Parametric Cycle Analysis of Dual-Spool Mixed-Exhaust Turbofan with Interstage Turbine Burner

摘要

Gas turbine scientists and engineers are attempting to improve engine efficiencies, to make it smaller, lighter, less fuel consumption, increase thrust-to-weight ratio and to widen the thrust range of engine operation. This paper focuses on a parametric cycle analysis of dual-spool mixed-exhaust turbofan engine with Interstage Turbine Burner (ITB). The ITB considered in this paper is a relatively new concept in modern jet engine propulsion. The ITB serves as a secondary combustor and is located between the high-pressure and the low-pressure turbine, i.e., the transition duct. In the paper, the engine design parameters and flight condition were used to obtain the engine performance parameters, such as specific thrust and its specific fuel consumption. Performance of a dual-spool mixed-exhaust turbofan engine and a dual-spool mixed-exhaust turbofan engine with ITB utilizing transition duct were compared. Results show that the major advantages associated with the use of ITB are an increase in thrust and thermal efficiency, and reduces the tradeoff between specific thrust and specific fuel consumption.