Abstract
This study focuses on the parametric cycle analysis of a dual-spool, separate-flow turbofan engine with an interstage turbine burner (ITB). The ITB considered in this paper is a relatively new concept in modern jet engine propulsion. It serves as a secondary combustor and is located between the high-pressure and the low-pressure turbines, that is, the transition duct. The objective of this study is to use engine design parameters, such as highpressure and low-pressure turbine inlet temperatures to obtain engine performance parameters, for example, specific thrust and thrust specific fuel consumption. A turbine cooling model is also included. Results confirm the advantages of ITB, that is, higher specific thrust, less cooling air, and possibly less NOx production, provided that the main-burner exit temperature and ITB exit temperature are properly specified.
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