CN105598790A - Method for machining sawtooth-shaped blade crown structure of turbine blade - Google Patents
Method for machining sawtooth-shaped blade crown structure of turbine blade Download PDFInfo
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- CN105598790A CN105598790A CN201610149313.2A CN201610149313A CN105598790A CN 105598790 A CN105598790 A CN 105598790A CN 201610149313 A CN201610149313 A CN 201610149313A CN 105598790 A CN105598790 A CN 105598790A
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- emery wheel
- blade
- working
- integral shroud
- working face
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- 238000000034 method Methods 0.000 title claims abstract description 14
- 238000003754 machining Methods 0.000 title abstract description 12
- 229910001651 emery Inorganic materials 0.000 claims description 76
- 238000003672 processing method Methods 0.000 claims description 21
- 230000008569 process Effects 0.000 claims description 9
- 230000007935 neutral effect Effects 0.000 claims description 3
- 239000004744 fabric Substances 0.000 claims description 2
- 238000000465 moulding Methods 0.000 claims description 2
- 230000008901 benefit Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000007493 shaping process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction 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
- 230000009467 reduction Effects 0.000 description 1
- 210000000332 tooth crown Anatomy 0.000 description 1
- 238000007514 turning 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 method for machining a sawtooth-shaped blade crown structure of a turbine blade. The method comprises the following steps that a, a stereoscopic coordinate system is established according to the relative positions of the non-work face of a blade crown and a grinding wheel; b, the posture of the blade is adjusted according to the stereoscopic coordinate system and the first work face of the designed first side face of the blade crown, the first work face is made to correspond to the grinding wheel, and the first work face and the first non-work face on the same side are machined through the grinding wheel; c, after the first work face and the first non-work face are machined, the blade is turned over, deflection of the blade is carried out, the second work face of the designed second side of the blade crown is made to correspond to the grinding wheel, and the second work face is machined through the grinding wheel; d, the grinding wheel moves and deviates in the radial direction of the grinding wheel, and the second non-work face on the same side with the second work face is machined; e, the sawtooth-shaped blade crown structure is machined through the same grinding wheel. Machining is convenient and fast. Machining cost can be reduced. It can be guaranteed that the surfaces of the faces to be machined are smooth.
Description
Technical field
The present invention relates to aero engine turbine blades processing technique field, especially, relate to a kind of turbo blade zigzag integral shroudThe processing method of structure.
Background technology
The zigzag integral shroud of aero engine turbine blades as shown in Figure 1, is made up of 2 working faces and 4 non-working surfaces. PhaseThe working face of adjacent two groups of blades is adjacent to mutually, and non-working surface will ensure certain gap. Traditional integral shroud as shown in Figure 2, as" the A-A section " of Fig. 2 a and be all to cut open in non-working surface as Fig. 2 c " C-C section ", can find out non-working surface and center(X-Y plane) do not have angled, and as the working face of Fig. 2 b, " B-B section and center (X-Y plane) is angled. AddMan-hour requirement is first two non-working surface grinding-shapings, and then grinding working face.
At present, power turbine blade zigzag integral shroud manufacturing procedure more complicated, need could add zigzag integral shroud with two cover emery wheelsWork moulding, two cover emery wheel processing certainly exist " connecing tool marks " in switching place, therefore have not round and smooth the asking of zigzag integral shroud machined surfaceTopic, causes noise in follow-up use procedure, vibration, mutually produces the problem such as active force, long service life reduction.
Summary of the invention
The invention provides a kind of processing method of turbo blade zigzag crown structure, to solve existing power turbine blade sawtoothShape integral shroud processing method, needing to overlap emery wheels with two could be by the machine-shaping of zigzag integral shroud, manufacturing procedure more complicated; Two cover emery wheelsProcessing certainly exists " connecing tool marks " in switching place, cause the not round and smooth technical problem of zigzag integral shroud machined surface.
The processing method that the invention provides a kind of turbo blade zigzag crown structure, comprises the following steps: a, non-according to integral shroudRelative position between working face and emery wheel is set up three-dimensional coordinate system; B, according to integral shroud first side of three-dimensional coordinate system and designThe first working face, adjust Leaf orientation and make the first working face corresponding with emery wheel, and carry out the first working face and homonymy by emery wheelThe processing of the first non-working surface; After c, the first working face and the first non-working surface completion of processing, upset blade, and carry out bladeDeflection, make second working face of integral shroud the second side of design corresponding with emery wheel, and carry out the processing of the second working face by emery wheel;D, emery wheel be along the biasing that moves radially of emery wheel, carries out the processing with the second non-working surface of the second working face homonymy; E, by sameEmery wheel completes the processing of zigzag crown structure.
Further, the foundation of step a neutral body coordinate system: integral shroud is designed with four non-working surfaces, and each side has the sawtooth of passing throughTwo non-working surfaces that shape face connects; Under the state of the first working face layout corresponding to emery wheel of integral shroud the first side, set leafFour non-working surfaces of hat are laid the X-Y plane that plane is three-dimensional coordinate system; Set emery wheel and lay the X-Z that plane is three-dimensional coordinate systemPlane; Determine X-axis, Y-axis and the Z axis of three-dimensional coordinate system simultaneously.
Further, the concrete implementation step of step b is: adjust four non-working surfaces of integral shroud to be processed, make four inoperativesThe X-Y plane of face in three-dimensional coordinate system; Adjust blade rotate around Z axis, make integral shroud to be processed the first working face sawtooth withThe grinding face of emery wheel coincide up and down; Move up and down and process the first working face and the first non-working surface simultaneously by control emery wheel.
Further, the concrete implementation step of step c is: integral shroud to be processed is realized turning over of blade 180 ° of X-Y plane rotationsTurn; Then by blade around X-axis deflection, make the second working face of integral shroud to be processed perpendicular to X-Y plane, and the second working faceThe grinding face of sawtooth and emery wheel coincide up and down; Move up and down and process the second working face by control emery wheel.
Further, blade is determined around X-axis deflection angle: the quantity according to turbine blade is determined deflection angle, deflection angleBe 360 ° and obtain the deflection angle around X-axis divided by blade quantity.
Further, the concrete implementation step of steps d is: by emery wheel along emery wheel radially to two the second non-works of integral shroud to be processedThe face direction of work is setovered and is carried out the processing of the second non-working surface, thereby forms two with respect to second of the inside biasing of the second working faceNon-working surface.
Further, the second non-working surface is 0.1mm-0.3mm with respect to the inside offset or dish of the second working face.
Further, emery wheel is copy grinding wheel, and the frosting profile of emery wheel is identical with the zigzag face shape of integral shroud; Emery wheel onlyCan move up and down and lay along emery wheel side direction and carry out transverse shifting.
Further, integral shroud to be processed is fixed on Digit Control Machine Tool, is carried out the attitude control to be processed of integral shroud to be processed by Digit Control Machine ToolSystem.
Further, after zigzag integral shroud completion of processing, carry out removing surface, obtain the turbo blade zigzag integral shroud knot of mouldingStructure.
The present invention has following beneficial effect:
The processing method of turbo blade zigzag crown structure of the present invention, sets blade by the relative position relation of integral shroud and emery wheelThe three-dimensional coordinate system shared with emery wheel is the integral shroud attitude that blade is adjusted on basis according to spatial coordinate, to realize same emery wheel pairThe processing of to be processed of the both sides of zigzag integral shroud is easy to process, quick; Owing to adopting a set of emery wheel to carry out zigzag integral shroudProcessing, can save processing cost; And by changing the attitude of zigzag integral shroud, adopt a set of emery wheel to zigzag integral shroudTo be processed of both sides row is processed continuously, can eliminate " connecing tool marks ", ensures the smooth surface of to be processed.
Except object described above, feature and advantage, the present invention also has other object, feature and advantage. BelowWith reference to the accompanying drawings, the present invention is further detailed explanation.
Brief description of the drawings
The accompanying drawing of a part that forms the application is used to provide a further understanding of the present invention, illustrative examples of the present invention andIts explanation is used for explaining the present invention, does 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 is the A-A profile of Fig. 2;
Fig. 2 b is the B-B profile of Fig. 2;
Fig. 2 c is the C-C profile of Fig. 2;
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 be the first working face machining state of the preferred embodiment of the present invention structural representation two;
Fig. 6 is one of structural representation of the second working face machining state of the preferred embodiment of the present invention;
Fig. 7 be the second working face machining state of the preferred embodiment of the present invention structural representation two.
Marginal data:
1, blade; 2, integral shroud to be processed; 201, the first working face; 202, the second working face; 203, the first non-working surface;204, the second non-working surface; 3, emery wheel.
Detailed description of the invention
Below in conjunction with accompanying drawing, embodiments of the invention are elaborated, but the present invention can be limited and be covered by followingMultitude of different ways 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 is thisOne of structural representation of the first working face machining state of invention preferred embodiment; Fig. 5 is first of the preferred embodiment of the present inventionTwo of the structural representation of working face machining state; Fig. 6 is the structure of the second working face machining state of the preferred embodiment of the present inventionOne of schematic diagram; Fig. 7 be the second working face machining state of the preferred embodiment of the present invention structural representation two.
As shown in Figure 3, the processing method of the turbo blade zigzag crown structure of the present embodiment, comprises the following steps: a, foundationRelative position between the non-working surface of integral shroud and emery wheel 3 is set up three-dimensional coordinate system; B, according to the leaf of three-dimensional coordinate system and designBe preced with the first working face 201 of the first side, adjust blade 1 attitude and make the first working face 201 corresponding with emery wheel 3, and pass through emery wheel3 carry out the processing of the first non-working surface 203 of the first working face 201 and homonymy; C, the first working face 201 and the first inoperativeAfter face 203 completion of processing, upset blade 1, and carry out the deflection of blade 1, make the second working face of integral shroud second side of design202 is corresponding with emery wheel 3, and carry out the processing of the second working face 202 by emery wheel 3; D, emery wheel 3 radially move along emery wheel 3Moving biasing, carries out the processing with the second non-working surface 204 of the second working face 202 homonymies; E, complete saw by same emery wheel 3The processing of profile of tooth crown structure. The processing method of turbo blade zigzag crown structure of the present invention, relative by integral shroud and emery wheelThe three-dimensional coordinate system that position relationship setting blade and emery wheel are shared, is the integral shroud attitude that blade is adjusted on basis according to spatial coordinate,To realize the processing of same emery wheel to be processed of the both sides of zigzag integral shroud, easy to process, quick; Owing to adopting a set of emery wheelCarry out the processing of zigzag integral shroud, can save processing cost; And by changing the attitude of zigzag integral shroud, adopt a set of sandWheel is processed continuously to be processed of the both sides of zigzag integral shroud row, can eliminate " connecing tool marks ", ensures the smooth surface of to be processed.
As shown in Figure 4, Figure 5, Figure 6 and Figure 7, in the present embodiment, the foundation of step a neutral body coordinate system: integral shroud is designed withFour non-working surfaces, each side has two non-working surfaces that connect by zigzag face; In the first work of integral shroud the first sideUnder the state of face 201 layout corresponding to emery wheel 3, set four non-working surfaces of integral shroud and lay the X-Y that plane is three-dimensional coordinate systemPlane; Set emery wheel 3 and lay the X-Z plane that plane is three-dimensional coordinate system; Determine simultaneously three-dimensional coordinate system X-axis, Y-axis andZ axis.
As described in Fig. 4 and Fig. 5, in the present embodiment, the concrete implementation step of step b is: adjust integral shroud 2 to be processed fourNon-working surface, makes the X-Y plane of four non-working surfaces in three-dimensional coordinate system; Adjust blade 1 and rotate around Z axis, make to be processedThe sawtooth of the first working face 201 of integral shroud 2 and the grinding face of emery wheel 3 coincide up and down; Move up and down simultaneously by controlling emery wheel 3Process the first working face 201 and the first non-working surface 203.
As shown in Figure 6 and Figure 7, in the present embodiment, the concrete implementation step of step c is: integral shroud 2 to be processed is at X-Y plane180 ° of rotations realize the upset of blade 1; Then by blade 1 around X-axis deflection, make the second working face 202 of integral shroud 2 to be processedPerpendicular to X-Y plane, and the grinding face of the sawtooth of the second working face 202 and emery wheel 3 coincide up and down; By controlling on emery wheel 3Lower movement processes the second working face 202.
As shown in Figure 6 and Figure 7, in the present embodiment, blade 1 is determined around X-axis deflection angle: according to the number of turbine blade 1Amount is determined deflection angle, and deflection angle is 360 ° and obtains the deflection angle around X-axis divided by blade 1 quantity.
As shown in Figure 6 and Figure 7, in the present embodiment, the concrete implementation step of steps d is: by emery wheel 3 along emery wheel 3 radially toTwo the second non-working surface 204 directions of integral shroud 2 to be processed are setovered and are carried out the processing of the second non-working surface 204, thereby formTwo with respect to inwardly the second non-working surface 204 of biasing of the second working face 202.
As shown in Figure 6 and Figure 7, in the present embodiment, the second non-working surface 204 is with respect to the inside biasing of the second working face 202Distance is 0.1mm-0.3mm.
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. the frosting of emery wheel 3Profile is identical with the zigzag face shape of integral shroud; Emery wheel 3 only can move up and down and carry out horizontal stroke along emery wheel 3 side cloth set directionsTo movement.
In the present embodiment, integral shroud 2 to be processed is fixed on Digit Control Machine Tool, carries out the to be processed of integral shroud 2 to be processed by Digit Control Machine ToolAttitude control.
In the present embodiment, after zigzag integral shroud completion of processing, carry out removing surface, obtain the turbo blade zigzag integral shroud of mouldingStructure.
When enforcement, provide a kind of processing method of turbo blade zigzag crown structure. Zigzag integral shroud designs as shown in Figure 1,First design a first zigzag face perpendicular to X-Y plane (the first working face 201 and the first non-working surface 203), by the left sideIntegral shroud cuts away; Then blade 1 overturn and the first working face 201 rotated to 7.2 degree around X-axis and (suppose it is 50 blades, angleDegree is 360/50) become the second working face 202, the second working faces 202 the right integral shroud is cut away, then by the second non-working surface 2040.2mm inward setovers.
Concrete implementation step is as follows:
Add and first the first zigzag face (the first working face 201 and the first non-working surface 203) is ground man-hour. By Fig. 5 and Fig. 6Known, emery wheel 3 is copy grinding wheel, identical with zigzag face shape. Emery wheel 3 can only be up and down with horizontal except self rotatesMobile, when saw gumming bit by bit down precession until be ground to position.
Be mill the second working face 202 with that, first blade 1 adjusted to turnback, then it is spent around X-axis deflection 7.2. ByFig. 6 and Fig. 7 can find out, after X-axis is rotated 7.2 degree, inclined-plane the second working face 202 originally become one verticalIn the face of " X-Y plane ", emery wheel 3 just can process this face like this; Again the second non-working surface 204 is setovered inward0.2mm, grinds the second non-working surface 204. There is deflection angle with respect to the second working face 202 in the second non-working surface 204. ByThis is visible, and this structure of the present invention only just can grind integral shroud with a set of emery wheel, easy to process, quick, cost-saving.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for those skilled in the art, the present invention can have various modifications and variations. Within the spirit and principles in the present invention all, any amendment of doing, etc.With replacement, improvement etc., within all should being included in protection scope of the present invention.
Claims (10)
1. a processing method for turbo blade zigzag crown structure, is characterized in that, comprises the following steps:
A, set up three-dimensional coordinate system according to the relative position between non-working surface and the emery wheel (3) of integral shroud;
B, according to first working face (201) of integral shroud first side of three-dimensional coordinate system and design, adjust blade (1)Attitude makes the first working face (201) corresponding with emery wheel (3), and carries out the first working face (201) by emery wheel (3)Processing with first non-working surface (203) of homonymy;
After c, the first working face (201) and the first non-working surface (203) completion of processing, upset blade (1), and carry outThe deflection of blade (1), makes second working face (202) of integral shroud the second side designing corresponding with emery wheel (3), and passes throughEmery wheel (3) carries out the processing of the second working face (202);
D, emery wheel (3), along the biasing that moves radially of emery wheel (3), carry out and second of the second working face (202) homonymyThe processing of non-working surface (204);
E, complete the processing of zigzag crown structure by same emery wheel (3).
2. the processing method of turbo blade zigzag crown structure according to claim 1, is characterized in that,
The foundation of described step a neutral body coordinate system:
Integral shroud is designed with four non-working surfaces, and each side has two non-working surfaces that connect by zigzag face;
Under first working face (201) of integral shroud the first side and the state of the corresponding layout of emery wheel (3), setting integral shroudFour non-working surfaces are laid the X-Y plane that plane is three-dimensional coordinate system; Setting emery wheel (3) laying plane is three-dimensional coordinate systemX-Z plane; Determine X-axis, Y-axis and the Z axis of three-dimensional coordinate system simultaneously.
3. the processing method of turbo blade zigzag crown structure according to claim 2, is characterized in that,
The concrete implementation step of described step b is:
Adjust four non-working surfaces of integral shroud to be processed (2), make the X-Y plane of four non-working surfaces in three-dimensional coordinate system;
Adjust blade (1) and rotate around Z axis, make sawtooth and the emery wheel of first working face (201) of integral shroud to be processed (2)(3) grinding face coincide up and down;
Move up and down and process the first working face (201) and the first non-working surface (203) simultaneously by control emery wheel (3).
4. the processing method of turbo blade zigzag crown structure according to claim 2, is characterized in that,
The concrete implementation step of described step c is:
Integral shroud to be processed (2) is realized the upset of blade (1) 180 ° of X-Y plane rotations;
Then by blade (1) around X-axis deflection, make second working face (202) of integral shroud to be processed (2) perpendicular to X-YPlane, and the grinding face of the sawtooth of the second working face (202) and emery wheel (3) coincide up and down;
Move up and down and process the second working face (202) by control emery wheel (3).
5. the processing method of turbo blade zigzag crown structure according to claim 4, is characterized in that,
Described blade (1) is determined around X-axis deflection angle:
Quantity according to turbine blade (1) is determined deflection angle,
Deflection angle is 360 ° and obtains the deflection angle around X-axis divided by blade (1) quantity.
6. the processing method of turbo blade zigzag crown structure according to claim 4, is characterized in that,
The concrete implementation step of described steps d is:
By emery wheel (3) along emery wheel (3) radially to two the second non-working surfaces (204) direction of integral shroud to be processed (2)Setover and carry out the processing of the second non-working surface (204), thereby with respect to the second working face (202) inwardly forming twoSecond non-working surface (204) of biasing.
7. the processing method of turbo blade zigzag crown structure according to claim 6, is characterized in that,
Described the second non-working surface (204) is 0.1mm-0.3mm with respect to the inside offset or dish of the second working face (202).
8. according to the processing method of the turbo blade zigzag crown structure described in any one in claim 1 to 7, it is characterized in that,
Described emery wheel (3) is copy grinding wheel (3), i.e. the frosting profile of described emery wheel (3) and the zigzag face of integral shroudShape is identical;
Described emery wheel (3) only can move up and down and carry out transverse shifting along emery wheel (3) side cloth set direction.
9. according to the processing method of the turbo blade zigzag crown structure described in any one in claim 1 to 7, it is characterized in that,
Integral shroud to be processed (2) is fixed on Digit Control Machine Tool, is carried out the appearance to be processed of integral shroud to be processed (2) by Digit Control Machine ToolState control.
10. according to the processing method of the turbo blade zigzag crown structure described in any one in claim 1 to 7, it is characterized in that,
After zigzag integral shroud completion of processing, carry out removing surface, obtain the turbo blade zigzag crown structure of moulding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610149313.2A CN105598790B (en) | 2016-03-16 | 2016-03-16 | The processing method of turbo blade zigzag crown structure |
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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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| CN105598790A true CN105598790A (en) | 2016-05-25 |
| CN105598790B CN105598790B (en) | 2017-12-19 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107457615A (en) * | 2017-09-04 | 2017-12-12 | 中国航发南方工业有限公司 | The grinding processing method of turbo blade step surface |
| CN109227224A (en) * | 2018-09-13 | 2019-01-18 | 沈阳透平机械股份有限公司 | The stator blade method for grinding of axial flow compressor |
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| CN105312864A (en) * | 2015-12-09 | 2016-02-10 | 中国南方航空工业(集团)有限公司 | Machining method of turbine working blade |
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| US4285108A (en) * | 1979-02-23 | 1981-08-25 | United Technologies Corporation | Apparatus and method for refinishing turbine blade airseals |
| US20040056399A1 (en) * | 2002-09-24 | 2004-03-25 | Jones Daniel Edward | Methods and apparatus for securing components for manufacture |
| CN1881118A (en) * | 2005-06-09 | 2006-12-20 | 通用电气公司 | System and method for adjusting performance of manufacturing operations or steps |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107457615A (en) * | 2017-09-04 | 2017-12-12 | 中国航发南方工业有限公司 | The grinding processing method of turbo blade step surface |
| 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 |
| CN109227224A (en) * | 2018-09-13 | 2019-01-18 | 沈阳透平机械股份有限公司 | The stator blade method for grinding of axial flow compressor |
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| Publication number | Publication date |
|---|---|
| CN105598790B (en) | 2017-12-19 |
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