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Method of predicting turbine wheel life

A technology of turbine impeller and life, which is applied in the field of micro-combustion turbine turbines, and can solve problems such as limited static strength

Pending Publication Date: 2021-09-21
北京永旭腾风新能源动力科技发展有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, most of the past studies were limited to static strength, and research on fatigue, damage tolerance, etc. is still insufficient.

Method used

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  • Method of predicting turbine wheel life
  • Method of predicting turbine wheel life
  • Method of predicting turbine wheel life

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0048] Embodiment 1 The method for predicting the service life of turbine impeller

[0049] The material of the turbine processed in this embodiment is exemplarily selected as K424 superalloy. K424 alloy is a new cast nickel-based superalloy independently developed by my country. It has high high-temperature strength, good plasticity and manufacturability, and high comprehensive performance. It is suitable for manufacturing turbine rotor blades and guide vanes that work below 950 ° C. part.

[0050] Such as figure 1 As shown in a and b, the geometric model of the turbine has a total of 12 blades, the radius of the wheel disc is 37mm, and the radius of the central hole matching the shaft is 4.5mm. Grooves and holes are dug on the turbine.

[0051]The specific material parameters of K424 cast superalloy are shown in Table 1.

[0052] Table 1 Material parameters of K424 alloy (600℃)

[0053]

[0054] The scheme for predicting the life of turbine blades is mainly based on th...

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Abstract

The invention discloses a method for predicting the service life of a turbine impeller. The method comprises the steps: setting a simulation criterion for simulating turbine crack propagation; according to stress analysis of the turbine, setting initial conditions and termination conditions for simulating crack propagation of the turbine; and based on the initial condition, utilizing a preset crack propagation algorithm to execute crack propagation simulation on the turbine impeller until a termination condition is met, obtaining a simulation result, and determining the predicted life of the crack propagation of the turbine impeller. According to the method for predicting the service life of the turbine impeller, the collapse unit is adopted to simulate the stress singularity of the crack tip on the basis of a method for simulating turbine crack propagation through the propagation finite element method, and the effect of simulating and predicting the crack propagation service life in a segmented mode is achieved. By means of the method, the crack propagation life of the turbine can be effectively predicted, stress intensity factors of cracks of different lengths of the turbine can be calculated, the crack propagation path can be determined, and a powerful basis is provided for fatigue analysis of the turbine.

Description

technical field [0001] The invention relates to a method for predicting the service life of a turbine impeller, which belongs to the technical field of turbines of micro-combustion engines. Background technique [0002] The micro-combustion engine uses continuously flowing gas as the working medium to drive the impeller to rotate at high speed, and converts the energy of the fuel into useful work. It is a rotating impeller heat engine. It mainly includes three parts: compressor, combustion chamber and turbine; the compressor inhales air from the external atmosphere, and compresses it step by step to pressurize it, and at the same time, the temperature of the air also increases accordingly; the compressed air is compressed to the combustion chamber and injected into the The fuel is mixed and burned to generate high-temperature and high-pressure gas; then it enters the turbine to expand and do work, pushing the turbine to drive the compressor and the external load rotor to rot...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/23G06F30/17G01M13/00G06F119/14
CPCG06F30/23G06F30/17G01M13/00G06F2119/14
Inventor 靳普
Owner 北京永旭腾风新能源动力科技发展有限公司
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