CN-121980860-A - Dual-performance disk transition zone trans-scale design method taking fatigue life as constraint

CN121980860ACN 121980860 ACN121980860 ACN 121980860ACN-121980860-A

Abstract

The invention discloses a cross-scale design method for a transition zone of a dual-performance disk with fatigue life as constraint. According to the invention, a low cycle fatigue life prediction method considering microstructure is established and combined with a macroscopic turbine disk model, so that trans-scale analysis from macroscopic turbine disk structure model stress strain distribution to microscopic grain structure energy distribution is realized, microscopic energy criteria are combined to determine the low cycle fatigue life of microstructure at different positions, and finally, the transition region position of the dual-performance disk is designed based on the principle of maximizing utilization of fatigue life storage, so that different tissue partition schemes of the final dual-performance disk are obtained. In addition, the method can fully consider the fatigue performance difference caused by different microstructures of the dual-performance disc, and the final design result has a larger improvement on the fatigue life compared with the existing scheme.

Inventors

JIANG RONG
ZHAO YANG
Wu Haokang
ZHANG SUYUAN
SONG YINGDONG

Assignees

南京航空航天大学

Dates

Publication Date: 20260505
Application Date: 20260121

Claims (5)

1. A method for cross-scale design of a dual-performance disk transition zone with fatigue life as a constraint, the method comprising the steps of: s1, sampling materials in different microstructure areas of a transition area of a dual-performance turbine disk of an aeroengine, and processing the materials into a standard tensile sample and a low-cycle fatigue sample to obtain tensile stress strain curves, fatigue hysteresis loops and fatigue lives of the materials with different microstructures; S2, carrying out microscopic finite element modeling on different microstructures of the transition region, and calibrating microscopic crystal plastic constitutive parameters by taking tensile stress strain curves and fatigue hysteresis loops of different tissue materials acquired in a material mechanical property acquisition stage as targets to obtain microscopic crystal plastic constitutive parameter values of the different tissue materials; S3, calibrating macroscopic viscoplastic constitutive parameters by taking the tensile stress strain curve and the fatigue hysteresis loop of the different tissue materials obtained in the material mechanical property obtaining stage as targets to obtain macroscopic viscoplastic constitutive parameter values of the different tissue materials; S4, performing ABAQUS finite element analysis on the macroscopic sample model by adopting a macroscopic Chaboche viscoplastic constitutive model to obtain stress strain distribution of dangerous parts, extracting local stress strain distribution of the dangerous parts by utilizing a sub-model method principle in ABAQUS finite element analysis software as a microscopic model loading boundary condition, and performing finite element analysis on the microscopic model to obtain strain energy dissipation density distribution; s5, taking the total strain energy dissipation density of the material during fatigue fracture as the property of the material, and establishing a life prediction model through two groups of low-cycle fatigue tests and corresponding finite element simulation; S6, carrying out finite element analysis on a real turbine disc structure, and obtaining the positions of stress and strain maximum values of different tissue areas of the real turbine disc structure as dangerous point positions of the turbine disc; S7, carrying out macroscopic stress strain analysis on the turbine disc with the uniform fine grain structure to obtain the stress distribution of dangerous points of the wheel center, adopting a trans-scale life prediction method to analyze the position of the wheel center to obtain the minimum low cycle fatigue life of the turbine disc with the uniform fine grain structure, carrying out trans-scale life prediction on different microstructures in a transition zone structure of the dual-performance disc to obtain the microstructure position with the minimum low cycle fatigue life in the transition zone structure and the constitutive parameter value thereof, setting the turbine disc material as the microstructure with the minimum low cycle fatigue life in the transition zone structure, carrying out macroscopic stress strain analysis on the microstructure to obtain the integral stress distribution, inserting corresponding microstructure submodels at the positions with different stress values along the direction from the wheel center to the wheel rim, carrying out life prediction to obtain the low cycle fatigue life of the different positions, comparing the low cycle fatigue life with the minimum cycle fatigue life of the turbine disc with the uniform fine grain structure, and selecting the stress position of the turbine disc with the transition zone when the two lives are close to be used as the boundary points of the fine grain structure and the transition zone structure of the dual-performance disc; S8, carrying out macroscopic stress strain analysis on the turbine disc with the uniform coarse-grain structure to obtain stress distribution at the root of the rim tongue-and-groove, analyzing the tongue-and-groove position by adopting a trans-scale life prediction method to obtain the minimum cycle fatigue life of the turbine disc rim with the uniform coarse-grain structure, and selecting the stress position of which the minimum cycle fatigue life of the turbine disc rim with the uniform coarse-grain structure is approximately equal to that of the turbine disc rim with the uniform coarse-grain structure as the boundary point of the coarse-grain structure and the transition region structure by adopting the microstructure material parameter with the lowest cycle fatigue life in the transition region structure as the turbine disc material parameter and repeating the method of selecting the boundary point of the fine-grain structure and the transition region structure.
2. The method of claim 1, wherein in step S1, different microstructure tensile stress strain curves, fatigue hysteresis loops and low cycle fatigue life are obtained by experimentation.
3. The method according to claim 1, characterized in that in step S2, microscopic finite element modeling work of different microstructures is done by the modeling method in patent CN120562190 a; In step S2, the microcosmic crystal plastic constitutive parameters are calibrated by the constitutive parameter calibration method in patent CN 114496122B.
4. The method according to claim 1, wherein in step S3, the macroscopic viscoplastic constitutive parameters are calibrated by the constitutive parameter calibration method in patent CN 110348055B.
5. The method of claim 1, wherein in step S5, the life prediction model is represented by the following formula: In the formula, The total strain energy dissipation density of the material at fatigue fracture; the fatigue cycle simulated when the fatigue is simulated for the finite element is repeated; the strain energy dissipation density of the model at the end of the finite element simulation fatigue; is the fatigue life of the material; The final fatigue cycle Zhou Cishi strain energy dissipation density increment is simulated for finite elements.

Description

Dual-performance disk transition zone trans-scale design method taking fatigue life as constraint Technical Field The invention relates to the technical field of aeroengine development, in particular to a cross-scale design method for a transition zone of a dual-performance disk with fatigue life as constraint. Background The turbine disk is one of the most critical core hot end components of the aero-engine, and the working environment is very harsh under the service environments of high temperature, high pressure, high rotating speed, alternating load and the like. The rim part is in direct contact with high-temperature fuel gas, so that the rim part is required to have higher temperature bearing capacity and higher lasting and creep strength requirements. The hub portion receives a very high centrifugal load due to a very high rotational speed of the turbine disk, although the hub portion receives a relatively low temperature. Thus, the hub portion is required to have high yield strength and low cycle fatigue performance. Aiming at different design requirements of different parts of the turbine disk component, the powder superalloy dual-performance disk processed by adopting the gradient heat treatment process can better meet the requirements. The dual-performance disc, namely the wheel rim is of a coarse-grain structure, has good durability and creep resistance, and the wheel hub is of a fine-grain structure, has good strength and fatigue resistance. Because of the different fatigue life caused by the uneven microstructure of different parts of the dual-performance disk, the microstructure difference must be taken into consideration in the design method for the design problem of the transition zone of the novel dual-performance disk with the fatigue life as a constraint. To achieve a new dual performance disk transition zone design that is constrained by fatigue life, a life assessment method that takes into account microstructure needs to be introduced and combined with a macroscopic turbine disk model. Most of the current patents for dual-performance disc structures focus on dual-performance disc structure preparation methods, and few patents are aimed at designing methods considering fatigue life of microstructure thereof. The patent with publication number CN115017756B 'a dual-performance disk fatigue life estimation method considering multi-axis stress gradient and grain size' mainly carries out fatigue life estimation based on macroscopic performance differences of different areas of the dual-performance disk, and does not consider microscopic differences of different positions of the dual-performance disk. Disclosure of Invention In order to overcome the defects and shortcomings of the prior art, the invention aims to provide a cross-scale design method for a transition zone of a dual-performance disk with fatigue life as constraint. The technical scheme provided by the invention is as follows: 1. A method for cross-scale design of a dual-performance disk transition zone with fatigue life as a constraint, the method comprising the steps of: S1, sampling materials in different microstructure areas of a transition area of a dual-performance turbine disk of an aeroengine, and processing the materials into a standard tensile sample and a low-cycle fatigue sample to obtain tensile stress strain curves, fatigue hysteresis loops and fatigue lives of the materials with different microstructures; S2, carrying out microscopic finite element modeling on different microstructures of the transition region, and calibrating microscopic crystal plastic constitutive parameters by taking tensile stress strain curves and fatigue hysteresis loops of different tissue materials acquired in a material mechanical property acquisition stage as targets to obtain microscopic crystal plastic constitutive parameter values of the different tissue materials; S3, calibrating macroscopic viscoplastic constitutive parameters by taking the tensile stress strain curve and the fatigue hysteresis loop of the different tissue materials obtained in the material mechanical property obtaining stage as targets to obtain macroscopic viscoplastic constitutive parameter values of the different tissue materials; S4, performing ABAQUS finite element analysis on the macroscopic sample model by adopting a macroscopic Chaboche viscoplastic constitutive model to obtain stress strain distribution of dangerous parts, extracting local stress strain distribution of the dangerous parts by utilizing a sub-model method principle in ABAQUS finite element analysis software as a microscopic model loading boundary condition, and performing finite element analysis on the microscopic model to obtain strain energy dissipation density distribution; s5, taking the total strain energy dissipation density of the material during fatigue fracture as the property of the material, and establishing a life prediction model through two groups of low-cycle fatigue tests an