CN115488734A - Chamfering machining method for edge plate face of compressor rotor blade - Google Patents
Chamfering machining method for edge plate face of compressor rotor blade Download PDFInfo
- Publication number
- CN115488734A CN115488734A CN202211201836.9A CN202211201836A CN115488734A CN 115488734 A CN115488734 A CN 115488734A CN 202211201836 A CN202211201836 A CN 202211201836A CN 115488734 A CN115488734 A CN 115488734A
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- China
- Prior art keywords
- blade
- axis
- edge plate
- rotor blade
- compressor rotor
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- 238000000034 method Methods 0.000 title claims abstract description 37
- 238000003754 machining Methods 0.000 title claims description 5
- 238000000227 grinding Methods 0.000 claims abstract description 36
- 238000003672 processing method Methods 0.000 claims abstract 2
- 238000009434 installation Methods 0.000 claims description 4
- 230000003746 surface roughness Effects 0.000 claims description 3
- 238000003801 milling Methods 0.000 abstract description 5
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B21/00—Machines or devices using grinding or polishing belts; Accessories therefor
- B24B21/16—Machines or devices using grinding or polishing belts; Accessories therefor for grinding other surfaces of particular shape
- B24B21/165—Machines or devices using grinding or polishing belts; Accessories therefor for grinding other surfaces of particular shape for vanes or blades of turbines, propellers, impellers, compressors and the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B41/00—Component parts such as frames, beds, carriages, headstocks
- B24B41/06—Work supports, e.g. adjustable steadies
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Grinding And Polishing Of Tertiary Curved Surfaces And Surfaces With Complex Shapes (AREA)
Abstract
The invention relates to the technical field of processing of rotor blades of an aero-engine compressor, in particular to a processing method for chamfering edge plate surfaces of a rotor blade of a compressor, which comprises the following steps: s1, assembling a clamp and abrasive belt grinding equipment; s2, assembling the blade and the clamp, and then debugging abrasive belt grinding equipment; and S3, grinding the blade according to the grinding track to obtain a finished blade. The method for processing the chamfer of the edge plate surface of the rotor blade of the gas compressor adopts automatic grinding, replaces a manual clamping process, and realizes efficient numerical control processing of the chamfer of the edge plate surface of the rotor blade of the high-pressure gas compressor. In addition, the method utilizes the technical characteristic of automatic grinding and form-following floating, and avoids the problem of scrapping of parts with out-of-tolerance sizes after processing caused by uneven margin of the edge plate in the milling process. Meanwhile, the method is simple and easy to implement, the processing cost of the blade is reduced, and the processing efficiency is improved.
Description
Technical Field
The invention relates to the technical field of processing of a rotor blade of an aircraft engine compressor, in particular to a method for processing a chamfer angle on an edge plate surface of a rotor blade of a compressor.
Background
At present, the main method for processing the chamfer angle of the edge plate surface of the rotor blade comprises the following steps: 1) Five-axis milling is adopted, positioning is carried out through tenon teeth, the workpiece is leveled through a clamp, a chamfer plane is milled through a cutter, and then the chamfer plane is polished to remove tool marks. The method has high requirement on the consistency of the height of the edge plate surface, the process is complex, the out-of-dimension scrapping caused by the inconsistent height of the edge plate surface is easy to occur, and the qualified rate is unstable; 2) Manual pliers are adopted for repair, and the pliers with rich requirements adopt file pliers for repair. The method has low efficiency and high requirement on personnel skills, can not meet the requirements on high-quality and high-efficiency processing of the blade, and becomes a bottleneck process of mass production and delivery.
With the improvement of the quality and the yield of the blade of the aero-engine, the quality and the efficiency of the blade are difficult to ensure by the existing process, and a process for replacing numerical control milling and clamping repair is urgently needed to be found, so that the conversion from blade processing to diversified processing is realized.
Disclosure of Invention
The invention provides a method for chamfering an edge plate surface of a compressor rotor blade, aiming at the problems of poor blade quality and low yield in the prior art.
The invention is realized by the following technical scheme:
a method for chamfering the edge plate surface of a compressor rotor blade comprises the following steps:
s1, assembling a clamp and abrasive belt grinding equipment;
s2, assembling the blade and the clamp, and then debugging abrasive belt grinding equipment;
and S3, grinding the blade according to the grinding track to obtain a finished blade.
Preferably, in S2, when the blade is assembled with the fixture, the tenon and the end face of the tenon air inlet edge of the blade are used as references to perform positioning.
Preferably, in S2, commissioning the belt grinding apparatus includes reference shaft commissioning and belt installation.
Preferably, the reference axis debugging comprises B axis debugging and Y axis debugging.
Preferably, the B-axis of the belt grinding installation is rotated by 8 °.
Preferably, the Y-axis moves linearly when the reference axis is adjusted.
Preferably, the abrasive belt is a pyramid abrasive belt.
Preferably, in S3, during grinding, the X-axis, Z-axis, a-axis and B-axis of the belt grinding machine are fixed, the Y-axis and C-axis are linked, and the U-axis is elastically floated.
Preferably, in S3, the elastic force on the U axis ranges from-5 to-10N.
Preferably, in S3, the chamfer angle length of the edge plate surface of the finished blade is 11 +/-1 mm, the width is 1 +/-0.5 mm, the shape angle is 8 +/-1 degrees, the arc radius is 6 +/-1 mm, and the surface roughness is more than Ra0.4.
Compared with the prior art, the invention has the following beneficial effects:
the method for processing the chamfer of the edge plate surface of the rotor blade of the gas compressor adopts automatic grinding, replaces a manual clamping process, and realizes efficient numerical control processing of the chamfer of the edge plate surface of the rotor blade of the high-pressure gas compressor. In addition, the method utilizes the technical characteristic of automatic grinding random floating, and avoids the problem of scrapping of parts with super-poor sizes after processing due to uneven margin of the edge plates in the milling process. Meanwhile, the method is simple and easy to implement, the processing cost of the blade is reduced, and the processing efficiency is improved.
Drawings
FIG. 1 is a schematic view of a blade configuration;
FIG. 2 is a schematic diagram of a blade blank structure;
FIG. 3 is a schematic view of a grinding process;
FIG. 4 is a schematic view of a fillet chamfer structure of a platform of a blade.
In the figure, 1, blade tip; 2. a leaf body; 3. an exhaust edge; 4. an air inlet edge; 5. a flange plate surface; 6. tenon teeth; 7. and (5) processing a boss.
Detailed Description
The present invention will now be described in further detail with reference to specific examples, which are intended to be illustrative, but not limiting, of the invention.
Referring to fig. 1, the blade is composed of a blade tip 1, a blade body 2, an exhaust edge 3, an air inlet edge 4, an edge plate surface 5 and a tenon tooth 6. The blade tip 1 is a circular arc curved surface, the edge plate surface 5 is a circular arc surface containing a chamfer, and the blade root is a dovetail circular arc tooth.
Referring to fig. 2, in the blank structure, the blade tip 1 is connected with a process boss 7, the tenon tooth 6 is connected with the process boss 7, the blade body 2 has no allowance, and the exhaust edge 3, the air inlet edge 4 and the tenon tooth 6 have machining allowances of 2.5 mm.
Referring to fig. 3, in the blade structure before chamfering, the blade body 2, the exhaust edge 3, the air inlet edge 4 and the tenon tooth 6 are processed, and the tenon tooth 6 is used as a positioning reference.
The invention discloses a method for chamfering a blade edge plate surface 5 of a compressor rotor, which comprises the following steps with reference to fig. 3:
s1, assembling a clamp and abrasive belt grinding equipment, namely placing the clamp on a platform of the abrasive belt grinding equipment and positioning and pressing the clamp;
and S2, assembling the blade and the clamp, and positioning by using the tenon of the blade and the end surface of the tenon air inlet edge 4 on the basis of the tenon tooth 6 of the blade during assembly.
And then, debugging the abrasive belt grinding equipment, including reference shaft debugging and abrasive belt installation. The specific operation of reference axis debugging is as follows: the B-axis of the belt grinding apparatus rotates 8 °, and the Y-axis moves along a straight line. The abrasive belt is a pyramid abrasive belt, the width of the abrasive belt is selected according to the width size of the edge plate and the abrasive belt grinding removal amount, and the abrasive belt with the thickness of 3mm is selected in the embodiment.
And S3, grinding the blade according to a grinding track, wherein during grinding, the X axis, the Z axis, the A axis and the B axis of the abrasive belt grinding equipment are fixed, the Y axis and the C axis are linked, and the U axis elastically floats (the elastic range on the U axis is-5 to-10N), so that a finished product blade is obtained.
Referring to fig. 4, the edge plate surface 5 of the finished blade has the chamfer angle length of 11 +/-1 mm, the width of 1 +/-0.5 mm, the shape angle of 8 +/-1 degrees, the arc radius of 6 +/-1 mm and the surface roughness of more than Ra0.4.
And then loosening the compression screws to detach the finished blade from the clamp, and finishing the processing of the chamfer angle of the blade edge plate surface 5.
The invention relates to a method for processing a chamfer angle of a blade edge plate surface 5 of a compressor rotor, which combines the structural characteristics of a blade and adopts abrasive belt grinding equipment to replace milling and clamping operations. The method realizes the application of the abrasive belt grinding equipment to the chamfer angle of the edge plate surface 5 of the rotor blade of the high-pressure compressor, simplifies the operation process, reduces the skill dependence of personnel and the processing cost, and improves the processing efficiency.
The above-mentioned embodiments are only preferred embodiments of the present invention, and are not intended to limit the technical solution of the present invention, and it should be understood by those skilled in the art that the technical solution can be modified and replaced by a plurality of simple modifications and replacements without departing from the spirit and principle of the present invention, and the modifications and replacements also fall into the protection scope covered by the claims.
Claims (10)
1. A method for chamfering the edge plate surface of a compressor rotor blade is characterized by comprising the following steps:
s1, assembling a clamp and abrasive belt grinding equipment;
s2, assembling the blade and the clamp, and then debugging abrasive belt grinding equipment;
and S3, grinding the blade according to the grinding track to obtain a finished blade.
2. The method for chamfering the edge plate surface of the compressor rotor blade according to claim 1, wherein in S2, when the blade is assembled with the jig, the tenon of the blade and the end surface of the tenon inlet edge are used for positioning with reference to the tenon tooth of the blade.
3. The compressor rotor blade edge face chamfer machining method according to claim 1, wherein, in S2, the commissioning of the belt grinding device includes reference shaft commissioning and belt installation.
4. The method of claim 3, wherein the datum axis adjustment comprises B-axis adjustment and Y-axis adjustment.
5. The method of claim 4 wherein the B axis of the belt grinding apparatus is rotated 8 °.
6. The compressor rotor blade edge panel chamfer machining method of claim 4, wherein the Y-axis moves linearly.
7. The method for chamfering the edge plate surface of the compressor rotor blade according to claim 3, wherein the abrasive belt is a pyramid abrasive belt.
8. The method for chamfering the edge plate face of the compressor rotor blade according to claim 1, wherein in S3, during the grinding process, the X-axis, the Z-axis, the a-axis and the B-axis of the belt grinding equipment are fixed, the Y-axis and the C-axis are linked, and the U-axis elastically floats.
9. The compressor rotor blade edge plate face chamfering method as set forth in claim 8, wherein in S3, the elastic force on the U-axis ranges from-5 to-10N.
10. The compressor rotor blade edge plate surface chamfering processing method according to claim 1, wherein in S3, the edge plate surface chamfering length of the finished blade is 11 ± 1mm, the width is 1 ± 0.5mm, the shape angle is 8 ° ± 1 °, the arc radius is 6 ± 1mm, and the surface roughness is greater than ra0.4.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211201836.9A CN115488734A (en) | 2022-09-29 | 2022-09-29 | Chamfering machining method for edge plate face of compressor rotor blade |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211201836.9A CN115488734A (en) | 2022-09-29 | 2022-09-29 | Chamfering machining method for edge plate face of compressor rotor blade |
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| CN115488734A true CN115488734A (en) | 2022-12-20 |
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| CN202211201836.9A Pending CN115488734A (en) | 2022-09-29 | 2022-09-29 | Chamfering machining method for edge plate face of compressor rotor blade |
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Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4051636A (en) * | 1975-04-30 | 1977-10-04 | Siemens Aktiengesellschaft | Method and apparatus for grinding turbine and compressor blades to dimension |
| JP2002326150A (en) * | 2001-05-01 | 2002-11-12 | Hmy Ltd | Blade surface polishing device and polishing method using the same |
| CN101234480A (en) * | 2007-01-31 | 2008-08-06 | 扬州大学 | Numerical Control Abrasive Belt Grinding Machine for Steam Turbine Blade and Its Control Method |
| CN102248467A (en) * | 2011-06-16 | 2011-11-23 | 西北工业大学 | Numerical control polishing method for blade edge plate and blade transitional arc part |
| FR2964585A1 (en) * | 2010-09-15 | 2012-03-16 | Snecma | METHOD AND MACHINE TOOL FOR ADJUSTING THE CONTOUR OF A WORKPIECE |
| CN203485005U (en) * | 2013-07-22 | 2014-03-19 | 北京胜为弘技数控装备有限公司 | Six-axle linkage numerical-control abrasive belt grinding machine used for horizontal multi-abrasive-belt mechanism |
| CN104440464A (en) * | 2014-12-01 | 2015-03-25 | 北京航空航天大学 | Method for three-axis linked double-spindle symmetric cantilever grinding machining of blade |
| CN104858747A (en) * | 2015-05-07 | 2015-08-26 | 北京航空航天大学 | Bi-directional inverted grinding method for full molded surface of blade with two ends having tip shrouds |
| CN104924181A (en) * | 2015-05-07 | 2015-09-23 | 北京航空航天大学 | Method and device for achieving full-profile grinding of blades with tenons through cylindrical coordinate three-axis linkage machine tool |
| CN105290925A (en) * | 2014-09-17 | 2016-02-03 | 电子科技大学 | Industrial-robot-based abrasive belt grinding device for profiles of controllable pitch propeller and manufacturing method of abrasive belt grinding device |
| CN110814983A (en) * | 2019-11-13 | 2020-02-21 | 中国航发动力股份有限公司 | Blade polishing device and polishing method |
| CN210115777U (en) * | 2019-05-13 | 2020-02-28 | 无锡航亚科技股份有限公司 | Device for polishing transition fillet between front and rear edges and edge plate of aviation precision forging blade |
| CN111376149A (en) * | 2020-03-31 | 2020-07-07 | 中国航发动力股份有限公司 | Guide blade machining method |
| CN114346840A (en) * | 2021-12-15 | 2022-04-15 | 武汉数字化设计与制造创新中心有限公司 | Blade full-characteristic multi-process force-control abrasive belt grinding and polishing device |
| CN114888702A (en) * | 2022-06-24 | 2022-08-12 | 中国航发贵州黎阳航空动力有限公司 | Numerical control polishing method for compressor blade |
-
2022
- 2022-09-29 CN CN202211201836.9A patent/CN115488734A/en active Pending
Patent Citations (15)
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|---|---|---|---|---|
| US4051636A (en) * | 1975-04-30 | 1977-10-04 | Siemens Aktiengesellschaft | Method and apparatus for grinding turbine and compressor blades to dimension |
| JP2002326150A (en) * | 2001-05-01 | 2002-11-12 | Hmy Ltd | Blade surface polishing device and polishing method using the same |
| CN101234480A (en) * | 2007-01-31 | 2008-08-06 | 扬州大学 | Numerical Control Abrasive Belt Grinding Machine for Steam Turbine Blade and Its Control Method |
| FR2964585A1 (en) * | 2010-09-15 | 2012-03-16 | Snecma | METHOD AND MACHINE TOOL FOR ADJUSTING THE CONTOUR OF A WORKPIECE |
| CN102248467A (en) * | 2011-06-16 | 2011-11-23 | 西北工业大学 | Numerical control polishing method for blade edge plate and blade transitional arc part |
| CN203485005U (en) * | 2013-07-22 | 2014-03-19 | 北京胜为弘技数控装备有限公司 | Six-axle linkage numerical-control abrasive belt grinding machine used for horizontal multi-abrasive-belt mechanism |
| CN105290925A (en) * | 2014-09-17 | 2016-02-03 | 电子科技大学 | Industrial-robot-based abrasive belt grinding device for profiles of controllable pitch propeller and manufacturing method of abrasive belt grinding device |
| CN104440464A (en) * | 2014-12-01 | 2015-03-25 | 北京航空航天大学 | Method for three-axis linked double-spindle symmetric cantilever grinding machining of blade |
| CN104858747A (en) * | 2015-05-07 | 2015-08-26 | 北京航空航天大学 | Bi-directional inverted grinding method for full molded surface of blade with two ends having tip shrouds |
| CN104924181A (en) * | 2015-05-07 | 2015-09-23 | 北京航空航天大学 | Method and device for achieving full-profile grinding of blades with tenons through cylindrical coordinate three-axis linkage machine tool |
| CN210115777U (en) * | 2019-05-13 | 2020-02-28 | 无锡航亚科技股份有限公司 | Device for polishing transition fillet between front and rear edges and edge plate of aviation precision forging blade |
| CN110814983A (en) * | 2019-11-13 | 2020-02-21 | 中国航发动力股份有限公司 | Blade polishing device and polishing method |
| CN111376149A (en) * | 2020-03-31 | 2020-07-07 | 中国航发动力股份有限公司 | Guide blade machining method |
| CN114346840A (en) * | 2021-12-15 | 2022-04-15 | 武汉数字化设计与制造创新中心有限公司 | Blade full-characteristic multi-process force-control abrasive belt grinding and polishing device |
| CN114888702A (en) * | 2022-06-24 | 2022-08-12 | 中国航发贵州黎阳航空动力有限公司 | Numerical control polishing method for compressor blade |
Non-Patent Citations (1)
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