Performance (Off-Design) Cycle Analysis for a Turbofan Engine With Interstage Turbine Burner

By National Aeronautics and Space Administration

This report presents the performance of a steady-state, dual-spool, separate-exhaust turbofan engine, with an interstage turbine burner (ITB) serving as a secondary combustor. The ITB, which is located in 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 off-design performance analysis of ITB engines is written in Microsoft(Registered Trademark) Excel (Redmond, Washington) macrocode with Visual Basic Application to calculate engine performances over the entire operating envelope. Several design-point engine cases are pre-selected using a parametric cycle-analysis code developed previously in Microsoft(Registered Trademark) Excel, for off-design analysis. The off-design code calculates engine performances (i.e. thrust and thrust-specific-fuel-consumption) at various flight conditions and throttle settings. Liew, K. H. and Urip, E. and Yang, S. L. and Mattingly, J. D. and Marek, C. J. Glenn Research Center NASA/TM-2005-213659, E-15149 WBS 22-066-10-12

• Format: Paperback
• Language: English
• ISBN: B08GG2RLDK
• ISBN13: 9798676604431
• Release Date: January 1
• Publisher: Independently Published
• Length: 80 Pages
• Weight: 0.46 lbs.
• Dimensions: 0.2" x 8.5" x 11.0"