Aeroengine combustion chamber service life prediction method

Abstract

The invention relates to an aeroengine combustion chamber service life prediction method. The method comprises following steps: aeroengine combustion chamber CFD analysis; aeroengine combustion chamber elastoplastic static analysis; aeroengine combustion chamber load spectrum compilation; aeroengine combustion chamber base alloy fatigue test piece design: designing hastelloy alloy creep-fatigue experimental standard pieces; aeroengine combustion chamber base alloy fatigue test load design; aeroengine combustion chamber base alloy test; using a combination of support vector machine (SVM) and genetic algorithm (GA), a model of alloy damage prediction for aeroengine combustor is established; aeroengine combustion chamber service life prediction is achieved.

Description

technical field [0001] The invention relates to a method for predicting the life of an aero-engine combustion chamber Background technique [0002] In order to improve the thrust-to-weight ratio of modern aero-engines, the operating temperature of aero-engines is getting higher and higher, and the thermal load of aero-engine hot-end parts is increasing. The aero-engine combustor is a key hot-end component of an aero-engine, and its fatigue reliability has a crucial impact on the safety of aircraft airworthiness and operation. Accurate prediction of the life of an aero-engine combustor is important for the development of aero-engine hot-end component damage theory. It has scientific significance and has engineering application value for ensuring flight safety and improving ground maintenance efficiency and economy. [0003] Limited by civil aviation operation safety regulations and experimental costs, it is difficult to reproduce the harsh service environment of aero-engine ...

AI Technical Summary

Problems solved by technology

Due to the complex and changeable actual operating conditions of aero-engine combustors, simple thermal boundary conditions cannot accurately reproduce the harsh working environment of aero-engine combustors; and some studies have shown that [4,5] , the cracking failure of the combustor matrix is ​​mainly caused by the interaction of fatigue and creep, and neither the Maansson-Coffin formula nor the modified Maansson-Coffin formula can reflect the effect of creep on the life of the aero-engine combustor

At present, some scholars have proposed some creep-fatigue life models based on damage mechanics or fracture mechanics. [6,7] , but these models need to fit the empirical parameters in the model through experiments. Since there are many factors affecting the creep-fatigue life, establishing an accurate life model requires a large number of fatigue tests, which leads to long test periods and high test costs; Moreover, due to the complex load of the aero-engine combustor, these models are difficult to accurately predict the life of the aero-engine combustor

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