CN104439945B - A kind of numerical-control processing method of aero-engine main injection jet class part - Google Patents
A kind of numerical-control processing method of aero-engine main injection jet class part Download PDFInfo
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- CN104439945B CN104439945B CN201410631634.7A CN201410631634A CN104439945B CN 104439945 B CN104439945 B CN 104439945B CN 201410631634 A CN201410631634 A CN 201410631634A CN 104439945 B CN104439945 B CN 104439945B
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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
- B23P15/008—Rocket engine parts, e.g. nozzles, combustion chambers
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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Abstract
The present invention relates to the numerical-control processing method of a kind of aero-engine main injection jet class part, described procedure is, by bar clamping on turn-milling complex machining center, utilize numerical-control processing method, it is processed according to following work step flow process: automatic charging, rough turn front end face, centering, boring, heavy boring endoporus, milling half slot, rough mill and cut line groove, rough turn rear end face, half finish turning rear end face, finish turning rear end face, half essence front end face, half right boring endoporus, finish-milling cuts line groove, finish turning front end face, car back chipping groove, right boring endoporus, dock and cut off, automatic discharging, Continuous maching goes out fabricated part.Advantages of the present invention: utilize digital control processing and emulation technology to carry out process optimization on turn-milling complex machining center, 8 procedures that technique after optimization is processed by former conventional equipment merge processing, change 1 procedure on turn-milling complex machining center into and machine.Through test and batch production checking, the part quality processed fully meets design requirement.
Description
Technical field
The processing method that the present invention relates to a kind of part, particularly to a kind of aero-engine main jet
The numerical-control processing method of mouth class part.
Background technology
Aero-engine main injection jet class design of part is complicated, machining accuracy and technical conditions requirement
Height, size is little, and having circumference uniform distribution at 8 is cutting line groove of 3 degree of inclinations, and its depth dimensions tolerance exists
In the range of 0.02, width requirement 0.04mm, is in place of on-the-spot processing difficulties is concentrated.This kind of part
Roughness requirements is the highest, it may be said that be the limit roughness requirements in turnery processing, original tradition
Processing technology is difficult to meet part requirements, has been used up in decades commonly adding with milling equipment
Work, owing to conventional equipment operation break-down is processed, uses fixture location, and part machining benchmark repeatedly becomes
Change, wherein positioning precision is substantially reduced, be cause part technical conditions defective one the heaviest
The reason wanted, secondly operation break-down processing makes the part process-cycle long, needs substantial amounts of special tooling,
The time of processing is 4 times of process time, the technology bottle in the always production of these factors
Neck.
Summary of the invention
The present invention provides the numerical-control processing method of a kind of aero-engine main injection jet class part, uses
Advanced turn-milling complex machining center, the method utilizing digital control processing, reasonably add by setting
Work scheme and technological parameter, solve the main injection jet class part process-cycle long, the problem that qualification rate is low.
Technical scheme is as follows:
Procedure described in the numerical-control processing method of a kind of aero-engine main injection jet class part is,
By bar clamping on turn-milling complex machining center, utilize numerical-control processing method, according to following work
Step flow process is processed: in automatic charging, rough turn front end face, centering, boring, heavy boring
Hole, milling half slot, rough mill cut line groove, rough turn rear end face, half finish turning rear end face, finish turning rear end
Face, half essence front end face, half right boring endoporus, finish-milling cut line groove, finish turning front end face, car back chipping groove,
Right boring endoporus, dock and cut off, automatic discharging, Continuous maching goes out fabricated part.
The numerical-control processing method of described aero-engine main injection jet class part, its preferred version
For, described part rear end face uses the mode of multiple cut, and uses reshaping cutter hub application numerical control
The anti-fine turning technique of lathe is processed.
The numerical-control processing method of described aero-engine main injection jet class part, its preferred version
For, described reshaping cutter hub forms for the conventional cutter hub transformation of the way, and routine cutter hub afterbody is truncated and processed
Wedgewise, processes a skewed slot, and processes one eight on cutter hub end face in cutter hub side
Font reference for installation.
The numerical-control processing method of described aero-engine main injection jet class part, its preferred version
For, described method is selected mechanical clamped cutting blade, to ensure Part Surface Roughness requirement.
Beneficial effects of the present invention: the technical method of the present invention is simple to operate, it is easy to accomplish,
Utilize digital control processing and emulation technology to carry out process optimization on turn-milling complex machining center, optimize
After 8 procedures processed by former conventional equipment of technique merge processing, change at turnning and milling multiple
Close 1 procedure on machining center to machine.Through test and batch production checking, zero processed
Part quality fully meets design requirement.The method can solve the problem that class part qualification rate, positioning precision
Low, operation is many, the problem of process-cycle length, uses numerical-control processing method so that adding of part
Work benchmark is combined into one, substantially increases the positioning precision of part, and time processing also improves life
Produce efficiency, on numerical control machining center, achieve the anti-fine turning technique of numerical control simultaneously and cut line groove automatically
Position milling technology practicality in spout processing, machining center can realize automatic charging technology.
The anti-fine turning technique of numerical control relies on reshaping cutter hub to realize, and the cutter after reshaping solves tool angle
Degree and lathe interference problem, disposably process back chipping groove, it is possible to meets the special of this part and wants
Ask.The machining accuracy utilizing numerical control device is that distribution of part dimension is concentrated, it is simple to later stage flow is adjusted
Examination.Owing to using the method to save a large amount of frock, save frock cost, so having weight
Big Social benefit and economic benefit.
Accompanying drawing explanation
Fig. 1 is main injection jet class part front view；
Fig. 2 is main injection jet class part side view；
Fig. 3 is conventional structure of the cutter body schematic diagram；
Fig. 4 is the structure of the cutter body schematic diagram after remodeling.
In figure: 1 for cutting line groove, 2 is front end face, and 3 is rear end face, and 4 is skewed slot, and 5 is peace
Dress benchmark.
Detailed description of the invention
As shown in Figure 1, Figure 2, Figure 4 shows, the numerical control of a kind of aero-engine main injection jet class part
Processing method, described procedure is, by bar clamping on turn-milling complex machining center, profit
With numerical-control processing method, it is processed according to following procedures flow process: automatic charging, rough turn front end
Face 2, centering, boring, heavy boring endoporus, milling half slot, rough mill cut line groove 1, rough turn
In rear end face 3, half finish turning rear end face 3, finish turning rear end face 3, half essence front end face 2, half right boring
Hole, finish-milling cut line groove 1, finish turning front end face 2, car back chipping groove, right boring endoporus, dock and cut
Disconnected, automatic discharging, Continuous maching goes out fabricated part；Described part rear end face 3 uses multitool to cut
The mode cut, and use the reshaping cutter hub anti-fine turning technique of application Digit Control Machine Tool to be processed；Described
Reshaping cutter hub forms for the conventional cutter hub transformation of the way, routine cutter hub afterbody is truncated and is processed into wedge shape,
Process a skewed slot 4 in cutter hub side, and on cutter hub end face, process a splayed peace
Dress benchmark 5；Selecting mechanical clamped cutting blade in described method, model is VCGT110202IC907, with
Ensure that Part Surface Roughness meets technology requirement.
Claims (4)
1. the numerical-control processing method of an aero-engine main injection jet class part, it is characterised in that
Described procedure is, by bar clamping on turn-milling complex machining center, utilizes digital control processing
Method, is processed according to following work step flow process: automatic charging, rough turn front end face, hit the heart
Hole, boring, heavy boring endoporus, milling half slot, rough mill cut line groove, rough turn rear end face, half finish turning
Rear end face, finish turning rear end face, half essence front end face, half right boring endoporus, finish-milling cut line groove, finish turning
Front end face, car back chipping groove, right boring endoporus, dock and cut off, automatic discharging, Continuous maching goes out
Fabricated part.
The digital control processing side of aero-engine main injection jet class part the most according to claim 1
Method, it is characterised in that described part rear end face uses the mode of multiple cut, and uses reshaping
The anti-fine turning technique of cutter hub application Digit Control Machine Tool is processed.
The digital control processing side of aero-engine main injection jet class part the most according to claim 2
Method, it is characterised in that described reshaping cutter hub forms, by routine cutter hub tail for the conventional cutter hub transformation of the way
Portion truncates and is processed into wedge shape, processes a skewed slot in cutter hub side, and on cutter hub end face
Process a splayed reference for installation.
The digital control processing side of aero-engine main injection jet class part the most according to claim 1
Method, it is characterised in that select mechanical clamped cutting blade in described method, to ensure Part Surface Roughness
Requirement.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410631634.7A CN104439945B (en) | 2014-11-11 | 2014-11-11 | A kind of numerical-control processing method of aero-engine main injection jet class part |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410631634.7A CN104439945B (en) | 2014-11-11 | 2014-11-11 | A kind of numerical-control processing method of aero-engine main injection jet class part |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104439945A CN104439945A (en) | 2015-03-25 |
| CN104439945B true CN104439945B (en) | 2016-08-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410631634.7A Expired - Fee Related CN104439945B (en) | 2014-11-11 | 2014-11-11 | A kind of numerical-control processing method of aero-engine main injection jet class part |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105710606A (en) * | 2015-11-25 | 2016-06-29 | 沈阳黎明航空发动机(集团)有限责任公司 | Machining method of gas generator nozzle head |
| CN110961663A (en) * | 2019-11-22 | 2020-04-07 | 辽宁程瑞砂轮有限公司 | Aperture turning tool for grinding wheel finish machining and machining method thereof |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ES2261667T3 (en) * | 2001-01-11 | 2006-11-16 | Volvo Aero Corporation | OUTPUT NOZZLE AND MANUFACTURING PROCEDURE OF THE SAME. |
| CN201143565Y (en) * | 2007-11-09 | 2008-11-05 | 杨向东 | Digital control vertical type pipe pile end plate lathe |
| CN201684936U (en) * | 2010-05-13 | 2010-12-29 | 湖南天能电机制造有限公司 | Tailored reverse turning tool |
| CN102528386B (en) * | 2010-12-30 | 2013-11-27 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for processing nozzle shell by using bar stock |
| CN102806443B (en) * | 2012-08-14 | 2014-04-16 | 沈阳黎明航空发动机(集团)有限责任公司 | Numerically-controlled processing method of nozzle housing piece |
| CN103111814A (en) * | 2013-01-05 | 2013-05-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Numerical control machining method of aero-engine disc-shaft integrated structure part |
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Address after: 110043 Liaoning Province, Shenyang City District East Street No. 6 Patentee after: Chinese Hangfa Shenyang Liming Aero engine limited liability company Address before: 110043 Liaoning Province, Shenyang City District East Street No. 6 Patentee before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160824 Termination date: 20201111 |
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| CF01 | Termination of patent right due to non-payment of annual fee |