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Anti-recrystallization method in repair process of turbine blade after service

A technology of turbine blade and recrystallization, which is applied in the direction of heat treatment process control, furnace type, furnace, etc., can solve the problems affecting the service performance of turbine blades and the defects of recrystallization of turbine blades.

Active Publication Date: 2021-11-26
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, when the turbine blades in service are directly repaired by general recovery heat treatment, recrystallization defects are easily formed on the turbine blades, which significantly affects the service performance of the turbine blades.

Method used

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  • Anti-recrystallization method in repair process of turbine blade after service
  • Anti-recrystallization method in repair process of turbine blade after service
  • Anti-recrystallization method in repair process of turbine blade after service

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0060] Example 1 Tissue Repair of Turbine Guide Vanes After Overheating Service

[0061] Turbine guide blades have overheated in service, and the overheated temperature is 1250°C (the normal service temperature is 1150°C).

[0062] First: observe the original structure of the turbine guide vane, and use the DSC analysis method to determine the initial melting back temperature T of the γ’ phase of the original turbine guide vane s 1280°C and complete melting back temperature T f The initial melting point temperature of the alloy is 1320°C and 1350°C.

[0063] Second: Stress-relief treatment is carried out on the guide vanes of overheated turbines in service. The specific parameters are: heating up to 900±20°C, holding for 3 hours, and cooling with the furnace.

[0064] Then, anti-recrystallization heat treatment is carried out, and the specific parameters are: increase to 1200±5°C at a rate of 10°C / min, hold for 0.5h, and then cool down to 1100±5°C at a rate of 10°C / min; cont...

Embodiment 2

[0068] Example 2 Tissue Repair of Turbine Working Blades in Creep Service

[0069] For the turbine working blade, it bears a certain centrifugal force, mainly due to the degradation of the structure after creep, including the dissolution, coarsening and rafting of the γ’ phase.

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Abstract

The invention belongs to the technical field of turbine blade repair treatment, and provides an anti-recrystallization method in the repair process of a turbine blade after service. The recrystallization behavior of the turbine blade in the repairing process after service is mainly caused by the fact that after the alloy is subjected to the high-temperature and high-load service process, the alloy structure degenerates, and a large number of dislocation structures generated due to high-temperature creep deformation are contained in the alloy structure. And when the turbine blade is in a recovery heat treatment process higher than the recrystallization temperature after service, dislocation rearrangement forms a large-angle grain boundary, and the large-angle grain boundary rapidly migrates to finally form recrystallized grains. According to the method, one-step anti-recrystallization heat treatment is carried out before solution treatment, a large number of dislocation existing in the alloy is pre-recovered, the dislocation density is reduced, and therefore recrystallization of the alloy in the subsequent heat treatment process is inhibited.

Description

technical field [0001] The invention relates to the technical field of turbine blade repair treatment, in particular to an anti-recrystallization method in the repair process of turbine blades after service. Background technique [0002] With the development of aero-engines, the requirements for the thrust-to-weight ratio of aero-engines and the temperature before the turbine are also continuously increasing. From the third generation to the fifth generation of aero-engines, the temperature before the turbine has also increased from 1655K to over 2000K. The turbine blades in aero-engines are also required to work stably for a long time under the conditions of high temperature, high pressure and high temperature gas corrosion, resulting in a very harsh service environment. On this basis, the innovation of turbine blade materials and related preparation processes is inevitable, and mastering the regular repair technology of advanced air-cooled blades after service is also of ...

Claims

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Application Information

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IPC IPC(8): C21D9/00C22F1/10C21D11/00
CPCC21D9/0068C22F1/10C21D11/00C22F1/002
Inventor 赵海根王琪李树索裴延玲茹毅宫声凯
Owner BEIHANG UNIV
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