CN105269277B - A kind of aero-engine compressor circle-arc tooth tenon blade machining process - Google Patents

A kind of aero-engine compressor circle-arc tooth tenon blade machining process Download PDF

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Publication number
CN105269277B
CN105269277B CN201410312140.2A CN201410312140A CN105269277B CN 105269277 B CN105269277 B CN 105269277B CN 201410312140 A CN201410312140 A CN 201410312140A CN 105269277 B CN105269277 B CN 105269277B
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China
Prior art keywords
blade
tenon
clamping
false boss
cuboid
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CN201410312140.2A
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Chinese (zh)
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CN105269277A (en
Inventor
马辉
张婵
冯全全
赵赟
张新东
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西安航空动力股份有限公司
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Priority to CN201410312140.2A priority Critical patent/CN105269277B/en
Publication of CN105269277A publication Critical patent/CN105269277A/en
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Publication of CN105269277B publication Critical patent/CN105269277B/en

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Abstract

The invention belongs to aero-engine compressor blade processing technology, the present invention provides a kind of aero-engine compressor circle-arc tooth tenon blade machining process, including:By the blade woollen clamping with root false boss and blade tip false boss on CNC milling machine, leading edge and exhaust side to blade are rough milled;Blade clamping after rough milling is poured into a mould blade, the blade profile after cast is cuboid in fixture is poured into a mould in positioning with low-melting alloy;Cuboid blade after CNC milling machine clamping cast, rough mills out the tenon and listrium positioned at root of blade, removes root of blade false boss;Delay in six axles into tenon is finish-ground into circle-arc tooth shape on grinding center;Cuboid blade is put into melting furnace, is heated to 180 DEG C, blade is taken out after low-melting alloy fusing;With tenon positioning and clamping, leading edge and exhaust side are refined on numerical control abrasive belt grinding machine;With tenon positioning and clamping, blade tip is processed on numerically controlled wire cutting machine, removes false boss.

Description

A kind of aero-engine compressor circle-arc tooth tenon blade machining process

Technical field

The invention belongs to aero-engine compressor blade processing technology, is related to aero-engine circle-arc tooth tenon class leaf The improvement of slice processing method.

Background technology

A kind of circle-arc tooth tenon blade construction of certain h type engine h compressor is referring to Fig. 1, and blade is by tenon 1, listrium 2, blade 3 Formed with blade tip 5.Tenon 1 is radial direction circular arc dove-tail form structure, and tenon 1 is connected with listrium 2, and listrium 2 is connected with blade 3.At present, Country's processing radial direction circular arc dove-tail form tenon blade mainly comprises the following steps:Using finish forge blank, inlet and outlet edge is first processed, then Poured into a mould with eutectic point location alloy package, then combine turnery processing tenon, and Milling Process blade tip, finally melted low melting point and determine Position alloy.The major defect of the processing method is:1) tenon machined surface profile tolerance is tighter, combines turning Machining Arc box pin joint The uniformity of head is poor, and tenon profile tolerance is difficult to ensure that, the tool marks left after Vehicle Processing are obvious, tenon finished surface matter Measure poor;2) turning circle-arc tooth tenon debugging cycle length is combined, processing efficiency is low.

The content of the invention

The technical problem to be solved in the present invention:It is proposed a kind of aero-engine compressor circle-arc tooth tenon blade processing side Method, to ensure the profile tolerance of blade tenon circle-arc tooth and surface quality, processing efficiency is improved, shortens the process-cycle.

Technical scheme:A kind of aero-engine compressor circle-arc tooth tenon blade machining process, including:

Step 1, by the blade woollen clamping with root false boss and blade tip false boss on CNC milling machine, to leaf The leading edge of piece and exhaust side are rough milled;

Step 2, will rough mill after blade clamping positioning pour into a mould fixture in, blade is poured into a mould with low-melting alloy, Blade profile after cast is cuboid;

Cuboid blade after step 3, CNC milling machine clamping cast, rough mills out the tenon and listrium positioned at root of blade, Remove root of blade false boss;

Step 4, delay into tenon is finish-ground into circle-arc tooth shape on grinding center in six axles;

Step 5, cuboid blade is put into melting furnace, is heated to 180 DEG C, blade is taken out after low-melting alloy fusing;

Step 6, with tenon positioning and clamping, leading edge and exhaust side are refined on numerical control abrasive belt grinding machine;

Step 7, with tenon positioning and clamping, blade tip is processed on numerically controlled wire cutting machine, removes false boss.

Beneficial effects of the present invention:The invention proposes a kind of aero-engine compressor circle-arc tooth tenon blade Improve processing method.1) this method ensure that the wheel of blade tenon circle-arc tooth using delaying into grinding process grinding circle-arc tooth tenon Wide degree and surface quality;2) it is simultaneously, more high in machining efficiency than original combination turning into grinding process using delaying, shorten processing week Phase.

Brief description of the drawings

Fig. 1 is a kind of circle-arc tooth tenon blade construction schematic diagram of certain h type engine h compressor that the present invention applies;

Fig. 2 is a kind of circle-arc tooth tenon blade blank schematic diagram of certain h type engine h compressor that the present invention applies;

Fig. 3 is the fine grinding blade arc box pin joint head schematic diagram that the present invention processes.

Embodiment

Technical scheme:A kind of aero-engine compressor circle-arc tooth tenon blade machining process, including:

Step 1, by the blade woollen clamping with root false boss and blade tip false boss on CNC milling machine, to leaf The leading edge of piece and exhaust side are rough milled;

Step 2, will rough mill after blade clamping positioning pour into a mould fixture in, blade is poured into a mould with low-melting alloy, Blade profile after cast is cuboid;

Cuboid blade after step 3, CNC milling machine clamping cast, rough mills out the tenon and listrium positioned at root of blade, Remove root of blade false boss;

Step 4, delay into tenon is finish-ground into circle-arc tooth shape on grinding center in six axles;

Step 5, cuboid blade is put into melting furnace, is heated to 180 DEG C, blade is taken out after low-melting alloy fusing;

Step 6, with tenon positioning and clamping, leading edge and exhaust side are refined on numerical control abrasive belt grinding machine;

Step 7, with tenon positioning and clamping, blade tip is processed on numerically controlled wire cutting machine, removes false boss.

Below by embodiment, the invention will be further described.

Embodiment

The circle-arc tooth tenon blade blank is fine forge piece, structure as shown in figure 1, blahk structure referring to Fig. 2, tenon 1 have plus Spare time measures, and blade 3 and inner platform 7 do not have surplus, and leading edge 4 has allowance, tenon 1 and the phase of false boss 8 with exhaust side 6 Even, blade tip 5 is connected with false boss 9.Its procedure of processing is:

(1) milling inlet and outlet side:Leading edge 4 is rough milled with false boss 8 and the positioning and clamping of false boss 9 on CNC milling machine With being vented side 6, the benchmark as the cast of step (2) eutectic point location alloy.

(2) eutectic point location alloy is poured into a mould:By blade clamping positioning pour into a mould fixture in, positioning cast fixture with blade 3, Leading edge 4 and inner platform 7 position, and eutectic point location alloy block is cuboid after blade casting complete.

(3) tenon is rough milled:Roughing tenon 1 and listrium 2 on CNC milling machine, false boss 8 is removed, rough mills the He of tenon 1 Listrium 2, refine tenon 1 for step (4) and listrium 2 is prepared.

(4) tenon is refined:The selection of tenon fine grinding is delayed into carrying out on grinding center in six axles, refines blade arc box pin joint Head schematic diagram is referring to Fig. 3, and lathe working shaft realizes six axle four-axle linkages during processing, and wherein X, Y, Z be linear axis, with B axle reality jointly It is existing four-axle linked, the processing of circle-arc tooth, A axles pendulum fixed angle are completed, C axles realize leaf basin, turn in two, blade back direction curved tooth face Change processing.

(5) eutectic point location alloy is melted:Blade with low-melting alloy block is put into melting furnace, is heated to 180 DEG C, Blade is taken out after low-melting alloy fusing.

(6) intake and exhaust edge is ground:Leading edge 4 and exhaust side 6 are refined on numerical control abrasive belt grinding machine, it is fixed with tenon 1 during grinding Position clamping, ensure leading edge 4 and be vented the shape and size on side 6.

(7) linear cutter blade tip:With the positioning and clamping of tenon 1 on numerically controlled wire cutting machine, blade tip 5 is processed, removes work Skill boss 9.

Claims (1)

  1. A kind of 1. aero-engine compressor circle-arc tooth tenon blade machining process, it is characterised in that including:
    Step 1, by the blade woollen clamping with root false boss and blade tip false boss on CNC milling machine, to blade Leading edge and exhaust side are rough milled;
    Step 2, will rough mill after blade clamping positioning pour into a mould fixture in, blade is poured into a mould with low-melting alloy, pour into a mould Blade profile afterwards is cuboid;
    Cuboid blade after step 3, CNC milling machine clamping cast, rough mills out the tenon and listrium positioned at root of blade, removes Root of blade false boss;
    Step 4, delay into tenon is finish-ground into circle-arc tooth shape on grinding center in six axles;
    Step 5, cuboid blade is put into melting furnace, is heated to 180 DEG C, blade is taken out after low-melting alloy fusing;
    Step 6, with tenon positioning and clamping, leading edge and exhaust side are refined on numerical control abrasive belt grinding machine;
    Step 7, with tenon positioning and clamping, blade tip is processed on numerically controlled wire cutting machine, removes false boss.
CN201410312140.2A 2014-07-02 2014-07-02 A kind of aero-engine compressor circle-arc tooth tenon blade machining process CN105269277B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201410312140.2A CN105269277B (en) 2014-07-02 2014-07-02 A kind of aero-engine compressor circle-arc tooth tenon blade machining process

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Application Number Priority Date Filing Date Title
CN201410312140.2A CN105269277B (en) 2014-07-02 2014-07-02 A kind of aero-engine compressor circle-arc tooth tenon blade machining process

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CN105269277B true CN105269277B (en) 2017-11-28

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CN105798556A (en) * 2016-04-06 2016-07-27 台州市椒江永固船舶螺旋桨厂 Propeller polishing technique
CN106270403A (en) * 2016-08-29 2017-01-04 中航动力股份有限公司 A kind of die forging rotor blade cast fixture
CN106392491B (en) * 2016-11-16 2019-01-04 贵州黎阳航空动力有限公司 A kind of Complex compressor blade is into row's side processing method
CN108326371A (en) * 2017-12-28 2018-07-27 东莞市慧淳金属制品有限公司 A kind of production method of vehicle-mounted camera pedestal
CN108971897A (en) * 2018-07-25 2018-12-11 广东职业技术学院 A kind of rim for automobile wheel process for machining
CN109373949B (en) * 2018-12-07 2020-05-19 中国航发南方工业有限公司 Turbine blade positioning base manufacturing device
CN109692990A (en) * 2018-12-17 2019-04-30 中国航发动力股份有限公司 A kind of band damping platform rotor blade 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
CN109604971B (en) * 2019-01-04 2020-05-19 中国航发南方工业有限公司 Method for machining complex-profile part
CN109759776B (en) * 2019-03-29 2020-12-04 上海摩软通讯技术有限公司 Method for manufacturing mesh component of mobile terminal and mobile terminal
CN110524318A (en) * 2019-08-30 2019-12-03 中国航发动力股份有限公司 A kind of blade machining process

Citations (4)

* 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
CN101417514A (en) * 2007-10-24 2009-04-29 沈阳黎明航空发动机(集团)有限责任公司 Titanium-alloy high-pressure compressor arc rabbet working-blade processing technique
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
CN102837246A (en) * 2012-09-14 2012-12-26 西安航空动力股份有限公司 Method for flexibly grinding gas inlet and exhaust edges of precision forged blade of aircraft engine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101417514A (en) * 2007-10-24 2009-04-29 沈阳黎明航空发动机(集团)有限责任公司 Titanium-alloy high-pressure compressor arc rabbet working-blade processing technique
CN101363327A (en) * 2008-09-26 2009-02-11 无锡透平叶片有限公司 Method for processing TC11 material blade
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
CN102837246A (en) * 2012-09-14 2012-12-26 西安航空动力股份有限公司 Method for flexibly grinding gas inlet and exhaust edges of precision forged blade of aircraft engine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
法国SNECMA公司叶片加工技术;张翼鸣;《航空工艺技术》;19980131(第2期);第21-23、27页 *

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Address after: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province

Patentee after: AVIC AVIATION ENGINE CORPORATION PLC

Address before: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province

Patentee before: Xian Aviation Power Co., Ltd.

Address after: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province

Patentee after: AECC AVIATION POWER CO., LTD.

Address before: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province

Patentee before: AVIC AVIATION ENGINE CORPORATION PLC

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