CN104308481A - Stator blade machining method of aeroengine compressor without mounting plate - Google Patents

Stator blade machining method of aeroengine compressor without mounting plate Download PDF

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Publication number
CN104308481A
CN104308481A CN201410583311.5A CN201410583311A CN104308481A CN 104308481 A CN104308481 A CN 104308481A CN 201410583311 A CN201410583311 A CN 201410583311A CN 104308481 A CN104308481 A CN 104308481A
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CN
China
Prior art keywords
blade
false boss
boss
machining
root
Prior art date
Application number
CN201410583311.5A
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Chinese (zh)
Other versions
CN104308481B (en
Inventor
冯全全
马辉
赵赟
张新冬
雷海峰
秦仁章
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西安航空动力股份有限公司
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Application filed by 西安航空动力股份有限公司 filed Critical 西安航空动力股份有限公司
Priority to CN201410583311.5A priority Critical patent/CN104308481B/en
Publication of CN104308481A publication Critical patent/CN104308481A/en
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Publication of CN104308481B publication Critical patent/CN104308481B/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—OTHER WORKING OF METAL; 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
    • B23P15/02—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps

Abstract

Disclosed is a stator blade machining method of aeroengine compressor with a mounting plate. The stator blade machining method includes adopting a stator blade blank without a mounting plate of a finish forge workpiece, positioning, clamping and machining an air inlet side and an exhaust side on a numerical-control milling machine by a first technical boss, a second technical boss, the end face of the second technical boss and a basin side of a blade body; polishing the air inlet side and the exhaust side, and ensuring that the size and the shape of the air inlet side and the exhaust side conform to the design requirements; positioning, clamping and machining a blade tip and a blade root on a numerical wire-cut machine by the basin side of the blade, the first technical boss, the second technical boss and the end face of the second technical boss, and removing the first technical boss and the second technical boss; finishing the blade tip and the blade root by clamps and removing wire-cut remelting layers on the blade tip and the blade root. By adopting the finish-forging blank, profile tolerance and surface quality of the molded profile of the blade are guaranteed, and the machined blade conforms to the design requirement and is high in yield. The stator blade machining method is simple in machining process, machining efficiency is effectively improved and machining period is shortened.

Description

A kind of aero-engine is without installing plate compressor stator blade processing method

Technical field

The invention belongs to aero-engine compressor blade processing technology, relate to the improvement of aero-engine without installing plate compressor stator blade processing method, be specifically related to a kind of aero-engine without installing plate compressor stator blade processing method.

Background technology

Certain h type engine h compressor one is without installing plate stator blade structure see Fig. 1, and blade is made up of blade tip 1, blade 2, exhaust limit 3, blade root 4 and leading edge 5.Blade tip 1 is made up of three sections of curved surfaces, and blade root 4 is with step, and leading edge 5 is the molded line changed with exhaust limit 3.At present, the main method of processing without installing plate stator blade is: 1) adopt die forging blank or plate, first numerical control milling blade profile, then polishing blade profile, final cutting blade tip and blade root.The method need process blade profile, complex process, and working (machining) efficiency is low, and blade profile profile tolerance qualification rate is low; 2) adopt plate, first rolling blade profile, then cut off blade tip and blade root.The method complex process, working (machining) efficiency is low.

Summary of the invention

The object of this invention is to provide the processing method of a kind of aero-engine compressor without installing plate stator blade, to ensure blade profile profile tolerance, improve working (machining) efficiency, shorten the process-cycle.

For achieving the above object, the present invention adopts following technical scheme:

1) milling inlet and outlet limit: adopt fine forge piece as without installing plate stator blade blank, blank comprises blade, be positioned at the exhaust limit of blade side, be positioned at the leading edge of blade opposite side, be positioned at first false boss of blade one end and be positioned at the second false boss of the blade other end, wherein blade comprises blade tip and blade root, blade tip connects the first false boss, blade root fastenings second false boss, the second false boss end face is that sharf is to benchmark;

With the positioning and clamping processing gas inlet limit, basin side of the first false boss, the second false boss, the second false boss end face and blade and exhaust limit on CNC milling machine, leading edge stays 0.05mm ~ 0.15mm surplus with exhaust limit;

2) polishing inlet and outlet limit: polishing leading edge and exhaust limit, makes the size and dimension on leading edge and exhaust limit meet designing requirement;

3) Linear cut blade tip and blade root: with the basin side of blade, the first false boss, the second false boss and the second false boss end face positioning and clamping on numerically controlled wire cutting machine, processing blade tip and blade root, remove the first false boss and the second false boss;

4) pincers are repaiied: pincers repair blade tip and blade root, removal step 3) in be retained in Linear cut remelted layer on blade tip and blade root, and make the surface roughness of blade tip and blade root meet designing requirement.

The leading edge of described blank has 2mm ~ 3mm allowance with exhaust limit.

Described step 2) in polishing on polishing machine, adopt bob and nylon wheel to carry out.

Described step 4) employing file repaiied by middle pincers and sand paper carries out.

Compared with prior art, the beneficial effect that the present invention has: the invention proposes the improvement processing method of a kind of aero-engine without installing plate stator blade, repair by carrying out milling intake and exhaust limit, polishing intake and exhaust limit, Linear cut blade tip blade root and pincers to finish forge blank, processing obtains aero-engine without installing plate compressor stator blade.The present invention has the following advantages: 1) the method adopts finish forge blank, ensure that blade type profile tolerance of a surface and surface quality, makes the blade obtained meet designing requirement; Because blank adopts fine forge piece, so make the qualification rate of obtained blade high, overcome the working (machining) efficiency that causes owing to adopting die forging blank or plate in prior art and the low problem of qualification rate; 2) method work flow provided by the invention is simple, effectively improves working (machining) efficiency, shortens the process-cycle.

Accompanying drawing explanation

Fig. 1 is that certain h type engine h compressor is a kind of without installing plate stator blade structural representation;

Fig. 2 is that certain h type engine h compressor is a kind of without installing plate stator blade blank schematic diagram;

Fig. 3 be the second false boss along A-A in Fig. 2 to sectional view.

In figure, 1 is blade tip, and 2 is blade, and 3 is exhaust limit, and 4 is blade root, and 5 is leading edge, and 6 is the first false boss, and 7 is the second false boss, and 8 is the second false boss end face.

Detailed description of the invention

Below in conjunction with accompanying drawing, the present invention is described in detail.

Aero-engine of the present invention is fine forge piece without the blank of installing plate stator blade, blahk structure is see Fig. 2 and Fig. 3, blank comprises blade 2, be positioned at the exhaust limit 3 of blade 2 side, be positioned at the leading edge 5 of blade 2 opposite side, be positioned at first false boss 6 of blade 2 one end and be positioned at the second false boss 7 of blade 2 other end, wherein blade 2 comprises blade tip 1 and blade root 4, blade tip 1 connects the first false boss 6, blade root 4 connects the second false boss 7, blade 2 does not have surplus, leading edge 5 has 2mm ~ 3mm allowance with exhaust limit 3, second false boss end face 8 is that sharf is to benchmark, its procedure of processing is:

1) milling inlet and outlet limit: with the positioning and clamping processing gas inlet limit, basin side 5 of the first false boss 6, second false boss 7, second false boss end face 8 and blade 2 and exhaust limit 3 on CNC milling machine, leading edge 5 stays 0.05mm ~ 0.15mm surplus with exhaust limit 3.

2) polishing inlet and outlet limit: use bob and nylon wheel polishing leading edge 5 and be vented limit 3 on polishing machine, ensures that leading edge 5 meets designing requirement with the size and dimension being vented limit 3.

3) Linear cut blade tip and blade root: with the basin side of blade 2, the first false boss 6, second false boss 7 and the second false boss end face 8 positioning and clamping on numerically controlled wire cutting machine, processing blade tip 1 and blade root 4, remove the first false boss 6 and the second false boss 7.

4) pincers are repaiied: clamp with file and sand paper and repair blade tip 1 and blade root 4, removal step 3) in be retained in Linear cut remelted layer on blade tip 1 and blade root 4, and ensure that the surface roughness of blade tip 1 and blade root 4 meets designing requirement.

Claims (4)

1. aero-engine is without an installing plate compressor stator blade processing method, it is characterized in that, comprises the following steps:
1) milling is entered, exhaust limit: adopt fine forge piece as without installing plate stator blade blank, blank comprises blade (2), be positioned at the exhaust limit (3) of blade (2) side, be positioned at the leading edge (5) of blade (2) opposite side, be positioned at first false boss (6) of blade (2) one end and be positioned at second false boss (7) of blade (2) other end, wherein blade (2) comprises blade tip (1) and blade root (4), blade tip (1) connects the first false boss (6), blade root (4) connects the second false boss (7), second false boss end face (8) is for sharf is to benchmark,
With positioning and clamping processing gas inlet limit, the basin side (5) of the first false boss (6), the second false boss (7), the second false boss end face (8) and blade (2) and exhaust limit (3) on CNC milling machine, leading edge (5) stays 0.05mm ~ 0.15mm surplus with exhaust limit (3);
2) polishing inlet and outlet limit: polishing leading edge (5) and exhaust limit (3), makes the size and dimension of leading edge (5) and exhaust limit (3) meet designing requirement;
3) Linear cut blade tip and blade root: with the basin side of blade (2), the first false boss (6), the second false boss (7) and the second false boss end face (8) positioning and clamping on numerically controlled wire cutting machine, processing blade tip (1) and blade root (4), remove the first false boss (6) and the second false boss (7);
4) pincers are repaiied: pincers repair blade tip (1) and blade root (4), removal step 3) in be retained in Linear cut remelted layer on blade tip (1) and blade root (4), and make the surface roughness of blade tip (1) and blade root (4) meet designing requirement.
2. a kind of aero-engine according to claim 1 is without installing plate compressor stator blade processing method, it is characterized in that, the leading edge (5) of described blank has 2mm ~ 3mm allowance with exhaust limit (3).
3. a kind of aero-engine according to claim 1 is without installing plate compressor stator blade processing method, it is characterized in that, described step 2) in polishing on polishing machine, adopt bob and nylon wheel to carry out.
4. a kind of aero-engine according to claim 1 is without installing plate compressor stator blade processing method, it is characterized in that, described step 4) employing file repaiied by middle pincers and sand paper carries out.
CN201410583311.5A 2014-10-27 2014-10-27 Stator blade machining method of aeroengine compressor without mounting plate CN104308481B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201410583311.5A CN104308481B (en) 2014-10-27 2014-10-27 Stator blade machining method of aeroengine compressor without mounting plate

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Application Number Priority Date Filing Date Title
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CN104308481A true CN104308481A (en) 2015-01-28
CN104308481B CN104308481B (en) 2017-01-11

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Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105252224A (en) * 2015-11-19 2016-01-20 华中科技大学无锡研究院 Machining method of outer duct outlet guide vane of aero-engine
CN105252233A (en) * 2015-11-19 2016-01-20 华中科技大学无锡研究院 Machining method for aero-engine high-temperature alloy counterweight blade
CN106271469A (en) * 2016-08-29 2017-01-04 中航动力股份有限公司 A kind of processing method of elongated hollow many cavity thin-walls compressor blade
CN106354927A (en) * 2016-08-29 2017-01-25 西北工业大学 Construction method of optimization model for adaptive processing of front and rear edges of precisely-forged blade
CN107520716A (en) * 2017-08-02 2017-12-29 安吉圆磨机械科技有限公司 A kind of technique for grinding of centrifugal automobile wheel
CN107520674A (en) * 2017-08-02 2017-12-29 安吉圆磨机械科技有限公司 A kind of centrifugal wheel polishing process
CN107520672A (en) * 2017-08-02 2017-12-29 安吉圆磨机械科技有限公司 A kind of polishing process of centrifugal automobile wheel
CN107520673A (en) * 2017-08-02 2017-12-29 安吉圆磨机械科技有限公司 A kind of centrifugal wheel technique for grinding
CN107984179A (en) * 2017-11-22 2018-05-04 中国航发沈阳黎明航空发动机有限责任公司 A kind of quick method for preparing double installing plate blades
CN108145393A (en) * 2017-11-29 2018-06-12 株洲丰发精工实业有限公司 A kind of aero-engine compressor blade and its processing method
CN108500574A (en) * 2018-03-30 2018-09-07 广汉天空动力机械有限责任公司 A kind of process preparing aero-engine cyclone using special processing technology
CN108714770A (en) * 2018-05-30 2018-10-30 中国航发动力股份有限公司 A kind of method of engine rectification guide vane processing
CN108747232A (en) * 2018-05-30 2018-11-06 中国航发动力股份有限公司 A kind of finish forge stator blade automatization processing method
CN109365884A (en) * 2018-12-17 2019-02-22 中国航发动力股份有限公司 A kind of rotor blade tip cutting off processing method and its application
CN109531198A (en) * 2018-11-27 2019-03-29 中国航发沈阳黎明航空发动机有限责任公司 Improve the method and process area refine fixture of large and complex structure blade processing precision

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108714771A (en) * 2018-05-30 2018-10-30 中国航发动力股份有限公司 A kind of aero-engine compressor stator blade processing method and products thereof

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101363327A (en) * 2008-09-26 2009-02-11 无锡透平叶片有限公司 Method for processing TC11 material blade
CN102152071A (en) * 2011-02-18 2011-08-17 常州市风机制造有限公司 Processing technique of Roots blower impeller component
WO2012042164A2 (en) * 2010-09-30 2012-04-05 Snecma "multi-effect" forming tooling for high-temperature forming
CN102773733A (en) * 2012-07-18 2012-11-14 西安航空动力股份有限公司 Method and clamp for moulding surface positioning clamping of finish forge blade
CN102825436A (en) * 2012-10-08 2012-12-19 南通中能机械制造有限公司 Method for machining small moving blade of turbine
CN103286532A (en) * 2013-05-13 2013-09-11 沈阳黎明航空发动机(集团)有限责任公司 Technique for processing stator blades
CN103586647A (en) * 2013-10-14 2014-02-19 西安航空动力股份有限公司 Forming method of aeroengine hollow guide vane

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101363327A (en) * 2008-09-26 2009-02-11 无锡透平叶片有限公司 Method for processing TC11 material blade
WO2012042164A2 (en) * 2010-09-30 2012-04-05 Snecma "multi-effect" forming tooling for high-temperature forming
CN102152071A (en) * 2011-02-18 2011-08-17 常州市风机制造有限公司 Processing technique of Roots blower impeller component
CN102773733A (en) * 2012-07-18 2012-11-14 西安航空动力股份有限公司 Method and clamp for moulding surface positioning clamping of finish forge blade
CN102825436A (en) * 2012-10-08 2012-12-19 南通中能机械制造有限公司 Method for machining small moving blade of turbine
CN103286532A (en) * 2013-05-13 2013-09-11 沈阳黎明航空发动机(集团)有限责任公司 Technique for processing stator blades
CN103586647A (en) * 2013-10-14 2014-02-19 西安航空动力股份有限公司 Forming method of aeroengine hollow guide vane

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105252233A (en) * 2015-11-19 2016-01-20 华中科技大学无锡研究院 Machining method for aero-engine high-temperature alloy counterweight blade
CN105252224A (en) * 2015-11-19 2016-01-20 华中科技大学无锡研究院 Machining method of outer duct outlet guide vane of aero-engine
CN106354927B (en) * 2016-08-29 2019-05-10 西北工业大学 A kind of construction method of precision forged blade front and rear edge adaptive machining Optimized model
CN106271469A (en) * 2016-08-29 2017-01-04 中航动力股份有限公司 A kind of processing method of elongated hollow many cavity thin-walls compressor blade
CN106354927A (en) * 2016-08-29 2017-01-25 西北工业大学 Construction method of optimization model for adaptive processing of front and rear edges of precisely-forged blade
CN107520716A (en) * 2017-08-02 2017-12-29 安吉圆磨机械科技有限公司 A kind of technique for grinding of centrifugal automobile wheel
CN107520674A (en) * 2017-08-02 2017-12-29 安吉圆磨机械科技有限公司 A kind of centrifugal wheel polishing process
CN107520672A (en) * 2017-08-02 2017-12-29 安吉圆磨机械科技有限公司 A kind of polishing process of centrifugal automobile wheel
CN107520673A (en) * 2017-08-02 2017-12-29 安吉圆磨机械科技有限公司 A kind of centrifugal wheel technique for grinding
CN107984179A (en) * 2017-11-22 2018-05-04 中国航发沈阳黎明航空发动机有限责任公司 A kind of quick method for preparing double installing plate blades
CN108145393A (en) * 2017-11-29 2018-06-12 株洲丰发精工实业有限公司 A kind of aero-engine compressor blade and its processing method
CN108500574A (en) * 2018-03-30 2018-09-07 广汉天空动力机械有限责任公司 A kind of process preparing aero-engine cyclone using special processing technology
CN108714770A (en) * 2018-05-30 2018-10-30 中国航发动力股份有限公司 A kind of method of engine rectification guide vane processing
CN108747232A (en) * 2018-05-30 2018-11-06 中国航发动力股份有限公司 A kind of finish forge stator blade automatization processing method
CN108747232B (en) * 2018-05-30 2020-02-11 中国航发动力股份有限公司 Automatic machining method for precisely forged stator blade
CN109531198A (en) * 2018-11-27 2019-03-29 中国航发沈阳黎明航空发动机有限责任公司 Improve the method and process area refine fixture of large and complex structure blade processing precision
CN109531198B (en) * 2018-11-27 2020-09-18 中国航发沈阳黎明航空发动机有限责任公司 Method for improving machining precision of large-scale complex-structure blade and fine trimming clamp of process table
CN109365884A (en) * 2018-12-17 2019-02-22 中国航发动力股份有限公司 A kind of rotor blade tip cutting off processing method and its application

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Address after: Weiyang Xu Jia Wan 710021 Shaanxi city of Xi'an Province

Patentee after: AECC AVIATION POWER CO., LTD.

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