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This paper presents the performance-cycle analysis of a dual-spool, separate-exhaust turbofan engine, with an interstage turbine burner (ITB) serving as a secondary combustor. The ITB, which is located at the transition duct between the high-and the low-pressure turbines, is a relatively new concept for increasing specific thrust and lowering pollutant emissions in modern jet engine propulsion. A detailed performance analysis of this engine has been conducted for steady-state engine performance prediction. A code is written and is capable of predicting engine performances (i.e., thrust and thrust specific fuel consumption) at varying flight conditions and throttle settings. Two design-point engines were studied to reveal trends in performance at both full and partial throttle operations. A mission analysis is also presented to ensure the advantage of saving fuel by adding ITB.

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Locating hotspots in metal engine components can be used as an impetus to design a better cooling system. This study focuses on a numerical investigation of a three-dimensional (3-D) transient heat transfer process for a Ford 5.4-L V8 engine. A 3-D transient finitevolume method to solve the heat conduction equation is presented first. This is followed by the implementation of the coupling equations at the gas-solid interface into the KIVA code. The numerical model is validated by a one-dimensional heat conduction problem. Finally, 3-D simulation of the Ford engine with conjugate heat transfer mode is presented and discussed.

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