A kind of hot working forming method of precipitation hardening stainless steel plate parts

A technology of precipitation hardening and thermal processing, which is applied in the field of thermal processing of precipitation hardening stainless steel plate parts, can solve the problems of high strength, low pass rate of finished parts, large deformation resistance, etc., and achieve obvious social benefits and significant Economic benefits, high deformation resistance

Active Publication Date: 2016-09-07
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] At present, the commonly used parts manufacturing process is generally to form welded parts at room temperature under solution heat treatment. The main problem is that due to the complex shape of the parts, there are usually two deformations of shrinkage and bulging during the molding process, and Precipitation-hardening martensitic stainless steel has the characteristics of high strength and high deformation resistance. The parts obtained under room temperature molding conditions have relatively large residual stress, which can easily lead to cracking of the formed parts, resulting in a low pass rate of the finished parts and making them unusable. At the same time, it is difficult to measure the dimensions of the parts

Method used

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  • A kind of hot working forming method of precipitation hardening stainless steel plate parts

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Embodiment 1

[0014] The structure of the dome parts of the aero-engine is as complex as figure 1 As shown, the blanking, roll bending and welding steps are included in the design of the part forming process. In this embodiment, the following steps are carried out when it is thermally processed and formed:

[0015] (1) For parts made of welded precipitation-hardening stainless steel plates, keep warm at 820°C for 2h, air-cool to room temperature, then keep warm at 600°C for 4h, and air-cool to room temperature;

[0016] (2) Heating parts that have been air-cooled to room temperature to 700°C;

[0017] (3) Heating the forming mold to 300°C for bulging to obtain the final formed precipitation-hardening stainless steel plate parts.

Embodiment 2

[0022] The structure of the bent pipe part of the aero-engine is complex, and the design process of the part includes blanking, rolling and welding steps. In this embodiment, the following steps are followed when it is hot-processed and formed:

[0023] (1) For parts made of welded precipitation-hardening stainless steel plates, keep warm at 810°C for 2h, air-cool to room temperature, then keep warm at 610°C for 4h, and air-cool to room temperature;

[0024] (2) Heating parts that have been air-cooled to room temperature to 720°C;

[0025] (3) Heating the forming mold to 280°C for bulging to obtain the final formed precipitation-hardened stainless steel plate parts. The obtained parts have no cracks on the surface, and the strength meets the design requirements, and they are qualified products after testing.

Embodiment 3

[0027] The structure of the dome part of the aero engine is complex, and the forming process of the part includes blanking, bending and welding steps. In this embodiment, the following steps are carried out when it is thermally processed and formed:

[0028] (1) For parts made of welded precipitation-hardening stainless steel plates, keep warm at 830°C for 2h, air-cool to room temperature, then keep warm at 590°C for 4h, and air-cool to room temperature;

[0029] (2) Heating parts that have been air-cooled to room temperature to 680°C;

[0030] (3) Heating the forming mold to 320°C for bulging to obtain the final formed precipitation-hardening stainless steel plate parts. The obtained parts have no cracks on the surface, and the strength meets the design requirements, and they are qualified products after testing.

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Abstract

The invention belongs to the field of manufacture of aero-engine parts, and particularly relates to a method for shaping parts made of a precipitation-hardening stainless steel plate through hot working. The method comprises the following steps: conducting heat preservation on the welded parts made of the precipitation-hardening stainless steel plate at 810-830 DEG C for 2 h, and carrying out air cooling till the temperature of the parts lowers to a room-temperature level; then conducting heat preservation again on the parts at 590-610 DEG C for 4 h, and carrying out air cooling again till the temperature of the parts lowers to the room-temperature level; heating the parts of which the temperature is cooled to the room-temperature level in air to 680-720 DEG C and heating shaping moulds to 280-320 DEG C for molding and bulging to obtain the finally shaped parts made of the precipitation-hardening stainless steel plate. The method has the advantages that no crack is formed in the final size of the parts and during the shaping process, so that the qualification rate of the parts is improved; material engineering application can be realized to satisfy the need of aero-engine manufacture, so that the social benefits and economic benefits are obvious and outstanding.

Description

technical field [0001] The invention belongs to the field of manufacturing parts of aero-engines, and in particular relates to a thermal forming method for parts made of precipitation-hardening stainless steel plates. Background technique [0002] The housing wall, dome, elbow, rear housing wall and other parts of the aero-engine have high requirements for comprehensive mechanical properties such as strength and toughness, and are generally made of precipitation-hardening martensitic stainless steel sheets. [0003] At present, the commonly used parts manufacturing process is generally to form welded parts at room temperature under solution heat treatment. The main problem is that due to the complex shape of the parts, there are usually two deformations of shrinkage and bulging during the molding process, and Precipitation-hardening martensitic stainless steel has the characteristics of high strength and high deformation resistance. The parts obtained under room temperature ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C21D8/00
Inventor 李许明宋玺玉闫磊段新民李凯峰
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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