Aeroengine combustion chamber service life prediction method

An aero-engine and life prediction technology, which is applied in computer-aided design, special data processing applications, instruments, etc., can solve the problems of high experimental cost, inability to accurately reproduce the aero-engine combustion chamber, and inability to reflect the impact of aero-engine combustion chamber life, etc. , to achieve the effect of reducing the number of experiments

Active Publication Date: 2018-04-10
TIANJIN UNIV
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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 h

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  • Aeroengine combustion chamber service life prediction method

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Embodiment Construction

[0025] The present invention will be described below in conjunction with the accompanying drawings and embodiments.

[0026] (1) CFD analysis of the aero-engine combustion chamber: the QAR data of the aircraft can be analyzed to obtain the typical working conditions of the aero-engine, and the engine is tested on the test bench to obtain the aerodynamic parameters of the combustion chamber inlet and outlet during the engine working process and Engine operating state parameters such as fuel consumption; conduct non-contact 3D scanning of the CFM56-3 engine solid model, obtain CFM56-3 engine point cloud data and generate a 3D engine model, and combine the structure of the engine to rationally simplify the 3D model and select the appropriate Computational domain, the grid discretization of the computational domain, considering the combustion process, the mixing process of hot and cold air flow, the heat transfer process between the fluid domain and the solid domain during the work...

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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 ...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/17G06F2119/04
Inventor 张俊红戴胡伟林杰威
Owner TIANJIN UNIV
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