Turbine disc-based low-cycle fatigue crack propagation life prediction method

A crack growth life, low cycle fatigue technology, applied in measuring devices, elasticity testing, machine/structural component testing, etc., can solve problems such as the inability to consider the effect of the crack growth rate of turbine disk grain size dispersion

Inactive Publication Date: 2017-05-10
BEIHANG UNIV
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Problems solved by technology

[0004] The technical solution of the present invention: Overcoming the inability of the existing technology to consider the dispersion of the grain size of different parts of the turbine disk and its influence on the crack growth rate, a method for predicting the life of a turbine disk structure under low-cycle fatigue crack growth can be accurately predicted Crack growth life, and obtain a life that satisfies a certain reliability, and quantify the failure risk of the structure

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  • Turbine disc-based low-cycle fatigue crack propagation life prediction method

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[0021] The method for predicting the life of a turbine disk based on the average grain size of low-cycle fatigue crack growth will be further described below in conjunction with the accompanying drawings.

[0022] From the perspective of grain size, strengthening phase / secondary phase distribution and other microstructures, combined with the observation of macroscopic crack closure, the influence of grain size on crack propagation behavior is quantified by introducing the life dispersion factor. The low-cycle crack growth research method of the size, its flow chart see figure 1 .

[0023] (1) Microscopic grain size data collection: Multiple samples were taken at three typical positions of the turbine disk edge A, disk center B and installation edge D, and the sampling frequency was 5-10 times. The microstructure characteristics were observed by scanning electron microscope. Including the distribution of grains, secondary phase / strengthening phase, measure and record the grain...

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Abstract

The invention relates to a turbine disc-based low-cycle fatigue crack propagation life prediction method, comprising the following steps: (1) collecting micro-data of different sampling positions of a turbine disc by using a scanning electron microscope, and obtaining a distribution rule; (2) designing a low-cycle fatigue test for the different positions, and collecting macro-data; (3) according to the data collected in steps (1) and (2), obtaining the distribution of a life scattering factor and a Paris formula considering the life dispersibility of the different sampling positions of the turbine disc; (4) performing static strength analysis to obtain a dangerous point position stress intensity factor deltaK, integrating by using the life scattering factor and the Paris formula considering the life dispersibility, which are obtained in step (3), then acquiring the relationship between crack propagation life and crack length, and giving the crack propagation life according to the crack length.

Description

technical field [0001] The invention is a method for predicting the life of a turbine / disc structure under low cycle fatigue crack growth in an aeroengine, which is a method for predicting the life of a turbine disk crack that can take into account the dispersion of factors such as grain size at different sampling locations, and belongs to aerospace engines. technology field. Background technique [0002] Aeroengine is an extreme product, working under complex loads / environments such as high temperature, high pressure, and high speed; the improvement of engine performance and safety indicators requires the engine to be light in weight, long in life, and high in reliability (for example, for safe flight Engine structural parts require a low probability of failure, up to 10 -5 -10 -7 times / flight hour). When predicting the traditional low-cycle fatigue crack growth life, the dispersion of the grain size in different parts of the turbine disk and its influence on the crack g...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N3/32G01M5/00
CPCG01N3/32G01M5/0033G01N2203/0066G01N2203/0073
Inventor 胡殿印刘茜毛建兴王西源王荣桥
Owner BEIHANG UNIV
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