CN-122020917-A - Fretting fatigue life prediction method, system, equipment, medium and product for turbine disk-guide disk rotor system

CN122020917ACN 122020917 ACN122020917 ACN 122020917ACN-122020917-A

Abstract

The application discloses a fretting fatigue life prediction method, a fretting fatigue life prediction system, fretting fatigue life prediction equipment, fretting fatigue life prediction medium and fretting fatigue life prediction products for a turbine disk-guide disk rotor system, and relates to the field of damage analysis of the turbine disk-guide disk rotor system; the method comprises the steps of identifying a dangerous area of a turbine disc-guide disc rotor system according to a dangerous area identification model, determining a corresponding surface optimization process according to a metal material, optimizing the surface state of the dangerous area to obtain an optimized dangerous area, further constructing a life prediction model, and determining the fretting fatigue life of the turbine disc-guide disc rotor system according to the life prediction model. The application can accurately predict the fretting fatigue life of the turbine disc-guide disc rotor system.

Inventors

ZHANG XIANCHENG
WU KUNYU
LI KAISHANG
WANG RUNZI
HE KANG
TU SHANDONG

Assignees

华东理工大学

Dates

Publication Date: 20260512
Application Date: 20260413

Claims (10)

1. The fretting fatigue life prediction method for the turbine disk-guide disk rotor system is characterized by comprising the following steps of: obtaining the geometric structure and the metal material of a turbine disc-guide disc rotor system; The method comprises the steps of constructing a dangerous area identification model according to the geometric structure and a metal material, identifying a dangerous area of a turbine disc-flow guiding disc rotor system according to the dangerous area identification model, carrying out finite element modeling according to the geometric structure by using the dangerous area identification model, simulating the mechanical property of the metal material by using an improved Chaboche circulation constitutive model to obtain a stress-strain-displacement field, introducing a circulating plastic work parameter driven by multi-parameter damage under the action of micro-motion and fatigue coupling load, and automatically identifying the dangerous area of the turbine disc-flow guiding disc rotor system, wherein the dangerous area is positioned at a connecting interface of the turbine disc and the flow guiding disc; analyzing a metal material of the dangerous area, and determining a surface optimization process to optimize the dangerous area, wherein the surface optimization process comprises a water jet strengthening process; the method comprises the steps of constructing a life prediction model according to an optimized dangerous area, determining the fretting fatigue life of a turbine disc-flow guiding disc rotor system according to the life prediction model, performing finite element modeling on the dangerous area based on a crystal plasticity finite element method by using the life prediction model, and determining the fretting fatigue life of the turbine disc-flow guiding disc rotor system by using an improved crystal plasticity constitutive model.
2. The method for predicting fretting fatigue life for a turbine disk-diaphragm rotor system according to claim 1, wherein the constructing a dangerous area identification model according to the geometry and the metal material specifically comprises: Determining corresponding mechanical test data according to the metal material of the turbine disc-flow guiding disc rotor system, wherein the mechanical test data comprises high-temperature tensile data and low-cycle fatigue data; performing parameter calibration on the Chaboche-cycle constitutive model according to the mechanical test data to obtain an improved Chaboche-cycle constitutive model; And constructing a dangerous area identification model according to the geometric structure and the improved Chaboche circulation constitutive model.
3. The method for predicting fretting fatigue life for a turbine disk-diaphragm rotor system of claim 1, wherein said analyzing the metallic material of the hazardous area to determine a surface optimization process to optimize the hazardous area comprises: extracting surface contour point coordinates and normal vectors of the dangerous area, and determining the contour of the dangerous area; planning an optimized track of the dangerous area according to the outline of the dangerous area; and optimizing the crystal grain morphology of the surface of the dangerous area by utilizing a surface optimization process according to the optimization track to obtain an optimized dangerous area.
4. The method for predicting fretting fatigue life of a turbine disk-diaphragm rotor system of claim 2, wherein said determining the fretting fatigue life of a turbine disk-diaphragm rotor system based on said life prediction model comprises: performing parameter calibration on the crystal plastic constitutive model according to the mechanical test data to obtain an improved crystal plastic constitutive model; Performing finite element modeling on the dangerous area by using a crystal plasticity finite element method, and determining accumulated energy dissipation of the dangerous area by using an improved crystal plasticity constitutive model; and determining the fretting fatigue life of the turbine disk-guide disk rotor system according to the accumulated energy dissipation.
5. The method for fretting fatigue life prediction for a turbine disk-diaphragm rotor system according to claim 4, wherein said determining and utilizing the improved crystal plasticity constitutive model determines cumulative energy dissipation in the hazard zone, specifically comprises: using the formula Determining cumulative energy dissipation in a hazardous area ; Wherein, the The number of the slip system is given, For the total number of slip trains, In order to be able to take the moment of time, Is the first The shear stress of the decomposition on the slip system, Is the first Shear strain rate on the slip train.
6. The method for predicting fretting fatigue life of a turbine disk-diaphragm rotor system of claim 4, wherein said determining the fretting fatigue life of a turbine disk-diaphragm rotor system based on the accumulated energy dissipation comprises: using the formula Determining the fretting fatigue life of the turbine disk-diaphragm rotor system; Wherein, the In order to accumulate the energy dissipation threshold value, In order to set the parameters of the hardening, In order for the fatigue crack to initiate life, Cumulative energy dissipation values for weekly times.
7. The fretting fatigue life prediction system for the turbine disk-guide disk rotor system is characterized by comprising the following components: The geometric structure and metal material acquisition module is used for acquiring the geometric structure and metal material of the turbine disc-flow guide disc rotor system; The system comprises a dangerous area identification model construction module, a dangerous area identification model, a dynamic area control module and a dynamic area control module, wherein the dangerous area identification model construction module is used for constructing a dangerous area identification model according to the geometric structure and a metal material, identifying a dangerous area of a turbine disc-flow guiding disc rotor system according to the dangerous area identification model, performing finite element modeling according to the geometric structure, simulating the mechanical property of the metal material by using an improved Chaboche cycle constitutive model to obtain a stress-strain-displacement field, introducing a cycle plastic work parameter driven by multi-parameter damage under the action of micro-motion and fatigue coupling load, and automatically identifying the dangerous area of the turbine disc-flow guiding disc rotor system, wherein the dangerous area is positioned at a connecting interface of the turbine disc and the flow guiding disc; The dangerous area optimizing module is used for analyzing the metal material of the dangerous area and determining a surface optimizing process to optimize the dangerous area, wherein the surface optimizing process comprises a water jet strengthening process; The life prediction model construction module is used for constructing a life prediction model according to the optimized dangerous area, determining the fretting fatigue life of the turbine disc-flow guiding disc rotor system according to the life prediction model, carrying out finite element modeling on the dangerous area based on a crystal plasticity finite element method, and determining the fretting fatigue life of the turbine disc-flow guiding disc rotor system by utilizing the improved crystal plasticity constitutive model.
8. A computer device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, wherein the processor executes the computer program to implement the method of fretting fatigue life prediction for a turbine disk-diaphragm rotor system of any of claims 1-6.
9. A computer readable storage medium having stored thereon a computer program, which when executed by a processor implements the fretting fatigue life prediction method for a turbine disk-diaphragm rotor system according to any of claims 1-6.
10. A computer program product comprising a computer program, characterized in that the computer program, when executed by a processor, implements the fretting fatigue life prediction method for a turbine disk-diaphragm rotor system according to any of claims 1-6.

Description

Fretting fatigue life prediction method, system, equipment, medium and product for turbine disk-guide disk rotor system Technical Field The application relates to the field of damage analysis of a turbine disc-flow guide disc rotor system, in particular to a fretting fatigue life prediction method, a fretting fatigue life prediction system, fretting fatigue life prediction equipment, fretting fatigue life prediction media and fretting fatigue life prediction products for the turbine disc-flow guide disc rotor system. Background When the damage of the turbine disc-guide disc rotor system is analyzed, the mechanical behavior and the damage evolution process of the hot end component in the service process need to be researched. However, the mechanical behavior and the damage evolution process of the hot end component in the service process are extremely complex, and are not only embodied on the nano-scale (such as atomic arrangement, dislocation movement or lattice distortion, etc.), but also embodied on the macroscopic scale (deformation behavior and stress state). For damage analysis of a high-temperature structure, research can be conducted from four scales of a nano scale, a micro scale, a macro scale and a structural scale. Currently, researchers are mostly focused on multi-scale damage studies in parallel and in series. Parallel multi-scale damage studies are often used for qualitative studies of damage. Although micro-nano scale characterization and simulation methods can well reveal the deformation and damage mechanisms of materials, the damage forms of engineering components cannot be quantitatively described. The serial multi-scale damage research can determine the corresponding relation between microscopic parameters and macroscopic service life and realize multi-scale simulation of the high-temperature component, but neglect the time-space synchronicity of interaction influence among different scales, so that the prediction capability is reduced. Therefore, based on the above-mentioned problems, it is highly desirable to provide a fretting fatigue life prediction method for a turbine disk-diaphragm rotor system, which can accurately predict the fretting fatigue life of the turbine disk-diaphragm rotor system. Disclosure of Invention The application aims to provide a fretting fatigue life prediction method, a fretting fatigue life prediction system, fretting fatigue life prediction equipment, fretting fatigue life prediction media and fretting fatigue life prediction products for a turbine disc-flow guiding disc rotor system. In order to achieve the above object, the present application provides the following solutions: in a first aspect, the present application provides a fretting fatigue life prediction method for a turbine disk-diaphragm rotor system, comprising: obtaining the geometric structure and the metal material of a turbine disc-guide disc rotor system; The method comprises the steps of constructing a dangerous area identification model according to the geometric structure and a metal material, identifying a dangerous area of a turbine disc-flow guiding disc rotor system according to the dangerous area identification model, carrying out finite element modeling according to the geometric structure by using the dangerous area identification model, simulating the mechanical property of the metal material by using an improved Chaboche circulation constitutive model to obtain a stress-strain-displacement field, introducing a circulating plastic work parameter driven by multi-parameter damage under the action of micro-motion and fatigue coupling load, and automatically identifying the dangerous area of the turbine disc-flow guiding disc rotor system, wherein the dangerous area is positioned at a connecting interface of the turbine disc and the flow guiding disc; analyzing a metal material of the dangerous area, and determining a surface optimization process to optimize the dangerous area, wherein the surface optimization process comprises a water jet strengthening process; the method comprises the steps of constructing a life prediction model according to an optimized dangerous area, determining the fretting fatigue life of a turbine disc-flow guiding disc rotor system according to the life prediction model, performing finite element modeling on the dangerous area based on a crystal plasticity finite element method by using the life prediction model, and determining the fretting fatigue life of the turbine disc-flow guiding disc rotor system by using an improved crystal plasticity constitutive model. Optionally, the building the dangerous area identification model according to the geometric structure and the metal material specifically comprises the following steps: Determining corresponding mechanical test data according to the metal material of the turbine disc-flow guiding disc rotor system, wherein the mechanical test data comprises high-temperature tensile data and low-cycle fatigue data;