CN107088737A - A kind of manufacture method of the disc component of aircraft engine - Google Patents
A kind of manufacture method of the disc component of aircraft engine Download PDFInfo
- Publication number
- CN107088737A CN107088737A CN201610614583.6A CN201610614583A CN107088737A CN 107088737 A CN107088737 A CN 107088737A CN 201610614583 A CN201610614583 A CN 201610614583A CN 107088737 A CN107088737 A CN 107088737A
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- CN
- China
- Prior art keywords
- coating
- annular groove
- blank body
- disc component
- assembling
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- 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.)
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Classifications
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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
-
- 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
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/01—Aircraft parts
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
The present invention relates to technical field of aerospace, the manufacture method of the disc component of more particularly to a kind of aircraft engine.The manufacture method of the disc component of aircraft engine includes：Labyrinth gas sealses ring and the grafting of disc pedestal are assembled, the assembling blank body of the disc component is constituted；To the assembling blank body processing coating annular groove；To the coating annular groove spray-on coating；By pre-set dimension, the coating is ground.Pass through the application of this method, carried out so that being assembled into for the processing of coating annular groove, spray-on coating and grinding coating in labyrinth gas sealses ring and disc pedestal grafting on the basis of assembling blank body, this causes above-mentioned procedure of processing to assemble blank body as overall processing object and Set and Positioning benchmark.Therefore, the application of the application significantly improves the machining accuracy of the disc component of aircraft engine, reduces percent defective.
Description
Technical field
The present invention relates to technical field of aerospace, the manufacturer of the disc component of more particularly to a kind of aircraft engine
Method.
Background technology
Need to apply a variety of manufacture methods during manufacture aircraft engine, wherein, assemble aircraft engine in manufacture
Disc component process in need to be manufactured by the method such as being ground, at present, for manufacturing aircraft engine and getting rid of oil
The accuracy of manufacture of disk component, and the requirement more and more higher in terms of the durability of product, therefore, improve the accuracy of manufacture and product
Durability turns into design object.
In the prior art, in the disc component process of manufacture aircraft engine, by the list in disc component
Part is machined out, coating spraying, and the assembling manufacturing method such as assembling and grinding, final to obtain disc component, however, most
The uniformity that coating in the disc component obtained eventually is ground is low, the excessively thin configuration state of local coatings occurs, this is caused
The accuracy of manufacture is low, and then causes the high situation of disc component percent defective.
Above in the prior art, it is low for the accuracy of manufacture during disc component assembling manufacturing, and disc group
The high defect of part percent defective is those skilled in the art's technical issues that need to address.
The content of the invention
It is an object of the invention to provide a kind of manufacture method of the disc component of aircraft engine, pass through answering for the present invention
With the accuracy of manufacture during disc component assembling manufacturing will be significantly improved, while rate of reducing the number of rejects and seconds.
In order to solve the above technical problems, the present invention provides a kind of manufacture method of the disc component of aircraft engine, bag
Include：
Labyrinth gas sealses ring and the grafting of disc pedestal are assembled, the assembling blank body of the disc component is constituted；
To the assembling blank body processing coating annular groove；
To the coating annular groove spray-on coating；
By pre-set dimension, the coating is ground.
On the basis of the above method, alternatively, before the processing coating annular groove, in addition to：
To the assembling blank body destressing processing.
It is alternatively, described that coating annular groove is processed to the assembling blank body on the basis of the above method, be specially：
To the coating annular groove of the assembling blank body Machining Arc transition.
It is alternatively, described that coating annular groove is processed to the assembling blank body on the basis of the above method, be specially：
To the coating annular groove of the assembling blank body chamfering transition.
In the embodiment of a manufacture method on the disc component of aircraft engine, including by labyrinth gas sealses
Ring is assembled with the grafting of disc pedestal, connected overall structure has been assembled to form by grafting, i.e. constitute disc component
The labyrinth gas sealses ring assembled in blank body, assembling blank body not yet completes processing with disc pedestal；And then, to assembling blank body
Coating annular groove is processed, coating annular groove is located at the sidewall locations of labyrinth gas sealses ring, and process coating annular groove necessarily to assembling blank
The overall of body carries out clamping and positioning, thus, is located at though processing the coating groove structure obtained on labyrinth gas sealses ring, processing
Benchmark is to carry out positioning composition to assemble the overall of blank body；To coating annular groove spray-on coating；After the completion of coating spraying, press
Pre-set dimension, is ground coating.The grinding of coating, this enables the coating surface after grinding to carry out assembling patch with other mating surfaces
Close, and the positioning datum for being ground coating is also integrally to carry out Set and Positioning to assemble blank, this causes the painting that grinding is obtained
Layer dimensional accuracy is improved so that the uniformity of coating is improved.Thus, the system of the disc component of this aircraft engine
Manufacturing accuracy is significantly improved, while also reducing processing percent defective.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
There is the accompanying drawing used required in technology description to be briefly described, it should be apparent that, drawings in the following description are only this
The embodiment of invention, for those of ordinary skill in the art, on the premise of not paying creative work, can also basis
The accompanying drawing of offer obtains other accompanying drawings.
Fig. 1 is the schematic flow sheet of the embodiment of the present application one；
Fig. 2 is structural reference schematic diagram in the application；
Wherein, in Fig. 2：Labyrinth gas sealses ring -1, coating annular groove -11, disc pedestal -2.
Embodiment
The core of the present invention is to provide a kind of manufacture method of the disc component of aircraft engine, passes through answering for the present invention
With the accuracy of manufacture during disc component assembling manufacturing will be significantly improved, while rate of reducing the number of rejects and seconds.
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Site preparation is described, it is clear that described embodiment is only a part of embodiment of the invention, rather than whole embodiments.It is based on
Embodiment in the present invention, it is every other that those of ordinary skill in the art are obtained under the premise of creative work is not made
Embodiment, belongs to the scope of protection of the invention.
Fig. 1 and Fig. 2 are refer to, Fig. 1 is the schematic flow sheet of the embodiment of the present application one, and Fig. 2 is structural reference in the application
Schematic diagram.
According to figure, in embodiment one, the manufacture method of the disc component of aircraft engine includes：
S101, labyrinth gas sealses ring 1 and the grafting of disc pedestal 2 assembled, constitute the assembling blank body of disc component.
On the basis of the entirety of assembling blank body is as fixed structure, for adding for each parts in assembling blank body
Work is all processed equivalent to the entirety to assembling blank body, and this causes the physical dimension of processing and made with assembling the overall of blank body
On the basis of.
S102, to assembling blank body processing coating annular groove 11.
S103, to the spray-on coating of coating annular groove 11；
S104, by pre-set dimension, be ground coating.
S102 to S104 above procedure of processing is carried out after S101 steps, for overall technical architecture
In, the processing of coating annular groove 11 and grinding coating are just all that this makes to assemble the overall structure of blank body as processing object
Obtain the physical dimension obtained after the completion of coating grinding and disclosure satisfy that default size requirement, pre-set dimension here is assembling hair
The overall structure pre-set dimension of base substrate, i.e. for assembling blank body by pre-set dimension be ground coating after the completion of gained be just
Into the disc component of processing.
In the prior art, the processing for coating annular groove is carried out before assembly, and this will cause the size of coating annular groove
It is qualified be using labyrinth gas sealses ring as overall structure for, in the structure that labyrinth gas sealses ring and disc pedestal are assembled, because
The position deviation of assembling structure, or labyrinth gas sealses ring caused by the stress in assembling process are deformed upon, and these will all lead
Processed coating annular groove is caused to be located at beyond the tolerance of the overall assembling structure of disc component, that is to say, that coating annular groove
Size requirement can be met with the monomer structure of labyrinth gas sealses ring, and in the assembly structure of disc component is assembled into, is applied
Layer annular groove can not meet dimension precision requirement because of above-mentioned factor, and then, during coating spraying, this is with disc component
Assembling it is overall as positioning machining benchmark, the benchmark of coating annular groove processing and the difference of coating spraying benchmark result in coating
Spraying in coating annular groove is uneven, thus, by being ground after coating, and the uniformity of the coating finally obtained is low, or even goes out
The state that existing local coatings grinding disappears.Compared to prior art floating coat annular groove processing using labyrinth gas sealses ring monomer as adding
Work object and machining benchmark, and coating spraying and grinding are using disc component overall structure as processing object and processing base
Standard, so as to result in the uneven situation of coating, the method that the present embodiment is provided significantly improves disc component assembling manufacturing
During the accuracy of manufacture, while rate of reducing the number of rejects and seconds.
On the basis of above method embodiment, on the basis of assembling blank body assembling is completed, coating annular groove is being carried out
Before 11 processing, it can also set and destressing processing is carried out to assembling blank body.So-called destressing processing, typically application heating
The operation that is removed for the stress of metal inside of mode so that assembling blank can be avoided in structure each position point should
Force deformation.Be assembled into assembling blank body for labyrinth gas sealses ring 1 and the grafting of disc pedestal 2, typically by be interference fitted into
What row grafting was realized, in this assembling process, the generation of the inside configuration stress of plug-in position is easily caused, in this stress state
Under, the easily generation of progress following process is overproof in response to local size caused by force deformation, therefore, and one can be entered by destressing processing
Step improves the dimensional accuracy of the disc component finally obtained.
In another example, for the coating annular groove 11 processed on assembling blank body, coating annular groove is further limited as circle
Connected between the coating annular groove of arc transition, that is, trench bottom and the side wall of groove by arc transition, and be not right angle
The structure outline of section, this to carry out enabling to coating being attached to coating annular groove in spraying operation for coating annular groove 11
The coating structure of the arc transition section of 11 bottom land, side wall and side wall and bottom land can constitute smooth Bulk coat, and this makes
Obtaining coating has smooth attachment facial contour, and the globality and adhesive strength for coating attachment surface can be improved, this
Be for setting bottom land and being connected with side wall by right angle, if bottom land is connected with side wall by right angle profile, first,
In spraying process, the low situation of coating adhesive rate easily occurs for square position, and then, after spraying is finished, the inside attachment of coating
There is right angle flex point in face, the rupture that coating occurs easily at right angle corner is defeated and dispersed, and compared to this, this example passes through arc transition
The processing of coating annular groove, it is possible to increase the effect of coating spraying.Certainly, beyond arc transition, it may be arranged as processing and fall
The coating annular groove of angle transition, its process principle is consistent with the coating annular groove of above-mentioned arc transition.
The foregoing description of the disclosed embodiments, enables professional and technical personnel in the field to realize or using the present invention.
A variety of modifications to these embodiments will be apparent for those skilled in the art, as defined herein
General Principle can be realized in other embodiments without departing from the spirit or scope of the present invention.Therefore, it is of the invention
The embodiments shown herein is not intended to be limited to, and is to fit to and principles disclosed herein and features of novelty phase one
The most wide scope caused.
Claims (4)
1. a kind of manufacture method of the disc component of aircraft engine, it is characterised in that including：
Labyrinth gas sealses ring and the grafting of disc pedestal are assembled, the assembling blank body of the disc component is constituted；
To the assembling blank body processing coating annular groove；
To the coating annular groove spray-on coating；
By pre-set dimension, the coating is ground.
2. the manufacture method of the disc component of aircraft engine as claimed in claim 1, it is characterised in that in the processing
Before coating annular groove, in addition to：
To the assembling blank body destressing processing.
3. the manufacture method of the disc component of aircraft engine as claimed in claim 1, it is characterised in that described to described
Blank body processing coating annular groove is assembled, is specially：
To the coating annular groove of the assembling blank body Machining Arc transition.
4. the manufacture method of the disc component of aircraft engine as claimed in claim 1, it is characterised in that described to described
Blank body processing coating annular groove is assembled, is specially：
To the coating annular groove of the assembling blank body chamfering transition.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610614583.6A CN107088737A (en) | 2016-07-29 | 2016-07-29 | A kind of manufacture method of the disc component of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610614583.6A CN107088737A (en) | 2016-07-29 | 2016-07-29 | A kind of manufacture method of the disc component of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107088737A true CN107088737A (en) | 2017-08-25 |
Family
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610614583.6A Pending CN107088737A (en) | 2016-07-29 | 2016-07-29 | A kind of manufacture method of the disc component of aircraft engine |
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| Country | Link |
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| CN (1) | CN107088737A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0865877A2 (en) * | 1997-02-05 | 1998-09-23 | Toyoda Koki Kabushiki Kaisha | Grinding wheel |
| CN1296087A (en) * | 1999-11-17 | 2001-05-23 | 西北工业大学 | Method and technology for reinforcing surface of piston ring groove |
| CN104863894A (en) * | 2015-04-30 | 2015-08-26 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas compressor wheel disk and rotor |
| CN204637641U (en) * | 2015-04-13 | 2015-09-16 | 昆明理工大学 | A kind of labyrinth type hypergravity liquid-liquid extraction separator |
| CN105296878A (en) * | 2015-11-17 | 2016-02-03 | 中国兵器科学研究院宁波分院 | Surface alloy strengthening method of aluminum-based piston ring grooves |
-
2016
- 2016-07-29 CN CN201610614583.6A patent/CN107088737A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0865877A2 (en) * | 1997-02-05 | 1998-09-23 | Toyoda Koki Kabushiki Kaisha | Grinding wheel |
| CN1296087A (en) * | 1999-11-17 | 2001-05-23 | 西北工业大学 | Method and technology for reinforcing surface of piston ring groove |
| CN204637641U (en) * | 2015-04-13 | 2015-09-16 | 昆明理工大学 | A kind of labyrinth type hypergravity liquid-liquid extraction separator |
| CN104863894A (en) * | 2015-04-30 | 2015-08-26 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas compressor wheel disk and rotor |
| CN105296878A (en) * | 2015-11-17 | 2016-02-03 | 中国兵器科学研究院宁波分院 | Surface alloy strengthening method of aluminum-based piston ring grooves |
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| PB01 | Publication | ||
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Address after: 412000 No. 2 Airway Road, Lusong District, Zhuzhou City, Hunan Province Applicant after: Hunan Nanfang General Aviation Engine Co., Ltd. Address before: 412000 No. 2 Airway Road, Lusong District, Zhuzhou City, Hunan Province Applicant before: AVIC HUNAN GENERAL AVIATION ENGINE CO., LTD. |
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| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170825 |