No abstract

The aero-gas turbine has undergone significant development to improve the thrust to weight ratio. These developments have increased the engine’s capability to withstand elevated temperatures which corresponds to both improved performance and increases in hot section creep. In addition, as the engine’s condition degrades over time, the gas generator’s rotational speed, free body stresses, and the hot gas temperature are further increased. To maximize the potential safe life of an engine and reduce operating costs, understanding the effects of engine component degradations on component life is essential. This paper examines the effects of engine degradation on the failure mechanism of creep, and presents a method in which the metal temperatures can be tied to transient parameters. The use of transient parameters enables engine stresses and temperatures to be determined at any operating point, which is essential for military aircraft engines.