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Performance analysis of an aero engine with inter-stage turbine burner

Part of: ISABE 2017 Sustainable Aerospace

Published online by Cambridge University Press:  04 September 2017

F. Yin  and
A. Gangoli Rao
F. Yin
Affiliation:
Faculty of Aerospace Engineering, Delft University of Technology, Delft, The Netherlands
A. Gangoli Rao*
Affiliation:
Faculty of Aerospace Engineering, Delft University of Technology, Delft, The Netherlands
*
A.gangolirao@tudelft.nl
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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.

Keywords

Performance optimisationInter-stage Turbine BurnerTurbine cooling reductionLow NOx emission

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 121 , Issue 1245 , November 2017 , pp. 1605 - 1626
Copyright
Copyright © Royal Aeronautical Society 2017 

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Footnotes

This paper was presented at the ISABE 2017 Conference, 3-8 September 2017, Manchester, UK.

References

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