Heat treatment method after repair of blades of aero-engine compressor integral blisks

A technology of aero-engine and heat treatment method, which is applied in heat treatment furnaces, heat treatment equipment, furnaces, etc., can solve the problems of not deteriorating the mechanical properties of GH4169G alloy matrix, and achieve the effects of not degrading mechanical properties, improving mechanical properties, and shortening production cycle.

Active Publication Date: 2018-10-30
国营川西机器厂
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to overcome the deficiencies of the prior art and provide a heat treatment method for the blade laser additive repair of the GH4169G alloy blisk. The problem of the mechanical properties of the area

Method used

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  • Heat treatment method after repair of blades of aero-engine compressor integral blisks
  • Heat treatment method after repair of blades of aero-engine compressor integral blisks
  • Heat treatment method after repair of blades of aero-engine compressor integral blisks

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0015] The compressor of a certain type of aero-engine adopts an integral blisk structure, and its material is GH4169G superalloy. Usually, GH4169G powder with the same chemical composition as the base material is used as the repair raw material, and the laser additive technology is used for repair. After repairing, adopt the heat treatment system of the present invention to process. at least 10 ～2 Under the condition of vacuum degree of Pa, put the repaired parts into the vacuum furnace, heat up to 760°C at 12°C / min, cool to 620°C at 50°C / h after holding for 2.0 hours, and cool to room temperature in air after holding for 4.0 hours. The performance test was carried out with furnace samples (including unrepaired substrates and semi-additive repaired plate samples). The hardness test shows that the matrix is ​​47.7-45.6HRC, and the additive repair area is 43.5-44.2HRC. The scanning electron microscope morphology of the substrate after heat treatment is as follows: figure 1 S...

Embodiment 2

[0028] The compressor of a certain type of aero-engine adopts an integral blisk structure, and its material is GH4169G superalloy. Usually, GH4169G powder with the same chemical composition as the base material is used as the repair raw material, and the laser additive technology is used for repair. After repairing, adopt the heat treatment system of the present invention to process. at least 10 ～2 Under the condition of vacuum degree of Pa, put the repaired parts into the vacuum furnace, heat up to 750°C at 10°C / min, cool to 610°C at 55°C / h after holding for 2.1 hours, and cool to room temperature in air after holding for 4.1 hours. The performance test was carried out with furnace samples (including unrepaired substrates and semi-additive repaired plate samples). The hardness test shows that the matrix is ​​47.4-45.6HRC, and the additive repair area is 43.5-44.1HRC.

[0029] The mechanical performance test results are shown in Table 4, Table 5, Table 6 and Table 7. The me...

Embodiment 3

[0040] The compressor of a certain type of aero-engine adopts an integral blisk structure, and its material is GH4169G superalloy. Usually, GH4169G powder with the same chemical composition as the base material is used as the repair raw material, and the laser additive technology is used for repair. After repairing, adopt the heat treatment system of the present invention to process. at least 10 ～2 Under the condition of Pa vacuum, put the repaired parts into the vacuum furnace, heat up to 770°C at 15°C / min, cool to 630°C at 45°C / h after holding for 1.9 hours, and cool to room temperature in air after holding for 3.9 hours. The performance test was carried out with furnace samples (including unrepaired substrates and semi-additive repaired plate samples). The hardness test shows that the matrix is ​​47.8-45.7HRC, and the additive repair area is 43.4-44.2HRC.

[0041] The mechanical performance test results are shown in Table 8, Table 9, Table 10 and Table 11. The mechanical...

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Abstract

The invention relates to a method for thermally treating a repaired blade of an integrated bladed disk of a gas compressor of an aero-engine. The thermal treatment method comprises the following steps: raising the temperature of a repaired part to 750-770 DEG C, preserving the heat for 1.9-2.1 hours, reducing the temperature to 610-630 DEG C at the speed of 45-55 DEG C per hour, preserving the heat for 3.9-4.1 hours, and air-cooling to the room temperature. The temperature in the first heat preservation is raised, the two-time heat preservation time is shortened, the treated part does not have the overaging phenomenon, the production cycle is shortened, the hardness of a thermally treated repaired area reaches more than 90% of the hardness of a matrix, the room temperature strength of the repaired area reaches more than 90% of the requirement of the technical condition of the matrix, the high temperature strength reaches more than 98% of the requirement of the technical condition of the matrix, and the high-cycle fatigue test of a plate sample is more than or equal to 107 cycles without ruptures. The method has the advantages that the mechanical property of the repaired area of a laser additive is also obviously improved while the mechanical property of the alloy matrix is not reduced.

Description

technical field [0001] The invention relates to the technical field of aero-engine maintenance, in particular to a heat treatment method for repaired blades of an integral blisk of an aero-engine compressor. Background technique [0002] The compressor of a certain type of aero-engine adopts an integral blisk structure, and its material is GH4169G superalloy. After a period of use, it is necessary to repair the damaged part of the blade of the blisk. Usually, GH4169G powder with the same chemical composition as the base material is used for repair. Raw materials are repaired using laser additive technology. Since the laser additive area is a rapidly cooled microstructure, the strength of the repaired area is low due to the lack of precipitation of the strengthening phase, which is difficult to meet the requirements of use, and corresponding heat treatment must be carried out. At present, the heat treatment of GH4146G alloy materials mainly includes solid solution + double a...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C21D9/00C21D1/773
CPCC21D1/773C21D9/0068
Inventor 张铀郭双全何勇侯廷红陈海生
Owner 国营川西机器厂
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