Turbine disc gradient structure regulation and control method based on preform and forging whole-process numerical simulation

Abstract

The invention relates to a turbine disc gradient structure regulation and control method based on preform and forging whole-process numerical simulation, which adopts a finite element numerical simulation technology, selects a proper forging preform shape and size, and determines forging and gradient heat treatment process parameters for obtaining an ordered gradient structure turbine disc. Activeregulation and control of a strain field, a gradient temperature field and grain size distribution in the whole turbine disc forging process are achieved by adjusting the characteristic size of the prefabricated blank and forging process parameters. Through adoption of the strain forging control method and by means of an existing heat insulation gradient heat treatment device, the problem that inthe prior art, a transition interface temperature field is suddenly changed due to a local circulating cooling water system, and consequently the grain size is suddenly changed is solved, ,an obviouscoarse grain and fine grain interface formed and manufactured by the double-performance turbine disc can be eliminated, and the structure performance requirement of the dual-performance turbine discis met.

Description

technical field [0001] The invention relates to the field of thermal processing of metal materials, in particular to a method for controlling gradual structure changes during forging and heat treatment, and in particular to a method for controlling gradual structure changes of turbine discs based on numerical simulation of the whole process of preform and forging. Background technique [0002] Integration and lightweight are the eternal themes pursued by the aerospace industry. The service environments of some of the integral components in different regions are significantly different, which requires different service performances in different regions of the components. Take the turbine disk of an aero-engine as an example: in the service state, the temperature at the edge of the turbine disk is relatively high, which requires a high ability to resist creep and fatigue crack growth; High yield strength and low cycle fatigue properties are required. It is well known that th...

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Problems solved by technology

[0004] The technical problem solved by the present invention is: in order to overcome the problem that the existing dual-performance turbine disk processing technology will produce obvious coarse grain-fine grain interface, the present invention provides a turbine disk gradual change based on the numerical simulation of the whole process of preform and forging Tissue control method, this method combines forging preform and forging process parameter design of the whole process, by adjusting the preform characteristic size and forging process parameters, in order to realize the active regulation of strain field and gradient temperature field under this process; through this control strain forging method and with the help of the existing adiabatic gradient heat treatment device ( figure 2 ) solves the problem of sudden change in the temperature field of the transition interface caused by the local circulating cooling water system in the background technology, and provides an effective way for the precise regulation of the gradual change structure of the turbine disk

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