Performance cycle analysis of a two-spool, separate-exhaust turbofan with interstage turbine burner
Document Type
Conference Proceeding
Publication Date
1-1-2004
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.
Publication Title
40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
Recommended Citation
Liew, K.,
Urip, E.,
Yang, S.,
Mattingly, J.,
&
Marek, C.
(2004).
Performance cycle analysis of a two-spool, separate-exhaust turbofan with interstage turbine burner.
40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.
http://doi.org/10.2514/6.2004-3311
Retrieved from: https://digitalcommons.mtu.edu/michigantech-p/13950