precision machining brake disk parts |
| GB2463392A (en) * | 2008-12-24 | 2010-03-17 | Benjamin John Ridehough | Hydraulic clamping device |
| CN201863020U (en) * | 2010-10-27 | 2011-06-15 | 中国北车集团大连机车研究所有限公司 | Drilling clamp for turbocharger turbine disk |
| 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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| Publication number | Priority date | Publication date | Assignee | Title |
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| US20090070977A1 (en) * | 2007-09-13 | 2009-03-19 | General Electric Company | Jig And Fixture For Wind Turbine Blade |
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| CN2322742Y (en) * | 1998-01-19 | 1999-06-09 | 黄南平 | Clamp for precision machining brake disk parts |
| GB2463392A (en) * | 2008-12-24 | 2010-03-17 | Benjamin John Ridehough | Hydraulic clamping device |
| CN201863020U (en) * | 2010-10-27 | 2011-06-15 | 中国北车集团大连机车研究所有限公司 | Drilling clamp for turbocharger turbine disk |
| 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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| CN102554825A (en) | 2012-07-11 |
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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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