Creep - low cycle fatigue and louver lip collapse have been established as primary gas turbine combustion chamber failure modes by observation of field service and in-house endurance test hardware. Analytical models for these two failure modes have been developed an incorporated into a mission analysis program. The mission analysis program relates component environment (temperature, pressure and flow) to the aircraft engine and flight characteristics and thereby provides the forcing functions for the turbine and combustor failure models. The combined mission analysis - failure model program was used to predict component lives for transport and fighter/attack aircraft over representative missions. The sensitivity of the prediction system was established by perturbations to the mission and input parameters.
Reliability Prediction for Combustors and Turbines. Volume I
1977
86 pages
Report
Keine Angabe
Englisch
Jet & Gas Turbine Engines , Gas turbines , Combustors , Life expectancy , Reliability , Creep , Fatigue(Mechanics) , Vents , Combustion chambers , Mathematical models , Failure , Endurance(General) , Life tests , Turbine blades , Elastic properties , Plastic properties , Stress strain relations , Weibull density functions
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