CN109604950A - A kind of processing method of aero-engine casing - Google Patents
A kind of processing method of aero-engine casing Download PDFInfo
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- CN109604950A CN109604950A CN201811488593.5A CN201811488593A CN109604950A CN 109604950 A CN109604950 A CN 109604950A CN 201811488593 A CN201811488593 A CN 201811488593A CN 109604950 A CN109604950 A CN 109604950A
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- cylinder
- face
- aero
- small end
- processing method
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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
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Drilling And Boring (AREA)
- Cylinder Crankcases Of Internal Combustion Engines (AREA)
Abstract
The invention discloses a kind of processing methods of aero-engine casing comprising following steps: 1) according to welding deformation trend and deflection designed and make process allowance big end installation while and small end install while；2) fanning strip is rolled into cylinder, which is in hollow round table shape, passes through solder joint；3) by big end install while and small end install while be respectively welded in cylinder both ends；4) explosive forming, the type that cylinder is placed in molding die is intracavitary, will ignite part and is arranged in the geometric center point of cylinder, and ignition and blasting part, an explosive forming, obtained cylinder is in cydariform；5) it finishes, cydariform cylinder is detached from from molding die, then machine finishing is until finished product.It can effectively reduce machining allowance, save material, reduce technology difficulty, improve production efficiency.
Description
Technical field
The present invention relates to aero-engine metal plate formings and welding manufacture technology, and in particular to a kind of aero-engine casing
Processing method.
Background technique
With the development of aeronautical and space technology, aero-engine performance of new generation requires higher and higher, design of part and type
Face becomes increasingly complex, and the processing in lumen type face is always a big difficulty of research and production in the casing of this part, because of common machine
Bed and numerically-controlled machine tool machining will treat material and have a biggish waste, and the process-cycle is longer and the disqualification rate of part is higher.
CN105397425B discloses a kind of aero-engine annular casing processing method, for removing the peace of annular casing
The surplus between seat and nozzle is filled, this method comprises: obtaining the technological parameter of annular casing to be processed, is selected and technological parameter phase
The milling cutter of adaptation；Annular casing to be processed is fixed on to the centre of gyration of lathe for machining, annular casing is driven to revolve around the centre of gyration
Turn, and the surplus of milling cutter layered cutting annular casing to be processed.It realizes the processing in annular casing inner cavity type face by milling, adds
Spare time amount is very big, and needs strict control milling process parameter, and processing technology is difficult, poor quality's control, production efficiency
It is lower.
CN102794610A discloses a kind of processing method of rotary structure thin walled welds casing, belongs to aero-engine
It is overproof to solve installation side own dimensions using whole predeformation welding/manufacturing process for metal plate forming and welding manufacture technical field
With after the welding of forward and backward installation side with main body concentricity is overproof and the unbalanced problem of weld assembly residual stress distribution.Including
Following steps: according to material plasticity deformation characteristic, installation side and the deformation of Thin-Wall Outer Casing main process structure welding are carried out before welding
Surplus Compensation Design；According to machine work department fit dimension and the requirement of part final structure size of swelling, Plastic Forming expansion block is carried out
Structure design；It carries out installation side and main body assembles automatic argon arc welding；Wheel chamber casing after welding is assembled together with expansion block swollen
In big machine work department, the Plastic Forming that swells is carried out, controls the forming dimension that swells by adjusting the machine pressure that swells；Unload the machine pressure that swells
Power withdraws the machine work department that swells, unloads part, complete a welding/forming process.It realizes lumen type in casing by the machine that swells
The processing in face there are certain requirements the plasticity of material, otherwise be easy to produce crackle, influence the use of casing, and swell machine at
Shape is slow, so that being easy to produce stress concentration in forming process, influences the service life of casing.
Summary of the invention
The object of the present invention is to provide a kind of processing methods of aero-engine casing, can effectively reduce more than processing
Amount saves material, reduces technology difficulty, improves production efficiency.
The processing method of aero-engine casing of the present invention comprising following steps:
1) designed according to welding deformation trend and deflection and make process allowance big end installation while and small end install while；
2) fanning strip is rolled into cylinder, which is in hollow round table shape, passes through solder joint；
3) by big end install while and small end install while be respectively welded in cylinder both ends；
4) explosive forming, the type that cylinder is placed in molding die is intracavitary, will ignite part and is arranged in the geometric center point of cylinder,
Ignition and blasting part, an explosive forming, obtained cylinder are in cydariform；
5) it finishes, cydariform cylinder is detached from from molding die, then machine finishing is until finished product.
Further, the material of the cylinder is titanium alloy.
Further, in the step 1) big end installation while and small end install while manufacturing method be hot rolling.
Further, multiple mounting bases are equipped in the cylinder lateral surface of explosive forming.
Further, it is preheated before the cylinder explosive forming, preheating temperature is 80 ~ 100 DEG C.
Further, the finishing in the step 5) includes thin turner sequence, smart car process and right boring process；Thin turner sequence:
The reparation of datum level is carried out using NC vertical lathe first, which is the large end face of cylinder, thin on the basis of datum level
Vehicle large end face is to single-sided process surplus, the then thin vehicle small end face on the basis of large end face, then thin vehicle cylinder big end and its inner hole, so
Thin vehicle cylinder small end and its inner hole afterwards, smart car process: smart car cylinder big end end face, small end end face and interior lumen type face；Right boring process:
Right boring cylinder big end inner hole and small end inner hole.
The present invention is acted on by explosive forming casing medial and lateral type face using the instantaneous impact of isolation explosion
Workpiece surface, so that workpiece and mold cavity assembly, forming part is change in shape, and thickness does not change, and is effectively avoided
Issuable stress raisers, reduce machining allowance, save material when mechanical molding, while reducing technique hardly possible
Degree, improves production efficiency.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of aero-engine casing of the invention.
In figure, 1-wheel chamber casing, 2-big ends install side, and 3-small ends install side, 4-mounting bases.
Specific embodiment
It elaborates in the following with reference to the drawings and specific embodiments to the present invention.
Referring to Fig. 1, shown in aero-engine casing finished product, including wheel chamber casing 1, shown wheel chamber casing are in cydariform,
Both ends are respectively fixed with big end installation when 2 and small end are installed 3, and lateral face is equipped with multiple mounting bases 4, shown mounting base 4
It is equipped with mounting hole.
A kind of processing method of aero-engine casing comprising following steps.
Rough turn reserved 1 ~ 2mm single-sided process surplus in manufacturing process, thin vehicle reserve 0.2 ~ 0.3 single-sided process surplus.
1) big end installation side and the small end installation of process allowance are designed and made according to welding deformation trend and deflection
Side, big end installation while and small end install while be referred to as installation side, processing method is: first checking for blank quality, cuts installation
The raw material that side needs, carry out jumping-up after heating, then punching installation side inner hole, and rough turn, reheating installation side is carried out to the inner hole
After carry out roughing, group prick after the completion of again heating carry out finish to gauge.Burr is cleared up after completing finish to gauge, is polished, after checking part size
It is heat-treated, removes internal stress.
2) board quality of manufacture wheel chamber casing is checked, the material of the plate is titanium alloy, by plate cutting at fanning strip,
Fanning strip is rolled into cylinder again, which is in hollow round table shape, passes through solder joint；
3) by big end install while and small end install while roughing to reserved size, then by big end install while and small end installation while distinguish
It is welded in cylinder both ends；
4) cylinder is preheated to 100 DEG C by explosive forming, and the type for being then placed into molding die is intracavitary, and explosive is arranged in cylinder
Geometric center point on, ignite explosive, an explosive forming, and connecting shaping mold makes the cylinder in hollow round table shape explode
Instantaneous pressure under be shaped to cydariform, forming part is that change in shape, thickness do not change, and explosive forming is due in moment
It completes, so almost without diffusion between composition phase, and crystal grain has little time to grow up, and may produce when effectively preventing mechanical molding
Raw stress raisers.Weld multiple mounting bases after the completion of explosive forming on cylinder lateral surface, the quantity of mounting base according to
Specific works require to be determined.
5) it finishes, cydariform cylinder is detached from from molding die, then machine finishing is until finished product.Finishing includes
Thin turner sequence, smart car process and right boring process；Thin turner sequence: carrying out the reparation of datum level using NC vertical lathe first, should
Datum level is the large end face of cylinder, and thin vehicle large end face is to single-sided process surplus on the basis of datum level, then using large end face as base
Quasi- thin vehicle small end face, then thin vehicle cylinder big end and its inner hole, then thin vehicle cylinder small end and its inner hole, on the outside of last thin vehicle cylinder
Mounting base on face, smart car process: then smart car cylinder big end end face, small end end face and interior lumen type face, then smart car mounting base exist
Mounting hole is bored in mounting base；Right boring process: right boring cylinder big end inner hole and small end inner hole.It is carried out at deburring after the completion of finishing
Reason examines storage after washing.
Claims (6)
1. a kind of processing method of aero-engine casing, characterized by the following steps:
1) designed according to welding deformation trend and deflection and make process allowance big end installation while and small end install while；
2) fanning strip is rolled into cylinder, which is in hollow round table shape, passes through solder joint；
3) by big end install while and small end install while be respectively welded in cylinder both ends；
4) explosive forming, the type that cylinder is placed in molding die is intracavitary, will ignite part and is arranged in the geometric center point of cylinder,
Ignition and blasting part, an explosive forming, obtained cylinder are in cydariform；
5) it finishes, cydariform cylinder is detached from from molding die, then machine finishing is until finished product.
2. the processing method of aero-engine casing according to claim 1, it is characterised in that: the material of the cylinder is
Titanium alloy.
3. the processing method of aero-engine casing according to claim 1, it is characterised in that: big end in the step 1)
Install while and small end install while manufacturing method be hot rolling.
4. the processing method of aero-engine casing according to claim 1, it is characterised in that: in the cylinder of explosive forming
Lateral surface is equipped with multiple mounting bases.
5. the processing method of aero-engine casing according to claim 1, it is characterised in that: the cylinder explosive forming
Before preheated, preheating temperature be 80 ~ 100 DEG C.
6. the processing method of aero-engine casing according to claim 1, it is characterised in that: the essence in the step 5)
Processing includes thin turner sequence, smart car process and right boring process；
Thin turner sequence: the reparation of datum level is carried out using NC vertical lathe first, which is the large end face of cylinder, with base
Thin vehicle large end face is to single-sided process surplus on the basis of quasi- face, then the thin vehicle small end face on the basis of large end face, then thin vehicle cylinder is big
End and its inner hole, then thin vehicle cylinder small end and its inner hole,
Smart car process: smart car cylinder big end end face, small end end face and interior lumen type face；
Right boring process: right boring cylinder big end inner hole and small end inner hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811488593.5A CN109604950A (en) | 2018-12-06 | 2018-12-06 | A kind of processing method of aero-engine casing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811488593.5A CN109604950A (en) | 2018-12-06 | 2018-12-06 | A kind of processing method of aero-engine casing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109604950A true CN109604950A (en) | 2019-04-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811488593.5A Pending CN109604950A (en) | 2018-12-06 | 2018-12-06 | A kind of processing method of aero-engine casing |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1454727A (en) * | 2003-05-21 | 2003-11-12 | 陈婉 | Shell one-time shaping |
| CA2603503A1 (en) * | 2006-10-02 | 2008-04-02 | Pratt & Whitney Canada Corp. | Annular gas turbine engine case and method of manufacturing |
| CN102319942A (en) * | 2011-09-05 | 2012-01-18 | 沈阳黎明航空发动机(集团)有限责任公司 | Titanium alloy welded case installation edge pre-deformation welding and micro forming method |
| CN102794610A (en) * | 2012-08-24 | 2012-11-28 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for processing thin wall welder cases of revolving body structures |
| CN107962354A (en) * | 2017-11-24 | 2018-04-27 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of processing technology of opposite opened casing |
| CN108480930A (en) * | 2018-04-11 | 2018-09-04 | 重庆天骄航空动力有限公司 | A kind of processing method of low-pressure compressor casing |
-
2018
- 2018-12-06 CN CN201811488593.5A patent/CN109604950A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1454727A (en) * | 2003-05-21 | 2003-11-12 | 陈婉 | Shell one-time shaping |
| CA2603503A1 (en) * | 2006-10-02 | 2008-04-02 | Pratt & Whitney Canada Corp. | Annular gas turbine engine case and method of manufacturing |
| CN102319942A (en) * | 2011-09-05 | 2012-01-18 | 沈阳黎明航空发动机(集团)有限责任公司 | Titanium alloy welded case installation edge pre-deformation welding and micro forming method |
| CN102794610A (en) * | 2012-08-24 | 2012-11-28 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for processing thin wall welder cases of revolving body structures |
| CN107962354A (en) * | 2017-11-24 | 2018-04-27 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of processing technology of opposite opened casing |
| CN108480930A (en) * | 2018-04-11 | 2018-09-04 | 重庆天骄航空动力有限公司 | A kind of processing method of low-pressure compressor casing |
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