CN106111773B - A kind of spin forming method of aero-engine compressor stator inner ring - Google Patents
A kind of spin forming method of aero-engine compressor stator inner ring Download PDFInfo
- Publication number
- CN106111773B CN106111773B CN201610770546.4A CN201610770546A CN106111773B CN 106111773 B CN106111773 B CN 106111773B CN 201610770546 A CN201610770546 A CN 201610770546A CN 106111773 B CN106111773 B CN 106111773B
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- CN
- China
- Prior art keywords
- spinning
- inner ring
- aero
- stator inner
- compressor stator
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D22/00—Shaping without cutting, by stamping, spinning, or deep-drawing
- B21D22/14—Spinning
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D53/00—Making other particular articles
- B21D53/84—Making other particular articles other parts for engines, e.g. connecting-rods
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/008—Rocket engine parts, e.g. nozzles, combustion chambers
Abstract
The invention discloses a kind of spin forming method of aero-engine compressor stator inner ring, comprise the following steps：1) plate is cut into some blankings, then edge rolling and welding is carried out to blanking, obtained cylindrical shape spinning blank, then cylindrical shape spinning blank is made annealing treatment again；2) spinning block tire is made；3) the notch position installation collet of the spinning block tire obtained in step 2)；4) the cylindrical shape spinning blank that step 1) obtains is put into spinning block tire along collet, then mould pressing is carried out to cylindrical shape spinning blank, obtain aero-engine compressor stator inner ring idiosome to be formed；5) technique edges of aero-engine compressor stator inner ring idiosome to be formed are cut, obtain aero-engine compressor stator inner ring, this method can effectively reduce that blend radius is not in place at aero-engine compressor stator inner ring bottom patch and the problem of being easily broken, and the qualification rate shaped is high.
Description
Technical field
The invention belongs to mechanical manufacturing field, is related to a kind of mould pressing side of aero-engine compressor stator inner ring
Method.
Background technology
Aero-engine compressor stator inner ring uses circular thin-wall structure, as shown in figure 1, titanium alloy material, wall thickness
1mm, overall diameter Φ 800 or so, is characterized in：Longitudinal cross-section is centripetal U-shaped, and bottom land is in High angle curve, and two side walls are with
Heart line is vertical, and big small end diameter of bore differs greatly, and because plasticity is poor under titanium alloy material normal temperature, aero-engine is calmed the anger
Machine stator inner ring still continues to use the manufacturing process such as the type that rises, and it is not in place blend radius easily occur, and the problem of easily rupture, it is difficult to shape
Go out qualified parts.
The content of the invention
A kind of the shortcomings that it is an object of the invention to overcome above-mentioned prior art, there is provided aero-engine compressor stator
The spin forming method of inner ring, this method can effectively reduce switching half at aero-engine compressor stator inner ring bottom patch
Footpath is not in place and the problem of being easily broken, and the qualification rate shaped is high.
To reach above-mentioned purpose, the spin forming method of aero-engine compressor stator inner ring of the present invention includes
Following steps：
1) plate is cut into some blankings, then edge rolling and welding is carried out to blanking, obtain cylindrical shape spinning blank, Ran Houzai
Cylindrical shape spinning blank is made annealing treatment, wherein, the axle of weld seam and cylindrical shape spinning blank on cylindrical shape spinning blank
Line intersects；
2) spinning block tire is made according to the shape of aero-engine compressor stator inner ring to be formed, wherein, spinning block tire
For groove structure, two walls of notch are respectively arc-shaped structure that radius is Mmm in the groove structure and radius is Nmm's
Arc-shaped structure；
3) the notch position installation collet of the spinning block tire obtained in step 2)；
4) the cylindrical shape spinning blank that step 1) obtains is put into spinning block tire along collet, then using preform into
Type spinning roller radial feed spinning cylinder shape spinning blank, complete the spinning of aero-engine compressor stator inner ring to be formed in advance into
Shape, then aero-engine compressor stator inner ring to be formed is made annealing treatment, wheel radial is then molded using essence shaping again
Spinning tubular spinning blank is fed, the spinning finishing shape of aero-engine compressor stator inner ring to be formed is completed, obtains to be formed
Aero-engine compressor stator inner ring idiosome；
5) cutting step 4) technique edges of aero-engine compressor stator inner ring idiosome to be formed are obtained, obtain aeroplane engine
Machine Profile For Compressor Stator inner ring.
The blanking is diamond structure, and the acute angle in the diamond structure is 30 ° -65 °.
Weld seam on cylindrical shape spinning blank is sped structure.
M is equal to 6, N and is equal to 23.5.
During the spinning preform and spinning finishing shape of aero-engine compressor stator inner ring to be formed collet with
Gap coordinates between cylindrical shape spinning blank.
Spinning roller radial feed spinning cylinder shape spinning blank in three times is molded using the preform of different-diameter in step 4).
Utilize laser cutting machine cutting step 4) obtain the technique of aero-engine compressor stator inner ring idiosome to be formed
Side.
The invention has the advantages that：
The spin forming method of aero-engine compressor stator inner ring of the present invention is in concrete operations, using pre-
Shaping shaping spinning roller radial feed spinning cylinder shape spinning blank, then feed spinning tubular spinning with the shaping shaping wheel radial that progresses greatly
Blank, aero-engine compressor stator inner ring idiosome to be formed is obtained, overcome the shaping of liquid inner high voltage or the shaping pair of soft formpiston
The problem of pressure requirements are high, the problem of blend radius is not in place at aero-engine compressor stator inner ring bottom patch is reduced,
Meanwhile the weld seam on tubular spinning blank intersects with the axis of cylindrical shape spinning blank, solve weld seam be on single bus and
The problem of causing to be easily broken off during shaping, so as to effectively improve the qualification rate of shaping.In addition, it is necessary to explanation, the present invention
The spinning by the way of radial feed, has disperseed spinning force, the problem of avoiding spinning force from excessively concentrating and cause to rupture at switching.
Further, kept off during the spinning preform of aero-engine compressor stator inner ring to be formed and spinning finishing shape
Between feed ring and cylindrical shape spinning blank gap coordinate, cylindrical shape spinning blank is served it is wrinkle resistant, and do not give cylindrical shape rotation
The barrel of dabbing base applies pressure, while can be entered by collet aimming circle tubular spinning blank in spinning block tire.
Further, spinning roller radial feed spinning cylinder shape spinning blank in three times is molded using the preform of different-diameter,
Reduce the risk ruptured at aero-engine compressor stator inner ring bottom patch.
Brief description of the drawings
Fig. 1 is the structural representation of aero-engine compressor stator inner ring in the present invention；
Fig. 2 is the structural representation of spinning block tire in the present invention；
Structural representation when Fig. 3 is first time pre-compaction forming；
Structural representation when Fig. 4 is second of pre-compaction forming；
Structural representation when Fig. 5 is third time pre-compaction forming；
Structural representation when Fig. 6 is finishing shape；
Fig. 7 is the structural representation that spinning roller is molded in the present invention.
Embodiment
The present invention is described in further detail below in conjunction with the accompanying drawings：
With reference to figure 1, the spin forming method of aero-engine compressor stator inner ring of the present invention includes following step
Suddenly：
1) plate is cut into some blankings, then edge rolling and welding is carried out to blanking, obtain cylindrical shape spinning blank, Ran Houzai
Cylindrical shape spinning blank is made annealing treatment, wherein, the axle of weld seam and cylindrical shape spinning blank on cylindrical shape spinning blank
Line intersects；
2) spinning block tire is made according to the shape of aero-engine compressor stator inner ring to be formed, wherein, spinning block tire
For groove structure, two walls of notch are respectively arc-shaped structure that radius is Mmm in the groove structure and radius is Nmm's
Arc-shaped structure；
3) the notch position installation collet of the spinning block tire obtained in step 2)；
4) the cylindrical shape spinning blank that step 1) obtains is put into spinning block tire along collet, then using preform into
Type spinning roller radial feed spinning cylinder shape spinning blank, complete the spinning of aero-engine compressor stator inner ring to be formed in advance into
Shape, then aero-engine compressor stator inner ring to be formed is made annealing treatment, wheel radial is then molded using essence shaping again
Spinning tubular spinning blank is fed, the spinning finishing shape of aero-engine compressor stator inner ring to be formed is completed, obtains to be formed
Aero-engine compressor stator inner ring idiosome；
5) cutting step 4) technique edges of aero-engine compressor stator inner ring idiosome to be formed are obtained, obtain aeroplane engine
Machine Profile For Compressor Stator inner ring.
The blanking is diamond structure, and the acute angle in the diamond structure is 30 ° -65 °.
Weld seam on cylindrical shape spinning blank is sped structure.
M is equal to 6, N and is equal to 23.5.
During the spinning preform and spinning finishing shape of aero-engine compressor stator inner ring to be formed collet with
Gap coordinates between cylindrical shape spinning blank.
Spinning roller radial feed spinning cylinder shape spinning blank in three times is molded using the preform of different-diameter in step 4).
Utilize laser cutting machine cutting step 4) obtain the technique of aero-engine compressor stator inner ring idiosome to be formed
Side.
In Fig. 7, t is thick for material, unilateral gaps of the G between spinning roller side and aero-engine compressor stator inner ring, in advance
G=0.20 during shaping, G=0.10 during finishing shape, wherein, the distance S of the line of symmetry of each spinning roller two sides to shaft shoulder reference plane
Should be consistent.
Embodiment one
The spin forming method of aero-engine compressor stator inner ring of the present invention comprises the following steps：
Respective radius is three of 30mm, 30mm and 5mm at aero-engine compressor stator inner ring bottom side switching
Preform is molded runner, at the bottom opposite side switching of aero-engine compressor stator inner ring respective radius be 30mm, 10mm and
5mm three preforms shaping runner, essence corresponding at aero-engine compressor stator inner ring two bottom sides switching are shaped as
Type wheel radius is 2mm, and cnc spinning machine was in the qualified phase；
1) plate is cut into some blankings, wherein, blanking is diamond structure, and the acute angle in the diamond structure is
62.76 °, blanking is then placed into roll bending in three axle rolling beds again, then welded, cylindrical shape spinning blank is obtained, then enters again
Row annealing；
2) spinning block tire is made, and runner is molded to cylindrical shape spinning blank by above-mentioned preform using cnc spinning machine
Spinning preform is carried out, then is made annealing treatment, then recycles cnc spinning machine to shape briquetting roller to cylinder by above-mentioned essence
Shape spinning blank carries out spinning finishing shape, obtains aero-engine compressor stator inner ring idiosome to be formed；
3) fluoroscopy is carried out to the surface of aero-engine compressor stator inner ring idiosome to be formed, then utilizes laser
Cutting machine cuts the technique edges of aero-engine compressor stator inner ring idiosome to be formed, obtains in aero-engine compressor stator
Ring.
Claims (7)
1. a kind of spin forming method of aero-engine compressor stator inner ring, it is characterised in that comprise the following steps：
1) plate is cut into some blankings, then edge rolling and welding is carried out to blanking, cylindrical shape spinning blank is obtained, then again to circle
Tubular spinning blank is made annealing treatment, wherein, the axis phase of weld seam and cylindrical shape spinning blank on cylindrical shape spinning blank
Hand over；
2) spinning block tire is made according to the shape of aero-engine compressor stator inner ring to be formed, wherein, spinning block tire is recessed
Slot structure, two walls of notch are respectively the arc-shaped structure that radius is Mmm and the circular arc that radius is Nmm in the groove structure
Shape structure；
3) the notch position installation collet of the spinning block tire obtained in step 2)；
4) the cylindrical shape spinning blank that step 1) obtains is put into spinning block tire along collet, then is molded and revolved using preform
Wheel radial feeds spinning cylinder shape spinning blank, completes the spinning preform of aero-engine compressor stator inner ring to be formed,
Aero-engine compressor stator inner ring to be formed is made annealing treatment again, wheel radial feeding is then molded using essence shaping again
Spinning cylinder shape spinning blank, the spinning finishing shape of aero-engine compressor stator inner ring to be formed is completed, obtains boat to be formed
Empty engine compressor stator inner ring idiosome；
5) cutting step 4) the obtained technique edges of aero-engine compressor stator inner ring idiosome to be formed, obtain aero-engine
Profile For Compressor Stator inner ring.
2. the spin forming method of aero-engine compressor stator inner ring according to claim 1, it is characterised in that institute
It is diamond structure to state blanking, and the acute angle in the diamond structure is 30 ° -65 °.
3. the spin forming method of aero-engine compressor stator inner ring according to claim 1, it is characterised in that circle
Weld seam on tubular spinning blank is sped structure.
4. the spin forming method of aero-engine compressor stator inner ring according to claim 1, it is characterised in that M
It is equal to 23.5 equal to 6, N.
5. the spin forming method of aero-engine compressor stator inner ring according to claim 1, it is characterised in that treat
Collet and cylindrical shape spinning during the spinning preform and spinning finishing shape of shaping aero-engine compressor stator inner ring
Gap coordinates between blank.
6. the spin forming method of aero-engine compressor stator inner ring according to claim 1, it is characterised in that step
Rapid 4) the middle preform using different-diameter is molded spinning roller radial feed spinning cylinder shape spinning blank in three times.
7. the spin forming method of aero-engine compressor stator inner ring according to claim 1, it is characterised in that profit
With laser cutting machine cutting step 4) the obtained technique edges of aero-engine compressor stator inner ring idiosome to be formed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610770546.4A CN106111773B (en) | 2016-08-29 | 2016-08-29 | A kind of spin forming method of aero-engine compressor stator inner ring |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610770546.4A CN106111773B (en) | 2016-08-29 | 2016-08-29 | A kind of spin forming method of aero-engine compressor stator inner ring |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106111773A CN106111773A (en) | 2016-11-16 |
| CN106111773B true CN106111773B (en) | 2017-12-26 |
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ID=57272337
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610770546.4A Active CN106111773B (en) | 2016-08-29 | 2016-08-29 | A kind of spin forming method of aero-engine compressor stator inner ring |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114986102B (en) * | 2022-06-29 | 2023-09-15 | 中国航发动力股份有限公司 | Outer guide ring and forming method thereof |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101672329A (en) * | 2009-07-22 | 2010-03-17 | 宁波达克轴承有限公司 | Bearing retainer and machining technique thereof |
| CN101797611A (en) * | 2010-03-16 | 2010-08-11 | 买联合 | Spoke molding method and device |
| CN101870057A (en) * | 2009-04-25 | 2010-10-27 | 山东兴民钢圈股份有限公司 | Processing technology of lightweight high-intensity rim |
| CN103121047A (en) * | 2012-06-28 | 2013-05-29 | 宝鸡市昌盛钛业有限公司 | Method for manufacturing pure titanium tube by welding and spinning rolling plate |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070197340A1 (en) * | 2006-02-17 | 2007-08-23 | Kim Young S | Internal ring gear with integral hub portion and method of manufacture |
-
2016
- 2016-08-29 CN CN201610770546.4A patent/CN106111773B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101870057A (en) * | 2009-04-25 | 2010-10-27 | 山东兴民钢圈股份有限公司 | Processing technology of lightweight high-intensity rim |
| CN101672329A (en) * | 2009-07-22 | 2010-03-17 | 宁波达克轴承有限公司 | Bearing retainer and machining technique thereof |
| CN101797611A (en) * | 2010-03-16 | 2010-08-11 | 买联合 | Spoke molding method and device |
| CN103121047A (en) * | 2012-06-28 | 2013-05-29 | 宝鸡市昌盛钛业有限公司 | Method for manufacturing pure titanium tube by welding and spinning rolling plate |
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| Publication number | Publication date |
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| CN106111773A (en) | 2016-11-16 |
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Address after: Weiyang Xu Jia Wan 710021 Shaanxi city of Xi'an Province Patentee after: AECC AVIATION POWER CO., LTD. Address before: Weiyang Xu Jia Wan 710021 Shaanxi city of Xi'an Province Patentee before: AVIC AVIATION ENGINE CORPORATION PLC |