CN108405941A - Blade of aviation engine blade type face high-efficiency and precision milling method - Google Patents
Blade of aviation engine blade type face high-efficiency and precision milling method Download PDFInfo
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- CN108405941A CN108405941A CN201810168745.7A CN201810168745A CN108405941A CN 108405941 A CN108405941 A CN 108405941A CN 201810168745 A CN201810168745 A CN 201810168745A CN 108405941 A CN108405941 A CN 108405941A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23C—MILLING
- B23C3/00—Milling particular work; Special milling operations; Machines therefor
- B23C3/16—Working surfaces curved in two directions
- B23C3/18—Working surfaces curved in two directions for shaping screw-propellers, turbine blades, or impellers
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/18—Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form
- G05B19/19—Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by positioning or contouring control systems, e.g. to control position from one programmed point to another or to control movement along a programmed continuous path
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23C—MILLING
- B23C2215/00—Details of workpieces
- B23C2215/04—Aircraft components
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23C—MILLING
- B23C2220/00—Details of milling processes
- B23C2220/60—Roughing
- B23C2220/605—Roughing and finishing
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- Mechanical Engineering (AREA)
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- Manufacturing & Machinery (AREA)
- Physics & Mathematics (AREA)
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- Automation & Control Theory (AREA)
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Abstract
A kind of blade of aviation engine blade type face high-efficiency and precision milling method, it is characterized in that, by the roughing milling cutter rail for drawing out unique step on the blank profile threedimensional model that reconstruct obtains, and cutter is calculated using the adaptive strain feeding processing method based on constant cut load and rough mills feed rate on each cutter location, rough mill blade type face to become feeding mode；Then the milling cutter rail of unique step is drawn out on rigidity threedimensional model, and using finish-milling feed rate of the cutter on each cutter location of milling cutter rail is calculated based on the adaptive strain feeding method that type face normal direction constant elastic deforms, to become feeding mode finish-milling blade type face.Invention significantly improves blade blade type face rough mill with finish-milling processing efficiency, to batch machining product carry effect effect it is especially notable；It effectively avoids the processing of weak rigid blade from allowing knife, improves machined surface quality.
Description
Technical field
The present invention relates to a kind of technology in aircraft manufacturing field, specifically a kind of blade of aviation engine blade type face
High-efficiency and precision milling method.
Background technology
Blade of aviation engine blade type face is usually free form surface, and blade is very thin, especially into the weak rigid region such as trailing edge
Flutter easily occurs in cutting process for domain, while the vane size precision, surface roughness requirements are very high, are consequently belonging to
Typical difficult processing structural member.It works since blade of aviation engine is chronically under high temperature and high frequency load, Service Environment is different
It is often severe, usually select titanium alloy as blade material, because of its, poor thermal conductivity low with elasticity modulus, chemism height, intensity
High, the features such as processing hardening phenomenon is serious is generally acknowledged in the industry difficult-to-machine material.
For the structure of certain type blade of aviation engine as shown in Figure 1, the blank of the blade is die forging blade, the country processes its leaf
The way in body type face is usually to use indexable formula wire rod quality by constant feed rate along the close larger step pitch for being around in blade first
Knife rail rough milled, then with monoblock type carbide-tipped milling cutter by constant feed rate along the knife of the close relatively half step distance for being around in blade
Rail carries out finish-milling.Work step is rough milled in blade type face, since blade blank is forging part, is influenced by blade is twist structured,
Surplus on die forging blade blade type face to make to rough mill cutter stand under load when to be constantly fed rate feed it is difficult to ensure that uniformly, become
Change greatly, causes cutter life low, rough mill inefficiency.And for type face finish-milling work step, since the work step of rough milling in preceding road eliminates
A large amount of blade type face surplus, causes blade thinning, and blade is rigidly deteriorated.The intrinsic variable cross-section distorted-structure feature of blade itself
Keep the rigidity at its type face different location widely different, when cutter presses constant feed rate finish-milling blade type face, cutter is weak
Rigid region because with respect to feed it is larger due to easily there is processing and allow knife, strong rigid region again because with respect to feed it is smaller due to affect processing effect
Rate.
Invention content
The present invention rough mills link for the prior art in die forging blade blade type face makes cutter exist because of surface surplus unevenness
Be constantly fed when rate feed occur stand under load variation greatly and resulting cutter life it is low, rough mill the problem of inefficiency,
With blade type face finish-milling link because distort blade type face at different locations stiffness difference it is larger due to make cutter with it is constant into
There is a problem of that the weak rigid region of blade easily makes knife, strong rigid region feed efficiency low when to rate feed, proposes a kind of aviation hair
Motivation blade blade type face high-efficiency and precision milling method significantly improves blade blade type face and rough mills and finish-milling processing effect
Rate, to batch machining product carry effect effect it is especially notable；It effectively avoids the processing of weak rigid blade from allowing knife, improves processing table
Face quality.
The present invention is achieved by the following technical solutions：
The present invention relates to a kind of blade of aviation engine blade type face high-efficiency and precision milling methods, by die forging leaf
The roughing milling cutter rail of unique step is drawn out on the blank profile threedimensional model that piece reconstructs, and using based on constant cut load
Adaptive strain feeding processing method calculates cutter and rough mills feed rate on each cutter location, and blade type is rough milled to become feeding mode
Face；Later, draw out the milling cutter rail of unique step on threedimensional model, and using deform based on type face normal direction constant elastic oneself
It adapts to change feeding method and calculates feed feed rate of the cutter on each cutter location of milling cutter rail, to become feeding mode finish-milling blade
Type face.
The present invention relates to a kind of systems for realizing the above method, including：Five-axis machine tool digital control system, type surface model generate mould
Block rough mills feed rate generation module, rigidity model generation module, finish-milling feed rate generation module, wherein：Type surface model generates mould
Block is connected with laser three coordinate measuring machine and transmits blade three-dimensional model information, rough mills feed rate generation module and blade three-dimensional mould
Type, which is connected and transmits blade type face, rough mills feed rate information, and rigidity model generation module is connected with blade threedimensional model and transmits leaf
The Stiffness Distribution information in body type face, finish-milling feed rate generation module are connected with blade type face rigidity field and transmit blade type face finish-milling
Feed rate information.
Description of the drawings
Fig. 1 is the structural schematic diagram of existing blade of aviation engine；
In figure：Blade root 1, blade 2；
Fig. 2 is flow chart of the present invention.
Specific implementation mode
As shown in Figure 1, the present embodiment on the obtained blank profile threedimensional model of reconstruct by the steps such as drawing out
Long roughing milling cutter rail, and cutter is calculated on each cutter location using the adaptive strain feeding processing method based on constant cut load
Rough mill feed rate, rough mill blade type face to become feeding mode；Then the finish-milling of unique step is drawn out on rigidity threedimensional model
Knife rail, and cutter is calculated in each knife of milling cutter rail using based on the adaptive strain feeding method that type face normal direction constant elastic deforms
Finish-milling feed rate on site, to become feeding mode finish-milling blade type face.
The reconstruct refers to：The three of the type millet cake cloud of blade mould forging blank are obtained using laser three coordinate measuring engine measurement
Coordinate data, and reconstruct and obtain accurate blank profile threedimensional model.
The reconstruct, using but be not limited to 3Dreshaper software reconfigurations and go out accurate blank profile threedimensional model.
The roughing milling cutter rail is obtained by the high-volume finish-milling margin value of the type face normal direction along blank profile threedimensional model
Roughing milling cutter rail enveloping surface, then draw to obtain by setting step pitch.
Described rough mills feed rate, poor by making to blank profile threedimensional model and roughing milling cutter rail enveloping surface, finds out and rough mills
Then the practical surplus of each cutter location on knife rail is calculated using the adaptive strain feeding processing method based on constant cut load
To cutter feed rate is rough milled on each cutter location.
The adaptive strain based on constant cut load feeds processing method：In cutting step pitch permanence condition
Under, cutting force Fz=c × ap×fy, wherein：C, y is constant related with machined material and manufacturing process system, a respectivelypIt is
Refer to the cutting depth of cutter, f refers to the feed speed of cutter；Deformation obtainsI.e. as chip-load FzIt remains unchanged
When, with cutting depth apVariation, the feed speed f of cutter also changes, as cutting depth apWhen increase, tool feeding
Speed then decreases；As cutting depth apWhen reduction, tool feeding speed then improves therewith.
Since the practical surplus on each cutter location of roughing milling cutter rail is different, cutter is rough milling blade type face process
In, to keep chip-load FzInvariable, the feed speed f of cutter can be carried out in real time according to the practical surplus of each cutter location
Adaptive adjustment obtains the feed rate of rough milling on each cutter location, and by being obtained to programming that is, according to feed speed calculating process
The numerical control code for rough milling program modify, judge the code fragment position of each cutter location successively and correspond to feed rate information
Write-in, to finally obtain the numerical control program after each cutter location rough mills Fe ed drive.
The programming, using but be not limited to C language realize.
It is described to rough mill blade type face to become feeding mode and refer to：Die forging blade blank is passed through into blade root and integral shroud portion clamping
In the above-mentioned number that in the rotary shaft of five-axis machine tool, will be handled using the adaptive strain feeding processing method based on constant cut load
Control program is input in five-axis machine tool digital control system, and then realizes that becoming feeding mode rough mills blade type face.
The roughing milling cutter rail enveloping surface, it is preferred to use UG softwares high-volume go out finish-milling surplus in its type face normal direction, you can obtain
Obtain the enveloping surface of roughing milling cutter rail.
The practical surplus, it is preferred to use UG softwares to by blank profile threedimensional model and roughing milling cutter rail enveloping surface simultaneously
It imported into UG softwares and the coordinate origin of the two is made to overlap, rough milled together along type face normal direction at each cutter location of roughing milling cutter rail later
It is poor that blank profile make, and finds out the practical surplus corresponding to each cutter location of roughing milling cutter rail.
The rigidity threedimensional model, the blade blade type face using kinetic test systematic survey and after being rough milled are each
Along the rigidity data of normal direction at a position, and reconstructs and obtain rigidity threedimensional model.
The kinetic test system includes power hammer, unidirectional accelerometer, data collecting card and dynamic analysis mould
Block is arranged unidirectional accelerometer by the back side at tested point and held in response, quickly tapped using power hammer as excitation end
Tested point, the excitation end signal and the collected card of response end signal for tapping generation are collected and enter into dynamics analysis module,
By analyzing excitation end signal and response end signal, you can obtain the rigidity data of tested point.
The described adaptive strain feeding method based on the deformation of type face normal direction constant elastic refers to：It is random on blade type face
Uniformly choose n point, wherein at the i-th point along the rigidity value of type face normal direction be Ki, the feed speed of cutter at this point is fi,
At this along the cutting component of type face normal direction be Fi, then the position because by cutting component due to type face normal direction occur elasticity become
Shape amount xi=Fi/Ki.Since the distinctive complicated distorted-structure of blade makes the stiffness K difference at its type face different location very big, it is
Ensure at the different location of blade type face that the elastic deformation amount x occurred in type face normal direction due to by cutting component F is identical, it is desirable that cut
Cut component F can with change in location of the cutter at finish-milling blade type face and direct ratio variation in the stiffness K of corresponding position.To meet
This requirement only need to be to the cutter speed of the feeding at the different location of blade type face in other Cutting Process parameter constants
It spends f and carries out real-time adaptive adjustment, i.e., according to elastic deformation amount's calculating process, the finish-milling feeding on each cutter location is calculated
Rate, and the numerical control code by programming obtained finish-milling program is modified, and judges the code fragment position of each cutter location successively
And feed rate information is corresponded to and is written, to finally obtain the numerical control program after each cutter location finish-milling Fe ed drive.
The programming, using but be not limited to C language realize.
Described refers to become feeding mode finish-milling blade type face：By using deform based on type face normal direction constant elastic oneself
The above-mentioned numerical control program for adapting to become feeding method processing is input in five-axis machine tool digital control system, the blade blade type after rough milling
Implement to become feeding mode finish-milling blade type face on the basis of face.
This method disclosed in embodiment is constantly fed the coarse-fine processing method of rate compared to traditional, and blade type face can be made thick
20% or more milling improved efficiency makes 15% or more blade type face finish-milling improved efficiency.
Above-mentioned specific implementation can by those skilled in the art under the premise of without departing substantially from the principle of the invention and objective with difference
Mode carry out local directed complete set to it, protection scope of the present invention is subject to claims and not by above-mentioned specific implementation institute
Limit, each implementation within its scope is by the constraint of the present invention.
Claims (11)
1. a kind of blade of aviation engine blade type face high-efficiency and precision milling method, which is characterized in that by reconstructing
To blank profile threedimensional model on draw out the roughing milling cutter rail of unique step, and using based on constant cut load from
It adapts to change feeding processing method calculating cutter and rough mills feed rate on each cutter location, blade type face is rough milled to become feeding mode；
Then draw out the milling cutter rail of unique step on rigidity threedimensional model, and using deform based on type face normal direction constant elastic oneself
It adapts to change feeding method and calculates finish-milling feed rate of the cutter on each cutter location of milling cutter rail, to become feeding mode finish-milling blade
Type face.
2. according to the method described in claim 1, it is characterized in that, the reconstruct refers to：It is surveyed using laser three coordinate measuring machine
Amount obtains three coordinate datas of the type millet cake cloud of blade mould forging blank, and reconstructs and obtain accurate blank profile threedimensional model.
3. according to the method described in claim 1, it is characterized in that, the roughing milling cutter rail, by along blank profile threedimensional model
Type face normal direction high-volume finish-milling margin value, that is, obtain roughing milling cutter rail enveloping surface, then draw to obtain by setting step pitch.
4. according to the method described in claim 1, it is characterized in that, described rough mills feed rate, by blank profile three-dimensional mould
It is poor that type is made with roughing milling cutter rail enveloping surface, finds out the practical surplus of each cutter location on roughing milling cutter rail, then using based on constant cut
The adaptive strain feeding processing method of load is calculated cutter and rough mills feed rate on each cutter location.
5. according to the method described in claim 1, it is characterized in that, it is described based on constant cut load adaptive strain feeding plus
Work method refers to：It is common to calculate cutting force F in the case where cutting step pitch permanence conditionz=c × ap×fy, wherein：C, y be respectively with
Machined material and the related constant of manufacturing process system, apRefer to the cutting depth of cutter, f refers to the feed speed of cutter；
Deformation obtainsI.e. as chip-load FzWhen remaining unchanged, with cutting depth apVariation, cutter feeding speed
Degree f also changes, as cutting depth apWhen increase, tool feeding speed then decreases；As cutting depth apWhen reduction, knife
Tool feed speed then improves therewith；Since the practical surplus on each cutter location of roughing milling cutter rail is different, cutter is thick
During milling blade type face, to keep chip-load FzInvariable, the feed speed f of cutter can be according to the reality of each cutter location
Surplus and carry out real-time adaptive adjustment, i.e., according to feed speed calculating process, obtain the feed rate of rough milling on each cutter location, and
It is modified, judge the code fragment position of each cutter location successively and incited somebody to action by the numerical control code for rough milling program obtained to programming
Feed rate information corresponds to write-in, to finally obtain the numerical control program after each cutter location rough mills Fe ed drive.
6. according to the method described in claim 1, it is characterized in that, it is described to rough mill blade type face to become feeding mode and refer to：It will
Die forging blade blank is clamped in by blade root and integral shroud portion in the rotary shaft of five-axis machine tool, will be using based on constant cut load
The numerical control program of adaptive strain feeding processing method processing is input in five-axis machine tool digital control system, and then is realized and become feeding mode
Rough mill blade type face.
7. according to the method described in claim 1, it is characterized in that, the roughing milling cutter rail enveloping surface, it is preferred to use UG softwares exist
Its type face normal direction high-volume goes out finish-milling surplus, you can obtains the enveloping surface of roughing milling cutter rail.
8. according to the method described in claim 1, it is characterized in that, the rigidity threedimensional model, using kinetic test system
Along the rigidity data of normal direction at each position in blade blade type face after measuring and being rough milled, and reconstructs and obtain rigidity three-dimensional mould
Type.
9. according to the method described in claim 1, it is characterized in that, it is described based on type face normal direction constant elastic deformation it is adaptive
Becoming feeding method refers to：It is random on blade type face uniformly to choose n point, wherein the rigidity value at the i-th point along type face normal direction is
Ki, the feed speed of cutter at this point is fi, it is at this point F along the cutting component of type face normal directioni, then the position because by
The elastic deformation amount x for cutting component and occurring in type face normal directioni=Fi/Ki, since the distinctive complicated distorted-structure of blade makes it
Stiffness K difference at the different location of type face is very big, in order to ensure at the different location of blade type face because by cutting component F due in type face
The elastic deformation amount x that normal direction occurs is identical, it is desirable that cutting component F can with change in location of the cutter at finish-milling blade type face and just
Than changing in the stiffness K of corresponding position, to meet this requirement, in other Cutting Process parameter constants, need pair
Feed speed f of the cutter at the different location of blade type face carries out real-time adaptive adjustment, i.e., it was calculated according to elastic deformation amount
The finish-milling feed rate on each cutter location is calculated in journey, and the numerical control code by programming obtained finish-milling program is modified,
Judge the code fragment position of each cutter location successively and correspond to feed rate information to be written, to finally obtain each cutter location finish-milling
Numerical control program after Fe ed drive.
10. according to the method described in claim 1, it is characterized in that, it is described to refer to become feeding mode finish-milling blade type face：It will
Five-axis machine tool number is input to using the numerical control program of the adaptive strain feeding method processing deformed based on type face normal direction constant elastic
In control system, implement to become feeding mode finish-milling blade type face on the basis of the blade blade type face after rough milling.
11. a kind of system for realizing any of the above-described claim the method, which is characterized in that including：Five-axis machine tool numerical control system
System, rough mills feed rate generation module, rigidity model generation module, finish-milling feed rate generation module at type surface model generation module,
In：Type surface model generation module is connected with laser three coordinate measuring machine and transmits blade three-dimensional model information, rough mills feed rate life
It is connected with blade threedimensional model at module and transmits blade type face and rough mills feed rate information, rigidity model generation module and blade three
Dimension module is connected and transmits the Stiffness Distribution information in blade type face, and finish-milling feed rate generation module is connected with blade type face rigidity field
And transmit blade type face finish-milling feed rate information.
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| CN201810168745.7A CN108405941B (en) | 2018-02-28 | 2018-02-28 | Efficient precise milling method for blade body profile of aero-engine blade |
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| CN201810168745.7A CN108405941B (en) | 2018-02-28 | 2018-02-28 | Efficient precise milling method for blade body profile of aero-engine blade |
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Cited By (13)
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| CN110076379A (en) * | 2019-04-30 | 2019-08-02 | 沈阳透平机械股份有限公司 | The secondary method for fine finishing of the impeller blade of centrifugal compressor and impeller blade |
| CN110315116A (en) * | 2019-05-31 | 2019-10-11 | 沈阳透平机械股份有限公司 | The process of shrouding disc milling 3 d impeller blade flank milling |
| CN110605543A (en) * | 2019-08-30 | 2019-12-24 | 江西佳时特精密机械有限责任公司 | Novel machining process for turbine blade |
| CN110744112A (en) * | 2019-11-26 | 2020-02-04 | 中国航发沈阳黎明航空发动机有限责任公司 | Vibration reduction milling method for large-torsion variable-fillet blade profile of integral impeller |
| CN111203579A (en) * | 2020-03-16 | 2020-05-29 | 沈阳飞机工业（集团）有限公司 | Machining method before quenching of AF1410 steel part |
| CN112828685A (en) * | 2021-01-25 | 2021-05-25 | 沈阳精合数控科技开发有限公司 | Additive manufacturing blank processing control method, device and system |
| CN113751974A (en) * | 2021-09-29 | 2021-12-07 | 中国航发航空科技股份有限公司 | Machining and forming method of aero-engine blade |
| CN113814673A (en) * | 2021-11-01 | 2021-12-21 | 中国航发沈阳黎明航空发动机有限责任公司 | Geometric self-adaptive machining method for titanium alloy blisk welding part of large fan |
| CN113976962A (en) * | 2021-11-16 | 2022-01-28 | 重庆江增船舶重工有限公司 | Fixed shaft roughing method of integral impeller |
| CN114211030A (en) * | 2022-01-04 | 2022-03-22 | 重庆江增船舶重工有限公司 | Machining method for prolonging service life of titanium alloy straight-line blade semi-finish milling cutter |
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| CN115586750A (en) * | 2022-11-11 | 2023-01-10 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for milling blade of whole blade ring of aero-engine in full program mode |
| CN116493874A (en) * | 2023-04-27 | 2023-07-28 | 深圳市锴诚精密模具有限公司 | CNC ultra-precise cutting process |
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| CN110076379A (en) * | 2019-04-30 | 2019-08-02 | 沈阳透平机械股份有限公司 | The secondary method for fine finishing of the impeller blade of centrifugal compressor and impeller blade |
| CN110076379B (en) * | 2019-04-30 | 2020-05-22 | 沈阳透平机械股份有限公司 | Secondary finish machining method for impeller blade of centrifugal compressor and impeller blade |
| CN110315116A (en) * | 2019-05-31 | 2019-10-11 | 沈阳透平机械股份有限公司 | The process of shrouding disc milling 3 d impeller blade flank milling |
| CN110605543A (en) * | 2019-08-30 | 2019-12-24 | 江西佳时特精密机械有限责任公司 | Novel machining process for turbine blade |
| CN110744112A (en) * | 2019-11-26 | 2020-02-04 | 中国航发沈阳黎明航空发动机有限责任公司 | Vibration reduction milling method for large-torsion variable-fillet blade profile of integral impeller |
| CN110744112B (en) * | 2019-11-26 | 2020-08-28 | 中国航发沈阳黎明航空发动机有限责任公司 | Vibration reduction milling method for large-torsion variable-fillet blade profile of integral impeller |
| CN111203579A (en) * | 2020-03-16 | 2020-05-29 | 沈阳飞机工业（集团）有限公司 | Machining method before quenching of AF1410 steel part |
| CN112828685A (en) * | 2021-01-25 | 2021-05-25 | 沈阳精合数控科技开发有限公司 | Additive manufacturing blank processing control method, device and system |
| CN113751974A (en) * | 2021-09-29 | 2021-12-07 | 中国航发航空科技股份有限公司 | Machining and forming method of aero-engine blade |
| CN113751974B (en) * | 2021-09-29 | 2022-08-12 | 中国航发航空科技股份有限公司 | Machining and forming method for aero-engine blade |
| CN113814673A (en) * | 2021-11-01 | 2021-12-21 | 中国航发沈阳黎明航空发动机有限责任公司 | Geometric self-adaptive machining method for titanium alloy blisk welding part of large fan |
| CN113976962A (en) * | 2021-11-16 | 2022-01-28 | 重庆江增船舶重工有限公司 | Fixed shaft roughing method of integral impeller |
| CN113976962B (en) * | 2021-11-16 | 2023-12-19 | 重庆江增船舶重工有限公司 | Fixed shaft rough cutting method of integral impeller |
| CN114211030A (en) * | 2022-01-04 | 2022-03-22 | 重庆江增船舶重工有限公司 | Machining method for prolonging service life of titanium alloy straight-line blade semi-finish milling cutter |
| CN114879601A (en) * | 2022-04-29 | 2022-08-09 | 沈阳飞机工业（集团）有限公司 | Numerical control machining method for complex-surface wallboard carbon felt forming die |
| CN114879601B (en) * | 2022-04-29 | 2024-08-20 | 沈阳飞机工业（集团）有限公司 | Numerical control machining method for complex molded panel carbon felt forming die |
| CN115586750A (en) * | 2022-11-11 | 2023-01-10 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for milling blade of whole blade ring of aero-engine in full program mode |
| CN115586750B (en) * | 2022-11-11 | 2024-04-26 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for milling blades of whole She Huanquan programs of aero-engine |
| CN116493874A (en) * | 2023-04-27 | 2023-07-28 | 深圳市锴诚精密模具有限公司 | CNC ultra-precise cutting process |
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