CN103600200A - Mounting seat replacing and repairing method of T300/BMP-316 composite material bypass duct case - Google Patents
Mounting seat replacing and repairing method of T300/BMP-316 composite material bypass duct case Download PDFInfo
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- CN103600200A CN103600200A CN201310499063.1A CN201310499063A CN103600200A CN 103600200 A CN103600200 A CN 103600200A CN 201310499063 A CN201310499063 A CN 201310499063A CN 103600200 A CN103600200 A CN 103600200A
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- mount pad
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- mounting seat
- rivet
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
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- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a mounting seat replacing and repairing method of a T300/BMP-316 composite material bypass duct case. The method is implemented as the following steps of part examination, part clamping, position degree measurement on a double-column jig borer, case disassembly, rivet removal, mounting seat to be replaced preparation, location and clamping, combined drill boring, riveting and assembling, combined boring, cleaning and test implementation. The mounting seat replacing and repairing method of the T300/BMP-316 composite material bypass duct case has the advantages that due to the facts that an aero-engine is an aeroplane power unit researched and developed independently in China and no relevant techniques on repair of the aero-engine exist in China, the successful development of the mounting seat replacing and repairing method is a precedent breakthrough for repairing and machining technologies of parts such as composite material cases and is prior to existing repair technologies in China.
Description
Technical field
The present invention relates to aero-engine service technique, is a kind of replacing repair method of T300/BMP-316 composite casing mount pad specifically.
Background technology
Composite by-pass air duct front and rear sections casing is the forward and backward support case of connecting engine, forms the outer Force transmission parts of containing runner and the non-drive annex in some outsides being installed.In engine operation, play very important effect, introduce the cold air that comes from atmosphere, give turbine rotor cooling, improve engine parts reliability.Due to the aircraft power plant that this aero-engine is domestic independent research, for this h type engine h, repair and also there is no at home relevant technology, the material that by-pass air duct casing adopts is T300/BMP-316 composite, this material is owing to having specific strength, specific stiffness is high, the features such as designability is strong, Aero-Space have been widely used in, medicine equipment, and in the field such as sports goods. composite laminated structures is in repair procedures, structure easily produces damage, and surface damage is generally very little, be difficult to observe directly, and inside tends to produce MATRIX CRACKING, carbon fiber layer is sheared, the microscopic damage such as layering and fibrous fracture, these internal injuries will make the mechanical property serious degradation of laminate structures, intensity even can weaken 35%～40%, the integral body of structure is destroyed and lost efficacy and form potential threat, even can directly cause the generation of accident, therefore, for processing characteristics and fault restoration, still do not have the mature technology can reference.
Summary of the invention
Aero-engine involved in the present invention is the advocate war recent and following significant period of time power set of machine of air force.This engine is now extremely urgent to longevity repairing, this engine by-pass air duct casing adopts current domestic new material development, in repairing and processing, also there is no ripe technology, therefore carry out the research of by-pass air duct casing service technique and played very important effect for getting through repair track.Technical scheme of the present invention is as follows:
T300/BMP-316 composite is contained casing mount pad outward and is changed a repair method, is to carry out according to following steps: parts inspection, clamping parts, at double column jig boring machine, carry out position measurement, casing is pulled down, removed rivet, gets and need mount pad, location clampings, combination drill bore hole, riveted joint assembling, combination bore hole, cleaning, the submission changed to check;
The method of described removal rivet is: with air drill and grinder buffing rivet projection, the blast 0.6Mpa that air drill uses, the amount of cutting, below 0.2mm, adopts the cooling rivet polishing of air position during polishing, guarantee that burnishing part temperature is lower than 60 ℃, the change color of parts is observed in attention;
The machined parameters of described combination drill bore hole:
Equipment: double column jig boring machine;
The speed of mainshaft: 80-130r/min;
Feed: 415/min;
The depth of cut: monolateral 1mm.
The allowance of the reserved 1mm of mount pad that outer culvert casing is changed.
After mount pad assembling has been riveted, outer culvert casing is installed on double column jig boring machine, mounting edge location with large end face, the nearer mount pad of mount pad of needs reparation of take is benchmark centering, calculating needs the position degree of supplementary processing mount pad and benchmark mount pad, determine axial and angle phase position, carry out boring processing mount pad hole.
The invention has the beneficial effects as follows: due to this aero-engine aircraft power plant that is domestic independent research, for this h type engine h, repair and also there is no at home relevant technology, succeeding in developing of this technology, can start repairing, the process technology beginning of composite casing class part, lead over domestic service technique.
Accompanying drawing explanation
Fig. 1 is composite by-pass air duct leading portion schematic diagram;
Fig. 2 is fuel manifold mount pad assembling schematic diagram;
Fig. 3 is rivet assembling schematic diagram;
In figure, 1 is fuel manifold mount pad, and 2 is rivet.
The specific embodiment
Aero-engine involved in the present invention is the advocate war recent and following significant period of time power set of machine of air force.This engine is now extremely urgent to longevity repairing, this engine by-pass air duct casing adopts current domestic new material development, in repairing and processing, also there is no ripe technology, therefore carry out the research of by-pass air duct casing service technique and played very important effect for getting through repair track.
Concrete technological difficulties:
(1) by-pass air duct front and rear sections casing material therefor is composite, and mount pad is titanium alloy material, and removing rivet easily affects casing material of main part because of the overheated fault of bringing;
(2) by-pass air duct front and rear sections casing parts are larger, decompose the size detection difficulty of mount pad and erection seat;
(3) outer contain casing mount pad and change after whether made allowance and later stage combination processing be the difficult point of this project, need to consider truly feasible scheme.
(4) process equipment, as: riveting equipment, boring equipment etc. need to determine by test.
With reference to figure 1-Fig. 3, for fixed mounting fault on by-pass air duct front and rear sections casing, that is: airplane air entraining pipe mount pad inner surface; Anti-icing air entraining pipe mount pad inner surface; Often there is wear-out failure in fuel manifold, anti-asthma pressure air entraining pipe base inner surface, the generation of these faults is the parts fretting wear that vibration causes in engine operation, in order to solve these faults, need to analyze the failure mode of mount pad, fault characteristic and parts are structural, concrete measure: can not meet the parts of job requirement for failure mode, adopt the method for changing fault mount pad to change.
Process program is determined
Process route is as follows: parts inspection, clamping parts, at double column jig boring machine, carry out position measurement, casing is pulled down, removed rivet (noting the composite burn that part is heated and brings), gets and need mount pad, location clampings, combination drill bore hole, riveted joint assembling, combination bore hole, cleaning, the submission changed to check.
Remove rivet technological parameter: with air drill and grinder buffing rivet projection, the blast 0.6Mpa that air drill uses, the amount of cutting, below 0.2mm, adopts pressure-air cooling rivet polishing position during polishing, guarantee that burnishing part temperature is lower than 60 ℃, the change color of parts is observed in attention.
The machined parameters of combination drill bore hole:
Equipment: double column jig boring machine
The speed of mainshaft: 80-130r/min
Feed: 415/min
The depth of cut: monolateral 1mm
Riveting process
Adopt riveting machine, adopt common processes to complete, riveting pressure is adjusted according to manufactured head requirement for height.
By to by-pass air duct front and rear sections casing drawing and Structural Performance Analysis, to the decomposition of mount pad and assembling; For the position dimension that decomposes and assemble rear each mount pad, adopt the method detecting on boring machine to determine, used for reference some measures and method during parts are manufactured simultaneously, guaranteed the position degree requirement after mount pad replacing, reached the object of expecting.
The allowance of the reserved 1mm of mount pad that outer culvert casing is changed, changes rear combination processing to guarantee to change the position degree of rear mount pad as mount pad.
Because existing parts to have certain distortion after the work of outer culvert casing, after mount pad assembling has been riveted, outer culvert casing is installed on double column jig boring machine, mounting edge location with large end face, the nearer mount pad of mount pad of needs reparation of take is benchmark centering, calculates the position degree that needs supplementary processing mount pad and benchmark mount pad, determines axial and angle phase position, carry out boring processing mount pad hole, guarantee drawing requirement.
By testpieces, process, the replacing of mount pad, after changing, parts can meet specification requirement.
The present invention is directed to composite and contain outward in the work of casing mount pad and wear and tear, off technical requirement causes outer culvert casing cannot use problem, adopts and removes rivet and mount pad, change mount pad, boring process method, has guaranteed that composite contains the requirement of casing operation technique outward, good through verification the verifying results.
Claims (3)
1. T300/BMP-316 composite is contained casing mount pad outward and is changed a repair method, it is characterized in that carrying out according to following steps: parts inspection, clamping parts, double column jig boring machine carry out position measurement, by casing pull down, remove rivet, get mount pad, location clampings, combination drill bore hole, riveted joint assembling that needs change, combine bore hole, cleaning, submission check;
The method of described removal rivet step is: with air drill and grinder buffing rivet projection, and the blast 0.6Mpa that air drill uses, the amount of cutting, below 0.2mm, adopts pressure-air cooling rivet polishing position during polishing, guarantee that burnishing part temperature is lower than 60 ℃;
The step machined parameters of described combination drill bore hole:
Equipment: double column jig boring machine;
The speed of mainshaft: 80-130r/min;
Feed: 415/min;
The depth of cut: monolateral 1mm.
2. method according to claim 1, is characterized in that: the allowance of containing the reserved 1mm of mount pad of casing replacing outward.
3. method according to claim 2, it is characterized in that: after mount pad assembling has been riveted, outer culvert casing is installed on double column jig boring machine, mounting edge location with large end face, the nearer mount pad of mount pad of needs reparation of take is benchmark centering, calculating needs the position degree of supplementary processing mount pad and benchmark mount pad, determines axially and angle phase position, carries out boring processing mount pad hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310499063.1A CN103600200B (en) | 2013-10-19 | 2013-10-19 | A kind of T300/BMP-316 composite contains casing mount pad replacing repair method outward |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310499063.1A CN103600200B (en) | 2013-10-19 | 2013-10-19 | A kind of T300/BMP-316 composite contains casing mount pad replacing repair method outward |
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| CN103600200A true CN103600200A (en) | 2014-02-26 |
| CN103600200B CN103600200B (en) | 2015-10-21 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106363345A (en) * | 2016-11-25 | 2017-02-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Replacement method of bearing casing crack lubricating oil pipes |
| CN106493503A (en) * | 2016-11-25 | 2017-03-15 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of rear housing precision bolt hole Combined machining process that repairs to the longevity |
| CN112199796A (en) * | 2020-10-16 | 2021-01-08 | 中国航发四川燃气涡轮研究院 | Method for designing composite material culvert casing layering |
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| US4736504A (en) * | 1987-08-12 | 1988-04-12 | The United States Of America As Represented By The Secretary Of The Navy | Alignment method for pressure welded bladed disk |
| JPH02271001A (en) * | 1988-12-27 | 1990-11-06 | United Technol Corp <Utc> | Production of rotor integral with blade and repairing method for its blade |
| CN102950415A (en) * | 2011-08-26 | 2013-03-06 | 北京新联铁科技股份有限公司 | Motor train unit bogie disintegration flow line maintenance system and maintenance method thereof |
| CN102962627A (en) * | 2012-10-30 | 2013-03-13 | 西安航空动力股份有限公司 | Repair method for aero-engine fan casing borescope base |
| CN203156294U (en) * | 2013-04-12 | 2013-08-28 | 山东电力建设第二工程公司 | Scaffold coupler punching riveting and repairing device |
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2013
- 2013-10-19 CN CN201310499063.1A patent/CN103600200B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4736504A (en) * | 1987-08-12 | 1988-04-12 | The United States Of America As Represented By The Secretary Of The Navy | Alignment method for pressure welded bladed disk |
| JPH02271001A (en) * | 1988-12-27 | 1990-11-06 | United Technol Corp <Utc> | Production of rotor integral with blade and repairing method for its blade |
| CN102950415A (en) * | 2011-08-26 | 2013-03-06 | 北京新联铁科技股份有限公司 | Motor train unit bogie disintegration flow line maintenance system and maintenance method thereof |
| CN102962627A (en) * | 2012-10-30 | 2013-03-13 | 西安航空动力股份有限公司 | Repair method for aero-engine fan casing borescope base |
| CN203156294U (en) * | 2013-04-12 | 2013-08-28 | 山东电力建设第二工程公司 | Scaffold coupler punching riveting and repairing device |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106363345A (en) * | 2016-11-25 | 2017-02-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Replacement method of bearing casing crack lubricating oil pipes |
| CN106493503A (en) * | 2016-11-25 | 2017-03-15 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of rear housing precision bolt hole Combined machining process that repairs to the longevity |
| CN106493503B (en) * | 2016-11-25 | 2019-02-12 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of rear housing precision bolt hole Combined machining process repaired to the longevity |
| CN112199796A (en) * | 2020-10-16 | 2021-01-08 | 中国航发四川燃气涡轮研究院 | Method for designing composite material culvert casing layering |
| CN112199796B (en) * | 2020-10-16 | 2022-09-20 | 中国航发四川燃气涡轮研究院 | Method for designing composite material culvert casing layering |
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| Publication number | Publication date |
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| CN103600200B (en) | 2015-10-21 |
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Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee after: Chinese Hangfa Shenyang Liming Aero engine limited liability company Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City |