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A kind of aero-engine sealing ring forging tooling group and its combined forming process

An aero-engine, combined molding technology, applied in engine components, manufacturing tools, mechanical equipment, etc., can solve the problem of high manufacturing cost of aero-engine sealing rings, and achieve the goal of improving the utilization rate of raw materials, complete product flow lines, and reducing production costs. Effect

Active Publication Date: 2022-06-21
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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  • A kind of aero-engine sealing ring forging tooling group and its combined forming process
  • A kind of aero-engine sealing ring forging tooling group and its combined forming process
  • A kind of aero-engine sealing ring forging tooling group and its combined forming process

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Effect test

Embodiment 1

[0031] like Figure 4 As shown, the present invention discloses an aero-engine sealing ring forging tooling assembly, which mainly includes: a first fire forming tool, a second fire forming tool, and a third fire forming tool, and the first fire forming tool includes: a forming barrel A and a forming punch A, the inner diameter of the forming barrel A is set to be inclined with a large upper and a small lower, the outer diameter of the forming punch A is inclined with a large upper and a small lower, and the second fire forming tool includes: : Forming barrel A and forming punch B, the outer diameter of the forming punch B has a slope that is large up and down, and the outer diameter of the upper end of the forming punch B is larger than that of the forming punch A, and the diameter of the forming punch B is larger than that of 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 for...

Embodiment 2

[0043] In embodiment 2, the structure of the tooling assembly is the same as that in embodiment 1, and the difference lies in the different processes, which mainly include the following steps:

[0044] S1. Blanking: cut into blanks according to process requirements;

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

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

[0047] S4. First fire forming: use a high temperature gas furnace to heat the ring forgings to 1000°C and keep the temperature for 2 hours. The forming barrel A is placed on t...

Embodiment 3

[0054] In Embodiment 3, the structure of the tooling assembly is the same as that in Embodiment 1, and the difference lies in the different processes, which mainly include the following steps:

[0055] S1. Blanking: cut into blanks according to process requirements;

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

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

[0058] S4. First fire forming: use a high temperature gas furnace to heat the ring forgings to 980°C and keep the temperature for 1.5 hours. The forming barrel A is place...

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Abstract

The present invention proposes 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 a forming Punch A, the second pyroforming tooling includes: forming barrel A and forming punch B, the third pyroforming tooling includes: forming barrel B and forming punch C, the invention also discloses an aero-engine seal The combined forming process of Yanhuan forgings mainly includes the following steps: blanking, punching, direct rolling, first fire forming, second fire forming, third fire forming, solution heat treatment, testing, and inspection. Through the above method, the special-shaped ring forging design of In718 sealing ring is realized, and the net near forming and less and no margin processing of the sealing ring forging are realized, the product performance is improved while the product production and processing cost is reduced, and the market competition of this type of structural product is enhanced. force.

Description

technical field [0001] The invention relates to the field of aero-engine parts manufacturing, in particular to an aero-engine sealing ring forging tooling assembly and a combined forming process thereof. Background technique [0002] The sealing ring is a commonly used part in aero-engines, and its material is mostly In718 superalloy. Its structure is generally special, and its cross-sectional structure is relatively complex (such as figure 1 ). The existing manufacturing process is generally to first forge a ring forging with a rectangular cross-section (such as figure 2 ), 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 section ring is thick, the rolling process is not fully rolled, and the core structure of the forging section is different from the outer surface structure; 2. The rectangular forging desi...

Claims

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Application Information

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Patent Type & Authority Patents(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