CN103600200B - A kind of T300/BMP-316 composite contains casing mount pad replacing repair method outward - Google Patents

A kind of T300/BMP-316 composite contains casing mount pad replacing repair method outward Download PDF

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Publication number
CN103600200B
CN103600200B CN201310499063.1A CN201310499063A CN103600200B CN 103600200 B CN103600200 B CN 103600200B CN 201310499063 A CN201310499063 A CN 201310499063A CN 103600200 B CN103600200 B CN 103600200B
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China
Prior art keywords
mount pad
casing
rivet
composite
bore hole
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CN201310499063.1A
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CN103600200A (en
Inventor
张革
庞玉甦
任武
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AECC Shenyang Liming Aero Engine Co Ltd
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Shenyang Liming Aero Engine Group Co Ltd
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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B23MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23PMETAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P6/00Restoring or reconditioning objects

Abstract

The present invention disclose a kind of T300/BMP-316 composite contain outward casing mount pad change repair method, be carry out according to following steps: parts inspection, clamping parts, carry out position measurement at double column jig boring machine, casing is pulled down, remove rivet, get need change mount pad, location clamping, combination drill bore hole, riveted joint assembling, combination bore hole, cleaning, submission check; The invention has the beneficial effects as follows: because this aero-engine is the aircraft power plant of domestic independent research, technology also not relevant is at home repaired for this h type engine h, succeeding in developing of this technology, the repairing of composite casing class part, the process technology beginning can be started, lead over domestic service technique.

Description

A kind of T300/BMP-316 composite contains casing mount pad replacing repair method outward
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 contained runner and install the non-drive annex in some outsides.In engine operation, play very important effect, introduce the cold air coming from air, to turbine rotor cooling, improve engine parts reliability.Due to the aircraft power plant that this aero-engine is domestic independent research, technology also not relevant is at home repaired for this h type engine h, 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, be widely used in Aero-Space, 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 general very little, be difficult to observe directly, and inside often produces 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 entirety of structure is destroyed and lost efficacy and forms potential threat, even directly can cause the generation of accident, therefore, still do not have mature technology can reference for processing characteristics and fault restoration.
Summary of the invention
Aero-engine involved in the present invention is that air force advocates war recent and following significant period of time the power set of machine.This engine is repaired now extremely urgent to the longevity, this engine by-pass air duct casing adopts current domestic new material development, repairing and also there is no ripe technology in processing, therefore carrying out the research of by-pass air duct casing service technique and serve very important effect for getting through repair track.Technical scheme of the present invention is as follows:
A kind of T300/BMP-316 composite is contained casing mount pad outward and is changed repair method, is carry out according to following steps: parts inspection, clamping parts, carry out position measurement, pulled down by casing, remove rivet, get the mount pad, location clamping, combination drill bore hole, riveted joint assembling, combination bore hole, cleaning, the submission that need to change and check at double column jig boring machine;
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, at below 0.2mm, adopts Air flow rivet polishing position during polishing, ensure that burnishing part temperature is lower than 60 DEG C, note the color change observing parts;
The machined parameters of described combination drill bore hole:
Equipment: double column jig boring machine;
The speed of mainshaft: 80-130r/min;
Feed: 415mm/min;
The depth of cut: monolateral 1mm.
The mount pad that outer culvert casing is changed reserves the allowance of 1mm.
After mount pad assembling riveted joint completes, outer culvert casing is installed on double column jig boring machine, locate with the mounting edge of large end face, with the mount pad needing the mount pad of reparation nearer for benchmark centering, calculate the position degree needing supplementary processing mount pad and benchmark mount pad, determine axis and angle phase position, carry out boring processing and bore is installed.
The invention has the beneficial effects as follows: because this aero-engine is the aircraft power plant of domestic independent research, technology also not relevant is at home repaired for this h type engine h, succeeding in developing of this technology, the repairing of composite casing class part, the process technology beginning can be started, 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.
Detailed description of the invention
Aero-engine involved in the present invention is that air force advocates war recent and following significant period of time the power set of machine.This engine is repaired now extremely urgent to the longevity, this engine by-pass air duct casing adopts current domestic new material development, repairing and also there is no ripe technology in processing, therefore carrying out the research of by-pass air duct casing service technique and serve 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 and brings fault because of overheated;
(2) by-pass air duct front and rear sections casing parts are comparatively large, decompose the size detection difficulty of mount pad and erection seat;
(3) contain outward casing mount pad change after whether made allowance and later stage Combined machining be the difficult point of this project, need to consider truly feasible scheme.
(4) process equipment, as: riveting equipment, boring equipment etc. need to be determined 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 by vibrating the parts fretting wear caused in engine operation, in order to solve these faults, need that the failure mode to mount pad, fault characteristic and parts are structural to be analyzed, concrete measure: the parts that can not meet job requirement for failure mode, adopts the method changing fault mount pad to change.
Process program is determined
Process route is as follows: parts inspection, clamping parts, carry out position measurement at double column jig boring machine, casing is pulled down, remove rivet (note part be heated bring composite burn), get need change mount pad, location clamping, combination drill bore hole, riveted joint assembling, combination bore hole, cleaning, submission 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, at below 0.2mm, adopts pressure-air cooling rivet polishing position during polishing, ensure that burnishing part temperature is lower than 60 DEG C, note the color change observing parts.
The machined parameters of combination drill bore hole:
Equipment: double column jig boring machine
The speed of mainshaft: 80-130r/min
Feed: 415mm/min
The depth of cut: monolateral 1mm
Riveting process
Adopt riveting machine, adopt common processes to complete, riveting pressure adjusts according to manufactured head requirement for height.
By to by-pass air duct front and rear sections casing drawing and Structural Performance Analysis, to decomposition and the assembling of mount pad; For the position dimension of each mount pad after decomposition and assembling, adopt the method that boring machine carries out detecting to determine, used for reference some measures and methods in parts manufacture simultaneously, ensure that the position degree requirement after mount pad replacing, reach the object of expection.
The mount pad that outer culvert casing is changed reserves the allowance of 1mm, and after changing as mount pad, Combined machining is to ensure the position degree changing rear mount pad.
Certain distortion is there is because there are parts after the work of outer culvert casing, after mount pad assembling riveted joint completes, outer culvert casing is installed on double column jig boring machine, locate with the mounting edge of large end face, with the mount pad needing the mount pad of reparation nearer for benchmark centering, calculate the position degree needing supplementary processing mount pad and benchmark mount pad, determine axis and angle phase position, carry out boring processing and bore is installed, ensure drawing requirement.
Processed by testpieces, the replacing of mount pad, after changing, parts can meet technical requirement.
The present invention is directed to composite to contain outward in the work of casing mount pad and wear and tear, off technical requirement causes outer culvert casing to use problem, adopts and removes rivet and mount pad, change mount pad, boring process method, ensure that composite contains the requirement of casing operation technique outward, good through verification the verifying results.

Claims (3)

1. T300/BMP-316 composite contain outward casing mount pad change a repair method, it is characterized in that carrying out according to following steps: parts inspection, clamping parts, carry out position measurement at double column jig boring machine, casing is pulled down, remove rivet, get needs change mount pad, location clamping, combination drill bore hole, riveted joint assembling, combine bore hole, cleaning, submission check;
The method of described removal rivet step is: with air drill and grinder buffing rivet projection, the blast 0.6Mpa that air drill uses, and the amount of cutting, at below 0.2mm, adopts pressure-air cooling rivet polishing position during polishing, ensure that burnishing part temperature is lower than 60 DEG C;
The step machined parameters of described combination drill bore hole:
Equipment: double column jig boring machine;
The speed of mainshaft: 80-130r/min;
Feed: 415mm/min;
The depth of cut: monolateral 1mm.
2. method according to claim 1, is characterized in that: the outer mount pad containing casing replacing reserves the allowance of 1mm.
3. method according to claim 2, it is characterized in that: after mount pad assembling riveted joint completes, outer culvert casing is installed on double column jig boring machine, locate with the mounting edge of large end face, with the mount pad needing the mount pad of reparation nearer for benchmark centering, calculate the position degree needing supplementary processing mount pad and benchmark mount pad, determine axis and angle phase position, carry out boring processing and bore is installed.
CN201310499063.1A 2013-10-19 2013-10-19 A kind of T300/BMP-316 composite contains casing mount pad replacing repair method outward Active CN103600200B (en)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
CN106363345B (en) * 2016-11-25 2018-09-14 沈阳黎明航空发动机(集团)有限责任公司 The replacing options of bearing case crackle oil pipe

Citations (4)

* Cited by examiner, † Cited by third party
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
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

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4873751A (en) * 1988-12-27 1989-10-17 United Technologies Corporation Fabrication or repair technique for integrally bladed rotor assembly

Patent Citations (4)

* Cited by examiner, † Cited by third party
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
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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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

CP01 Change in the name or title of a patent holder