Performance Cycle Analysis of a Two-Spool, Separate-Exhaust Turbofan with Interstage Turbine Burner

Abstract

This paper presents the performance cycle analysis of a dual-spool, separate-exhaust turbofan engine, with an Interstage Turbine Burner 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 full and partial throttle operations. © 2004 by the American Institute of Aeronautics and Astronautics, Inc.