Parametric cycle analysis of a turbofan engine with an interstage turbine burner

Document Type

Article

Publication Date

1-1-2005

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 high-pressure 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.

Publication Title

Journal of Propulsion and Power

Link to Full Text

Share

COinS