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A method for the assessment of operational severity for a high pressure turbine blade of an aero-engine
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Abstract
This paper provides a tool for the estimation of
the operational severity of a high pressure turbine blade
of an aero engine. A multidisciplinary approach using aircraft/
engine performance models which provide inputs to
a thermo-mechanical fatigue damage model is presented.
In the analysis, account is taken of blade size, blade
metal temperature distribution, relevant heat transfer coefficients and mechanical and thermal stresses. The leading
edge of the blade is selected as the critical part in the
estimation of damage severity for different design and operational
parameters. The study also suggests a method for
production of operational severity data for the prediction
of maintenance intervals.
Title: A method for the assessment of operational severity for a high
pressure turbine blade of an aero-engine
Description:
Abstract
This paper provides a tool for the estimation of
the operational severity of a high pressure turbine blade
of an aero engine.
A multidisciplinary approach using aircraft/
engine performance models which provide inputs to
a thermo-mechanical fatigue damage model is presented.
In the analysis, account is taken of blade size, blade
metal temperature distribution, relevant heat transfer coefficients and mechanical and thermal stresses.
The leading
edge of the blade is selected as the critical part in the
estimation of damage severity for different design and operational
parameters.
The study also suggests a method for
production of operational severity data for the prediction
of maintenance intervals.
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