CN102513587B - Method for machining flat groove on front edge of low-pressure air intake guide blade of aeroengine - Google Patents
Method for machining flat groove on front edge of low-pressure air intake guide blade of aeroengine Download PDFInfo
- Publication number
- CN102513587B CN102513587B CN201110445955.4A CN201110445955A CN102513587B CN 102513587 B CN102513587 B CN 102513587B CN 201110445955 A CN201110445955 A CN 201110445955A CN 102513587 B CN102513587 B CN 102513587B
- Authority
- CN
- China
- Prior art keywords
- blade
- flat groove
- aero
- guide vane
- leading edge
- Prior art date
- 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.)
- Active
Links
Landscapes
- Milling Processes (AREA)
Abstract
The invention discloses a method for machining a flat groove on the front edge of a low-pressure air intake guide blade of an aeroengine, which mainly comprises: clamping the two ends of a blade and the middle blade profile part on the back of a blade basin by using a tool clamp, and fixing the blade on the working table of a miller; and coarsely grooving and completing main machining amount by using a side and face milling cutter, finely milling the residual amount by using an arc-shaped milling cutter matched with the arc shape at the bottom of the groove, and machining the flat groove by designed size and shape. The machining method disclosed by the invention solves the problems of cutter clamping, blade breaking, blade through milling and high rejection rate of the machining of the flat groove on the front edge of the low-pressure air intake guide blade of the aeroengine in the prior art, increases the low-pressure air intake guide blade machining rate to 90 percent from the original 50 percent, and greatly reduce the machining and manufacturing cost of the blade.
Description
Technical field
The present invention relates to blade of aviation engine processing method, more specifically, relate to the processing method of the flat groove of aero-engine low-pressure admission guide vane leading edge.
Background technology
At blade of aviation engine manufacture field, because the blade profile (blade) of blade is different with the shape of tenon, the processing method relating to has a lot, but milling processing depth-to-width ratio reaches 20 dark narrow groove on vane foil edge, in blade processing field or a new problem.Certain model aero-engine, according to the designing requirement in its overall structure, need to be processed the flat groove of long 470mm at a wide 2mm, dark 40mm penetrating blade air inlet lateral lobe type edge on the blade profile edge of low-pressure admission guide vane air inlet one side.This flat groove forms passage after the associated baffle plate riveted joint of blade.The processing of this flat groove, the method for prior art is that the two ends that clamp blade by frock clamp are fixed on blade on milling machine table face, adopts a kind of milling cutter of edge structure to complete whole processing of flat groove.This processing method of prior art, because Inlet Guide Vane blade profile thickness is limited, the flat groove of processing in the middle of the blade profile edge of guide vane air inlet one side, deflection slightly in process, will wear blade milling, causes part to be scrapped.The processing method of the flat groove of Inlet Guide Vane leading edge of prior art, part passing rate of processing is very low, only has 50%.Cause the reason that passing rate of processing is low to mainly contain the following aspects: the one, the flat groove of blade is narrow and dark, is difficult for chip removal, by existing one-shot forming milling cutter handling ease, occurs folder cutter and forges a knife, and causes part to scrap; The 2nd, the flat notch of blade is opened and is positioned at air inlet one lateral edges, and accessory size is long, rigidity is low, and in installation and process, part easily deforms and trembles, and causes milling partially and forges a knife, thereby causing part to scrap; It three is that, because the allowance on whole depth of rebate has 40-23.2mm (two ends surplus is large, and intermediate host groove surplus is little), the parameter of the depth of cut and feed is selected bad, easily causes notch to dehisce too large, causes part to be scrapped.The processing of the flat groove of aero-engine low-pressure admission guide vane leading edge at present, the scrappage of workpiece is very high, tall and big more than 50%, causes a large amount of materials, equipment, work waste, and processing and manufacturing cost is multiplied.How solving the processing of the flat groove of low-pressure admission guide vane leading edge, improve the success rate of blade processing, is an aero-engine low-pressure admission guide vane manufacture field technical barrier anxious to be resolved.
Summary of the invention
The deficiency existing for the flat groove processing method of the aero-engine low-pressure admission guide vane leading edge of prior art, object of the present invention aims to provide a kind of flat groove processing method of aero-engine low-pressure admission guide vane leading edge that power is high that is processed into, to solve the low problem of aero-engine low-pressure admission guide vane leading edge flat groove converted products qualification rate.
The problems referred to above to be solved by this invention, can complete by the flat groove processing method of aero-engine low-pressure admission guide vane leading edge of following technical proposals.
The flat groove processing method of aero-engine low-pressure admission guide vane leading edge provided by the invention, its main contents comprise:
(1) by the frock clamp clamping two ends of blade and the middle blade profile part at the blade basin back side, blade is fixed on milling machine table face;
(2) first with being provided with, strengthen chip pocket, by main sword be positioned at that face and side cutter that the secondary sword of main sword both sides forms is slotted and the roughing of main processing capacity, use again afterwards the arcuate blade milling cutter matching with bottom land arc to carry out the processing of surplus finish-milling, flat groove is machined to design size and shape
(3) with the processing capacity of the rough machined feed for the first time of face and side cutter fluting, be not more than 3mm, the allowance of all the other feeds is each time not more than 6mm, and the processing capacity that carries out surplus fine finishining one-pass with arcuate blade milling cutter is not more than 3.5mm.
The further technical scheme of the present invention, the Milling Speed of flat groove milling processing can be controlled in 20～40mm/min scope, is preferably controlled at 28～32mm/min scope.
The further technical scheme of the present invention, with the face and side cutter rough machined one-pass processing capacity of slotting, preferably successively increases, until the processing capacity of conventional one-pass.
The further technical scheme of the present invention, the most handy face and side cutter roughing is to being not more than the degree of depth of 3.5mm apart from groove projected depth surplus, and accurately machined surplus is controlled at and is not more than 3.5mm, completes the fine finishining of flat groove by one-pass.
The further technical scheme of the present invention, preferably grips the middle blade profile part in blade two ends and the blade basin back side with the frock clamp being connected as one.
The flat groove processing method of aero-engine low-pressure admission guide vane leading edge provided by the invention, is that inventor is carrying out a large amount of tests and bold exploration, and constantly processing technology scheme, frock clamp and machined parameters, be finally just accomplished.Processing method of the present invention, change the milling cutter machine-shaping by a kind of sword type originally into milling cutter machine-shaping by two kinds of sword types, the roughing of main processing capacity completes with specially designed face and side cutter, surplus uses the arcuate blade milling cutter finish-milling matching with bottom land arc to machine again, has solved the folder cutter in prior art process and the problem of forging a knife.Blade grips the middle blade profile part in blade two ends and the blade basin back side with the frock clamp being connected as one, at the vane foil basin back of the body, increase by three places and compress point, blade is fixed on milling machine table face, solved the air inlet one lateral edges bending that the distortion that produces causes not straight in blade processing process, and the problem such as forging a knife of causing of process Leaf vibration.Feed working process parameter in the process of exploring in conjunction with the present invention, captured a difficult problem for the flat groove processing of aero-engine low-pressure admission guide vane leading edge, blade processing qualification rate brings up to 90% by original 50%, obtained greatly improving, avoid a large amount of wastes such as material, equipment, work, greatly reduced the processing and manufacturing cost of blade.
Of the present invention research successfully, to processing the breakthrough of narrow deep trouth technology on blade parts side, for the processing of the flat groove of aero-engine low-pressure admission guide vane leading edge provides a kind of effective ways, also can be widely used in processing groove width and be not more than the narrow deep trouth that 5mm, depth-to-width ratio are greater than 10 on other part.
The specific embodiment
By the following examples the present invention is further described specifically.Be necessary to be pointed out that at this; embodiment is only for the present invention is described further; can not be interpreted as limiting the scope of the invention; affiliated art skilled person, according to the invention described above content, the present invention is made to some nonessential improvement and adjustment is specifically implemented; be not a difficult problem, but such specific embodiment should still belong to protection scope of the present invention.
Embodiment 1
The object of processing is the narrow and dark flat groove on certain model aero-engine low-pressure admission guide vane air inlet one lateral lobe type edge, the wide 2mm of flat groove, dark 40mm, long 470mm, flat groove penetrating blade air inlet one lateral lobe type edge, allowance on whole depth of rebate has 40-23.2mm (two ends surplus is large, and intermediate host groove surplus is little).
Processing technology is as follows;
(1) with being coupled to each other the frock clamp clamping two ends of blade and the middle blade profile part at the blade basin back side being integrated, blade is fixed on milling machine table face;
(2) first with being provided with, strengthen chip pocket, by main sword be positioned at the two ends of the face and side cutter working groove that the secondary sword of main sword both sides forms, then the roughing of fluting and the main processing capacity of integral channel is carried out in feed for 5 times, be machined to the degree of depth of main body groove depth 20.mm, use again the arcuate blade milling cutter feed matching with bottom land arc once to carry out the processing of surplus finish-milling, flat groove is machined to design size and shape;
(3) with being provided with large chip pocket, by main sword be positioned at face and side cutter that the secondary sword of main sword both sides the forms rough machined process parameter control of slotting and be: the rough machined feed depth of cut for the first time of body groove fluting is 2mm, the feed depth of cut is for the second time 4mm, the feed depth of cut is for the third time 5mm, the depth of cut of the 4th feed is 5mm, and the 5th time the feed depth of cut is 4mm; With the arcuate blade milling cutter feed matching with bottom land arc, once carry out the processing of surplus finish-milling, chipping allowance is 3.2mm.The Milling Speed of milling cutter is 30mm/min.
Claims (10)
1. the flat groove processing method of aero-engine low-pressure admission guide vane leading edge, is characterized in that mainly comprising:
(1) by the frock clamp clamping two ends of blade and the middle blade profile part at the blade basin back side, blade is fixed on milling machine table face;
(2) first with being provided with, strengthen chip pocket, by main sword be positioned at that face and side cutter that the secondary sword of main sword both sides forms is slotted and the roughing of main processing capacity, use again afterwards the arcuate blade milling cutter matching with bottom land arc to carry out the finish-milling processing of surplus, flat groove is machined to design size and shape;
(3) with the processing capacity of the rough machined feed for the first time of face and side cutter fluting, be not more than 3mm, the allowance of all the other feeds is each time not more than 6mm, and the processing capacity that carries out surplus fine finishining one-pass with arcuate blade milling cutter is not more than 3.5mm.
2. the flat groove processing method of aero-engine low-pressure admission guide vane leading edge according to claim 1, is characterized in that Milling Speed is controlled at 20～40mm/min.
3. the flat groove processing method of aero-engine low-pressure admission guide vane leading edge according to claim 2, is characterized in that Milling Speed is controlled at 28～32mm/min.
4. according to the flat groove processing method of aero-engine low-pressure admission guide vane leading edge described in claim 1 or 2 or 3, it is characterized in that successively increasing with the face and side cutter rough machined one-pass processing capacity of slotting, until the processing capacity of conventional one-pass.
5. according to the flat groove processing method of aero-engine low-pressure admission guide vane leading edge described in claim 1 or 2 or 3, it is characterized in that with face and side cutter roughing to be not more than the degree of depth of 3.5mm apart from groove projected depth surplus.
6. the flat groove processing method of aero-engine low-pressure admission guide vane leading edge according to claim 4, is characterized in that with face and side cutter roughing to be not more than the degree of depth of 3.5mm apart from groove projected depth surplus.
7. according to the flat groove processing method of aero-engine low-pressure admission guide vane leading edge described in claim 1 or 2 or 3, it is characterized in that gripping the middle blade profile part in blade two ends and the blade basin back side with the frock clamp being connected as one.
8. the flat groove processing method of aero-engine low-pressure admission guide vane leading edge according to claim 4, is characterized in that gripping the middle blade profile part in blade two ends and the blade basin back side with the frock clamp being connected as one.
9. the flat groove processing method of aero-engine low-pressure admission guide vane leading edge according to claim 5, is characterized in that gripping the middle blade profile part in blade two ends and the blade basin back side with the frock clamp being connected as one.
10. the flat groove processing method of aero-engine low-pressure admission guide vane leading edge according to claim 6, is characterized in that gripping the middle blade profile part in blade two ends and the blade basin back side with the frock clamp being connected as one.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110445955.4A CN102513587B (en) | 2011-12-28 | 2011-12-28 | Method for machining flat groove on front edge of low-pressure air intake guide blade of aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110445955.4A CN102513587B (en) | 2011-12-28 | 2011-12-28 | Method for machining flat groove on front edge of low-pressure air intake guide blade of aeroengine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102513587A CN102513587A (en) | 2012-06-27 |
| CN102513587B true CN102513587B (en) | 2014-02-12 |
Family
ID=46284797
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201110445955.4A Active CN102513587B (en) | 2011-12-28 | 2011-12-28 | Method for machining flat groove on front edge of low-pressure air intake guide blade of aeroengine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102513587B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103357933B (en) * | 2013-03-15 | 2015-07-15 | 哈尔滨汽轮机厂有限责任公司 | Processing cutter and processing method for head and tail blade locking slots of diamond-shaped blade root of steam turbine blade |
| CN103659276A (en) * | 2013-11-08 | 2014-03-26 | 中航飞机股份有限公司西安飞机分公司 | Method for numerical control machining of titanium alloy part with deep groove structure |
| CN103639494B (en) * | 2013-11-18 | 2016-09-14 | 四川成发航空科技股份有限公司 | A kind of method processing the little jam plate of aero-engine guide vane |
| CN116587024B (en) * | 2023-07-17 | 2023-09-15 | 沈阳强航时代精密科技有限公司 | Self-adaptive clamp for production of aero-engine double-positioning reference table blade |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3859700A (en) * | 1974-05-07 | 1975-01-14 | Illinois Tool Works | Inserted blade cutter |
| DE3121005A1 (en) * | 1980-07-19 | 1982-12-16 | Bernhard 6259 Brechen Eisenbach | Milling apparatus |
| CN1136289A (en) * | 1993-09-29 | 1996-11-20 | 西门子公司 | Process for milling a turbine balde section extending along a main axis |
| CN101417396A (en) * | 2008-11-27 | 2009-04-29 | 西安交通大学 | Turbine hollow blade rabbet processing locating clamping method and device |
| CN201537822U (en) * | 2009-11-27 | 2010-08-04 | 中国北车集团大连机车研究所有限公司 | Turbocharger compressor impeller-type milling fixture |
-
2011
- 2011-12-28 CN CN201110445955.4A patent/CN102513587B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3859700A (en) * | 1974-05-07 | 1975-01-14 | Illinois Tool Works | Inserted blade cutter |
| DE3121005A1 (en) * | 1980-07-19 | 1982-12-16 | Bernhard 6259 Brechen Eisenbach | Milling apparatus |
| CN1136289A (en) * | 1993-09-29 | 1996-11-20 | 西门子公司 | Process for milling a turbine balde section extending along a main axis |
| CN101417396A (en) * | 2008-11-27 | 2009-04-29 | 西安交通大学 | Turbine hollow blade rabbet processing locating clamping method and device |
| CN201537822U (en) * | 2009-11-27 | 2010-08-04 | 中国北车集团大连机车研究所有限公司 | Turbocharger compressor impeller-type milling fixture |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102513587A (en) | 2012-06-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102513587B (en) | Method for machining flat groove on front edge of low-pressure air intake guide blade of aeroengine | |
| CN102101253B (en) | Special six-shaft multi-station integration grinding machine for double-edge blade | |
| CN202539594U (en) | Polycrystalline diamond combined tool for carbon electrode excircle machining | |
| CN102411334A (en) | Plunge milling cutter path optimization method | |
| CN108274023A (en) | A kind of wheel machine adds cutter | |
| CN209452823U (en) | A kind of compound billmpse tool | |
| CN105081471A (en) | Chamfer tool | |
| CN201960185U (en) | Rough and fine composite cutter | |
| CN105312645B (en) | The processing method of thin web plate titanium alloy edge strip | |
| CN206464597U (en) | A kind of new PCD milling cutters | |
| CN204276934U (en) | A kind of twolip turning insert | |
| CN202356643U (en) | Combined tool for processing O-ring grooves | |
| CN205733184U (en) | A kind of radial groove process tool | |
| CN2527381Y (en) | Large blade inclination angle high strength machine clamping knife | |
| CN202845889U (en) | T-shaped milling cutter | |
| CN204818256U (en) | Three surface broachs | |
| CN102528107A (en) | Machine clamping powerful cutter | |
| CN202861428U (en) | Parting-off lathe tool | |
| CN204639287U (en) | Edge planer knife rest frock | |
| CN205733030U (en) | A kind of hoop groove processing cutter | |
| CN202367437U (en) | Dual-purpose cutting tool for turning and cutting | |
| CN205888200U (en) | Can realize that no burr does not have milling cutter that chamfering slot mills | |
| CN202461565U (en) | Machine-clamped powerful cutter | |
| CN201493551U (en) | One-step forming broach for oil pipe wrench | |
| CN214977818U (en) | Double-edge crescent slotting cutter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: Xindu District of Chengdu city in Sichuan province 610503 Shulong avenue into the industrial park into the Group Technology Center Patentee after: China Hangfa aviation Polytron Technologies Inc Address before: Xindu District of Chengdu city in Sichuan province 610503 Shulong avenue into the industrial park into the Group Technology Center Patentee before: Sichuan Chengfa Aviation Science & Technology Co., Ltd. |
|
| CP01 | Change in the name or title of a patent holder |