CN105328399B - A kind of processing method of Split Casing in Aeroengine class part - Google Patents
A kind of processing method of Split Casing in Aeroengine class part Download PDFInfo
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- CN105328399B CN105328399B CN201510772316.7A CN201510772316A CN105328399B CN 105328399 B CN105328399 B CN 105328399B CN 201510772316 A CN201510772316 A CN 201510772316A CN 105328399 B CN105328399 B CN 105328399B
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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
- B23P13/00—Making metal objects by operations essentially involving machining but not covered by a single other subclass
- B23P13/02—Making metal objects by operations essentially involving machining but not covered by a single other subclass in which only the machining operations are important
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Milling Processes (AREA)
- Forging (AREA)
Abstract
A kind of processing method of Split Casing in Aeroengine class part, step are：The longitudinally mounted side of milling, directly on part blank will installation in both sides end face, installation while faying face be machined to final form, reprocessing mounting hole to final form, now complete the one-stop processing of installation faying face and mounting hole in both sides end face, installation；Part installation side both sides end face complete maximum performance processing after, by the assembling parts of two halves state together；Part reference plane is processed by Milling Machining mode；Finishing processing is carried out to part inner mold face, selection disposably machines inner mold face, until meeting design size requirement；Finish-milling processing is carried out to part outer mold surface, until meeting design size requirement, then pore structure processing is completed, now completes the one-stop processing of outer mold surface, pore structure；Part in assembling volume morphing is split, then concentration removal is carried out to the manufacturing deficiency of part.This invention ensures that part crudy, shortens part process cycle.
Description
Technical field
The invention belongs to technical field of aircraft engine part manufacture, more particularly to a kind of aero-engine to start
The processing method of casket class part.
Background technology
At this stage, the cooked mode of Split Casing class part remains in " pancake formula ", i.e., is added by the reverse of part
Work ensures the base condition of part, to carry out the calculating of Reference Transforming and dimension chain in following process, so as to ensureing part
Final design requirement.
The processing method of traditional Split Casing class part is：Marking surplus → end face milling, faying face → driller's skill
Hole → → carries out part by two halves assembling parts together → the inside and outside type face of roughing (staying 2mm left right models face allowance)
Split → to part progress aging strengthening model → finish-milling faying face → grinding faying face (to 90% fitting) → brill, hinge mounting hole →
Again by two halves assembling parts together → the inside and outside type face of car benchmark → finishing (until reaching design requirement).
Traditional processing method is related to 10 Vehicle Processing processes, 21 Milling Machining processes, 7 disassembly processes, ground for 1 time altogether
Grinder sequence and some pincers repair process, and the processing especially in conjunction with face is, it is necessary to which reprocessabilty is multiple, and only guaranteed faying face is complete
Full fitting, just can guarantee that being smoothed out for subsequent processing operations, and the processing efficiency of faying face and crudy still influence zero
The key factor of part process-cycle.
Therefore, it is necessary to existing processing method is improved, will also maximum while part crudy is ensured
The process-cycle of the shortening part of degree.
The content of the invention
The problem of existing for prior art, the present invention provide a kind of processing side of Split Casing in Aeroengine class part
Method, ensure farthest shorten the process-cycle of part while part crudy.
To achieve these goals, the present invention adopts the following technical scheme that：A kind of Split Casing in Aeroengine class part
Processing method, comprise the following steps：
Step 1：The longitudinally mounted side of milling, directly when that will be installed on part blank in both sides end face, installation, faying face is processed
To final form, reprocessing mounting hole to final form, installation faying face and mounting hole in both sides end face, installation are now completed
One-stop processing；
Step 2：After completing maximum performance processing in part installation side both sides end face, will be in by screw, nut and pin
The assembling parts of two halves state are together；
Step 3：Part reference plane is processed by Milling Machining mode；
Step 4：Finishing processing is carried out to part inner mold face, until meeting design size requirement；
Step 5：Finish-milling processing is carried out to part outer mold surface, until meeting design size requirement, then pore structure is completed and adds
Work, now complete the one-stop processing of outer mold surface, pore structure；
Step 6：Part in assembling volume morphing is split, then concentration removal is carried out to the manufacturing deficiency of part.
When carrying out finishing processing to part inner mold face, selection disposably machines inner mold face.
Beneficial effects of the present invention：
The present invention successfully realizes to be merged to roughing with what is finished, forms " one-stop " cooked mode, and traditional
" pancake formula " cooked mode is compared, and farthest avoids the handling and turnover of part in process, only in turnover
Between on can save at least 48 hours, ensure part crudy while also farthest shorten part processing week
Phase, the overall production efficiency for lifting aero-engine, there is very positive facilitation.
Brief description of the drawings
Fig. 1 is final aspect graph at certain type Split Casing in Aeroengine class part faying face；
Fig. 2 is A-A sectional views in Fig. 1；
In figure, 1-faying face, 2-longitudinally mounted side, 3-mounting hole.
Embodiment
The present invention is described in further detail with specific embodiment below in conjunction with the accompanying drawings.
A kind of processing method of Split Casing in Aeroengine class part, comprises the following steps：
Step 1：The longitudinally mounted side of milling, directly when that will be installed on part blank in both sides end face, installation, faying face is processed
To final form, reprocessing mounting hole to final form, installation faying face and mounting hole in both sides end face, installation are now completed
One-stop processing；
Step 2：After completing maximum performance processing in part installation side both sides end face, will be in by screw, nut and pin
The assembling parts of two halves state are together；Compared with traditional diamond-making technique, due to being directly machined to installation side both sides end face most
End form state, the interference of screw, nut is effectively prevent, ensure that following process can be smoothed out；
Step 3：Part reference plane is processed by Milling Machining mode；Compared with traditional diamond-making technique, by traditional car benchmark
Mode is changed to milling benchmark mode, ensure that the processing of part and the uniformity used, and avoid because clamping is made repeatedly
Into dimensional tolerance loss；
Step 4：Finishing processing is carried out to part inner mold face, until meeting design size requirement, allowed in lathe processing equipment
In the case of, preferably disposably inner mold face is machined, can not only ensure the uniformity in part type face, can also effectively be met
Every design tolerance requirement of part；
Step 5：Finish-milling processing is carried out to part outer mold surface, until meeting design size requirement, then pore structure is completed and adds
Work, the one-stop processing of outer mold surface, pore structure is now completed, ensure that the uniformity of pore structure and part body tolerance；
Step 6：Part in assembling volume morphing is split, then concentration removal is carried out to the manufacturing deficiency of part, is dropped
Low part collides with because repeatedly transferring in week.
The present invention successfully realizes to be merged to roughing with what is finished, forms " one-stop " cooked mode, and traditional
" pancake formula " cooked mode is compared, and farthest avoids the handling and turnover of part in process, only in turnover
Between on can save at least 48 hours, the overall production efficiency for lifting aero-engine, there is very positive promotion to make
With.
Scheme in embodiment and the scope of patent protection for being not used to the limitation present invention, it is all without departing from carried out by the present invention etc.
Effect implements or change, is both contained in the scope of the claims of this case.
Claims (1)
1. a kind of processing method of Split Casing in Aeroengine class part, it is characterised in that comprise the following steps：
Step 1：The longitudinally mounted side of milling, directly when will be installed on part blank in both sides end face, installation, faying face is machined to most
End form state, reprocessing mounting hole to final form, now complete installation in both sides end face, installation faying face and mounting hole one
Standing posture is processed；
Step 2：To be in two halves by screw, nut and pin after completing maximum performance processing in part installation side both sides end face
The assembling parts of state are together；
Step 3：Part reference plane is processed by Milling Machining mode；
Step 4：Finishing processing is carried out to part inner mold face, until meeting design size requirement, and selected disposably by inner mold face
Machine；
Step 5：Finish-milling processing is carried out to part outer mold surface, until meeting design size requirement, then completes pore structure processing, this
When complete outer mold surface, pore structure one-stop processing；
Step 6：Part in assembling volume morphing is split, then concentration removal is carried out to the manufacturing deficiency of part.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510772316.7A CN105328399B (en) | 2015-11-11 | 2015-11-11 | A kind of processing method of Split Casing in Aeroengine class part |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510772316.7A CN105328399B (en) | 2015-11-11 | 2015-11-11 | A kind of processing method of Split Casing in Aeroengine class part |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105328399A CN105328399A (en) | 2016-02-17 |
| CN105328399B true CN105328399B (en) | 2018-01-16 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510772316.7A Active CN105328399B (en) | 2015-11-11 | 2015-11-11 | A kind of processing method of Split Casing in Aeroengine class part |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109551178A (en) * | 2018-11-28 | 2019-04-02 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of control method of Split Casing machining deformation |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109702430A (en) * | 2017-10-26 | 2019-05-03 | 沈阳黎明国际动力工业有限公司 | A kind of processing method that gas turbine improves machining accuracy and roughness with casing |
| CN113352051B (en) * | 2021-06-24 | 2023-03-28 | 中国民用航空飞行学院 | Piston type aeroengine casing joint surface repairing method |
| CN115178980B (en) * | 2022-08-04 | 2023-12-01 | 中国航发南方工业有限公司 | Guide vane casing machining method |
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| EP1651370A1 (en) * | 2003-07-30 | 2006-05-03 | ROLLS-ROYCE plc | Deformed forging |
| CN102248380A (en) * | 2011-07-04 | 2011-11-23 | 南京航空航天大学 | Method for processing integral casing of engine |
| CN103009003A (en) * | 2012-12-24 | 2013-04-03 | 潍坊盛瑞动力机械科技有限公司 | Machining process of flywheel shell |
| CN103286525A (en) * | 2012-03-02 | 2013-09-11 | 沈阳黎明航空发动机(集团)有限责任公司 | Numerical control machining method for large thin-walled split casing of die forging |
| CN103769816A (en) * | 2014-01-15 | 2014-05-07 | 西安航空动力股份有限公司 | Processing method for stop plate-free split casing |
-
2015
- 2015-11-11 CN CN201510772316.7A patent/CN105328399B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1651370A1 (en) * | 2003-07-30 | 2006-05-03 | ROLLS-ROYCE plc | Deformed forging |
| CN102248380A (en) * | 2011-07-04 | 2011-11-23 | 南京航空航天大学 | Method for processing integral casing of engine |
| CN103286525A (en) * | 2012-03-02 | 2013-09-11 | 沈阳黎明航空发动机(集团)有限责任公司 | Numerical control machining method for large thin-walled split casing of die forging |
| CN103009003A (en) * | 2012-12-24 | 2013-04-03 | 潍坊盛瑞动力机械科技有限公司 | Machining process of flywheel shell |
| CN103769816A (en) * | 2014-01-15 | 2014-05-07 | 西安航空动力股份有限公司 | Processing method for stop plate-free split casing |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109551178A (en) * | 2018-11-28 | 2019-04-02 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of control method of Split Casing machining deformation |
| CN109551178B (en) * | 2018-11-28 | 2020-10-16 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for controlling machining deformation of split case |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105328399A (en) | 2016-02-17 |
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Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee after: AECC SHENYANG LIMING AERO-ENGINE Co.,Ltd. Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee before: Aecc Shenyang Liming Aero Engine Co., Ltd. |
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Effective date of registration: 20180523 Address after: 110004 Hunnan New Road, Hunnan New District, Shenyang, Liaoning 15 Patentee after: SHENYANG LIMING INTERNATIONAL POWER INDUSTRY Co.,Ltd. Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee before: AECC SHENYANG LIMING AERO-ENGINE Co.,Ltd. |
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Effective date of registration: 20230410 Address after: 110043 Liaoning Province, Shenyang City District East Street No. 6 Patentee after: AECC SHENYANG LIMING AERO-ENGINE Co.,Ltd. Address before: 110004 Hunnan New Road, Hunnan New District, Shenyang, Liaoning 15 Patentee before: SHENYANG LIMING INTERNATIONAL POWER INDUSTRY Co.,Ltd. |