CN106825614A - A kind of aero-compressor hubcap profile surface processing method - Google Patents
A kind of aero-compressor hubcap profile surface processing method Download PDFInfo
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- CN106825614A CN106825614A CN201710130743.4A CN201710130743A CN106825614A CN 106825614 A CN106825614 A CN 106825614A CN 201710130743 A CN201710130743 A CN 201710130743A CN 106825614 A CN106825614 A CN 106825614A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B1/00—Methods for turning or working essentially requiring the use of turning-machines; Use of auxiliary equipment in connection with such methods
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Abstract
The invention discloses a kind of aero-compressor hubcap profile surface processing method, the situation of interruption hole, hard sprayed coating is there are for parts profile face, invent a kind of method in machining profile face, reduce the cutting force that cutter is applied to part to greatest extent, ensure that contoured surface is not acted on and deformed by external force, it is ensured that contoured surface size qualification.To realize：1. avoid the knife that shakes occurred during the interrupted hole of tool sharpening, allow knife phenomenon；The excessive cutting force produced when 2. eliminating tool sharpening hard coat；3. effectively control or reduce the cutting deformation and stress released-deformation of part.
Description
Technical field
The present invention relates to contoured surface processing technique field, more particularly to a kind of aero-compressor hubcap profile surface processing method.
Background technology
The material of existing hood of calming the anger is wrought superalloy, major diameter, wall thickness ultra-thin (0.5-2mm), contoured surface essence
Degree annular class part high, such part shape is irregular, and wall unevenness is even and surface has hard coat, and structural rigidity is not
Foot, machinability is poor, and contoured surface is easily deformed by external force.Such part is mainly used in aero-engine manufacture field.
Certain company's model is calmed the anger hood, size：φ 450mm × φ 230mm × 100mm, minimum wall thickness (MINI W.)：0.5mm, belongs to
Ultra-thin-wall annular element, in irregular shape, poor structure rigidity；Material is nickel base superalloy, and Tool in Cutting is poor, easily by external force
Deformation；There is the interruption hole of 2 groups of different sizes and position on parts profile face, as shown in figure 1, Fig. 1 is aviation of the prior art
Calm the anger the structural representation of hood, cutter is constituted interrupted cut, cutter has the knife that shakes, allow knife phenomenon, and then causes part to become
Shape, as shown in Fig. 2 Fig. 2 is the schematic diagram of aero-compressor cover procedure of processing of the prior art.
Prior art is as follows：1. tool sharpening route and order：Rough turn lubrication groove profile surface (see Fig. 2, route 1) → rough turn
Profile end face (see Fig. 2, route 2) → rough turn skewed slot (see Fig. 2, route 3) → rough turn outer mold surface is (see Fig. 2, route 4,5) → smart car
Skewed slot (see Fig. 2, route 6) → smart car lubrication groove profile surface (see Fig. 2, route 7) → smart car outer mold surface cylindrical (see Fig. 2, route 8) → essence
Car outer mold surface end face (see Fig. 2, route 9) → smart car profile end face (see Fig. 2, route 10)；
Processing the problem for producing has：1. due to the presence in interruption hole, cutter constitutes interrupted cut, there is the knife that shakes, allows knife to show
As while the cutting force for being applied to part is uneven；Cutter is easy to wear, and then increases cutting force, part lubrication groove profile surface, profile base
End face is acted on and deformed by cutting force at quasi- end face A, the first interruption hole；
2. because diameter of part is big and wall is thin, parts profile face exist cutter shake knife, allow knife phenomenon, it is flat relative to benchmark
Face degree, the depth of parallelism, surface profile cannot ensure；
3. after unloading part, in a free state, due to cutting stress release, parts profile face size is with fixture about for part
Dimension measurement result is inconsistent under pencil state, and size is seriously overproof, it is impossible to ensure qualified；
4. because sprayed coating hardness is high, surface irregularity, coating layer thickness is uneven, causes Tool in Cutting power unequal,
Part is acted on by cutting force and forms irregular deformation..
Specifically, its problem is：
1. the knife that shakes occurred during the interrupted hole of tool sharpening cannot be avoided, knife phenomenon is allowed；
The excessive cutting force produced when 2. cannot eliminate tool sharpening hard coat；
3. cannot effectively control or reduce the cutting deformation and stress released-deformation of part.
The content of the invention
In view of this, it is an object of the invention to provide a kind of aero-compressor hubcap profile surface processing method, to realize：
1. avoid the knife that shakes occurred during the interrupted hole of tool sharpening, allow knife phenomenon；
The excessive cutting force produced when 2. eliminating tool sharpening hard coat；
3. effectively control or reduce the cutting deformation and stress released-deformation of part.
In order to achieve the above object, the present invention provides following technical scheme：
A kind of aero-compressor hubcap profile surface processing method, for processing the ultra-thin-wall ring with hard coat and interruption hole
Shape part contoured surface, it is characterised in that including：
Step 1) skewed slot on rough turn aero-compressor cover,
The cross-sectional edge point of the skewed slot is point E1 and point G, and the point E1 is than the point G closer to outer rim；
Step 2) rough turn lubrication groove profile surface,
The Internal periphery face has the hard coat of arc, and its cross-sectional edge point is point A and point C, and point C is located at profile end face
With the lubrication groove profile surface junction, selected point B, as cutter starting point, is cutter and institute at the point B between point A and point C
The upper angle and lower angle for stating the contact point of hard coat are equal, then according to point B to point A- points B to point C- point B to point
A- points B to point C carries out rough turn；
Step 3) end face at rough turn interruption hole,
Wherein, the cross-sectional edge point of profile end face be point F and point C, the point F than the point C closer to outer rim, it is described
The point G and point F is located in the same horizontal line of cross section, has one second interruption hole, institute at the interruption hole on end face
State the cross-sectional edge point in the second interruption hole for point E and point D, the point E than the point D closer to outer rim, the point E and described
It is end face at the interruption hole between point D, its cutting direction is from the point E to the point D；
Step 4) rough turn profile end face,
Its direction is from the point C to the point F；
Step 5) rough turn outer mold surface end face,
The cross-sectional edge point of the top end face of the aero-compressor cover is the point G1 and point F1 in same level, described
Point G1 is located at the left side of the point F1, and the point F1 is interrupted hole between the point E1 with first, in cross section vertical direction
The upper point F1 to the point F is outer mold surface end face, and its direction is from the point F1 to the point F；
Step 6) rough turn outer mold surface is cylindrical,
The point G1 to the point F is that outer mold surface is cylindrical, and its direction is from point G1 described in the point F；
Step 7) skewed slot described in smart car；
Step 8) end face at interruption hole described in half smart car,
Its cutting direction is from the point E to the point D；
Step 9) lubrication groove profile surface described in smart car part,
Its cutting direction is the point B to the point A；
Step 10) the rough turn part lubrication groove profile surface and whole profile end faces,
Its cutting direction is the point B to the point F；
Step 11) outer mold surface described in smart car is cylindrical,
Its direction is from point G1 described in the point F1；
Step 12) outer mold surface end face described in smart car,
Its direction is from the point F1 to the point F；Step 13) profile end face described in refine,
Its direction is from the point C to the point F；
Step 14) outer mold surface end face described in refine,
Its direction is from the point F1 to the point E1；
Step 15) refine benchmark is cylindrical.
Preferably, above-mentioned steps 2) and the step 4) in cutter for same be Boring cutter, its parameter be R0.8*80 °.
Preferably, above-mentioned steps 9), step 10), step 13) in cutter used be cylindrical cutter, its parameter is R0.8*
80°。
Preferably, above-mentioned steps 1), the step 7) in cutter used be skewed slot knife.
Preferably, above-mentioned steps 3), the step 8) in cutter used be right-hand cutter, its parameter is R0.8*35 °.
Preferably, above-mentioned steps 5), the step 6), the step 11), the step 12), the step 14), it is described
Step 15) in cutter used be cylindrical cutter, its parameter is R0.8*80 °.
Preferably, roughing is 0.3-0.8mm, and it is 0.15-0.2mm to finish, and refine is 0-0.05mm.
Preferably, above-mentioned steps 2) in point B to point A- points B to point C- points B extremely point A- points B extremely point C carry out it is rough turn, specifically
For the roughing in one group of point B to point A- points B to point C above is 0.3mm.
Preferably, upper coarse-fine processing rotating speed S=30 rev/min, feed speed F=0.1 millimeters/every turn, the first interruption
Rotating speed S=15 rev/min, feed speed F=0.1 millimeters/every turn at hole and the second interruption hole.
The aero-compressor hubcap profile surface processing method that the present invention is provided, interruption hole, hard is there are for parts profile face
The situation of matter sprayed coating, invents a kind of method in machining profile face, and the cutting force that cutter is applied to part is reduced to greatest extent,
Ensure that contoured surface is not acted on and deformed by external force, it is ensured that contoured surface size qualification.
The present invention provide aero-compressor hubcap profile surface processing method primarily directed to：
(1) the processing of hard sprayed coating：1. the processing of lubrication groove profile surface hard sprayed coating is divided into two using point B as separation
Duan Jiagong, reason：Increase blade and the angle of part machined surface, reduce cutting force and are easy to chip removal；2. in step 2 point B to point
Removed in one group of point B to point A- points B to point C before in A- points B to point C- points B to point A- points B to point C convex at lubrication groove profile surface
The coating layer thickness for rising, makes sprayed coating smooth, is that rough turn lubrication groove profile surface preparation is uniformly in one group of point B below to point A- points B to point C
Roughing surplus, it is to avoid produce excessive cutting force and cause part to be in irregular deformation.
(2) the processing at the first interruption hole：1. semifinishing first is interrupted end face at hole in step 12, and removal is most of remaining
Amount, while eliminating rough machined stress deformation；2. due to first interruption hole at wall thickness it is most thin, deform most serious, arrange step 14
End face at the last interruption of refine first hole, eliminates end face because cutter shakes knife, the deformation that allows knife to cause, it is ensured that the depth of parallelism is qualified；
(3) the processing at the second interruption hole：1. step 3 removal second is arranged to be interrupted the roughing surplus of end face at hole, it is to avoid
Occur causing the cutting force excessive deformation for causing due to the change of cutter moment cutting state during the rough turn profile end face of step 4；②
Step 8 semifinishing profile end face is arranged, rough machined stress deformation is eliminated；3. step 13 is arranged in last time processing refine
End face at profile end face and the second interruption hole, eliminates the stress deformation of end face, it is ensured that benchmark A flatnesses size and surface profile chi
It is very little；
(4) the processing of benchmark B：The step 15 final stage cylindrical B of refine benchmark is arranged, the deformation of benchmark B is eliminated, it is ensured that base
Quasi- B is correct；
(5) Roughing and fine machining cutter is separated, it is to avoid because of the part deformation that tool wear causes.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
The accompanying drawing to be used needed for having technology description is briefly described, it should be apparent that, drawings in the following description are the present invention
Some embodiments, for those of ordinary skill in the art, on the premise of not paying creative work, can also basis
These accompanying drawings obtain other accompanying drawings.
Fig. 1 is the structural representation of aero-compressor cover of the prior art；
Fig. 2 is the schematic diagram of aero-compressor cover procedure of processing of the prior art
The step of Fig. 3 is aero-compressor hubcap profile surface processing method provided in an embodiment of the present invention schematic diagram.
In figure 1 above -3：
Interruption hole 1, interruption hole 2.
Specific embodiment
To make the purpose, technical scheme and advantage of the embodiment of the present invention clearer, below in conjunction with the embodiment of the present invention
In accompanying drawing, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that described embodiment is
A part of embodiment of the present invention, rather than whole embodiments.Based on the embodiment in the present invention, those of ordinary skill in the art
The every other embodiment obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.
Fig. 2 is refer to, Fig. 2 is the structural representation of aero-compressor hubcap profile surface processing method provided in an embodiment of the present invention
Figure.
Aero-compressor hubcap profile surface processing method provided in an embodiment of the present invention, for process have hard coat and
The ultra-thin-wall annular element contoured surface in disconnected hole, including：
Step 1) skewed slot on rough turn aero-compressor cover, (label 1 in corresponding diagram 3)
The cross-sectional edge point of skewed slot is point E1 and point G, and point E1 is than point G closer to outer rim；
Step 2) rough turn lubrication groove profile surface, (label 2,3,4,5 in corresponding diagram 3)
The Internal periphery face has the hard coat of arc, and its cross-sectional edge point is point A and point C, and point C is located at profile end face
With lubrication groove profile surface junction, selected point B is cutter and hard coat as cutter starting point, at point B between point A and point C
The upper angle of contact point and lower angle are equal, are then entered according to point B to point A- points B to point C- points B to point A- points B to point C
Row is rough turn；
Step 3) end face, (label 6 in corresponding diagram 3) at rough turn interruption hole
Wherein, the cross-sectional edge point of profile end face is that point F and point C, point F are located at than point C closer to outer rim, point G and point F
In the same horizontal line of cross section, there is one second interruption hole 2, the cross section side in the second interruption hole 2 at interruption hole on end face
Edge point is that point E and point D, point E are end face at interruption hole than point D closer to outer rim, between point E and point D, and its cutting direction is from point
E to point D；
Step 4) rough turn profile end face, (label 7 in corresponding diagram 3)
Its direction is from point C to point F；
Step 5) rough turn outer mold surface end face, (label 8 in corresponding diagram 3)
The cross-sectional edge point of the top end face of aero-compressor cover is point G1 and point F1 in same level, and point G1 is located at
The left side of point F1, has the first interruption hole 1 between point F1 to point E1, point F1 to point F is outer mold surface on the vertical direction of cross section
End face, its direction is from point F1 to point F；
Step 6) rough turn outer mold surface is cylindrical, (label 9 in corresponding diagram 3)
Point G1 to point F is that outer mold surface is cylindrical, and its direction is from point F points G1；
Step 7) smart car skewed slot；(label 10 in corresponding diagram 3)
Step 8) half smart car interruption hole at end face, (label 11 in corresponding diagram 3)
Its cutting direction is from point E to point D；
Step 9) smart car part lubrication groove profile surface, (label 12 in corresponding diagram 3)
Its cutting direction is point B to point A；
Step 10) rough turn part lubrication groove profile surface and whole profile end faces, (label 13 in corresponding diagram 3)
Its cutting direction is point B to point F；
Step 11) smart car outer mold surface is cylindrical, (label 14 in corresponding diagram 3)
Its direction is from point F1 points G1；
Step 12) smart car outer mold surface end face, (label 15 in corresponding diagram 3)
Its direction is from point F1 to point F；
Step 13) refine profile end face, (label 16 in corresponding diagram 3)
Its direction is from point C to point F；
Step 14) refine outer mold surface end face, (label 17 in corresponding diagram 3)
Its direction is from point F1 to point E1；
Step 15) refine benchmark is cylindrical, (label 18 in corresponding diagram 3).
Aero-compressor hubcap profile surface processing method provided in an embodiment of the present invention, interruption is there are for parts profile face
Hole, the situation of hard sprayed coating, invent a kind of method in machining profile face, cutter is reduced to greatest extent and is applied to cutting for part
Cut power, it is ensured that contoured surface is not acted on and deformed by external force, it is ensured that contoured surface size qualification.
Aero-compressor hubcap profile surface processing method provided in an embodiment of the present invention primarily directed to：
(1) the processing of hard sprayed coating：1. the processing of lubrication groove profile surface hard sprayed coating is divided into two using point B as separation
Duan Jiagong, reason：Increase blade and the angle of part machined surface, reduce cutting force and are easy to chip removal；2. in step 2 point B to point
Removed in one group of point B to point A- points B to point C before in A- points B to point C- points B to point A- points B to point C convex at lubrication groove profile surface
The coating layer thickness for rising, makes sprayed coating smooth, is that rough turn lubrication groove profile surface preparation is uniformly in one group of point B below to point A- points B to point C
Roughing surplus, it is to avoid produce excessive cutting force and cause part to be in irregular deformation.
(2) the processing at the first interruption hole 1：1. semifinishing first is interrupted end face at hole 1 in step 12, and removal is most of
Surplus, while eliminating rough machined stress deformation；2. due to first interruption hole 1 at wall thickness it is most thin, deform most serious, arrange step
14 last refine first are interrupted end face at holes 1, eliminate end face because cutter shakes knife, the deformation that allows knife to cause, it is ensured that the depth of parallelism is closed
Lattice；
(3) the processing at the second interruption hole 2：1. arrange step 3 removal second to be interrupted the roughing surplus of end face at hole 2, keep away
Exempt to occur because the change of cutter moment cutting state causes the excessive deformation for causing of cutting force during the rough turn profile end face of step 4；
2. step 8 semifinishing profile end face is arranged, rough machined stress deformation is eliminated；3. step 13 is arranged to process essence in last time
End face at profile end face and the second interruption hole 2 is repaiied, the stress deformation of end face is eliminated, it is ensured that benchmark A flatnesses size and facial contour
Degree size；
(4) the processing of benchmark B：The step 15 final stage cylindrical B of refine benchmark is arranged, the deformation of benchmark B is eliminated, it is ensured that base
Quasi- B is correct；
(5) Roughing and fine machining cutter is separated, it is to avoid because of the part deformation that tool wear causes.
Wherein, step 2) and step 4) in cutter for same be Boring cutter, its parameter be R0.8*80 °.Step 9), step
10), step 13) in cutter used be cylindrical cutter, its parameter is R0.8*80 °.Step 1), step 7) in cutter used be
Skewed slot knife.Step 3), step 8) in cutter used be right-hand cutter, its parameter is R0.8*35 °.Step 5), step 6), step
11), step 12), step 14), step 15) in cutter used be cylindrical cutter, its parameter is R0.8*80 °.Roughing is 0.3-
0.8mm, it is 0.15-0.2mm to finish, and refine is 0-0.05mm.Step 2) in point B to point A- points B extremely point C- point B to point A-
Point B to point C carry out it is rough turn, specifically, the roughing in one group of point B above to point A- points B extremely point C is 0.3mm.Coarse-fine processing
Rotating speed S=30 rev/min, feed speed F=0.1 millimeters/every turn, rotating speed S=at the first interruption hole 1 and second interruption hole 2
15 rev/min, feed speed F=0.1 millimeters/every turn.
The foregoing description of the disclosed embodiments, enables professional and technical personnel in the field to realize or uses the present invention.
Various modifications to these embodiments will be apparent for those skilled in the art, as defined herein
General Principle can be realized in other embodiments without departing from the spirit or scope of the present invention.Therefore, the present invention
The embodiments shown herein is not intended to be limited to, and is to fit to and principles disclosed herein and features of novelty phase one
The scope most wide for causing.
Claims (9)
1. a kind of aero-compressor hubcap profile surface processing method, has the ultra-thin wall circular of hard coat and interruption hole for processing
Part contoured surface, it is characterised in that including：
Step 1) skewed slot on rough turn aero-compressor cover,
The cross-sectional edge point of the skewed slot is point E1 and point G, and the point E1 is than the point G closer to outer rim；
Step 2) rough turn lubrication groove profile surface,
The Internal periphery face has the hard coat of arc, and its cross-sectional edge point is point A and point C, and point C is located at profile end face and institute
Lubrication groove profile surface junction is stated, selected point B is that cutter is hard with described as cutter starting point, at the point B between point A and point C
The upper angle of the contact point of matter coating and lower angle are equal, then according to point B to point A- points B to point C- points B to point A- points B
Carried out to point C rough turn；
Step 3) end face at rough turn interruption hole,
Wherein, the cross-sectional edge point of profile end face be point F and point C, the point F than the point C closer to outer rim, the point G
It is located in the same horizontal line of cross section with the point F, there is one second interruption hole, described the at the interruption hole on end face
The cross-sectional edge points in two interruption holes for point E and point D, the point E than the point D closer to outer rim, the point E and point D
Between be end face at the interruption hole, its cutting direction is from the point E to the point D；
Step 4) rough turn profile end face,
Its direction is from the point C to the point F；
Step 5) rough turn outer mold surface end face,
The cross-sectional edge point of the top end face of the aero-compressor cover is point G1 and point F1, the point G1 in same level
Positioned at the left side of the point F1, the point F1 is interrupted hole, the institute on the vertical direction of cross section between the point E1 with first
Point F1 to the point F is stated for outer mold surface end face, its direction is from the point F1 to the point F；
Step 6) rough turn outer mold surface is cylindrical,
The point G1 to the point F is that outer mold surface is cylindrical, and its direction is from point G1 described in the point F；9
Step 7) skewed slot described in smart car；
Step 8) end face at interruption hole described in half smart car,
Its cutting direction is from the point E to the point D；
Step 9) lubrication groove profile surface described in smart car part,
Its cutting direction is the point B to the point A；
Step 10) the rough turn part lubrication groove profile surface and whole profile end faces,
Its cutting direction is the point B to the point F；
Step 11) outer mold surface described in smart car is cylindrical,
Its direction is from point G1 described in the point F1；
Step 12) outer mold surface end face described in smart car,
Its direction is from the point F1 to the point F；
Step 13) profile end face described in refine,
Its direction is from the point C to the point F；
Step 14) outer mold surface end face described in refine,
Its direction is from the point F1 to the point E1；
Step 15) refine benchmark is cylindrical.
2. aero-compressor hubcap profile surface processing method according to claim 1, it is characterised in that the step 2) and institute
State step 4) in cutter for same be Boring cutter, its parameter be R0.8*80 °.
3. aero-compressor hubcap profile surface processing method according to claim 1, it is characterised in that the step 9), step
It is rapid 10), step 13) in cutter used be cylindrical cutter, its parameter is R0.8*80 °.
4. aero-compressor hubcap profile surface processing method according to claim 1, it is characterised in that the step 1), institute
State step 7) in cutter used be skewed slot knife.
5. aero-compressor hubcap profile surface processing method according to claim 1, it is characterised in that the step 3), institute
State step 8) in cutter used be right-hand cutter, its parameter is R0.8*35 °.
6. aero-compressor hubcap profile surface processing method according to claim 1, it is characterised in that the step 5), institute
State step 6), the step 11), the step 12), the step 14), the step 15) in cutter used be cylindrical cutter,
Its parameter is R0.8*80 °.
7. aero-compressor hubcap profile surface processing method according to claim 1, it is characterised in that roughing is 0.3-
0.8mm, it is 0.15-0.2mm to finish, and refine is 0-0.05mm.
8. aero-compressor hubcap profile surface processing method according to claim 7, it is characterised in that the step 2) in
Point B to point A- points B to point C- points B to point A- points B extremely point C carry out it is rough turn, specifically, one group of point B above extremely point A- point B are to point
Roughing in C is 0.3mm.
9. aero-compressor hubcap profile surface processing method according to claim 1, it is characterised in that coarse-fine processing rotating speed S
Rotating speed S=15 rpms at=30 rev/min, feed speed F=0.1 millimeters/every turn first interruption hole and the second interruption hole
Clock, feed speed F=0.1 millimeters/every turn.
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| CN107537951A (en) * | 2017-10-27 | 2018-01-05 | 湖南南方通用航空发动机有限公司 | One kind is calmed the anger hood horn mouth part forming methods |
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| CN103753110A (en) * | 2014-01-09 | 2014-04-30 | 北华航天工业学院 | Thin-wall elliptical part numerical control machining method |
| CN105081681A (en) * | 2014-05-20 | 2015-11-25 | 哈尔滨飞机工业集团有限责任公司 | Machining method for helicopter fairing supporting piece |
| CN104097041A (en) * | 2014-06-30 | 2014-10-15 | 中国南方航空工业(集团)有限公司 | Processing method for barrel type thin-walled part |
| CN105312647A (en) * | 2015-12-02 | 2016-02-10 | 中国南方航空工业(集团)有限公司 | Processing method of thin vanes of engines |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107537951A (en) * | 2017-10-27 | 2018-01-05 | 湖南南方通用航空发动机有限公司 | One kind is calmed the anger hood horn mouth part forming methods |
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Address after: 412000 No. 2 Airway Road, Lusong District, Zhuzhou City, Hunan Province Patentee after: Hunan Nanfang General Aviation Engine Co., Ltd. Address before: 412000 No. 2 Airway Road, Lusong District, Zhuzhou City, Hunan Province Patentee before: AVIC HUNAN GENERAL AVIATION ENGINE CO., LTD. |