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A method of manufacturing a hollow turbine disk

A manufacturing method and technology of turbine discs, which are applied in the field of manufacturing turbine discs, can solve the problems of complex manufacturing process of turbine disc blanks, high operating costs, time-consuming and labor-consuming, etc., and achieve obvious weight reduction effects, low operating costs, and materials The effect of high utilization

Active Publication Date: 2019-04-23
GUANGDONG UNIV OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Since the above three production processes require large-tonnage extrusion equipment and fully enclosed isothermal forging presses and devices, the investment is huge and the operating costs are high, and the manufacturing process of the turbine disc blank is complicated, time-consuming and labor-intensive.

Method used

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  • A method of manufacturing a hollow turbine disk
  • A method of manufacturing a hollow turbine disk
  • A method of manufacturing a hollow turbine disk

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Experimental program
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Effect test

Embodiment 1

[0025] A method for manufacturing a hollow turbine disk, comprising the steps of:

[0026] S1. Draw the 3D model of the cavity turbine disk in the 3D drawing software, then perform data processing on the 3D model to generate processing codes;

[0027] S2. Continuous beam laser and powder feeding system According to the processing code, the laser beam irradiates the superalloy metal powder, and the coaxial powder feeding device in the light is controlled by the mechanical arm to scan the processing substrate according to the processing path to perform welding and forming. Laser shock forging is carried out on the welding zone with continuous laser beam;

[0028] S3. When the cladding layer reaches a certain height, the robot moves the processing substrate to the working area of ​​the milling machine, and uses the milling cutter to mill the turbine disc;

[0029] S4. Clean the turbine disk after milling, and then move the processed substrate to the laser processing area by the ...

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Abstract

The invention adopts continuous laser cladding superalloy powder and pulse laser impact forging combined processing technology to process the turbine disk containing the cavity, so that the comprehensive performance of the formed part is not lower than that of the forged part. In the process of forming the cavity turbine disk Among them, the high-precision milling of the cavity and the surface of the turbine disk is carried out at the same time, and the process is simplified at one time. This method is a typical additive manufacturing process, with high material utilization and high manufacturing efficiency, and does not require large extrusion equipment. The operating cost Low, the cavity turbine disk has obvious weight reduction effect, which is of great significance to the development of high thrust-to-weight ratio aeroengine.

Description

technical field [0001] The invention relates to a method for manufacturing a turbine disk, in particular to a method for manufacturing a cavity turbine disk. Background technique [0002] The turbine disk is one of the main parts of the aircraft engine. As the core rotating part of the aircraft engine, it is subjected to the superposition of high temperature and high stress. The working conditions are extremely harsh, the preparation process is complicated, and the technology is difficult. It has long been the development of my country's engines. One of the difficulties. [0003] At present, the powder superalloy turbine disc manufacturing technology is one of the symbols of advanced aero-engines. Many military aircraft engines in western countries use superplastic isothermal forging powder superalloy turbine discs. At present, only a few countries in the world, such as the United States, Britain, Russia, France and Germany, have mastered the production technology of powder ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B23P15/00B22F3/105B22F3/24B22F5/00B33Y10/00
CPCB22F3/24B22F5/009B23P15/00B33Y10/00B22F2003/247B22F10/00B22F10/36B22F10/25B22F12/41B22F10/368B22F10/50B22F12/45Y02P10/25
Inventor 张永康杨青天蔡显新
Owner GUANGDONG UNIV OF TECH
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