CN102513587A - 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
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- CN102513587A CN102513587A CN2011104459554A CN201110445955A CN102513587A CN 102513587 A CN102513587 A CN 102513587A CN 2011104459554 A CN2011104459554 A CN 2011104459554A CN 201110445955 A CN201110445955 A CN 201110445955A CN 102513587 A CN102513587 A CN 102513587A
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- guide vane
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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 the 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 the blade of aviation engine manufacture field, because the shape of the blade profile (blade) of blade and tenon is different, the processing method that relates to has a lot, reaches 20 dark narrow groove but on the vane foil edge, mill the processing depth-to-width ratio, still is a new problem in the blade processing field.Certain model aero-engine need be processed the flat groove of long 470mm at a wide 2mm, dark 40mm and penetrating blade air inlet lateral lobe type edge according to the designing requirement on its overall structure on the blade profile edge of low-pressure admission guide vane air inlet one side.This flat groove forms passage in the associated baffle plate riveted joint of blade back.The processing of this flat groove, the method for prior art be two ends through frock clamp clamping blade with vanes fixed on the milling machine table face, adopt a kind of milling cutter of edge structure to accomplish whole processing of flat groove.This processing method of prior art, because the Inlet Guide Vane blade profile thickness is limited, the flat groove of processing has deflection slightly in the process in the middle of the blade profile edge of guide vane air inlet one side, will blade be milled and wear, and causes part to be scrapped.The processing method of the flat groove of Inlet Guide Vane leading edge of prior art, the part processing qualification rate is very low, only has 50%.Cause the low reason of passing rate of processing to mainly contain the following aspects: the one, the flat groove of blade is narrow and dark, is difficult for chip removal, the folder cutter occurs and forges a knife with existing one-shot forming milling cutter handling ease, 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, install with process in part be prone to deform and tremble, cause and mill partially and forge a knife, thereby cause part to scrap; It three is, because the allowance on the whole depth of rebate has 40-23.2mm (the two ends surplus is big, and intermediate host groove surplus is little), the parameter selection of the depth of cut and feed is bad, and it is too big to cause notch to dehisce easily, 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, and is tall and big more than 50%, causes wide variety of materials, equipment, work waste, and the 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 solved.
Summary of the invention
Deficiency to the flat groove processing method existence of the aero-engine low-pressure admission guide vane leading edge of prior art; The object of the invention aims to provide a kind of high flat groove processing method of aero-engine low-pressure admission guide vane leading edge of power 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 be accomplished through 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) with the middle blade profile part at the two ends and the blade basin back side of frock clamp clamping blade, with vanes fixed on the milling machine table face;
(2) earlier strengthen chip pocket with being provided with, by main sword be positioned at that face and side cutter that the secondary sword of main sword both sides constitutes is slotted and the roughing of main processing capacity; Use the arcuate blade milling cutter that is complementary with the bottom land arc to carry out the processing of surplus finish-milling afterwards again, flat groove is machined to design size and shape
(3) be not more than 3mm with the slot processing capacity of the rough machined feed first time of face and side cutter, the allowance of all the other feeds each time is not more than 6mm, and the processing capacity that carries out surplus fine finishining one-pass with the arcuate blade milling cutter is not more than 3.5mm.
The further technical scheme of the present invention, flat groove are milled the milling speed-controllable of processing built in 20～40mm/min scope, preferably are 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 increases, until the processing capacity of conventional one-pass one by one.
The further technical scheme of the present invention, the most handy face and side cutter roughing is to the degree of depth that is not more than 3.5mm apart from groove projected depth surplus, and promptly accurately machined surplus is controlled at and is not more than 3.5mm, accomplishes the fine finishining of flat groove through one-pass.
The further technical scheme of the present invention preferably grips the middle blade profile part in the blade two ends and the blade basin back side with the frock clamp that is connected as one.
The flat groove processing method of aero-engine low-pressure admission guide vane leading edge provided by the invention, be the inventor having carried out lot of test and bold exploration, constantly improve processing technology scheme, frock clamp and machined parameters, just be accomplished at last.Processing method of the present invention; With changing milling cutter machine-shaping into a kind of milling cutter machine-shaping of sword type originally with two kinds of sword types; The roughing of main processing capacity is accomplished with specially designed face and side cutter; Surplus uses the arcuate blade milling cutter finish-milling that is complementary with the bottom land arc to machine again, has solved the folder cutter in the prior art process and the problem of forging a knife.Blade grips the middle blade profile part in the blade two ends and the blade basin back side with the frock clamp that is connected as one; Increasing by three places at the vane foil basin back of the body compresses a little; With vanes fixed on the milling machine table face; It is not straight to have solved the air inlet one lateral edges bending that is caused by the distortion that produces in the blade processing process, and buffeting of vane causes in the process problem such as forge a knife.Feed working process parameter in the process of exploring in conjunction with the present invention; Captured the difficult problem of the flat groove processing of aero-engine low-pressure admission guide vane leading edge; The blade processing qualification rate brings up to 90% by original 50%; Obtained improving greatly, avoided a large amount of wastes such as material, equipment, work, greatly reduced the processing of leaves manufacturing cost.
Of the present invention research successfully; It is breakthrough to the narrow deep trouth technology of processing on the 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 not more than 5mm, depth-to-width ratio greater than 10 narrow deep trouth adaptable across processing groove width on other part.
The specific embodiment
Below through embodiment the present invention is further specifically described.Be necessary to be pointed out that at this; Embodiment only is used for the present invention is done further explanation; Can not be interpreted as restriction to protection domain of the present invention; Affiliated art skilled person according to the invention described above content the present invention is made some nonessential improvement and practical implementation is carried out in adjustment, 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 the whole depth of rebate has 40-23.2mm (the two ends surplus is big, and intermediate host groove surplus is little).
Processing technology is following;
(1) use to be coupled to each other and be the two ends of the frock clamp clamping blade of one and the middle blade profile part at the blade basin back side, with vanes fixed on the milling machine table face;
(2) earlier strengthen chip pocket with being provided with, 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 constitutes; The roughing of fluting with the main processing capacity of integral channel is carried out in feed for 5 times then; Be machined to the degree of depth of main body groove depth 20.mm; Use the arcuate blade milling cutter feed that is complementary with the bottom land arc once to carry out the processing of surplus finish-milling again, flat groove is machined to design size and shape;
(3) be provided with big chip pocket, by main sword be positioned at face and side cutter that the secondary sword of main sword both sides the constitutes rough machined technological parameter of slotting and be controlled to be: the body groove rough machined feed first time depth of cut of slotting is 2mm; The depth of cut of feed for the second time is 4mm; The feed depth of cut for the third time is 5mm; The depth of cut of the 4th feed is 5mm, and the 5th time the feed depth of cut is 4mm; Use the arcuate blade milling cutter feed that is complementary with the bottom land arc once to 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. flat groove processing method of aero-engine low-pressure admission guide vane leading edge is characterized in that mainly comprising:
(1) with the middle blade profile part at the two ends and the blade basin back side of frock clamp clamping blade, with vanes fixed on the milling machine table face;
(2) earlier strengthen chip pocket with being provided with, by main sword be positioned at that face and side cutter that the secondary sword of main sword both sides constitutes is slotted and the roughing of main processing capacity; Use the arcuate blade milling cutter that is complementary with the bottom land arc to carry out the finish-milling processing of surplus afterwards again, flat groove is machined to design size and shape;
(3) be not more than 3mm with the slot processing capacity of the rough machined feed first time of face and side cutter, the allowance of all the other feeds each time is not more than 6mm, and the processing capacity that carries out surplus fine finishining one-pass with the 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 the milling speed controlling is 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 the milling speed controlling is at 28～32mm/min.
4. according to claim 1 or the flat groove processing method of 2 or 3 described aero-engine low-pressure admission guide vane leading edges, it is characterized in that increasing one by one, until the processing capacity of conventional one-pass with the face and side cutter rough machined one-pass processing capacity of slotting.
5. according to claim 1 or the flat groove processing method of 2 or 3 described aero-engine low-pressure admission guide vane leading edges, it is characterized in that with face and side cutter roughing to the degree of depth that is not more than 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 the degree of depth that is not more than 3.5mm apart from groove projected depth surplus.
7. according to claim 1 or the flat groove processing method of 2 or 3 described aero-engine low-pressure admission guide vane leading edges, it is characterized in that gripping the middle blade profile part in the blade two ends and the blade basin back side with the frock clamp that is 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 the blade two ends and the blade basin back side with the frock clamp that is 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 the blade two ends and the blade basin back side with the frock clamp that is 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 the blade two ends and the blade basin back side with the frock clamp that is 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 |
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| Publication Number | Publication Date |
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| CN102513587A true CN102513587A (en) | 2012-06-27 |
| CN102513587B CN102513587B (en) | 2014-02-12 |
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| 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 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103357933A (en) * | 2013-03-15 | 2013-10-23 | 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 |
| CN103639494A (en) * | 2013-11-18 | 2014-03-19 | 四川成发航空科技股份有限公司 | Method used for processing aeroengine guide vane small lock plate |
| 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 |
| CN116587024A (en) * | 2023-07-17 | 2023-08-15 | 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)
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| 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 |
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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 |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103357933A (en) * | 2013-03-15 | 2013-10-23 | 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 |
| 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 |
| CN103639494A (en) * | 2013-11-18 | 2014-03-19 | 四川成发航空科技股份有限公司 | Method used for processing aeroengine guide vane small lock plate |
| 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 |
| CN116587024A (en) * | 2023-07-17 | 2023-08-15 | 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 |
| 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 |
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|---|---|
| CN102513587B (en) | 2014-02-12 |
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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. |