CN112122539B - Aeroengine sealing ring forging workpiece tool set and combined forming process thereof - Google Patents
Aeroengine sealing ring forging workpiece tool set and combined forming process thereof Download PDFInfo
- Publication number
- CN112122539B CN112122539B CN202010882549.3A CN202010882549A CN112122539B CN 112122539 B CN112122539 B CN 112122539B CN 202010882549 A CN202010882549 A CN 202010882549A CN 112122539 B CN112122539 B CN 112122539B
- Authority
- CN
- China
- Prior art keywords
- ring forging
- forming
- fire
- shaping
- temperature gas
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21K—MAKING FORGED OR PRESSED METAL PRODUCTS, e.g. HORSE-SHOES, RIVETS, BOLTS OR WHEELS
- B21K1/00—Making machine elements
- B21K1/76—Making machine elements elements not mentioned in one of the preceding groups
- B21K1/761—Making machine elements elements not mentioned in one of the preceding groups rings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21H—MAKING PARTICULAR METAL OBJECTS BY ROLLING, e.g. SCREWS, WHEELS, RINGS, BARRELS, BALLS
- B21H1/00—Making articles shaped as bodies of revolution
- B21H1/06—Making articles shaped as bodies of revolution rings of restricted axial length
-
- 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
-
- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
- C21D9/40—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for rings; for bearing races
Abstract
The invention provides an aeroengine sealing ring forging workpiece tool set, which mainly comprises: first fire shaping frock, second fire shaping frock, third fire shaping frock, first fire shaping frock includes: shaping bucket A and shaping drift A, second fire shaping frock includes: shaping bucket A and shaping drift B, third fire shaping frock includes: the invention also discloses a combined forming process of the aeroengine sealing ring forging, which mainly comprises the following steps: blanking, punching, direct rolling, first fire forming, second fire forming, third fire forming, solid solution heat treatment, testing and inspecting. Through the mode, the special-shaped ring forging design of the In718 sealing ring is realized, net and near forming and less and allowance-free machining of the sealing ring forging are achieved, the product performance is improved, the production and machining cost of the product is reduced, and the market competitiveness of the product with the structure is improved.
Description
Technical Field
The invention relates to the field of manufacturing of parts of an aero-engine, in particular to a sealing ring forging tool set of the aero-engine and a combined forming process thereof.
Background
The sealing ring is a common part In an aeroengine, is made of In718 high-temperature alloy, and is generally special In structure and complex In cross-sectional structure (as shown In figure 1). The existing manufacturing process generally includes forging a ring forging with a rectangular cross section (as shown in fig. 2), and then obtaining a final part structure through a large number of machining methods.
The existing manufacturing and processing technology has the following defects: 1. the thickness of the ring-shaped piece with the rectangular section is thicker, the phenomenon of rolling impermeability exists in the rolling process, and the difference exists between the core structure and the outer surface structure of the section of the forge piece; 2. the utilization rate of the design raw materials of the rectangular forge piece is extremely low, In718 is a noble metal, the production cost is extremely high, and the product has no market competitiveness; 3. the forging flow line of the rectangular ring forging is inconsistent with the flow line direction of the contour of the finished product shape, the integrity of the flow line is damaged by a large amount of subsequent machining, and the service life of the product is influenced.
Disclosure of Invention
In order to solve the problems, the invention provides an aeroengine sealing ring forging tool set and a combined forming process thereof, which can solve the problem of high manufacturing cost of the existing aeroengine sealing ring.
The main content of the invention comprises: the utility model provides an aeroengine seals ring forging frock group, mainly includes: first fire shaping frock, second fire shaping frock, third fire shaping frock, first fire shaping frock includes: shaping bucket A and shaping drift A, shaping bucket A's internal diameter sets up to big-end-up's slope form, shaping drift A's external diameter is big-end-up's inclination, the shaping frock of second fire includes: shaping bucket A and shaping drift B, shaping drift B's external diameter is big-end-up's inclination, shaping drift B's upper end external diameter is greater than shaping drift A, and shaping drift B's inclination is greater than shaping drift A, and shaping drift B's height is less than shaping drift A, third fire shaping frock includes: the forming barrel B and the forming punch C, the inner diameter of the forming barrel B is set to be in an inclined shape with a large upper part and a small lower part, the inner diameter profile of the forming barrel B is set to be consistent with the outer diameter profile of the sealing ring forging, and the outer diameter profile of the forming punch C is set to be consistent with the inner diameter profile of the sealing ring forging.
Preferably, the outer diameters of the forming barrel A and the forming barrel B are provided with groove steps.
The invention also discloses a combined forming process of the aeroengine sealing ring forging, which mainly comprises the following steps:
s1, blanking: cutting into blanks according to the process requirements;
s2, punching: heating the blank by a high-temperature gas furnace to 1000-1060 ℃, preserving heat for 1.5-3 hours, taking out the blank from the high-temperature gas furnace, transporting the blank to a press, and upsetting and punching the blank;
s3, straight rolling: heating the punched ring forging to 980-1020 ℃ by using a high-temperature gas furnace, preserving heat for 0.5-2 hours, taking out the ring forging from the high-temperature gas furnace, and transferring the ring forging to a ring rolling mill for multi-fire direct rolling;
s4, first fire forming: heating the ring forging by using a high-temperature gas furnace to 960-1000 ℃, keeping the temperature for 0.5-2 hours, placing a forming barrel A on a lower table of a press, placing the directly-rolled ring forging into the forming barrel A, moving an upper table of the press downwards to locally compress and form the lower end of a product, then placing a forming punch A into the inner diameter of the directly-rolled ring forging, moving the upper table of the press downwards to extrude and press the forming punch A downwards to locally extrude and form the upper end of the product;
s5, second fire forming: heating the ring forging to 960-1000 ℃ by adopting a high-temperature gas furnace, preserving heat for 0.5-2 hours, placing a forming barrel A on a lower table of a press, placing the ring forging into the forming barrel A, then placing a forming punch B into the inner diameter of the directly rolled ring forging, downward pressing the forming punch B on an upper table of the press, extruding the product to continuously extrude and form the upper part of the product, and further expanding the opening size;
s6, third fire forming: heating the ring forging to 960-1000 ℃ by adopting a high-temperature gas furnace, preserving heat for 0.5-2 hours, inverting the forming punch C on the lower table of a press, inverting the forming ring forging on the forming punch C, inverting the forming barrel B on the forming ring forging, and extruding the product to the final shape by descending the upper table of the press;
s7, solution heat treatment: carrying out heat treatment on the ring forging by adopting a heat treatment furnace, keeping the temperature at 950-1000 ℃ for 1-2 hours, and then discharging from the furnace for air cooling or water cooling;
s8, testing: testing the product sample to verify whether the product sample meets the specification requirements;
s9, checking: and (5) checking according to the required size of a drawing.
Preferably, in the step S2, a high-temperature gas furnace is used to heat the blank to 1040-1060 ℃, and the temperature is kept for 2.5-3 hours.
Preferably, in the step S3, a high-temperature gas furnace is used to heat the punched ring forging to 1000-1020 ℃ and the temperature is kept for 1-2 hours.
Preferably, the first fire forming in S4: heating the ring forging to 980-1000 deg.c with high temperature gas furnace and maintaining for 1.5-2 hr.
Preferably, the second fire forming in S5: heating the ring forging to 980-1000 deg.c with high temperature gas furnace and maintaining for 1.5-2 hr.
Preferably, the third fire forming in S6: heating the ring forging to 980-1000 deg.c with high temperature gas furnace and maintaining for 1.5-2 hr.
Preferably, the solution heat treatment in S7: and (3) carrying out heat treatment on the ring forging by adopting a heat treatment furnace, keeping the temperature at 970-1000 ℃ for 1-2 hours, and then discharging from the furnace for air cooling.
The invention has the beneficial effects that: 1. according to the sealing ring part structure, a special-shaped ring forging piece with the outline close to the outline of the part is designed, so that less and no allowance processing is realized, the utilization rate of raw materials is improved, and the production cost of a product is reduced; 2. the forging profile is close to the part profile, so that net and near forming is realized, the product streamline is complete, and the service life is prolonged; 3. the direct rolling process adopts a low-temperature rolling process at 980-1020 ℃, and is combined with large deformation of 20-40% per firing time to obtain a uniform finer grain structure; 4. the die forging forming adopts a multi-pass part-by-part local forming mode to reduce the risk of product cracking and reduce the pressure required by equipment in the forming process; 5. the die forging forming adopts a low-temperature forming process of 960-1000 ℃ to prevent coarse grains caused by small deformation at high temperature; 6. the crystal grains of the product are finer and more uniform, and the comprehensive performance is improved.
Drawings
FIG. 1 is a schematic view of a conventional seal ring;
FIG. 2 is a schematic structural diagram of a rectangular ring forging in the prior art;
FIG. 3 is a schematic structural view of a special-shaped ring forging of the present invention;
FIG. 4 is a schematic view of the overall flow of the combined forming process of the present invention;
reference numerals: 1. a sealing ring, 2, a rectangular ring forging and 3, a special-shaped ring forging.
Detailed Description
The technical scheme protected by the invention is specifically explained in the following by combining the attached drawings.
Example 1
As shown in FIG. 4, the invention discloses an aeroengine sealing ring forging tool set, which mainly comprises: first fire shaping frock, second fire shaping frock, third fire shaping frock, first fire shaping frock includes: shaping bucket A and shaping drift A, shaping bucket A's internal diameter sets up to big-end-up's slope form, shaping drift A's external diameter is big-end-up's inclination, the shaping frock of second fire includes: shaping bucket A and shaping drift B, shaping drift B's external diameter is big-end-up's inclination, shaping drift B's upper end external diameter is greater than shaping drift A, and shaping drift B's inclination is greater than shaping drift A, and shaping drift B's height is less than shaping drift A, third fire shaping frock includes: the forming barrel B and the forming punch C, the inner diameter of the forming barrel B is set to be in an inclined shape with a large upper part and a small lower part, the inner diameter profile of the forming barrel B is set to be consistent with the outer diameter profile of the sealing ring forging, and the outer diameter profile of the forming punch C is set to be consistent with the inner diameter profile of the sealing ring forging. The outer diameter of the forming barrel A and the outer diameter of the forming barrel B are provided with groove steps, so that the forklift can be clamped conveniently.
The invention also discloses a combined forming process of the aeroengine sealing ring forging, which mainly comprises the following steps:
s1, blanking: cutting into blanks according to the process requirements;
s2, punching: heating the blank by a high-temperature gas furnace to 1000 ℃, preserving heat for 1.5 hours, taking out the blank from the high-temperature gas furnace, transporting the blank to a press, and upsetting and punching the blank;
s3, straight rolling: heating the punched ring forging to 980 ℃ by using a high-temperature gas furnace, preserving heat for 0.5 hour, taking out the ring forging from the high-temperature gas furnace, and transferring the ring forging to a ring rolling mill for multi-fire direct rolling;
s4, first fire forming: heating the ring forging to 960 ℃ by adopting a high-temperature gas furnace, preserving heat for 0.5 hour, placing a forming barrel A on a lower table of a press, placing a directly-rolled ring forging into the forming barrel A, moving an upper table of the press downwards to locally compress and form the lower end of a product, then placing a forming punch A into the inner diameter of the directly-rolled ring forging, moving the upper table of the press downwards to press the forming punch A to locally extrude and form the upper end of the product;
s5, second fire forming: heating the ring forging to 960 ℃ by adopting a high-temperature gas furnace, preserving heat for 0.5 hour, placing a forming barrel A on a lower table top of a press, placing the ring forging into the forming barrel A, then placing a forming punch B into the inner diameter of the directly rolled ring forging, downward pressing the forming punch B on an upper table top of the press, extruding the product to continuously extrude and form the upper part of the product, and further expanding the opening size;
s6, third fire forming: heating the ring forging to 960 ℃ by adopting a high-temperature gas furnace, preserving heat for 0.5 hour, inverting the forming punch C on the lower table surface of the press, inverting the forming ring forging on the forming punch C, inverting the forming barrel B on the forming ring forging, and extruding the product to a final shape by the upper table surface of the press;
s7, solution heat treatment: carrying out heat treatment on the ring forging by using a heat treatment furnace, keeping the temperature at 950 ℃ for 1 hour, and then discharging from the furnace for air cooling;
s8, testing: testing the product sample to verify whether the product sample meets the specification requirements;
s9, checking: and (5) checking according to the required size of the drawing.
Example 2
In embodiment 2, the structure of the tooling set is the same as that in embodiment 1, but the difference is that the process is different, and the tooling set mainly comprises the following steps:
s1, blanking: cutting into blanks according to the process requirements;
s2, punching: heating the blank by a high-temperature gas furnace to 1060 ℃, preserving heat for 3 hours, taking out the blank from the high-temperature gas furnace, transporting the blank to a press, and upsetting and punching the blank;
s3, straight rolling: heating the punched ring forging to 1020 ℃ by using a high-temperature gas furnace, preserving heat for 2 hours, taking out the ring forging from the high-temperature gas furnace, and transferring the ring forging to a ring rolling mill for multi-fire direct rolling;
s4, first fire forming: heating the ring forging to 1000 ℃ by adopting a high-temperature gas furnace, keeping the temperature for 2 hours, placing a forming barrel A on a lower table of a press, placing a directly-rolled ring forging into the forming barrel A, moving an upper table of the press downwards to locally compress and form the lower end of a product, then placing a forming punch A into the inner diameter of the directly-rolled ring forging, moving the upper table of the press downwards to press the forming punch A downwards to locally extrude and form the upper end of the product;
s5, second fire forming: heating the ring forging to 1000 ℃ by adopting a high-temperature gas furnace, keeping the temperature for 2 hours, placing a forming barrel A on a lower table top of a press, placing the ring forging into the forming barrel A, then placing a forming punch B into the inner diameter of the directly-rolled ring forging, downward pressing the forming punch B on an upper table top of the press, extruding the product to continuously extrude and form the upper part of the product, and further expanding the opening size;
s6, third fire forming: heating the ring forging to 1000 ℃ by adopting a high-temperature gas furnace, keeping the temperature for 2 hours, inverting the forming punch C on the lower table surface of the press, inverting the forming ring forging on the forming punch C, inverting the forming barrel B on the forming ring forging, and extruding the product to a final shape by the upper table surface of the press;
s7, solution heat treatment: carrying out heat treatment on the ring forging by adopting a heat treatment furnace, keeping the temperature at 1000 ℃ for 2 hours, discharging from the furnace and cooling by water;
s8, testing: testing the product sample to verify whether the product sample meets the specification requirements;
s9, checking: and (5) checking according to the required size of the drawing.
Example 3
In example 3, the structure of the tool set is the same as that in example 1, the difference is that the process is different, and the method mainly comprises the following steps:
s1, blanking: cutting into blanks according to the process requirements;
s2, punching: heating the blank by a high-temperature gas furnace to 1040 ℃, preserving heat for 2.5 hours, taking out the blank from the high-temperature gas furnace, transporting the blank to a press, and upsetting and punching the blank;
s3, straight rolling: heating the punched ring forging to 1000 ℃ by using a high-temperature gas furnace, preserving heat for 1 hour, taking out the ring forging from the high-temperature gas furnace, and transferring the ring forging to a ring rolling mill for multi-fire direct rolling;
s4, first fire forming: heating the ring forging by using a high-temperature gas furnace to 980 ℃, preserving heat for 1.5 hours, placing a forming barrel A on a lower table top of a press, placing a directly-rolled ring forging into the forming barrel A, moving an upper table top of the press downwards to locally compress and form the lower end of a product, then placing a forming punch A into the inner diameter of the directly-rolled ring forging, moving the upper table top of the press downwards to extrude and press the forming punch A downwards to locally extrude and form the upper end of the product;
s5, second fire forming: heating the ring forging to 980 ℃ by using a high-temperature gas furnace, preserving heat for 1.5 hours, placing a forming barrel A on a lower table top of a press, placing the ring forging into the forming barrel A, then placing a forming punch B into the inner diameter of the directly rolled ring forging, downwards pressing the forming punch B on an upper table top of the press, extruding the product to continuously extrude and form the upper part of the product, and further expanding the opening size;
s6, third fire forming: heating the ring forging to 980 ℃ by using a high-temperature gas furnace, preserving heat for 1.5 hours, inverting the forming punch C on the lower table surface of the press, inverting the forming ring forging on the forming punch C, inverting the forming barrel B on the forming ring forging, and extruding the product to the final shape by the upper table surface of the press;
s7, solution heat treatment: carrying out heat treatment on the ring forging by using a heat treatment furnace, keeping the temperature at 970 ℃ for 1 hour, and then discharging from the furnace for air cooling;
s8, testing: testing the product sample to verify whether the product meets the specification requirements;
s9, checking: and (5) checking according to the required size of the drawing.
The above description is only an embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications of equivalent structures and equivalent processes performed by the present specification and drawings, or directly or indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (7)
1. The combined forming process of the aeroengine sealing ring forging is characterized by preparing an aeroengine sealing ring forging tool set, wherein the aeroengine sealing ring forging tool set comprises the following steps: first fire shaping frock, second fire shaping frock, third fire shaping frock, first fire shaping frock includes: shaping bucket A and shaping drift A, shaping bucket A's internal diameter sets up to big-end-up's slope form, shaping drift A's external diameter is big-end-up's inclination, the shaping frock of second fire includes: shaping bucket A and shaping drift B, shaping drift B's external diameter is big-end-up's inclination, shaping drift B's upper end external diameter is greater than shaping drift A's upper end external diameter, and shaping drift B's inclination is greater than shaping drift A's inclination, and shaping drift B's height is less than shaping drift A's height, third fire shaping frock includes: the inner diameter of the forming barrel B is set to be in an inclined shape with a large upper part and a small lower part, the inner diameter profile of the forming barrel B is set to be consistent with the outer diameter profile of the sealing ring forging, and the outer diameter profile of the forming punch C is set to be consistent with the inner diameter profile of the sealing ring forging;
the outer diameters of the forming barrel A and the forming barrel B are provided with groove steps;
the combined forming process comprises the following steps:
s1, blanking: cutting into blanks according to the process requirements;
s2, punching: heating the blank by a high-temperature gas furnace to 1000-1060 ℃, preserving heat for 1.5-3 hours, taking out the blank from the high-temperature gas furnace, transporting the blank to a press, and upsetting and punching the blank;
s3, straight rolling: heating the punched ring forging to 980-1020 ℃ by using a high-temperature gas furnace, preserving heat for 0.5-2 hours, taking out the ring forging from the high-temperature gas furnace, and transferring the ring forging to a ring rolling mill for multi-fire direct rolling;
s4, first fire forming: heating the ring forging to 960-1000 ℃ by adopting a high-temperature gas furnace, preserving heat for 0.5-2 hours, placing a forming barrel A on a lower table of a press, placing the ring forging into the forming barrel A, enabling an upper table of the press to move downwards to compress and form the lower end part of the ring forging, then placing a forming punch A into the inner diameter of the ring forging, and enabling the upper table of the press to move downwards to extrude the forming punch A to press the ring forging to extrude the upper end part of the ring forging;
s5, second fire forming: heating the ring forging to 960-1000 ℃ by adopting a high-temperature gas furnace, preserving heat for 0.5-2 hours, placing a forming barrel A on a lower table top of a press, placing the ring forging into the forming barrel A, then placing a forming punch B into the inner diameter of the ring forging, downward pressing the forming punch B on an upper table top of the press, extruding the ring forging to continuously extrude and form the upper end part of the ring forging, and further expanding the opening size;
s6, third fire forming: heating the ring forging to 960-1000 ℃ by adopting a high-temperature gas furnace, preserving heat for 0.5-2 hours, inverting the forming punch C on the lower table of a press, inverting the ring forging on the forming punch C, inverting the forming barrel B on the ring forging, and extruding the ring forging to a final shape by descending the upper table of the press;
s7, solution heat treatment: carrying out solution heat treatment on the ring forging by adopting a heat treatment furnace, keeping the temperature at 950-1000 ℃ for 1-2 hours, and then discharging from the furnace for air cooling or water cooling;
s8, testing: testing the ring forging sample to verify whether the ring forging sample meets the specification requirements;
s9, checking: and (5) checking according to the required size of the drawing.
2. The combined forming process of the aeroengine sealing ring forging according to claim 1, wherein in S2, a high-temperature gas furnace is adopted to heat the blank to 1040-1060 ℃, and the temperature is kept for 2.5-3 hours.
3. The combined forming process of the aeroengine sealing ring forging according to claim 1, wherein in S3, a high-temperature gas furnace is adopted to heat the punched ring forging to 1000-1020 ℃, and the temperature is kept for 1-2 hours.
4. The combined forming process of the aeroengine sealing ring forging as claimed in claim 1, wherein the first fire forming in S4 is as follows: heating the ring forging to 980-1000 deg.c with high temperature gas furnace and maintaining for 1.5-2 hr.
5. The combined forming process of the aeroengine sealing ring forging as claimed in claim 1, wherein in the step S5, the second fire forming: heating the ring forging to 980-1000 deg.c with high temperature gas furnace and maintaining for 1.5-2 hr.
6. The combined forming process of the aeroengine sealing ring forging as claimed in claim 1, wherein the third fire forming in S6 is as follows: heating the ring forging to 980-1000 deg.c with high temperature gas furnace and maintaining for 1.5-2 hr.
7. The combined forming process of an aeroengine sealing ring forging according to claim 1, wherein the solution heat treatment in S7 is as follows: and carrying out solution heat treatment on the ring forging by adopting a heat treatment furnace, keeping the temperature at 970-1000 ℃ for 1-2 hours, and then discharging from the furnace for air cooling.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010882549.3A CN112122539B (en) | 2020-08-28 | 2020-08-28 | Aeroengine sealing ring forging workpiece tool set and combined forming process thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010882549.3A CN112122539B (en) | 2020-08-28 | 2020-08-28 | Aeroengine sealing ring forging workpiece tool set and combined forming process thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112122539A CN112122539A (en) | 2020-12-25 |
| CN112122539B true CN112122539B (en) | 2022-06-21 |
Family
ID=73847810
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010882549.3A Active CN112122539B (en) | 2020-08-28 | 2020-08-28 | Aeroengine sealing ring forging workpiece tool set and combined forming process thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112122539B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000015326A (en) * | 1998-07-02 | 2000-01-18 | Daido Steel Co Ltd | Die for copper hot extrusion and its manufacture |
| CN103447769A (en) * | 2013-08-27 | 2013-12-18 | 贵州安大航空锻造有限责任公司 | Preparing method of TC4 alloy large-scale special-shaped cross section annular blank |
| CN104384826A (en) * | 2014-08-18 | 2015-03-04 | 贵州航宇科技发展股份有限公司 | Forging method of GH4169 alloy inner cartridge receiver special-shaped ring part |
| CN105396995A (en) * | 2015-12-02 | 2016-03-16 | 贵州安大航空锻造有限责任公司 | Forming method of cobalt-based high-temperature alloy multi-step large special-shaped ring |
| CN107138538A (en) * | 2017-06-16 | 2017-09-08 | 奥科宁克航空机件(苏州)有限公司 | A kind of forging method of fining high temperature alloy annular forging piece grain size |
| CN108500189A (en) * | 2018-03-07 | 2018-09-07 | 东南大学 | A kind of molding die with straight-edge conical cylinder forging and forging process for fuel method |
| CN109702434A (en) * | 2018-12-13 | 2019-05-03 | 贵州航宇科技发展股份有限公司 | A kind of manufacturing method with flange GH4169 low-pressure turbine casing forging |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8302314B2 (en) * | 2003-08-13 | 2012-11-06 | Technische Universität Dresden | Method for producing internally or externally profiled rings and arrangement therefor |
-
2020
- 2020-08-28 CN CN202010882549.3A patent/CN112122539B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000015326A (en) * | 1998-07-02 | 2000-01-18 | Daido Steel Co Ltd | Die for copper hot extrusion and its manufacture |
| CN103447769A (en) * | 2013-08-27 | 2013-12-18 | 贵州安大航空锻造有限责任公司 | Preparing method of TC4 alloy large-scale special-shaped cross section annular blank |
| CN104384826A (en) * | 2014-08-18 | 2015-03-04 | 贵州航宇科技发展股份有限公司 | Forging method of GH4169 alloy inner cartridge receiver special-shaped ring part |
| CN105396995A (en) * | 2015-12-02 | 2016-03-16 | 贵州安大航空锻造有限责任公司 | Forming method of cobalt-based high-temperature alloy multi-step large special-shaped ring |
| CN107138538A (en) * | 2017-06-16 | 2017-09-08 | 奥科宁克航空机件(苏州)有限公司 | A kind of forging method of fining high temperature alloy annular forging piece grain size |
| CN108500189A (en) * | 2018-03-07 | 2018-09-07 | 东南大学 | A kind of molding die with straight-edge conical cylinder forging and forging process for fuel method |
| CN109702434A (en) * | 2018-12-13 | 2019-05-03 | 贵州航宇科技发展股份有限公司 | A kind of manufacturing method with flange GH4169 low-pressure turbine casing forging |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112122539A (en) | 2020-12-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101695739B (en) | Forging process of large tee and large skew tee | |
| CN107252866B (en) | The multiple protrusion ozzle large-sized end enclosure forging integral forging and forming methods of nuclear reactor band | |
| CN103071743B (en) | Preparation method for TC11 titanium alloy small-bore thick-walled cylindrical part | |
| CN106670359B (en) | A kind of GH4169 alloy rings and preparation method thereof | |
| CN1919530A (en) | Manufacturing technique of heavy caliber alloy seamless steel pipe | |
| EP3683007A1 (en) | Profiled metal construction forming method | |
| CN112355208A (en) | Near-net rolling forming method of GH907 special-shaped ring forging | |
| CN112264565A (en) | Manufacturing method of high-performance aluminum alloy cylindrical forging for spaceflight | |
| CN109794570B (en) | Simple die forging method for double-flange large valve body | |
| CN112589021A (en) | Manufacturing method of IN718 alloy double-flange high-barrel casing ring piece | |
| US20120090375A1 (en) | Zoning closed-die extruding device and method | |
| CN112453305B (en) | Forming die and method for inhibiting local extrusion cracks | |
| CN114472776A (en) | Die forging blank making and die ring rolling forming process for high-neck flange forging for wind tower | |
| CN112122539B (en) | Aeroengine sealing ring forging workpiece tool set and combined forming process thereof | |
| CN111250639B (en) | Blank forming method for GH4169 large-sized special-shaped ring forging | |
| CN113510205A (en) | Die forging and roll forming method for high-temperature alloy special-shaped section flange disc-shaped part | |
| CN101618499B (en) | Method for eliminating seaming coarse grains of rolling vane | |
| CN106862449B (en) | The closed die forging forging method of complete-section tunnel boring machine hobboing cutter cutter ring | |
| RU2381083C1 (en) | Manufacturing method of scapular blanks | |
| CN112122541A (en) | Method for forming asymmetric complex-section special-shaped ring | |
| CN114260406A (en) | Manufacturing method of GH4169 alloy die forging | |
| CN110814249B (en) | Forming method of stainless steel long pipe forging | |
| CN107695163B (en) | Nuclear island evaporator end socket integral stamping forming device and stamping forming method | |
| CN104308457B (en) | A kind of manufacture method on the square installation limit of aero-engine GH3536 | |
| CN114309403A (en) | Low-cost forging forming method of titanium alloy blade |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |