CN107984179A - A kind of quick method for preparing double installing plate blades - Google Patents
A kind of quick method for preparing double installing plate blades Download PDFInfo
- Publication number
- CN107984179A CN107984179A CN201711169873.5A CN201711169873A CN107984179A CN 107984179 A CN107984179 A CN 107984179A CN 201711169873 A CN201711169873 A CN 201711169873A CN 107984179 A CN107984179 A CN 107984179A
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- process area
- blade
- installing plate
- quick method
- milling
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
It is an object of the invention to provide a kind of quick method for preparing double installing plate blades, specific embodiment is：1) upper/lower terminal process area, is processed：A process area is processed respectively in blade blank upper and lower ends, and upper process area connection blade tenon or upper mounting plate lateral surface, lower process area connect blade lower installation board lateral surface；2), clamping structure is designed on the basis of upper/lower terminal process area；3), thick/finish-milling installing plate and blade type face on the basis of upper and lower ends process area；4) blade type face, is polished；5) blade upper and lower ends process area, is removed.The blade of current air compressor structure complexity be this method solve in mechanical processing, complex process, clamping is difficult, and precision is difficult to guarantee, and process is tediously long, the problems such as quality efficiency is low.
Description
Technical field
The present invention relates to aero-engine compressor rotor, stator blade, especially provides a kind of double installing plates of quick preparation
The method of blade.
Background technology
Compressor turns, stator blade is complicated, and tenon or upper and lower installing plate are more into circular arc camber, blade profile curvature of curved surface
Change is big, and caused moment of torsion is larger during processing.Size and geometric tolerance required precision are high, to ensure to have standard with build-up member
True position fit precision requirement, reaches design requirement.
Traditional vane manufacturing process of mounting plates structure up and down is：Blank uses forging part, forging part blade type face
6 points are rough benchmark, and machine is subject to rough benchmark positioning cast low-melting alloy, is converted into the technique base of blade mechanism processing
It is accurate.The process route is tediously long, and cast alloying technology is complicated, and weight increases severely after pouring alloy, clamping stability and poor repeatability, auxiliary
Time is grown, and process is more dispersed, and part Reference Transforming error is big, and processing quality and efficiency are low.And after removing alloy, it need to increase
Pollute process.Since blade processing process is unstable, assembling quality and the performance of engine are not only have impact on, and be unable to reach leaf
The precision milling in piece type face, the three-dimensional coordinates measurement machine testing of some new technology such as batches, mechanical polishing or finishing also can not be real
It is existing.For this reason, we study double installing plate blade processing techniques, finally definite blank both ends increase process area, machine add
When, with the process area of standard, as the technological datum through manufacture overall process, clamped one time, lower installation board and leaf in completion
Body type face all processes, so as to solve the structure blade manufacturing issue.
The content of the invention
In order to solve the blade of current air compressor structure complexity in mechanical processing, complex process, clamping is difficult, excessively program-controlled
Make unstable, can not realize precision milling, blade profile uniformity is poor, and quality fluctuation is big, and precision is difficult to guarantee, and process is tediously long, quality effect
The low problem of rate, the present invention provides a kind of quick method for preparing double installing plate blades.
Technical solution of the present invention is as follows：
A kind of quick method for preparing double installing plate blades, it is characterised in that technical process is：
1) upper/lower terminal process area, is processed：A process area, upper process area are processed respectively in blade blank upper and lower ends
Blade tenon or upper mounting plate lateral surface are connected, lower process area connects blade lower installation board lateral surface；
2), clamping structure is designed on the basis of upper/lower terminal process area；
3), thick/finish-milling installing plate and blade type face on the basis of upper and lower ends process area；
4) blade type face, is polished；
5), remove blade upper and lower ends process area (can be removed using wire cutting mode), then completed using usual manner
The following process of blade.
By the way of blank increases process area using both ends, the machine added-time, using the process area of standard as through manufacturing process
Technological datum, clamped one time, completes tenon or upper lower installation board and blade type face all processes, and makes clamp structure simpler
Single, clamping is more stablized, efficiently, and a set of same structural clips, suitable for coarse-fine processing all process steps, and are suitable for a series of leaves
Piece, is greatly reduced fixture quantity, reduces fixture manufacture difficulty；Processing quality and processing efficiency have a distinct increment；It is more applicable
In new machine blade rapid development.
The present invention carries out Set and Positioning using blank both ends standard shape process area, so that integration processes the whole of blade
Body structure, process area structure design is reasonable, i.e., to consider blade construction, forging manufacturability, considers that machine adds clamping process again
Property, and material, processing cost and efficiency.Most upper/lower terminal process area is designed as cuboid or cylindrical structure, size at last
Be preferably designed for, cuboid：15mm × 10mm × 15mm or 25mm × 15mm × 25mm, cylinder：Diameter and height are Φ
The size of 10mm × 15mm or bigger, can also be adjusted according to blade concrete condition.Designed on the basis of the process area of standard
Tool structure is, it can be achieved that the quick change of a variety of blade processing clampings.
Process area of the present invention is as rear procedure technology clamping benchmark, it is desirable to and its size, relative positional accuracy are high, upper,
Lower both ends process area is designed to coplanar, more conducively positioning, processing and detection as the vertical plane of benchmark.
As preferable technical solution：
In step 1), process upper and lower ends process area when, using on blade blank lower installation board as locating and machining, clamp
Benchmark, cancels cast low spot alloy mode, more efficient than linear cutter using milling mode.
In step 3), when rough milling, it is detected on the basis of upper and lower ends process area, detection efficiency is high.After finish-milling, detection
Blade quasi spline benchmark establishes three coordinate measurement coordinate systems, it is not possible to again using both ends process area.
After rough milling destressing heat treatment, process area is deformed, and need to arrange to repair technique stage fiducial process, to ensure that finish-milling fills
Clamp the precision of position.
Beneficial effects of the present invention are：
1st, integration processing：Using both ends process area as unified benchmark, blade overall processing is completed, ensure that each portion of blade
Position relative positional accuracy.
2nd, clamp structure modularization：Fixture is simpler, and clamping is more stablized, efficiently, and a set of same structural clips, are suitable for
Coarse-fine processing all process steps, and it is suitable for a series of blades, fixture quantity is greatly reduced, reduces fixture manufacture difficulty.
3rd, type face high precision machining：Due to stablizing high-precision installation way, blade type face reaches numerical control without surplus milling
(reaching poor in design profile), mechanical polishing or finishing remove tool marks, realize the automation processing of type face, digital measuring.Reduce
Manual intervention, blade profile uniformity are good.
4th, blade processing quality and efficiency improve, and qualification rate brings up to more than 90%.
5th, new machine blade rapid development is more suitable for, shortens the new machine blade lead time.
Brief description of the drawings
Fig. 1 fans level-one stator blade blank and design finished product schematic diagram；
Fig. 2 process area design position schematic diagrames (front view)；
Fig. 3 process area design position schematic diagrames (top view)；
Fig. 4 processes upper/lower terminal process area clamping schematic diagram；
Fig. 5 thick/finish-milling installing plate and blade type face schematic diagram on the basis of upper and lower ends process area.
Reference numeral：1st, upper process area, 2, upper mounting plate (blank), 3, lower process area, 4, lower installation board (blank).
Embodiment
Embodiment 1
A kind of quick method for preparing double installing plate blades, it is characterised in that technical process is：
1) upper/lower terminal process area, is processed：A process area, upper process area are processed respectively in blade blank upper and lower ends
Blade tenon or upper mounting plate lateral surface are connected, lower process area connects blade lower installation board lateral surface；Upper/lower terminal process area is set
Rectangular parallelepiped structure is calculated as, size is length, width and height：15mm×10mm×15mm；
2), clamping structure is designed on the basis of upper/lower terminal process area；
3), thick/finish-milling installing plate and blade type face on the basis of upper and lower ends process area；
4) blade type face, is polished；
5), blade upper and lower ends process area (can employing mode remove) is removed in wire cutting, is then completed using usual manner
The following process of blade.
Typical blade technique, frock modularization are the method achieve, realizes the quick preparation of blade high-quality and high-efficiency low cost；
Blade profile is using stable high-precision milling, it is achieved thereby that the batch application of mechanical polishing and digitalization test；Leaf
Piece assembling site location precision obtains good guarantee, ensure that obtained blade meets engine performance requirement.
Embodiment 2
It is with the difference of embodiment 1：Upper/lower terminal process area is designed as cylindrical structure, is designed and sized to：Directly
Footpath and height are Φ 10mm × 15mm.
Embodiment 3
It is with the difference of embodiment 1：Upper/lower terminal process area is designed as rectangular parallelepiped structure, and size is length, width and height
25mm×15mm×25mm；After step 3) rough mills destressing heat treatment, process area is deformed, and is scheduled and is repaiied technique stage fiducial
Process, to ensure the precision of finish-milling Set and Positioning.
The above embodiments merely illustrate the technical concept and features of the present invention, and its object is to allow person skilled in the art
Scholar can understand present disclosure and implement according to this, and it is not intended to limit the scope of the present invention.It is all according to the present invention
The equivalent change or modification that Spirit Essence is made, should be covered by the protection scope of the present invention.
Claims (6)
- A kind of 1. quick method for preparing double installing plate blades, it is characterised in that technical process is：1) upper/lower terminal process area, is processed：A process area, upper process area connection are processed respectively in blade blank upper and lower ends Blade tenon or upper mounting plate lateral surface, lower process area connect blade lower installation board lateral surface；2), clamping structure is designed on the basis of upper/lower terminal process area；3), thick/finish-milling installing plate and blade type face on the basis of upper and lower ends process area；4) blade type face, is polished；5) blade upper and lower ends process area, is removed.
- 2. according to the quick method for preparing double installing plate blades described in claim 1, it is characterised in that：Upper/lower terminal process area Vertical plane as benchmark is designed to coplanar.
- 3. according to the quick method for preparing double installing plate blades described in claim 1, it is characterised in that：In step 1), upper and lower two It is cuboid or cylindrical structure to hold process area, is designed and sized to, cuboid：15mm × 10mm × 15mm or 25mm × 15mm × 25mm, cylinder：Diameter and height are the sizes of Φ 10mm × 15mm or bigger.
- 4. according to the quick method for preparing double installing plate blades described in claim 1, it is characterised in that：In step 3), when rough milling, It is detected on the basis of upper and lower ends process area, after finish-milling, detection blade quasi spline benchmark establishes three coordinate measurement coordinates System.
- 5. according to the quick method for preparing double installing plate blades described in claim 1, it is characterised in that：In step 3), rough mill After stress heat treatment, technique stage fiducial process is repaiied in arrangement, ensures the precision of finish-milling Set and Positioning.
- 6. according to the quick method for preparing double installing plate blades described in claim 1, it is characterised in that：In step 1), in processing During lower both ends process area, lower installation board is processed as locating and machining, the benchmark of clamping using milling mode using on blade blank.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201711169873.5A CN107984179A (en) | 2017-11-22 | 2017-11-22 | A kind of quick method for preparing double installing plate blades |
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| CN201711169873.5A CN107984179A (en) | 2017-11-22 | 2017-11-22 | A kind of quick method for preparing double installing plate blades |
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| CN107984179A true CN107984179A (en) | 2018-05-04 |
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| CN201711169873.5A Pending CN107984179A (en) | 2017-11-22 | 2017-11-22 | A kind of quick method for preparing double installing plate blades |
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Cited By (13)
| 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 |
| 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 |
| CN111571153A (en) * | 2020-05-29 | 2020-08-25 | 重庆水轮机厂有限责任公司 | Method for machining blade profile of Kaplan turbine blade |
| CN112059562A (en) * | 2020-09-01 | 2020-12-11 | 南通中能机械制造有限公司 | Production process of moving blade without crown |
| CN112809059A (en) * | 2020-12-22 | 2021-05-18 | 成都和鸿科技有限公司 | Processing method of journal type compressor blade |
| CN113369830A (en) * | 2021-06-30 | 2021-09-10 | 中国航发动力股份有限公司 | Machining method for forging low-pressure turbine blade |
| CN113369831A (en) * | 2021-06-30 | 2021-09-10 | 中国航发动力股份有限公司 | Machining process of aero-engine blade |
| CN113523729A (en) * | 2021-08-09 | 2021-10-22 | 无锡航亚科技股份有限公司 | Efficient and stable machining process of thin-wall annular part |
| CN114918632A (en) * | 2022-06-22 | 2022-08-19 | 中国航发贵州黎阳航空动力有限公司 | Device and method for machining blade arc mounting plate |
| CN115846739A (en) * | 2023-02-28 | 2023-03-28 | 沈阳强航时代精密科技有限公司 | Machining method for online datum correction of rotor blade die forging |
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| CN106392491A (en) * | 2016-11-16 | 2017-02-15 | 贵州黎阳航空动力有限公司 | Processing method of inlet and outlet sides of complex compressor blade |
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| GB173106A (en) * | 1920-10-12 | 1921-12-29 | Vickers Ltd | Improvements in or relating to the manufacture of turbine blades |
| US3156808A (en) * | 1956-11-20 | 1964-11-10 | Rolls Royce | Manufacture of turbine and compressor blades |
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| CN106363374A (en) * | 2016-11-16 | 2017-02-01 | 贵州黎阳航空动力有限公司 | Numerical control processing method and device for complex molded surface of rotor blade of air compressor |
| CN106392491A (en) * | 2016-11-16 | 2017-02-15 | 贵州黎阳航空动力有限公司 | Processing method of inlet and outlet sides of complex compressor blade |
Cited By (16)
| 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 |
| 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 |
| CN111571153A (en) * | 2020-05-29 | 2020-08-25 | 重庆水轮机厂有限责任公司 | Method for machining blade profile of Kaplan turbine blade |
| CN112059562A (en) * | 2020-09-01 | 2020-12-11 | 南通中能机械制造有限公司 | Production process of moving blade without crown |
| CN112809059A (en) * | 2020-12-22 | 2021-05-18 | 成都和鸿科技有限公司 | Processing method of journal type compressor blade |
| CN112809059B (en) * | 2020-12-22 | 2022-06-24 | 成都和鸿科技股份有限公司 | Processing method of journal type compressor blade |
| CN113369830A (en) * | 2021-06-30 | 2021-09-10 | 中国航发动力股份有限公司 | Machining method for forging low-pressure turbine blade |
| CN113369831A (en) * | 2021-06-30 | 2021-09-10 | 中国航发动力股份有限公司 | Machining process of aero-engine blade |
| CN113523729A (en) * | 2021-08-09 | 2021-10-22 | 无锡航亚科技股份有限公司 | Efficient and stable machining process of thin-wall annular part |
| CN114918632A (en) * | 2022-06-22 | 2022-08-19 | 中国航发贵州黎阳航空动力有限公司 | Device and method for machining blade arc mounting plate |
| CN115846739A (en) * | 2023-02-28 | 2023-03-28 | 沈阳强航时代精密科技有限公司 | Machining method for online datum correction of rotor blade die forging |
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