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Gas Turbine Engine Accelerated Life Test Commissioning Method

An accelerated life test and gas turbine technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve the problems of many life test cycles and high costs

Active Publication Date: 2017-01-11
CHINA AVIATION POWER MACHINE INST
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  • Claims
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Problems solved by technology

[0005] The purpose of the present invention is to provide a gas turbine engine accelerated life test test method, to solve the existing accelerated life test technology is difficult to implement fatigue damage, which will cause more life test cycles and high cost technical problems

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  • Gas Turbine Engine Accelerated Life Test Commissioning Method
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  • Gas Turbine Engine Accelerated Life Test Commissioning Method

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Embodiment Construction

[0055] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in various ways defined and covered.

[0056] figure 1 It is a schematic flow chart of the gas turbine engine accelerated life test test method of a preferred embodiment of the present invention, as figure 1 As shown, the preferred embodiment of the present invention provides a gas turbine engine accelerated life test test method, comprising the following steps: a, set up the acceleration factor analysis model under the gas turbine engine simulated operating conditions; b, according to the acceleration factor analysis model , use the support vector machine method to establish a proxy model for three-dimensional finite element stress analysis; c, use the proxy model to obtain the stress at the dangerous point of the acceleration factor analysis model, and obtain the life index of the acceleration factor analy...

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Abstract

The invention discloses a test run method for an accelerated life test of a gas turbine engine. The test run method comprises the steps that an accelerated factor analysis model of the gas turbine engine under simulated running conditions is established; according to the accelerated factor analysis model, a support vector machine method is used for establishing a surrogate model of three-dimensional finite element stress analysis; the surrogate model is used for obtaining dangerous point stress of the accelerated factor analysis model, and then life indexes of the accelerated factor analysis model are obtained; a Monte Carlo method is used for conducting stochastic simulation on random variables of the life indexes; an optimal design mathematical model of an accelerated life test scheme of stress under the simulated running conditions of the gas turbine engine is established and analyzed, and the test scheme is optimized according to the optimal design mathematical model; a mixing optimization method is adopted to optimize the mathematical model, and the optimized accelerated life test scheme is obtained according to the optimized mathematical model. By means of the test run method, the test period is shortened, and life test expenditure is reduced.

Description

technical field [0001] The invention relates to the field of gas turbine engine testing, in particular to a gas turbine engine accelerated life test test method. Background technique [0002] Reliability and durability are important indicators of gas turbine engines. As one of the most important and basic contents of reliability test, life test has a very important position. Through it, the distribution law of product life can be obtained, and important reliability indicators such as product failure rate and average life can be calculated. Early gas turbine engines had short lifespans and a life management model of periodic overhaul. The life test method is usually a 1:1 life long-term test run, and the life assessment of the first refurbishment period is generally carried out first, and the life after the refurbishment of the engine is then subjected to a long-life test until the total life is determined. However, in the past 20 years, due to the improvement of gas turbin...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
Inventor 米栋钱正明蔡显新
Owner CHINA AVIATION POWER MACHINE INST
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