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

An accelerated life test and turbine rotor technology, applied in design optimization/simulation, testing material strength by applying repetitive force/pulsation force, testing material strength by applying stable tension/pressure, etc., can solve the problem of blade acceleration rationality, very Issues such as blade life are less mentioned and difficult to explain, so as to achieve the effect of detailed basic data, guaranteed safety, and accurate calculation results

CN107247002APending Publication Date: 2017-10-13BEIHANG UNIV
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Publication Date
2017-10-13

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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.
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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...

Examples

Embodiment Construction

[0055] The technical solutions of the present invention will be further described below in conjunction with the accompanying drawings and through specific implementation methods.

[0056] Such as figure 1 Shown is the blade accelerated life test load spectrum design method considering the flight spectrum damage conversion in the present invention, comprising the following steps:

[0057] Step 1: Perform frequency mixing and rainflow counting processing on aero-engine flight missions and training subjects to obtain the frequency and time of each speed cycle in actual flight, consider ground maintenance and test data, and generate basic load data of the engine for 1000 flight hours;

[0058] Step 2: Use the finite element method to obtain the temperature field and stress-strain distribution of the blade in each state, analyze the static strength and enduring strength of the blade, and determine the life assessment position of the blade;

[0059] Step 3: Considering the engine f...