CN106825614B - 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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- CN106825614B CN106825614B CN201710130743.4A CN201710130743A CN106825614B CN 106825614 B CN106825614 B CN 106825614B CN 201710130743 A CN201710130743 A CN 201710130743A CN 106825614 B CN106825614 B CN 106825614B
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- 238000005520 cutting process Methods 0.000 claims abstract description 36
- 238000005461 lubrication Methods 0.000 claims description 21
- 239000011248 coating agent Substances 0.000 claims 1
- 238000000576 coating method Methods 0.000 claims 1
- 238000005507 spraying Methods 0.000 abstract description 10
- 238000003754 machining Methods 0.000 abstract description 5
- 238000010586 diagram Methods 0.000 description 20
- 230000000875 corresponding Effects 0.000 description 15
- 238000000034 method Methods 0.000 description 7
- 230000001788 irregular Effects 0.000 description 5
- 239000011247 coating layer Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- PXHVJJICTQNCMI-UHFFFAOYSA-N nickel Chemical compound data:image/svg+xml;base64,PD94bWwgdmVyc2lvbj0nMS4wJyBlbmNvZGluZz0naXNvLTg4NTktMSc/Pgo8c3ZnIHZlcnNpb249JzEuMScgYmFzZVByb2ZpbGU9J2Z1bGwnCiAgICAgICAgICAgICAgeG1sbnM9J2h0dHA6Ly93d3cudzMub3JnLzIwMDAvc3ZnJwogICAgICAgICAgICAgICAgICAgICAgeG1sbnM6cmRraXQ9J2h0dHA6Ly93d3cucmRraXQub3JnL3htbCcKICAgICAgICAgICAgICAgICAgICAgIHhtbG5zOnhsaW5rPSdodHRwOi8vd3d3LnczLm9yZy8xOTk5L3hsaW5rJwogICAgICAgICAgICAgICAgICB4bWw6c3BhY2U9J3ByZXNlcnZlJwp3aWR0aD0nMzAwcHgnIGhlaWdodD0nMzAwcHgnIHZpZXdCb3g9JzAgMCAzMDAgMzAwJz4KPCEtLSBFTkQgT0YgSEVBREVSIC0tPgo8cmVjdCBzdHlsZT0nb3BhY2l0eToxLjA7ZmlsbDojRkZGRkZGO3N0cm9rZTpub25lJyB3aWR0aD0nMzAwLjAnIGhlaWdodD0nMzAwLjAnIHg9JzAuMCcgeT0nMC4wJz4gPC9yZWN0Pgo8dGV4dCB4PScxMzguMCcgeT0nMTcwLjAnIGNsYXNzPSdhdG9tLTAnIHN0eWxlPSdmb250LXNpemU6NDBweDtmb250LXN0eWxlOm5vcm1hbDtmb250LXdlaWdodDpub3JtYWw7ZmlsbC1vcGFjaXR5OjE7c3Ryb2tlOm5vbmU7Zm9udC1mYW1pbHk6c2Fucy1zZXJpZjt0ZXh0LWFuY2hvcjpzdGFydDtmaWxsOiMzQjQxNDMnID5OPC90ZXh0Pgo8dGV4dCB4PScxNjUuNicgeT0nMTcwLjAnIGNsYXNzPSdhdG9tLTAnIHN0eWxlPSdmb250LXNpemU6NDBweDtmb250LXN0eWxlOm5vcm1hbDtmb250LXdlaWdodDpub3JtYWw7ZmlsbC1vcGFjaXR5OjE7c3Ryb2tlOm5vbmU7Zm9udC1mYW1pbHk6c2Fucy1zZXJpZjt0ZXh0LWFuY2hvcjpzdGFydDtmaWxsOiMzQjQxNDMnID5pPC90ZXh0Pgo8L3N2Zz4K data:image/svg+xml;base64,PD94bWwgdmVyc2lvbj0nMS4wJyBlbmNvZGluZz0naXNvLTg4NTktMSc/Pgo8c3ZnIHZlcnNpb249JzEuMScgYmFzZVByb2ZpbGU9J2Z1bGwnCiAgICAgICAgICAgICAgeG1sbnM9J2h0dHA6Ly93d3cudzMub3JnLzIwMDAvc3ZnJwogICAgICAgICAgICAgICAgICAgICAgeG1sbnM6cmRraXQ9J2h0dHA6Ly93d3cucmRraXQub3JnL3htbCcKICAgICAgICAgICAgICAgICAgICAgIHhtbG5zOnhsaW5rPSdodHRwOi8vd3d3LnczLm9yZy8xOTk5L3hsaW5rJwogICAgICAgICAgICAgICAgICB4bWw6c3BhY2U9J3ByZXNlcnZlJwp3aWR0aD0nODVweCcgaGVpZ2h0PSc4NXB4JyB2aWV3Qm94PScwIDAgODUgODUnPgo8IS0tIEVORCBPRiBIRUFERVIgLS0+CjxyZWN0IHN0eWxlPSdvcGFjaXR5OjEuMDtmaWxsOiNGRkZGRkY7c3Ryb2tlOm5vbmUnIHdpZHRoPSc4NS4wJyBoZWlnaHQ9Jzg1LjAnIHg9JzAuMCcgeT0nMC4wJz4gPC9yZWN0Pgo8dGV4dCB4PSczNS4wJyB5PSc1My42JyBjbGFzcz0nYXRvbS0wJyBzdHlsZT0nZm9udC1zaXplOjIzcHg7Zm9udC1zdHlsZTpub3JtYWw7Zm9udC13ZWlnaHQ6bm9ybWFsO2ZpbGwtb3BhY2l0eToxO3N0cm9rZTpub25lO2ZvbnQtZmFtaWx5OnNhbnMtc2VyaWY7dGV4dC1hbmNob3I6c3RhcnQ7ZmlsbDojM0I0MTQzJyA+TjwvdGV4dD4KPHRleHQgeD0nNTEuMCcgeT0nNTMuNicgY2xhc3M9J2F0b20tMCcgc3R5bGU9J2ZvbnQtc2l6ZToyM3B4O2ZvbnQtc3R5bGU6bm9ybWFsO2ZvbnQtd2VpZ2h0Om5vcm1hbDtmaWxsLW9wYWNpdHk6MTtzdHJva2U6bm9uZTtmb250LWZhbWlseTpzYW5zLXNlcmlmO3RleHQtYW5jaG9yOnN0YXJ0O2ZpbGw6IzNCNDE0MycgPmk8L3RleHQ+Cjwvc3ZnPgo= [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 229910000601 superalloy Inorganic materials 0.000 description 2
- 230000001914 calming Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000001815 facial Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
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Classifications
-
- 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
Abstract
The invention discloses a kind of aero-compressor hubcap profile surface processing methods, for parts profile face, there are interruption holes, the situation of hard spray coating, a kind of method for inventing machining profile face, reduce the cutting force that cutter is applied to part to the maximum extent, guarantee that contoured surface is not deformed by external force, guarantees contoured surface size qualification.To realize: the vibration knife that occurs when 1. avoiding the interrupted hole of tool sharpening allows knife phenomenon；The excessive cutting force generated when 2. eliminating tool sharpening hard coat；3. the effectively cutting deformation and stress released-deformation of control or reduction 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 methods.
Background technique
The material of existing hood of calming the anger is wrought superalloy, major diameter, wall thickness ultra-thin (0.5-2mm), contoured surface essence
High annular class part is spent, 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 deformed vulnerable to external force.Such part is mainly used in aero-engine manufacturing field.
Certain company's model is calmed the anger hood, and 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, vulnerable to external force
Deformation；There is the interruption hole of 2 groups of difference size and location on parts profile face, as shown in FIG. 1, FIG. 1 is aviations in the prior art
It calms the anger the structural schematic diagram of hood, cutter is made to constitute interrupted cut, cutter has vibration knife, allows knife phenomenon, and then part is caused to become
Shape, as shown in Fig. 2, Fig. 2 is the schematic diagram of aero-compressor cover procedure of processing in the prior art.
Prior art is as follows: 1. tool sharpening route and sequence: 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 outer circle (see Fig. 2, route 8) → essence
Vehicle outer mold surface end face (see Fig. 2, route 9) → smart car profile end face (see Fig. 2, route 10)；
Processing has: 1. since the presence in interruption hole, cutter constitute interrupted cut, there is vibration knife, makes knife existing
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
Quasi- end face A, the first interruption end face Kong Chu are acted on by cutting force and are deformed；
2. since diameter of part is big and wall is thin, parts profile face there are cutter vibration knife, allow knife phenomenon, relative to the flat of benchmark
Face degree, the depth of parallelism, surface profile not can guarantee；
3. after unloading part, in a free state, since cutting stress discharges, parts profile face size and fixture are about for part
Dimension measurement result is inconsistent under pencil state, and size is seriously overproof, not can guarantee qualification；
4. surface irregularity, coating layer thickness is uneven since spray coating hardness is high, cause Tool in Cutting power unequal,
Part is acted on by cutting force and forms irregular deformation.
Specifically, its problem are as follows:
The vibration knife that occurs when 1. not can avoid the interrupted hole of tool sharpening allows knife phenomenon；
The excessive cutting force generated when 2. tool sharpening hard coat can not be eliminated；
3. the cutting deformation and stress released-deformation of part can not be controlled effectively or be reduced.
Summary of the invention
In view of this, the purpose of the present invention is to provide a kind of aero-compressor hubcap profile surface processing method, to realize:
1. avoiding the vibration knife occurred when the interrupted hole of tool sharpening, allowing knife phenomenon；
The excessive cutting force generated when 2. eliminating tool sharpening hard coat；
3. the effectively cutting deformation and stress released-deformation of control or reduction part.
In order to achieve the above object, the invention provides the following technical scheme:
A kind of aero-compressor hubcap profile surface processing method, for processing with hard coat and being interrupted the ultra-thin-wall ring in hole
Shape part contoured surface characterized by comprising
Skewed slot on the rough turn aero-compressor cover of step 1),
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；
The rough turn lubrication groove profile surface of step 2),
The Internal periphery face has the hard coat of arc, and 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 institute at the point B as cutter starting point between point A and point C
The upper angle and lower angle for stating the contact point of hard coat be it is equal, then according to point B to point A- point B extremely point C- point B to point
A- point B to point C carries out rough turn；
The rough turn end face interruption Kong Chu of step 3),
Wherein, the cross-sectional edge point of profile end face is point F and point C, the point F than the point C closer to outer rim, it is described
Point G and the point F are located in the same horizontal line of cross section, have one second interruption hole, institute on the end face interruption Kong Chu
The cross-sectional edge point for stating the second interruption hole is point E and point D, the point E than the point D closer to outer rim, the point E and described
It is the end face interruption Kong Chu between point D, cutting direction is from the point E to the point D；
The rough turn profile end face of step 4),
Its direction is from the point C to the point F；
The rough turn outer mold surface end face of step 5),
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 to having the first interruption hole between the point E1, in cross section vertical direction
The upper point F1 to the point F is outer mold surface end face, and direction is from the point F1 to the point F；
The rough turn outer mold surface outer circle of step 6),
The point G1 to the point F is outer mold surface outer circle, and direction is from the point F to the point G1；
Skewed slot described in step 7) smart car；
It is interrupted the end face Kong Chu described in half smart car of step 8),
Its cutting direction is from the point E to the point D；
Lubrication groove profile surface described in step 9) 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 all the profile end face,
Its cutting direction is the point B to the point F；
Outer mold surface outer circle described in step 11) smart car,
Its direction is from the point F1 to the point G1；
Outer mold surface end face described in step 12) smart car,
Its direction is from the point F1 to the point F；Profile end face described in step 13) refine,
Its direction is from the point C to the point F；
Outer mold surface end face described in step 14) refine,
Its direction is from the point F1 to the point E1；
Step 15) refine benchmark outer circle, the cross section of the benchmark outer circle are the point F to the point G.
Preferably, above-mentioned steps 2) and the step 4) in cutter for same be Boring cutter, parameter be R0.8*80 °.
Preferably, above-mentioned steps 9), step 10), cutter used in step 13) be cylindrical cutter, parameter R0.8*
80°。
Preferably, above-mentioned steps 1), cutter used in the step 7) be skewed slot knife.
Preferably, above-mentioned steps 3), cutter used in the step 8) be right-hand cutter, parameter is R0.8*35 °.
Preferably, above-mentioned steps 5), it is the step 6), the step 11), the step 12), the step 14), described
Cutter used in step 15) is cylindrical cutter, and parameter is R0.8*80 °.
Preferably, cutter bite are as follows: roughing 0.3-0.8mm finishes as 0.15-0.2mm, refine 0-
0.05mm。
Preferably, above-mentioned steps 2) in point B Zhi point A- point B Zhi point C- point B Zhi point A- point B Zhi point C carry out it is rough turn, specifically
For the rough machined cutter bite in one group of point B Zhi point A- point B Zhi point C of front is 0.3mm.
Preferably, upper coarse-fine processing revolving speed S=30 rev/min, F=0.1 millimeters/every turn of feed speed, the first interruption
Revolving speed S=15 rev/min at hole and the second interruption hole, F=0.1 millimeters/every turn of feed speed.
Aero-compressor hubcap profile surface processing method provided by the invention, for parts profile face, there are interruption holes, hard
The situation of matter spray coating, a kind of method for inventing machining profile face reduce the cutting force that cutter is applied to part to the maximum extent,
Guarantee that contoured surface is not deformed by external force, guarantees contoured surface size qualification.
Aero-compressor hubcap profile surface processing method provided by the invention primarily directed to:
(1) the processing of lubrication groove profile surface hard spray coating 1. the processing of hard spray coating: is divided into two using point B as separation
Duan Jiagong, reason: increasing the angle of blade and part machined surface, reduces cutting force and is convenient for chip removal；2. in step 2 point B to point
It is removed in one group of point B Zhi point A- point B Zhi point C before in A- point B to point C- point B to point A- point B to point C convex at lubrication groove profile surface
The coating layer thickness risen, keeps spray coating smooth, is that rough turn lubrication groove profile surface preparation is uniform in subsequent one group of point B to point A- point B to point C
Roughing surplus, avoid generating excessive cutting force and cause part in irregular deformation.
(2) the processing at the first interruption hole: 1. semifinishing first is interrupted the end face Kong Chu in step 12, removes more than major part
Amount, while eliminating rough machined stress deformation；2. deforming most serious since wall thickness is most thin at the first interruption hole, arranging step 14
Last refine first is interrupted the end face Kong Chu, eliminate end face due to cutter vibration knife, allow deformation caused by knife, guarantee that the depth of parallelism is qualified；
(3) the processing at the second interruption hole: the roughing surplus of the second interruption of step 3 removal end face Kong Chu is 1. arranged, is avoided
Occurs deformation caused by causing cutting force excessive due to the variation of cutter moment cutting state when 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 refine in last time
Profile end face and the second interruption end face Kong Chu, eliminate the stress deformation of end face, guarantee benchmark A flatness size and surface profile ruler
It is very little；
(4) the processing of benchmark B: arranging step 15 final stage refine benchmark outer circle B, eliminates the deformation of benchmark B, guarantees base
Quasi- B is correct；
(5) Roughing and fine machining cutter separates, part deformation caused by avoiding because of tool wear.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is the present invention
Some embodiments for those of ordinary skill in the art without creative efforts, can also basis
These attached drawings obtain other attached drawings.
Fig. 1 is the structural schematic diagram of aero-compressor cover in the prior art；
Fig. 2 is the schematic diagram of aero-compressor cover procedure of processing in the prior art
Fig. 3 is the step schematic diagram of aero-compressor hubcap profile surface processing method provided in an embodiment of the present invention.
In figure 1 above -3:
It is interrupted hole 1, interruption hole 2.
Specific embodiment
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below in conjunction with the embodiment of the present invention
In attached drawing, technical scheme in the embodiment of the invention is clearly and completely described, it is clear that described embodiment is
A part of the embodiment of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, those of ordinary skill in the art
Every other embodiment obtained without making creative work, shall fall within the protection scope of the present invention.
Referring to FIG. 3, Fig. 3 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, comprising:
Skewed slot on the rough turn aero-compressor cover of step 1), (label 1 in corresponding diagram 3)
The cross-sectional edge point of skewed slot is point E1 and point G, and point E1 ratio point G is closer to outer rim；
The rough turn lubrication groove profile surface of step 2), (label 2,3,4,5 in corresponding diagram 3)
The Internal periphery face has the hard coat of arc, and 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 at point B as cutter starting point between point A and point C
The upper angle of contact point and lower angle be it is equal, then according to point B to point A- point B to point C- point B extremely point A- point B extremely point C into
Row is rough turn；
The rough turn end face interruption Kong Chu of step 3), (label 6 in corresponding diagram 3)
Wherein, the cross-sectional edge point of profile end face is point F and point C, and point F ratio point C is located at closer to outer rim, point G and point F
In the same horizontal line of cross section, being interrupted on the end face Kong Chu has one second interruption hole 2, the cross section side in the second interruption hole 2
Edge point is point E and point D, and point E ratio point D is the interruption end face Kong Chu between point E and point D, cutting direction is from point closer to outer rim
E to point D；
The rough turn profile end face of step 4), (label 7 in corresponding diagram 3)
Its direction is from point C to point F；
The rough turn outer mold surface end face of step 5), (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, point F1 is to having the first interruption hole 1 between point E1, and point F1 extremely point F is outer mold surface on the vertical direction of cross section
End face, direction are from point F1 to point F；
The rough turn outer mold surface outer circle of step 6), (label 9 in corresponding diagram 3)
Point G1 to point F is outer mold surface outer circle, and direction is from point F to point G1；
Step 7) smart car skewed slot；(label 10 in corresponding diagram 3)
Half smart car of step 8) is interrupted the end face Kong Chu, (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；
The rough turn part lubrication groove profile surface of step 10) and whole profiles end face, (label 13 in corresponding diagram 3)
Its cutting direction is point B to point F；
Step 11) smart car outer mold surface outer circle, (label 14 in corresponding diagram 3)
Its direction is from point F1 to point 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 outer circle, (label 18 in corresponding diagram 3).
Aero-compressor hubcap profile surface processing method provided in an embodiment of the present invention, for parts profile face, there are interruptions
Hole, hard spray coating situation, a kind of method for inventing machining profile face, to the maximum extent reduce cutter be applied to cutting for part
Power is cut, guarantees that contoured surface is not deformed by external force, guarantees 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 lubrication groove profile surface hard spray coating 1. the processing of hard spray coating: is divided into two using point B as separation
Duan Jiagong, reason: increasing the angle of blade and part machined surface, reduces cutting force and is convenient for chip removal；2. in step 2 point B to point
It is removed in one group of point B Zhi point A- point B Zhi point C before in A- point B to point C- point B to point A- point B to point C convex at lubrication groove profile surface
The coating layer thickness risen, keeps spray coating smooth, is that rough turn lubrication groove profile surface preparation is uniform in subsequent one group of point B to point A- point B to point C
Roughing surplus, avoid generating excessive cutting force and cause part 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. deforming most serious since wall thickness is most thin at the first interruption hole 1, arranging step
14 last refine first are interrupted end faces at hole 1, eliminate end face due to cutter vibration knife, allow deformation caused by knife, guarantee that the depth of parallelism is closed
Lattice；
(3) the processing at the second interruption hole 2: the roughing surplus of end face at the second interruption of step 3 removal hole 2 is 1. arranged, is kept away
Occurs deformation caused by causing cutting force excessive due to the variation of cutter moment cutting state when exempting from the rough turn profile end face of step 4；
2. arranging step 8 semifinishing profile end face, 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 repaired, the stress deformation of end face is eliminated, guarantees benchmark A flatness size and facial contour
Size is spent, benchmark A is the plane on point C to point F；
(4) the processing of benchmark B: arranging step 15 final stage refine benchmark outer circle B, i.e. benchmark B, eliminates the change of benchmark B
Shape guarantees that benchmark B is correct, and the cross section of benchmark outer circle is point F to point G；
(5) Roughing and fine machining cutter separates, part deformation caused by avoiding because of tool wear.
Wherein, step 2) and cutter for same in step 4) are Boring cutter, and parameter is R0.8*80 °.Step 9), step
10), cutter used in step 13) is cylindrical cutter, and parameter is R0.8*80 °.Cutter used in step 1), step 7) is
Skewed slot knife.Cutter used in step 3), step 8) is right-hand cutter, and parameter is R0.8*35 °.Step 5), step 6), step
11), step 12), step 14), cutter used in step 15) are cylindrical cutter, and parameter is R0.8*80 °.Roughing is 0.3-
0.8mm finishes as 0.15-0.2mm, refine 0-0.05mm.Point B Zhi point A- point B Zhi point C- point B to point A- in step 2)
Point B to point C progress is rough turn, specifically, the roughing in one group of point B Zhi point A- point B Zhi point C of front is 0.3mm.Coarse-fine processing
Revolving speed S=30 rev/min, F=0.1 millimeters/every turn of feed speed, revolving speed S=at hole 2 is interrupted in the first interruption hole 1 and second
15 rev/min, F=0.1 millimeters/every turn of feed speed.
The foregoing description of the disclosed embodiments enables those skilled in the art to implement or use the present invention.
Various modifications to these embodiments will be readily apparent to 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, of the invention
It is not intended to be limited to the embodiments shown herein, and is to fit to and the principles and novel features disclosed herein phase one
The widest scope of cause.
Claims (9)
1. a kind of aero-compressor hubcap profile surface processing method, for processing with hard coat and being interrupted the ultra-thin wall circular in hole
Part contoured surface characterized by comprising
Skewed slot on the rough turn aero-compressor cover of step 1),
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；
The rough turn lubrication groove profile surface of step 2),
The Internal periphery face has the hard coat of arc, and 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 cutter and described hard at the point B as cutter starting point between point A and point C
The upper angle of the contact point of matter coating and lower angle be it is equal, then according to point B to point A- point B to point C- point B extremely point A- point B
It is carried out to point C rough turn；
The rough turn end face interruption Kong Chu of step 3),
Wherein, the cross-sectional edge point of profile end face is point F and point C, and the point F is 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 on the end face interruption Kong Chu, described the
The cross-sectional edge point in two interruption holes is point E and point D, and the point E is than the point D closer to outer rim, the point E and the point D
Between be the end face interruption Kong Chu, cutting direction is from the point E to the point D；
The rough turn profile end face of step 4),
Its direction is from the point C to the point F；
The rough turn outer mold surface end face of step 5),
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 with first between the point E1
Stating point F1 to the point F is outer mold surface end face, and direction is from the point F1 to the point F；
The rough turn outer mold surface outer circle of step 6),
The point G1 to the point F is outer mold surface outer circle, and direction is from the point F to the point G1；
Skewed slot described in step 7) smart car；
It is interrupted the end face Kong Chu described in half smart car of step 8),
Its cutting direction is from the point E to the point D；
Lubrication groove profile surface described in step 9) 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 all the profile end face,
Its cutting direction is the point B to the point F；
Outer mold surface outer circle described in step 11) smart car,
Its direction is from the point F1 to the point G1；
Outer mold surface end face described in step 12) smart car,
Its direction is from the point F1 to the point F；
Profile end face described in step 13) refine,
Its direction is from the point C to the point F；
Outer mold surface end face described in step 14) refine,
Its direction is from the point F1 to the point E1；
Step 15) refine benchmark outer circle, the cross section of the benchmark outer circle are the point F to the point G.
2. aero-compressor hubcap profile surface processing method according to claim 1, which is characterized in that the step 2) and institute
Stating cutter for same in step 4) is Boring cutter, and parameter is R0.8*80 °.
3. aero-compressor hubcap profile surface processing method according to claim 1, which is characterized in that the step 9), step
It is rapid 10), cutter used in step 13) be cylindrical cutter, parameter be R0.8*80 °.
4. aero-compressor hubcap profile surface processing method according to claim 1, which is characterized in that the step 1), institute
Stating cutter used in step 7) is skewed slot knife.
5. aero-compressor hubcap profile surface processing method according to claim 1, which is characterized in that the step 3), institute
Stating cutter used in step 8) is right-hand cutter, and parameter is R0.8*35 °.
6. aero-compressor hubcap profile surface processing method according to claim 1, which is characterized in that the step 5), institute
Stating step 6), the step 11), the step 12), the step 14), cutter used in the step 15) is cylindrical cutter,
Its parameter is R0.8*80 °.
7. aero-compressor hubcap profile surface processing method according to claim 1, which is characterized in that cutter bite are as follows:
Roughing is 0.3-0.8mm, is finished as 0.15-0.2mm, refine 0-0.05mm.
8. aero-compressor hubcap profile surface processing method according to claim 7, which is characterized in that in the step 2)
Point B to point A- point B to point C- point B to point A- point B extremely point C progress is rough turn, specifically, one group of point B Zhi point A- point B of front is to point
Rough machined cutter bite in C is 0.3mm.
9. aero-compressor hubcap profile surface processing method according to claim 1, which is characterized in that coarse-fine processing revolving speed S
=30 rev/min, F=0.1 millimeters/every turn of feed speed, at the first interruption hole and the second interruption hole revolving speed S=15 turn/it is every
Minute, F=0.1 millimeters/every turn of feed speed.
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8015902B2 (en) * | 2009-04-09 | 2011-09-13 | Mori Seiki Co., Ltd. | Machine tool and workpiece inner surface machining method using the machine tool |
| CN103286324A (en) * | 2013-05-28 | 2013-09-11 | 沈阳黎明航空发动机(集团)有限责任公司 | One-step machining and forming method for grooves of high-temperature alloy integral casings |
| CN103753110A (en) * | 2014-01-09 | 2014-04-30 | 北华航天工业学院 | Thin-wall elliptical part numerical control machining method |
| 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 |
| 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 |
| 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 |
| CN103128312B (en) * | 2011-12-05 | 2016-06-01 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of thin-walled dish part controls deformation processing technique |
-
2017
- 2017-03-07 CN CN201710130743.4A patent/CN106825614B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8015902B2 (en) * | 2009-04-09 | 2011-09-13 | Mori Seiki Co., Ltd. | Machine tool and workpiece inner surface machining method using the machine tool |
| CN103128312B (en) * | 2011-12-05 | 2016-06-01 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of thin-walled dish part controls deformation processing technique |
| CN103286324A (en) * | 2013-05-28 | 2013-09-11 | 沈阳黎明航空发动机(集团)有限责任公司 | One-step machining and forming method for grooves of high-temperature alloy integral casings |
| 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 |
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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. |