CN102806510A - Numerically controlled polishing method for titanium alloy blade of aircraft engine - Google Patents
Numerically controlled polishing method for titanium alloy blade of aircraft engine Download PDFInfo
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- CN102806510A CN102806510A CN2012102885301A CN201210288530A CN102806510A CN 102806510 A CN102806510 A CN 102806510A CN 2012102885301 A CN2012102885301 A CN 2012102885301A CN 201210288530 A CN201210288530 A CN 201210288530A CN 102806510 A CN102806510 A CN 102806510A
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Abstract
The invention provides a numerically controlled polishing method for a titanium alloy blade of an aircraft engine. The method comprises the following steps: firstly measuring sizes of wave crests and wave troughs on the surface of the blade and determining a process program of the blade according to the measured sizes; then selecting the hardness of an abrasive belt contact wheel, the particle size of an abrasive belt and an output force for supporting an abrasive belt contact wheel actuating mechanism, according to the process program; subsequently determining the polishing travel and feeding rate of a polishing piece according to the process program; and finally aligning the blade to be polished with the contact wheel, and enabling the contact wheel to complete the numerically controlled polishing treatment on the blade according to the above-determined polishing parameters. Based on the reasonable plan of the polishing process, the method performs the combined treatment of rigid coarse polishing, semi-fine polishing and flexible fine polishing on the blade, can effectively improve the polishing quality of the blade surface and increase the polishing efficiency of the aircraft engine blade, and solves the problem that the blade surface quality is poor because of incorrect selection of polishing parameters. Besides, the polishing process is controlled by the numerical control techniques, so that the stability of blade surface quality is greatly improved.
Description
Technical field
The present invention relates to the blade of aviation engine field of machining, be specially aero-engine titanium alloy blade numerical control polishing process.
Background technology
In engine art; Especially aero-engine field of machining, blade profile is a free form surface, generally cuts processing with rose cutter is capable; Must form Wave crest and wave trough; And the motion in the section because cutter is expert at, reasons such as the different and location of path curves curvature, also can cause in the ranks residual height to differ than the processing of leaves quality has significant effects to the reliability of aero-engine; And the surface quality of blade directly has influence on the aeroperformance of blade, and then has influence on the performance of aero-engine.The polishing processed is to improve the main method of blade surface quality; Owing to the polishing field that efficient is high, characteristics such as surface quality is good, precision height are widely used in blade of abrasive band polishing, and the existing technological overwhelming majority utilizes the abrasive band technology that blade is polished.Also there are a lot of disclosed technical literatures to study though have to the polishing processing of blade; But often all the definite or profile finishing method of polishing locus method in these public technologies to certain part of blade; And a certain operation is carried out in all polishing process that are directed against, and does not have the glossing of relevant blade.The glossing that present blade is adopted is simple rigidity polishing or flexible polishing, so not only can not improve the quality of finish of blade, causes blade polished surface polishing vestige serious.Simultaneously, the integration polishing process of the blade of not making rational planning for is unfavorable for the raising of blade processing whole efficiency.
Summary of the invention
The technical problem that solves
Can't obviously improve the blade surface quality for solving existing blade glossing, simultaneously whole polishing process not made rational planning for, cause the low problem of blade polishing efficiency, the present invention proposes a kind of aero-engine titanium alloy blade numerical control polishing process.
Technical scheme
Technical scheme of the present invention is:
Said aero-engine titanium alloy blade numerical control polishing process is characterized in that: may further comprise the steps:
Step 1: measure the size of blade surface Wave crest and wave trough, and confirm the processing of leaves operation in view of the above: when the difference in height δ of crest and trough＜0.2mm, the blade polishing process is divided into thick throwing and smart throwing; When the difference in height δ of crest and trough >=0.2mm, the blade polishing process is divided into thick throwing, half smart the throwing and smart the throwing;
Step 2: the power output of selecting abrasive band contact wheel hardness, abrasive band granularity and support abrasive band contact wheel force application mechanism according to the operation content: when slightly throwing, contact wheel hardness span is 80～105Hs, abrasive band granularity P30～50, force application mechanism power output F>=50N; During half smart the throwing, contact wheel hardness span is 50～75Hs, abrasive band granularity P120～180, force application mechanism power output 5＜F≤15N; During smart the throwing, contact wheel hardness span is 30～45Hs, abrasive band granularity P240～600, force application mechanism power output F≤5N;
Step 3: confirm polishing line-spacing and feed speed to polishing workpiece according to the operation content: the polishing line-spacing is less than 1/4 of contact wheel width when slightly throwing, and feed speed is less than 100mm/min; The polishing line-spacing is 1/4～1/3 of a contact wheel width during half smart the throwing, and feed speed is 100～200mm/min; The polishing line-spacing is the half the of contact wheel width during smart the throwing, feed speed 300～500mm/min; Polishing locus is along the length of blade direction, and obtains polishing path through the ruled surface parameter fitting;
Step 4: after polished blade and contact wheel tool setting, the burnishing parameters that contact wheel is confirmed according to step 1～step 4 is accomplished blade digital control is polished.
Beneficial effect
The present invention is through reasonably planning polishing process; Blade adopted rigidity is slightly thrown, half smart the throwing and the flexible smart process combined of throwing; Can effectively improve the quality of finish of blade surface, improved the polishing efficiency of blade of aviation engine, avoid that blade surface quality that cause is lower because the selection of burnishing parameters is improper; Adopt Numeric Control Technology control polishing process simultaneously, blade surface quality stability also improves greatly.
The specific embodiment
Below in conjunction with specific embodiment the present invention is described:
Embodiment 1:
Employing silicon carbide abrasive particles in the present embodiment is as employed abrasive band abrasive particle, and concrete aero-engine titanium alloy blade numerical control polishing process may further comprise the steps:
Step 1: measure the size of blade surface Wave crest and wave trough, and confirm the processing of leaves operation in view of the above: when the difference in height δ of crest and trough＜0.2mm, the blade polishing process is divided into thick throwing and smart throwing; When the difference in height δ of crest and trough >=0.2mm, the blade polishing process is divided into thick throwing, half smart the throwing and smart the throwing.The difference in height of blade surface wave peak and trough is 0.3mm in the present embodiment, is thick throwing, half smart the throwing and three operations of smart throwing so confirm the processing of leaves operation.
Step 2: the power output of selecting abrasive band contact wheel hardness, abrasive band granularity and support abrasive band contact wheel force application mechanism according to the operation content: when slightly throwing, contact wheel hardness span is 80～105Hs, abrasive band granularity P30～50, force application mechanism power output F>=50N; During half smart the throwing, contact wheel hardness span is 50～75Hs, abrasive band granularity P120～180, force application mechanism power output 5＜F≤15N; During smart the throwing, contact wheel hardness span is 30～45Hs, abrasive band granularity P240～600, force application mechanism power output F≤5N.
In the present embodiment, when slightly throwing, contact wheel hardness value is 80Hs, abrasive band granularity P30, and force application mechanism power output F is 80N; During half smart the throwing, contact wheel hardness value is 50Hs, abrasive band granularity P150, force application mechanism power output 10N; During smart the throwing, contact wheel hardness value is 40Hs, abrasive band granularity P400, and force application mechanism power output F is 3N.
Step 3: confirm polishing line-spacing and feed speed to polishing workpiece according to the operation content: the polishing line-spacing is less than 1/4 of contact wheel width when slightly throwing, and feed speed is less than 100mm/min; The polishing line-spacing is 1/4～1/3 of a contact wheel width during half smart the throwing, and feed speed is 100～200mm/min; The polishing line-spacing is the half the of contact wheel width during smart the throwing, feed speed 300～500mm/min; Polishing locus is along the length of blade direction, and obtains polishing path through the ruled surface parameter fitting.
In the present embodiment, the contact wheel width is 20mm, and the polishing line-spacing is 2mm when slightly throwing, and feed speed is 80mm/min; The polishing line-spacing is 5mm during half smart the throwing, and feed speed is 150mm/min; The polishing line-spacing is 10mm during smart the throwing, and feed speed is 500mm/min.
Step 4: after polished blade and contact wheel tool setting, the thick throwing that contact wheel is confirmed according to step 1～step 4, half smart throwing and smart glossing order and the technological parameter of throwing carry out numerical control polishing successively, can accomplish the numerical control polishing to blade of aviation engine.
Embodiment 2:
Employing silicon carbide abrasive particles in the present embodiment is as employed abrasive band abrasive particle, and concrete aero-engine titanium alloy blade numerical control polishing process may further comprise the steps:
Step 1: measure the size of blade surface Wave crest and wave trough, and confirm the processing of leaves operation in view of the above: when the difference in height δ of crest and trough＜0.2mm, the blade polishing process is divided into thick throwing and smart throwing; When the difference in height δ of crest and trough >=0.2mm, the blade polishing process is divided into thick throwing, half smart the throwing and smart the throwing.The difference in height of blade surface wave peak and trough is 0.15mm in the present embodiment, is that thick the throwing with essence thrown two operations so confirm the processing of leaves operation.
Step 2: the power output of selecting abrasive band contact wheel hardness, abrasive band granularity and support abrasive band contact wheel force application mechanism according to the operation content: when slightly throwing, contact wheel hardness span is 80～105Hs, abrasive band granularity P30～50, force application mechanism power output F>=50N; During half smart the throwing, contact wheel hardness span is 50～75Hs, abrasive band granularity P120～180, force application mechanism power output 5＜F≤15N; During smart the throwing, contact wheel hardness span is 30～45Hs, abrasive band granularity P240～600, force application mechanism power output F≤5N.
In the present embodiment, when slightly throwing, contact wheel hardness value is 90Hs, abrasive band granularity P40, and force application mechanism power output F is 80N; During smart the throwing, contact wheel hardness value is 30Hs, abrasive band granularity P240, and force application mechanism power output F is 3N.
Step 3: confirm polishing line-spacing and feed speed to polishing workpiece according to the operation content: the polishing line-spacing is less than 1/4 of contact wheel width when slightly throwing, and feed speed is less than 100mm/min; The polishing line-spacing is 1/4～1/3 of a contact wheel width during half smart the throwing, and feed speed is 100～200mm/min; The polishing line-spacing is the half the of contact wheel width during smart the throwing, feed speed 300～500mm/min; Polishing locus is along the length of blade direction, and obtains polishing path through the ruled surface parameter fitting.
In the present embodiment, the contact wheel width is 20mm, and the polishing line-spacing is 2mm when slightly throwing, and feed speed is 80mm/min; The polishing line-spacing is 10mm during smart the throwing, and feed speed is 400mm/min.
Step 4: after polished blade and contact wheel tool setting, contact wheel carries out numerical control polishing according to the thick throwing that step 1～step 4 is confirmed with smart glossing order and the technological parameter of throwing successively, can accomplish the numerical control polishing to blade of aviation engine.
Embodiment 3:
Employing silicon carbide abrasive particles in the present embodiment is as employed abrasive band abrasive particle, and concrete aero-engine titanium alloy blade numerical control polishing process may further comprise the steps:
Step 1: measure the size of blade surface Wave crest and wave trough, and confirm the processing of leaves operation in view of the above: when the difference in height δ of crest and trough＜0.2mm, the blade polishing process is divided into thick throwing and smart throwing; When the difference in height δ of crest and trough >=0.2mm, the blade polishing process is divided into thick throwing, half smart the throwing and smart the throwing.The difference in height of blade surface wave peak and trough is 0.5mm in the present embodiment, is thick throwing, half smart the throwing and three operations of smart throwing so confirm the processing of leaves operation.
Step 2: the power output of selecting abrasive band contact wheel hardness, abrasive band granularity and support abrasive band contact wheel force application mechanism according to the operation content: when slightly throwing, contact wheel hardness span is 80～105Hs, abrasive band granularity P30～50, force application mechanism power output F>=50N; During half smart the throwing, contact wheel hardness span is 50～75Hs, abrasive band granularity P120～180, force application mechanism power output 5＜F≤15N; During smart the throwing, contact wheel hardness span is 30～45Hs, abrasive band granularity P240～600, force application mechanism power output F≤5N.
In the present embodiment, when slightly throwing, contact wheel hardness value is 105Hs, abrasive band granularity P50, and force application mechanism power output F is 50N; During half smart the throwing, contact wheel hardness value is 75Hs, abrasive band granularity P180, force application mechanism power output 15N; During smart the throwing, contact wheel hardness value is 45Hs, abrasive band granularity P600, and force application mechanism power output F is 5N.
Step 3: confirm polishing line-spacing and feed speed to polishing workpiece according to the operation content: the polishing line-spacing is less than 1/4 of contact wheel width when slightly throwing, and feed speed is less than 100mm/min; The polishing line-spacing is 1/4～1/3 of a contact wheel width during half smart the throwing, and feed speed is 100～200mm/min; The polishing line-spacing is the half the of contact wheel width during smart the throwing, feed speed 300～500mm/min; Polishing locus is along the length of blade direction, and obtains polishing path through the ruled surface parameter fitting.
In the present embodiment, the contact wheel width is 20mm, and the polishing line-spacing is 2mm when slightly throwing, and feed speed is 70mm/min; The polishing line-spacing is 5mm during half smart the throwing, and feed speed is 200mm/min; The polishing line-spacing is 10mm during smart the throwing, and feed speed is 300mm/min.
Step 4: after polished blade and contact wheel tool setting, the thick throwing that contact wheel is confirmed according to step 1～step 4, half smart throwing and smart glossing order and the technological parameter of throwing carry out numerical control polishing successively, can accomplish the numerical control polishing to blade of aviation engine.
Claims (1)
1. aero-engine titanium alloy blade numerical control polishing process is characterized in that: may further comprise the steps:
Step 1: measure the size of blade surface Wave crest and wave trough, and confirm the processing of leaves operation in view of the above: when the difference in height δ of crest and trough＜0.2mm, the blade polishing process is divided into thick throwing and smart throwing; When the difference in height δ of crest and trough >=0.2mm, the blade polishing process is divided into thick throwing, half smart the throwing and smart the throwing;
Step 2: the power output of selecting abrasive band contact wheel hardness, abrasive band granularity and support abrasive band contact wheel force application mechanism according to the operation content: when slightly throwing, contact wheel hardness span is 80～105Hs, abrasive band granularity P30～50, force application mechanism power output F>=50N; During half smart the throwing, contact wheel hardness span is 50～75Hs, abrasive band granularity P120～180, force application mechanism power output 5＜F≤15N; During smart the throwing, contact wheel hardness span is 30～45Hs, abrasive band granularity P240～600, force application mechanism power output F≤5N;
Step 3: confirm polishing line-spacing and feed speed to polishing workpiece according to the operation content: the polishing line-spacing is less than 1/4 of contact wheel width when slightly throwing, and feed speed is less than 100mm/min; The polishing line-spacing is 1/4～1/3 of a contact wheel width during half smart the throwing, and feed speed is 100～200mm/min; The polishing line-spacing is the half the of contact wheel width during smart the throwing, feed speed 300～500mm/min; Polishing locus is along the length of blade direction, and obtains polishing path through the ruled surface parameter fitting;
Step 4: after polished blade and contact wheel tool setting, the burnishing parameters that contact wheel is confirmed according to step 1～step 4 is accomplished blade digital control is polished.
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| CN2012102885301A CN102806510A (en) | 2012-08-14 | 2012-08-14 | Numerically controlled polishing method for titanium alloy blade of aircraft engine |
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| CN2012102885301A CN102806510A (en) | 2012-08-14 | 2012-08-14 | Numerically controlled polishing method for titanium alloy blade of aircraft engine |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103302592A (en) * | 2013-06-08 | 2013-09-18 | 西北工业大学 | Numerically-controlled abrasive band polishing cutter axis control method for achieving effective fitting of contact wheel and moulded surface |
| CN103692327A (en) * | 2013-11-29 | 2014-04-02 | 广东鸿泰科技股份有限公司 | Polishing method for radiation rib of die-casting mould |
| CN104227511A (en) * | 2013-06-21 | 2014-12-24 | 镇江德隆机电设备有限公司 | Tool polishing method |
| CN104439987A (en) * | 2014-11-09 | 2015-03-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Machining method for guaranteeing shape completeness of air inlet and air outlet side circular arcs of blade |
| CN107020548A (en) * | 2017-05-19 | 2017-08-08 | 西北工业大学 | A kind of polishing method for improving compressor blade aeroperformance |
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| US4747237A (en) * | 1986-06-20 | 1988-05-31 | Giebmanns Karl Hienz | Method for manufacturing a finished turbine blade from a raw workpiece |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103302592A (en) * | 2013-06-08 | 2013-09-18 | 西北工业大学 | Numerically-controlled abrasive band polishing cutter axis control method for achieving effective fitting of contact wheel and moulded surface |
| CN104227511A (en) * | 2013-06-21 | 2014-12-24 | 镇江德隆机电设备有限公司 | Tool polishing method |
| CN103692327A (en) * | 2013-11-29 | 2014-04-02 | 广东鸿泰科技股份有限公司 | Polishing method for radiation rib of die-casting mould |
| CN104439987A (en) * | 2014-11-09 | 2015-03-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Machining method for guaranteeing shape completeness of air inlet and air outlet side circular arcs of blade |
| CN107020548A (en) * | 2017-05-19 | 2017-08-08 | 西北工业大学 | A kind of polishing method for improving compressor blade aeroperformance |
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Application publication date: 20121205 |