Turbine rotor blade accelerated life test load design method taking regard of flight damage

Abstract

The invention relates to a turbine rotor blade accelerated life test load design method taking regard of flight damage. The method includes: 1) conducting frequency mixing treatment and rain flow counting on aeroengine flight missions and training subjects to acquire the frequency and time of each rotation speed cycle in actual flight, thus obtaining the load basic data of an engine within certain flight hours; 2) acquiring the temperature field and stress strain distribution of the blade under all states by finite element method, analyzing the blade static strength and endurance, and determining a lifetime testing part of the blade; 3) calculating the fatigue damage and creep damage of the blade testing part under a true flight load to acquire a ratio of creep damage and fatigue damage during rise and fall of a flight; and 4) designing a accelerated life test load spectrum of a full-size blade, and determining a conversion coefficient of the blade test load spectrum relative to out-field flight. The method provided by the invention can be used for acquiring the technical life of the blade and studying the remaining life of the blade, and saves time and economic cost for the fatigue-creep lifetime test of the blade.

Description

technical field [0001] The invention relates to the field of life testing of parts and components, and relates to a load design method for accelerated life tests of turbine rotor blades considering flight damage, which is mainly used in the life test research of turbine rotor blades of aeroengines, and provides technical support for determining and prolonging the life of engine turbine blades . Background technique [0002] Aeroengine rotor blades suffer from the interaction of fatigue damage and creep damage during operation, which is one of the frequent failures of aeroengines. The failure of turbine rotor blades will directly affect the maintenance cost of the engine, and its life research is an important part of engine life research. Theoretically, the prediction method of structural fatigue-creep life is still not perfect, so it is an important link in blade design and life research to carry out fatigue-creep life test research on blades. [0003] How to ensure that t...

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Problems solved by technology

[0004] The transition state and ground maintenance data during the actual flight of the engine are rarely considered in the current blade life research, which directly affects the accuracy of the damage calculation of the blade under the flight load; the relationship between the test load spectrum and the damage conversion under the flight load is also seldom It is mentioned that it is difficult to use the blade life test results to quantitatively explain the life of the blade under flight load; the rationality of the stress magnitude selection in the blade accelerated life test load spectrum is rarely mentioned

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