A three-dimensional numerical simulation method for extrusion strengthen process of turbine disk hole

Abstract

The invention relates to a three-dimensional numerical simulation method for an extrusion strengthen process of a turbine disk hole, wherein, the three-dimensional modeling of the extrusion strengthening process establishes three-dimensional models of a central circular hole plate and a mandrel with a certain interference amount; the finite element model of extrusion strengthening process is established, and in the preprocessing module of the finite element analysis software ANSYS / LS-DYNA, according to the actual working conditions, the material properties and parameters are set, and the finite element mesh is divided. Load and boundary conditions are set to simulate the relative motion of the mandrel and the central circular hole plate; solution analysis and post-processing is performed to create an analysis job to solve the problem and obtain the residual stress field.

Description

technical field [0001] The invention is a three-dimensional numerical simulation simulation method for the extrusion strengthening process of the nickel-based high-temperature alloy turbine disc hole of an aero-engine, which can consider the interference amount, front and rear ends of the mandrel during the extrusion strengthening process of the wheel disc hole. The simulation method of process parameters such as angle and mandrel speed and factors such as turbine disk material belongs to the technical field of aerospace engines. Background technique [0002] As an important load-bearing part of an aero-engine, the turbine disc is subjected to the joint action of centrifugal load, thermal load and vibration load caused by high speed in the service environment, especially the discs and turbine discs in the rear stages of the compressor have high temperature and large temperature difference, and the working conditions are even worse. Therefore, airworthiness regulations stipul...

AI Technical Summary

Problems solved by technology

At present, a large number of nickel-based superalloy turbine disks are surface-strengthened by shot peening, but the depth of the residual stress field in the hole structure is small, the surface roughness after strengthening is high, the process parameters are difficult to control accurately, and the residual stress is unstable under high-temperature fatigue loads. Therefore, there is an urgent need for an effective surface strengthening process of the turbine disc hole structure to improve the fatigue life

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