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Aero-engine sealing ring forging tool set and combined forming process therefor

An aero-engine and combined molding technology, which is applied in the direction of engine components, furnace types, mechanical equipment, etc., can solve the problems of high manufacturing cost of aero-engine sealing rings, achieve improved raw material utilization, finer and more uniform grains, and longer service life Improved effect

Active Publication Date: 2020-12-25
豪梅特航空机件(苏州)有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In order to solve the above problems, the present invention proposes an aero-engine sealing ring forging tooling set and its combined forming process, which can solve the problem of high manufacturing cost of the existing aero-engine sealing ring

Method used

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  • Aero-engine sealing ring forging tool set and combined forming process therefor
  • Aero-engine sealing ring forging tool set and combined forming process therefor
  • Aero-engine sealing ring forging tool set and combined forming process therefor

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Embodiment 1

[0031] Such as Figure 4 As shown, the present invention discloses an aero-engine sealing ring forging tooling set, which mainly includes: a first pyroforming tooling, a second pyroforming tooling, and a third pyroforming tooling, and the first pyroforming tooling includes: a forming barrel A and the forming punch A, the inner diameter of the forming barrel A is set as an inclined shape with a large top and a small bottom, and the outer diameter of the forming punch A is a slope with a large top and a small bottom, and the second pyroforming tooling includes : Forming barrel A and forming punch B, the outer diameter of the forming punch B is a slope with a large up and down, the outer diameter of the upper end of the forming punch B is larger than the forming punch A, and the forming punch B The inclination is greater than that of the forming punch A, and the height of the forming punch B is smaller than that of the forming punch A. The third thermal forming tooling includes: ...

Embodiment 2

[0043]In embodiment 2, the structure of tooling group is identical with embodiment 1, and its difference is that technology is different, mainly comprises the following steps:

[0044] S1, blanking: cut into blanks according to the process requirements;

[0045] S2. Punching: use a high-temperature gas furnace to heat the billet to 1060°C, keep it warm for 3 hours, then take the billet out of the high-temperature gas furnace and transport it to a press, and then upset and punch the billet;

[0046] S3. Direct rolling: use a high-temperature gas furnace to heat the punched ring forging to 1020°C, keep it warm for 2 hours, then take the ring forging out of the high-temperature gas furnace and transfer it to a ring rolling mill for multi-fire direct rolling ;

[0047] S4. First fire molding: use a high-temperature gas furnace to heat the ring forging to 1000°C and keep it warm for 2 hours. The forming barrel A is placed on the lower table of the press, and the direct-rolled ring...

Embodiment 3

[0054] In embodiment 3, the structure of tooling group is identical with embodiment 1, and its difference is that technology is different, mainly comprises the following steps:

[0055] S1, blanking: cut into blanks according to the process requirements;

[0056] S2. Punching: use a high-temperature gas furnace to heat the billet to 1040°C, keep it warm for 2.5 hours, then take the billet out of the high-temperature gas furnace and transport it to a press, and then upset and punch the billet;

[0057] S3. Direct rolling: use a high-temperature gas furnace to heat the punched ring forging to 1000°C, keep it warm for 1 hour, then take the ring forging out of the high-temperature gas furnace and transfer it to a ring rolling mill for multi-fire direct rolling ;

[0058] S4. First fire molding: use a high-temperature gas furnace to heat the ring forging to 980°C and keep it warm for 1.5 hours. The forming barrel A is placed on the lower table of the press, and the direct-rolled r...

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Abstract

The invention provides an aero-engine sealing ring forging tool set, mainly comprising a first fire forming tool, a second fire forming tool and a third fire forming tool. The first fire forming toolcomprises a forming barrel A and a forming punch A; the second fire forming tool comprises a forming barrel A and a forming punch B; and the third fire forming tool comprises a forming barrel B and aforming punch C. The invention further discloses a combined forming process for an aero-engine sealing ring forging, mainly comprising the following steps: blanking, punching, direct rolling, first fire forming, second fire forming, third fire forming, solid solution heat treatment, testing and inspection. Through the mode, the design of a special-shaped ring forging of an In718 sealing ring is implemented, net forming and little / zero-allowance machining of the sealing ring forging are achieved, the product production and machining cost is reduced while the product performance is improved, andthe market competitiveness of this type of products is improved.

Description

technical field [0001] The invention relates to the field of aero-engine component manufacturing, in particular to an aero-engine sealing ring forging tooling set and its combined forming process. Background technique [0002] Sealing rings are commonly used parts in aero-engines, and the material is mostly In718 superalloy. Its structure is generally special, and its cross-sectional structure is relatively complicated (such as Figure 1 ). The existing manufacturing process is generally first forged into a rectangular ring forging (such as Figure II ), and then obtain the final part structure through a large number of machining methods. [0003] The existing manufacturing and processing technology has the following shortcomings: 1. The thickness of the rectangular cross-section ring is relatively thick, and there is a phenomenon that the rolling process is impenetrable, and there is a difference between the core structure of the forging cross-section and the outer surface...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B21K1/76B21H1/06B23P15/00C21D9/40
CPCB21K1/761B21H1/06B23P15/00C21D9/40
Inventor 刘小刚王星阳黄震侯俊楠
Owner 豪梅特航空机件(苏州)有限公司