CN105598790B - The processing method of turbo blade zigzag crown structure - Google Patents
The processing method of turbo blade zigzag crown structure Download PDFInfo
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- CN105598790B CN105598790B CN201610149313.2A CN201610149313A CN105598790B CN 105598790 B CN105598790 B CN 105598790B CN 201610149313 A CN201610149313 A CN 201610149313A CN 105598790 B CN105598790 B CN 105598790B
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- emery wheel
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- integral shroud
- working face
- blade
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- 238000003672 processing method Methods 0.000 title claims abstract description 23
- 229910001651 emery Inorganic materials 0.000 claims abstract description 85
- 238000007493 shaping process Methods 0.000 claims description 6
- 230000007935 neutral effect Effects 0.000 claims description 3
- 239000004744 fabric Substances 0.000 claims description 2
- 230000001815 facial effect Effects 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 7
- 230000008569 process Effects 0.000 abstract description 6
- 238000003754 machining Methods 0.000 description 8
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000004576 sand Substances 0.000 description 2
- 101100450138 Neurospora crassa (strain ATCC 24698 / 74-OR23-1A / CBS 708.71 / DSM 1257 / FGSC 987) hat-2 gene Proteins 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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
- B24B19/00—Single-purpose machines or devices for particular grinding operations not covered by any other main group
- B24B19/14—Single-purpose machines or devices for particular grinding operations not covered by any other main group for grinding turbine blades, propeller blades or 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
- B24B1/00—Processes of grinding or polishing; Use of auxiliary equipment in connection with such processes
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Finish Polishing, Edge Sharpening, And Grinding By Specific Grinding Devices (AREA)
Abstract
The invention discloses a kind of processing method of turbo blade zigzag crown structure, comprise the following steps：A, three-dimensional coordinate system is established according to the relative position between the non-working surface and emery wheel of integral shroud；B, make the first working face corresponding with emery wheel according to three-dimensional coordinate system and the first working face of the integral shroud first side of design, adjustment Leaf orientation, and pass through the processing of emery wheel the first working face of progress and the first non-working surface of homonymy；C, after the first working face and the first non-working surface completion of processing, blade is overturn, and carries out the deflection of blade, makes the second working face of the side of integral shroud second of design corresponding with emery wheel, and passes through the processing of emery wheel the second working face of progress；D, move radially biasing of the emery wheel along emery wheel, the processing with the second non-working surface of the second working face homonymy is carried out；E, the processing of zigzag crown structure is completed by same emery wheel.It is easy to process, quick；Processing cost can be saved；It can guarantee that the surface in face to be processed is smooth.
Description
Technical field
The present invention relates to aero engine turbine blades processing technique field, especially, is related to a kind of turbo blade sawtooth
The processing method of shape crown structure.
Background technology
The zigzag integral shroud of aero engine turbine blades 2 working faces and 4 non-working surfaces as shown in figure 1, be made up of.
The working face of two adjacent groups blade is mutually adjacent to, and non-working surface will then ensure certain gap.Traditional integral shroud as shown in Fig. 2
" A-A sections " such as Fig. 2 a and " the C-C sections " such as Fig. 2 c are cutd open in non-working surface, it can be seen that non-working surface and center
(X-Y plane) without angled, such as Fig. 2 b working face, " B-B sections and center (X-Y plane) are angled.Needed during processing
Then to regrind first two non-working surface grinding-shapings and cut working face.
At present, power turbine blade zigzag integral shroud manufacturing procedure is more complicated, need to could be by zigzag with two sets of emery wheels
Integral shroud machine-shaping, two sets of emery wheel processing certainly exist " connecing tool marks " at switching, therefore zigzag integral shroud machined surface be present not
The problem of round and smooth, cause the noise during follow-up use, vibration, mutually act power, the problems such as service life length reduces.
The content of the invention
The invention provides a kind of processing method of turbo blade zigzag crown structure, to solve existing power turbine leaf
Piece zigzag integral shroud processing method, need to could be more complicated by zigzag integral shroud machine-shaping, manufacturing procedure with two sets of emery wheels；Two
Set emery wheel processing certainly exists " connecing tool marks " at switching, causes the not round and smooth technical problem of zigzag integral shroud machined surface.
The present invention provides a kind of processing method of turbo blade zigzag crown structure, comprises the following steps：A, according to leaf
Relative position between the non-working surface and emery wheel of hat establishes three-dimensional coordinate system；B, according to three-dimensional coordinate system and the integral shroud of design
First working face of first side, adjustment Leaf orientation makes the first working face corresponding with emery wheel, and carries out the first work by emery wheel
Make the processing of the first non-working surface of face and homonymy；C, after the first working face and the first non-working surface completion of processing, blade is overturn,
And the deflection of blade is carried out, make the second working face of the side of integral shroud second of design corresponding with emery wheel, and second is carried out by emery wheel
The processing of working face；D, move radially biasing of the emery wheel along emery wheel, carry out and the second non-working surface of the second working face homonymy
Processing；E, the processing of zigzag crown structure is completed by same emery wheel.
Further, the foundation of step a neutral bodies coordinate system：Integral shroud is designed with four non-working surfaces, has per side logical
Cross two non-working surfaces of zigzag face connection；In the state of the first working face of integral shroud first side arrangement corresponding with emery wheel
Under, four non-working surfaces for setting integral shroud lay X-Y plane of the plane as three-dimensional coordinate system；Set emery wheel and lay plane as solid
The X-Z plane of coordinate system；The X-axis, Y-axis and Z axis of three-dimensional coordinate system are determined simultaneously.
Further, step b specific implementation step is：Adjust four non-working surfaces of integral shroud to be processed, make four it is non-
Working face is in the X-Y plane of three-dimensional coordinate system；Adjustment blade turns about the Z axis, and makes the saw of the first working face of integral shroud to be processed
The grinding surface of tooth and emery wheel is coincide up and down；By controlling emery wheel to move up and down while processing the first working face and the first inoperative
Face.
Further, step c specific implementation step is：Integral shroud to be processed realizes blade for 180 ° in X-Y plane rotation
Upset；Then blade is deflected around X-axis, makes the second working face of integral shroud to be processed perpendicular to X-Y plane, and the second working face
The grinding surface of sawtooth and emery wheel is coincide up and down；The second working face is processed by controlling emery wheel to move up and down.
Further, blade determines around X-axis deflection angle：Quantity according to turbine blade determines deflection angle, deflects
Angle is that 360 ° divided by blade quantity obtain the deflection angle around X-axis.
Further, step d specific implementation step is：By emery wheel along emery wheel radially to two second of integral shroud to be processed
Non-working surface direction biases and carries out the processing of the second non-working surface, is inwardly biased relative to the second working face so as to form two
The second non-working surface.
Further, the second non-working surface is 0.1mm-0.3mm relative to the inside offset or dish of the second working face.
Further, emery wheel is copy grinding wheel, i.e., the frosted facial contour of emery wheel is identical with the zigzag face shape of integral shroud；Sand
Wheel, which can only move up and down and lay direction along emery wheel side, carries out transverse shifting.
Further, integral shroud to be processed is fixed on Digit Control Machine Tool, and the to be processed of integral shroud to be processed is carried out by Digit Control Machine Tool
Gesture stability.
Further, after zigzag integral shroud completion of processing, removing surface is carried out, obtains the turbo blade zigzag leaf of shaping
It is preced with structure.
The invention has the advantages that：
The processing method of turbo blade zigzag crown structure of the present invention, is set by the relative position relation of integral shroud and emery wheel
The three-dimensional coordinate system that fixed blade shares with emery wheel, it is same to realize according to the integral shroud posture that blade is adjusted based on three-dimensional coordinate system
Processing of one emery wheel to the both sides face to be processed of zigzag integral shroud is easy to process, quick；Due to carrying out sawtooth using a set of emery wheel
The processing of shape integral shroud, processing cost can be saved；And by changing the posture of zigzag integral shroud, using a set of emery wheel to sawtooth
The both sides row Continuous maching in face to be processed of shape integral shroud, can eliminate " connecing tool marks ", ensure that the surface in face to be processed is smooth.
In addition to objects, features and advantages described above, the present invention also has other objects, features and advantages.
Below with reference to accompanying drawings, the present invention is further detailed explanation.
Brief description of the drawings
The accompanying drawing for forming the part of the application is used for providing a further understanding of the present invention, schematic reality of the invention
Apply example and its illustrate to be used to explain the present invention, do not form inappropriate limitation of the present invention.In the accompanying drawings：
Fig. 1 is the zigzag integral shroud splicing construction schematic diagram of power turbine adjacent blades；
Fig. 2 is the structural representation of zigzag integral shroud；
Fig. 2 a are Fig. 2 A-A profiles；
Fig. 2 b are Fig. 2 B-B profiles；
Fig. 2 c are Fig. 2 C-C profiles；
Fig. 3 is the FB(flow block) of the processing method of the turbo blade zigzag crown structure of the preferred embodiment of the present invention；
Fig. 4 is one of structural representation of the first working face machining state of the preferred embodiment of the present invention；
Fig. 5 is the two of the structural representation of the first working face machining state of the preferred embodiment of the present invention；
Fig. 6 is one of structural representation of the second working face machining state of the preferred embodiment of the present invention；
Fig. 7 is the two of the structural representation of the second working face machining state of the preferred embodiment of the present invention.
Marginal data：
1st, blade；2nd, integral shroud to be processed；201st, the first working face；202nd, the second working face；203rd, the first non-working surface；
204th, the second non-working surface；3rd, emery wheel.
Embodiment
Embodiments of the invention are described in detail below in conjunction with accompanying drawing, but the present invention can be limited by following and
The multitude of different ways of covering is implemented.
Fig. 3 is the FB(flow block) of the processing method of the turbo blade zigzag crown structure of the preferred embodiment of the present invention；Fig. 4
It is one of structural representation of the first working face machining state of the preferred embodiment of the present invention；Fig. 5 is the preferred embodiment of the present invention
The first working face machining state structural representation two；Fig. 6 is the second working face processing shape of the preferred embodiment of the present invention
One of structural representation of state；Fig. 7 is the two of the structural representation of the second working face machining state of the preferred embodiment of the present invention.
As shown in figure 3, the processing method of the turbo blade zigzag crown structure of the present embodiment, comprises the following steps：a、
Three-dimensional coordinate system is established according to the relative position between the non-working surface and emery wheel 3 of integral shroud；B, according to three-dimensional coordinate system and setting
First working face 201 of the integral shroud first side of meter, the adjustment posture of blade 1 makes the first working face 201 corresponding with emery wheel 3, and leads to
Cross the processing that emery wheel 3 carries out the first non-working surface 203 of the first working face 201 and homonymy；C, the first working face 201 and first is non-
After the completion of processing of working face 203, blade 1 is overturn, and carries out the deflection of blade 1, makes the second work of the side of integral shroud second of design
Face 202 is corresponding with emery wheel 3, and the processing of the second working face 202 is carried out by emery wheel 3；D, the moving radially along emery wheel 3 of emery wheel 3
Biasing, carry out the processing with the second non-working surface 204 of the homonymy of the second working face 202；E, zigzag is completed by same emery wheel 3
The processing of crown structure.The processing method of turbo blade zigzag crown structure of the present invention, pass through the relative position of integral shroud and emery wheel
The three-dimensional coordinate system that relation setting blade shares with emery wheel is put, the integral shroud posture of blade is adjusted based on foundation three-dimensional coordinate system,
It is easy to process, quick to realize processing of the same emery wheel to the both sides face to be processed of zigzag integral shroud；Due to using a set of emery wheel
The processing of zigzag integral shroud is carried out, processing cost can be saved；And by changing the posture of zigzag integral shroud, using a set of sand
The both sides row Continuous maching in face to be processed to zigzag integral shroud is taken turns, " connecing tool marks " can be eliminated, ensure the surface light in face to be processed
It is sliding.
As shown in Figure 4, Figure 5, Figure 6 and Figure 7, in the present embodiment, the foundation of step a neutral body coordinate systems：Integral shroud is designed with
Four non-working surfaces, there are two non-working surfaces connected by zigzag face per side；In the first work of integral shroud first side
In the state of making the arrangement corresponding with emery wheel 3 of face 201, four non-working surfaces for setting integral shroud lay X- of the plane as three-dimensional coordinate system
Y plane；Set emery wheel 3 and lay X-Z plane of the plane as three-dimensional coordinate system；The X-axis, Y-axis and Z of three-dimensional coordinate system are determined simultaneously
Axle.
As described in Fig. 4 and Fig. 5, in the present embodiment, step b specific implementation step is：Adjust four of integral shroud 2 to be processed
Non-working surface, four non-working surfaces are made to be in the X-Y plane of three-dimensional coordinate system；Adjustment blade 1 turns about the Z axis, and makes leaf to be processed
The sawtooth of first working face 201 of hat 2 coincide up and down with the grinding surface of emery wheel 3；By controlling emery wheel 3 to move up and down while processing
Go out the first working face 201 and the first non-working surface 203.
As shown in Figure 6 and Figure 7, in the present embodiment, step c specific implementation step is：Integral shroud 2 to be processed is in X-Y plane
180 ° of upsets for realizing blade 1 of rotation；Then blade 1 is deflected around X-axis, makes the second working face 202 of integral shroud 2 to be processed vertical
It is coincide up and down in the grinding surface of X-Y plane, and the sawtooth of the second working face 202 and emery wheel 3；By controlling emery wheel 3 to move up and down
Process the second working face 202.
As shown in Figure 6 and Figure 7, in the present embodiment, blade 1 determines around X-axis deflection angle：Number according to turbine blade 1
Amount determines deflection angle, and deflection angle is that 360 ° divided by the quantity of blade 1 obtain the deflection angle around X-axis.
As shown in Figure 6 and Figure 7, in the present embodiment, step d specific implementation step is：By emery wheel 3 along the radial direction of emery wheel 3 to
Two directions of the second non-working surface 204 of integral shroud 2 to be processed bias and carry out the processing of the second non-working surface 204, so as to be formed
Two the second non-working surfaces 204 inwardly biased relative to the second working face 202.
As shown in Figure 6 and Figure 7, in the present embodiment, the second non-working surface 204 is biased inwardly relative to the second working face 202
It is 0.1mm-0.3mm to put distance.
As shown in Figure 4, Figure 5, Figure 6 and Figure 7, in the present embodiment, emery wheel 3 is copy grinding wheel 3, i.e., outside the frosting of emery wheel 3
Shape is identical with the zigzag face shape of integral shroud；Emery wheel 3 can only be moved up and down and carried out laterally along the side cloth set direction of emery wheel 3
It is mobile.
In the present embodiment, integral shroud 2 to be processed is fixed on Digit Control Machine Tool, and treating for integral shroud 2 to be processed is carried out by Digit Control Machine Tool
Machining posture controls.
In the present embodiment, after zigzag integral shroud completion of processing, removing surface is carried out, obtains the turbo blade zigzag of shaping
Crown structure.
During implementation, there is provided a kind of processing method of turbo blade zigzag crown structure.Zigzag integral shroud is designed such as Fig. 1 institutes
Show, one is first designed perpendicular to the first zigzag face of X-Y plane (the first working face 201 and the first non-working surface 203), by a left side
Side integral shroud is cut away；Then by blade 1 overturn and by the first working face 201 around X-axis rotate 7.2 degree (assuming that be 50 blades, angle
360/50) to become the second working face 202, the second working face 202 cuts away the right integral shroud, then the second non-working surface 204 is past
In bias 0.2mm.
Specific implementation step is as follows：
First the first zigzag face (the first working face 201 and the first non-working surface 203) is ground during processing.By Fig. 5 and
Fig. 6 understands that emery wheel 3 is copy grinding wheel, i.e., identical with zigzag face shape.Emery wheel 3 can only be up and down and horizontal in addition to itself rotates
To movement, during saw gumming bit by bit down precession untill being ground to position.
It is the second working face 202 of mill with that, blade 1 is turned into 180 degree first, it is then deflected 7.2 degree around X-axis.
After 7.2 degree are turned about the X axis it can be seen from Fig. 6 and Fig. 7, original the second working face of inclined-plane 202 become one perpendicular to
The face of " X-Y plane ", such can of emery wheel 3 process this face；The second non-working surface 204 is biased into 0.2mm inward again,
Grind the second non-working surface 204.Deflection angle be present relative to the second working face 202 in the second non-working surface 204.As can be seen here,
This structure of the present invention only with a set of emery wheel can by integral shroud grind come, it is easy to process, quick, it is cost-effective.
The preferred embodiments of the present invention are the foregoing is only, are not intended to limit the invention, for the skill of this area
For art personnel, the present invention can have various modifications and variations.Within the spirit and principles of the invention, that is made any repaiies
Change, equivalent substitution, improvement etc., should be included in the scope of the protection.
Claims (10)
1. a kind of processing method of turbo blade zigzag crown structure, including step：
A, three-dimensional coordinate system is established according to the relative position between the non-working surface and emery wheel (3) of integral shroud；
It is characterized in that, further comprising the steps of：
B, make according to three-dimensional coordinate system and the first working face (201) of the integral shroud first side of design, adjustment blade (1) posture
First working face (201) is corresponding with emery wheel (3), and the first non-work of the first working face (201) and homonymy is carried out by emery wheel (3)
Make the processing of face (203)；
C, after the first working face (201) and the first non-working surface (203) completion of processing, blade (1) is overturn, and carry out blade (1)
Deflection, make the second working face (202) of the side of integral shroud second of design corresponding with emery wheel (3), and pass through emery wheel (3) carry out second
The processing of working face (202)；
D, move radially biasing of the emery wheel (3) along emery wheel (3), the second non-working surface with the second working face (202) homonymy is carried out
(204) processing；
E, the processing of zigzag crown structure is completed by same emery wheel (3).
2. the processing method of turbo blade zigzag crown structure according to claim 1, it is characterised in that
The foundation of the step a neutral body coordinate systems：
Integral shroud is designed with four non-working surfaces, has two non-working surfaces connected by zigzag face per side；
In the state of the first working face (201) arrangement corresponding with emery wheel (3) of integral shroud first side, set integral shroud four are non-
Working face lays the X-Y plane that plane is three-dimensional coordinate system；Set emery wheel (3) and lay X-Z plane of the plane as three-dimensional coordinate system；
The X-axis, Y-axis and Z axis of three-dimensional coordinate system are determined simultaneously.
3. the processing method of turbo blade zigzag crown structure according to claim 2, it is characterised in that
The specific implementation step of the step b is：
Four non-working surfaces of integral shroud to be processed (2) are adjusted, four non-working surfaces is in the X-Y plane of three-dimensional coordinate system；
Adjustment blade (1) turns about the Z axis, and makes the mill of the sawtooth and emery wheel (3) of the first working face (201) of integral shroud to be processed (2)
Bevel coincide up and down；
By controlling emery wheel (3) to move up and down while processing the first working face (201) and the first non-working surface (203).
4. the processing method of turbo blade zigzag crown structure according to claim 2, it is characterised in that
The specific implementation step of the step c is：
Integral shroud (2) to be processed is in 180 ° of upsets for realizing blade (1) of X-Y plane rotation；
Then blade (1) is deflected around X-axis, makes the second working face (202) of integral shroud to be processed (2) perpendicular to X-Y plane, and the
The sawtooth of two working faces (202) coincide up and down with the grinding surface of emery wheel (3)；
The second working face (202) is processed by controlling emery wheel (3) to move up and down.
5. the processing method of turbo blade zigzag crown structure according to claim 4, it is characterised in that
The blade (1) determines around X-axis deflection angle：
Quantity according to turbine blade (1) determines deflection angle,
Deflection angle is that 360 ° divided by blade (1) quantity obtain the deflection angle around X-axis.
6. the processing method of turbo blade zigzag crown structure according to claim 4, it is characterised in that
The specific implementation step of the step d is：
Two the second non-working surface (204) directions biasing by emery wheel (3) along emery wheel (3) radially to integral shroud to be processed (2) is gone forward side by side
The processing of the non-working surface of row second (204), so as to form two the second non-works inwardly biased relative to the second working face (202)
Make face (204).
7. the processing method of turbo blade zigzag crown structure according to claim 6, it is characterised in that
Second non-working surface (204) is 0.1mm-0.3mm relative to the inside offset or dish of the second working face (202).
8. the processing method of turbo blade zigzag crown structure according to any one of claim 1 to 7, its feature exist
In,
The emery wheel (3) is copy grinding wheel (3), i.e., the zigzag face shape phase of the frosted facial contour and integral shroud of described emery wheel (3)
Together；
The emery wheel (3) can only move up and down and carry out transverse shifting along emery wheel (3) side cloth set direction.
9. the processing method of turbo blade zigzag crown structure according to any one of claim 1 to 7, its feature exist
In,
Integral shroud (2) to be processed is fixed on Digit Control Machine Tool, and the posture control to be processed of integral shroud to be processed (2) is carried out by Digit Control Machine Tool
System.
10. the processing method of turbo blade zigzag crown structure according to any one of claim 1 to 7, its feature
It is,
After zigzag integral shroud completion of processing, removing surface is carried out, obtains the turbo blade zigzag crown structure of shaping.
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| CN201610149313.2A CN105598790B (en) | 2016-03-16 | 2016-03-16 | The processing method of turbo blade zigzag crown structure |
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| CN107457615B (en) * | 2017-09-04 | 2019-05-24 | 中国航发南方工业有限公司 | The grinding processing method of turbo blade step surface |
| CN109227224B (en) * | 2018-09-13 | 2021-03-02 | 沈阳透平机械股份有限公司 | Stationary blade grinding method for axial flow compressor |
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| US4285108A (en) * | 1979-02-23 | 1981-08-25 | United Technologies Corporation | Apparatus and method for refinishing turbine blade airseals |
| US6830240B2 (en) * | 2002-09-24 | 2004-12-14 | General Electric Company | Methods and apparatus for securing components for manufacture |
| US7784183B2 (en) * | 2005-06-09 | 2010-08-31 | General Electric Company | System and method for adjusting performance of manufacturing operations or steps |
| CN201650377U (en) * | 2010-05-19 | 2010-11-24 | 中国航空动力机械研究所 | Blade with crest |
| CN201907047U (en) * | 2010-11-01 | 2011-07-27 | 株洲南方燃气轮机成套制造安装有限公司 | Clamp for turbine blade and grinding machine comprising same |
| CN104858747B (en) * | 2015-05-07 | 2017-04-19 | 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 |
| CN105081691B (en) * | 2015-07-30 | 2017-09-19 | 南通中能机械制造有限公司 | Diamond shaped tooth form circular-arc roots of vanes movable vane slice processing method |
| CN105312864B (en) * | 2015-12-09 | 2017-08-15 | 中国南方航空工业(集团)有限公司 | The processing method of moving turbine blade |
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