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 PDFInfo
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- 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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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
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)
- 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.
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 |
Applications Claiming Priority (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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| Publication Number | Publication Date |
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| CN105269277A CN105269277A (en) | 2016-01-27 |
| CN105269277B true CN105269277B (en) | 2017-11-28 |
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| 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 |
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| CN112207334B (en) * | 2020-09-29 | 2022-02-11 | 中国航发动力股份有限公司 | Blade tenon machining method |
| CN112276618B (en) * | 2020-10-20 | 2021-07-13 | 成都和鸿科技有限公司 | Method for machining tenon of blade of gas compressor |
| CN112338465B (en) * | 2020-10-23 | 2021-11-19 | 西安远航真空钎焊技术有限公司 | Three-axis numerical milling method for small-size blades |
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| CN113649658A (en) * | 2021-09-10 | 2021-11-16 | 南京航空航天大学 | Electric spark and abrasive flow combined machining method for working blade of gas compressor |
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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 Corp.,PLC Address after: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee after: AVIC AVIATION ENGINE Corp.,PLC Address before: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee before: XI'AN AVIATION POWER Co.,Ltd. |