CN202480003U - Secutity clamp for assembly of turbine vanes - Google Patents
Secutity clamp for assembly of turbine vanes Download PDFInfo
- Publication number
- CN202480003U CN202480003U CN2011205464521U CN201120546452U CN202480003U CN 202480003 U CN202480003 U CN 202480003U CN 2011205464521 U CN2011205464521 U CN 2011205464521U CN 201120546452 U CN201120546452 U CN 201120546452U CN 202480003 U CN202480003 U CN 202480003U
- Authority
- CN
- China
- Prior art keywords
- positioning seat
- turbine disk
- leading edge
- blade
- exhaust limit
- 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.)
- Withdrawn - After Issue
Links
Images
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model discloses a security clamp for assembly of turbine vanes and a clamping method of a vane wheel and belongs to the technical field of the assembly of the gas turbine vanes of aircraft engines. At least three bosses are evenly arranged on an edge portion of an inner end face of a locating seat of a gas inlet side of a turbine disk. A threaded rod penetrates through the locating seat of the gas inlet side of the turbine disk and is fixed in the middle of the locating seat of a gas exhaust side of the turbine disk. When the security clamp for the assembly of the turbine vanes is used, the turbine vanes are placed between the locating seat of the gas inlet side of the turbine disk and the locating seat of the gas exhaust side of the turbine disk, the locating seat of the gas inlet side of the turbine disk and the bosses are matched with the locating seat of the gas exhaust side of the turbine disk to fix the turbine vanes. Through the utilization of the security clamp for the assembly of the turbine vanes, the secured vanes can meet a demand for the size of 3.4+/-0.05 millimeters, and therefore the vanes can be prevented from being pushed to become loose and qualified rate of the assembly of the turbine vanes is increased.
Description
Technical field
The utility model relates to aero-engine gas-turbine blade mounting technology, and 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.
The utility model content
The utility model purpose of the utility model is: to the problem of above-mentioned existence; Provide a kind of simple in structure, easy and simple to handle, satisfy the turbo blade assembling insurance anchor clamps that the assembling of engine turbine rotor blade is used; 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.
The technical scheme that the utility model adopts is following:
The turbo blade assembling insurance anchor clamps of the utility model; 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; Turbo blade can be 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 loosening and be out of shape, thereby guarantee the qualification rate that impeller is installed; Especially when needs assemble impeller; Need impeller (being turbo blade) be placed between turbine disk leading edge positioning seat and turbine disk exhaust limit positioning seat, be fixed, make turbine disk leading edge positioning seat, boss cooperate turbo blade is fixed with turbine disk exhaust limit positioning seat; Can effectively impeller be positioned and fix; Not only 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; Thereby can reduce maintenance cost effectively, be fit to apply.
The turbo blade assembling insurance anchor clamps of the utility model, 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.
The turbo blade assembling insurance anchor clamps of the utility model; 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.
The turbo blade assembling insurance anchor clamps of the utility model, 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.
The turbo blade assembling insurance anchor clamps of the utility model; 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.
In sum, owing to adopted technique scheme, the beneficial effect of the utility model is:
1, the turbo blade of the utility model assembling insurance anchor clamps are simple in structure, easy and simple to handle, satisfy the assembling of engine turbine rotor blade and use;
2, the turbo blade of the utility model 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.
Description of drawings
The utility model will explain through example and with reference to the mode of accompanying drawing, wherein:
Fig. 1 is the structural representation of the turbo blade assembling insurance anchor clamps of the utility model;
Fig. 2 is a turbine disk leading edge positioning seat structural representation in the utility model;
Fig. 3 is the left view of Fig. 2;
Fig. 4 is the blade wheel structure sketch map that needs insurance in the utility model.
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 the turbo blade assembling insurance anchor clamps of the utility model, is example with above-mentioned four accompanying drawings, to these anchor clamps with and clamping method tell about.In the utility model; 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.
The turbo blade assembling insurance anchor clamps of the utility model; 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 the employing of the utility model 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 °.
The turbo blade assembling insurance anchor clamps of the utility model 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 beneficial effect of the utility model is: 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 utility model is not limited to the aforesaid specific embodiment.The utility model 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 (6)
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); Turbo blade can be 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 to be provided with turbine disk leading edge positioning seat boss (11) on three 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).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205464521U CN202480003U (en) | 2011-12-23 | 2011-12-23 | Secutity clamp for assembly of turbine vanes |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205464521U CN202480003U (en) | 2011-12-23 | 2011-12-23 | Secutity clamp for assembly of turbine vanes |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202480003U true CN202480003U (en) | 2012-10-10 |
Family
ID=46954463
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011205464521U Withdrawn - After Issue CN202480003U (en) | 2011-12-23 | 2011-12-23 | Secutity clamp for assembly of turbine vanes |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202480003U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102554825A (en) * | 2011-12-23 | 2012-07-11 | 四川亚美动力技术有限公司 | Turbine blade assembling insurance clamp and method for performing impeller clamping thereof |
| CN105291015A (en) * | 2015-11-30 | 2016-02-03 | 李功文 | Fixing device for mounting impellers |
| CN107584273A (en) * | 2017-10-23 | 2018-01-16 | 中国航发成都发动机有限公司 | A kind of engine turbine blade integral installation and provision for disengagement and method |
-
2011
- 2011-12-23 CN CN2011205464521U patent/CN202480003U/en not_active Withdrawn - After Issue
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102554825A (en) * | 2011-12-23 | 2012-07-11 | 四川亚美动力技术有限公司 | Turbine blade assembling insurance clamp and method for performing impeller clamping thereof |
| CN102554825B (en) * | 2011-12-23 | 2014-07-16 | 四川亚美动力技术有限公司 | Turbine blade assembling insurance clamp and method for performing impeller clamping thereof |
| CN105291015A (en) * | 2015-11-30 | 2016-02-03 | 李功文 | Fixing device for mounting impellers |
| CN107584273A (en) * | 2017-10-23 | 2018-01-16 | 中国航发成都发动机有限公司 | A kind of engine turbine blade integral installation and provision for disengagement and method |
| CN107584273B (en) * | 2017-10-23 | 2019-05-14 | 中国航发成都发动机有限公司 | A kind of engine turbine blade integral installation and provision for disengagement and method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102554825B (en) | Turbine blade assembling insurance clamp and method for performing impeller clamping thereof | |
| WO2009112776A3 (en) | Blade with non-axisymmetric platform: recess and boss on the extrados | |
| CN202480003U (en) | Secutity clamp for assembly of turbine vanes | |
| CA2657264A1 (en) | Method of machining airfoil root fillets | |
| MX2007011794A (en) | Locking arrangement for radial entry turbine blades. | |
| US9797257B2 (en) | Attachment of composite article | |
| JPH0586809A (en) | Combined fan stator assenbly | |
| WO2009112775A3 (en) | Blade with non-axisymmetric platform | |
| JP2017057851A (en) | Blade/disk dovetail backcut for blade disk stress reduction | |
| US20180017074A1 (en) | System and method for reduced stress vane shroud assembly | |
| US9957842B2 (en) | Method and apparatus for supporting blades | |
| CN205927972U (en) | Fan big blades profile mills quick resilient mounting positioner | |
| CN210564669U (en) | Blade retainer for impeller machinery | |
| CN110509089B (en) | Vibration reduction tool for processing wide-chord hollow fan blade | |
| US9777579B2 (en) | Attachment of composite article | |
| JP7220977B2 (en) | Lockwire tab backcut to reduce blade stress | |
| CN215296706U (en) | Sampling device for mechanical property sample of blade tenon of aero-engine | |
| CN211202062U (en) | Connection structure of gas turbine blade and turbine disc | |
| CN205173057U (en) | Axial -flow blower blade retention mechanism | |
| CN110216623A (en) | A kind of engine turbine blade quick decomposing device and method | |
| CN210818588U (en) | A mounting fixture that is used for turbine shell to immediately process usefulness | |
| CN217176718U (en) | High-strength turbine blade | |
| CN210790149U (en) | Anchor clamps are used in processing of turbine shell four-axis | |
| CN214464413U (en) | High-precision complex curved surface supercharger turbine | |
| CN219725297U (en) | Tool fixture for clamping exhaust part of turbocharger |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20121010 Effective date of abandoning: 20140716 |
|
| RGAV | Abandon patent right to avoid regrant |