Performance analysis of an Aero Engine with Interstage Turbine Burner

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Abstract

The historical trends of reduction in fuel consumption and emissions from aero engines have been mainly due to the improvement in the thermal efficiency, propulsive efficiency and combustion technology. The engine Overall Pressure Ratio (OPR) and Turbine Inlet Temperature (TIT) are being increased in the pursuit of increasing the engine thermal efficiency. However, this has an adverse effect on engine NOx emission. The current paper investigates a possible solution to overcome this problem for future generation Very High Bypass Ratio (VHBR)/Ultra High Bypass Ratio (UHBR) aero-engines in the form of an Inter-stage Turbine Burner (ITB). The ITB concept is investigated on a next generation baseline VHBR aero engine to evaluate its effect on the engine performance and emission characteristics for different ITB energy fractions. It is found that the ITB can reduce the bleed air required for cooling the HPT substantially (around 80%) and also reduce the NOx emission significantly (>30%) without penalising the engine specific fuel consumption.
Original languageEnglish
Pages (from-to)1605-1626
Number of pages22
JournalThe Aeronautical Journal
Volume121
DOIs
Publication statusE-pub ahead of print - 2017
Event23rd ISABE 2017 Conference - Manchester, United Kingdom
Duration: 3 Sep 20178 Sep 2017
Conference number: 23
https://isabe2017.org/

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