Hostname: page-component-586b7cd67f-g8jcs Total loading time: 0 Render date: 2024-11-28T01:38:48.932Z Has data issue: false hasContentIssue false
  • English
  • Français

Scale effects on conventional and intercooled turbofan engine performance

Part of: ISABE 2017

Published online by Cambridge University Press:  08 June 2017

Andrew Rolt ,
Vishal Sethi ,
Florian Jacob ,
Joshua Sebastiampillai ,
Carlos Xisto ,
Tomas Grönstedt  and
Lorenzo Raffaelli
Andrew Rolt*
Affiliation:
School of Aerospace, Transport and Manufacturing, Cranfield University, Bedfordshire, UK
Vishal Sethi
Affiliation:
School of Aerospace, Transport and Manufacturing, Cranfield University, Bedfordshire, UK
Florian Jacob
Affiliation:
School of Aerospace, Transport and Manufacturing, Cranfield University, Bedfordshire, UK
Joshua Sebastiampillai
Affiliation:
School of Aerospace, Transport and Manufacturing, Cranfield University, Bedfordshire, UK
Carlos Xisto
Affiliation:
Department of Mechanics and Maritime Sciences, Chalmers University of Technology, Göteborg, Sweden
Tomas Grönstedt
Affiliation:
Department of Mechanics and Maritime Sciences, Chalmers University of Technology, Göteborg, Sweden
Lorenzo Raffaelli
Affiliation:
Performance Analysis Department, Rolls-Royce plc, Derby, UK
*
[email protected]
Get access Rights & Permissions [Opens in a new window]

Abstract

New commercial aero engines for 2050 are expected to have lower specific thrusts for reduced noise and improved propulsive efficiency, but meeting the ACARE Flightpath 2050 fuel-burn and emissions targets will also need radical design changes to improve core thermal efficiency. Intercooling, recuperation, inter-turbine combustion and added topping and bottoming cycles all have the potential to improve thermal efficiency. However, these new technologies tend to increase core specific power and reduce core mass flow, giving smaller and less efficient core components. Turbine cooling also gets more difficult as engine cores get smaller. The core-size-dependent performance penalties will become increasingly significant with the development of more aerodynamically efficient and lighter-weight aircraft having lower thrust requirements. In this study the effects of engine thrust and core size on performance are investigated for conventional and intercooled aeroengine cycles. Large intercooled engines could have 3%–4% SFC improvement relative to conventional cycle engines, while smaller engines may only realize half of this benefit. The study provides a foundation for investigations of more complex cycles in the EU Horizon 2020 ULTIMATE programme.

Keywords

Horizon 2020ULTIMATEFlightpath 2050propulsion
Type
Research Article
Information
The Aeronautical Journal , Volume 121 , Special Issue 1242: The International Society of Air-breathing Engines (ISABE) 2017 Conference Special Issue , August 2017 , pp. 1162 - 1185
Copyright
Copyright © Royal Aeronautical Society 2017 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

Footnotes

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

References

REFERENCES

1. Parker, R. Challenges of advanced propulsion systems development for future civil air transport, General Lecture 1, ICAS-2014-0.2 ICAS Conference, 9 September 2014, St. Petersburg, Russia.Google Scholar
2. Grönstedt, T. et al. Ultra low emissions technology innovations for mid-century aircraft turbine engines, GT2016-56123, ASME Turbo Expo, June 2016, Seoul, Korea.Google Scholar
3.ULTIMATE project website: Available at: http://www.ultimate.aero.Google Scholar
4. ACARE. Realising Europe's vision for aviation, strategic research & innovation agenda, Volume 1, Advisory Council for Aviation Research and Innovation in Europe, 2012. Available at: http://www.acare4europe.com/sites/acare4europe.org/files/attachment/SRIA%20Volume%201.pdf Google Scholar
5. Rolt, A. and Baker, N. Intercooled turbofan engine design and technology research in the EU framework 6 NEWAC programme, ISABE-2009-1278, ISABE 2009 Conference, 2009, Montreal, Canada.Google Scholar
6. Rolt, A. and Kyprianidis, K. Assessment of new aeroengine core concepts and technologies in the EU framework 6 NEWAC programme, ICAS-2010-408, ICAS Conference, September 2010, Nice, France.Google Scholar
7. Kyprianidis, K. and Rolt, A. On the optimisation of a geared fan intercooled core engine design, J Engineering for Gas Turbines and Power, 2015, 137, (4), p 041201.CrossRefGoogle Scholar
8. Camilleri, W. et al. Performance characteristics and optimisation of a geared intercooled reverse flow core engine, Proceedings of the Institution of Mechanical Engineers, Part G: J Aerospace Engineering, 2015, vol. 229, no. (2), pp 269–279.Google Scholar
9. Camilleri, W. et al. Concept description and assessment of the main features of a geared intercooled reversed flow core engine, Proceedings of the Institution of Mechanical Engineers, Part G: J Aerospace Engineering, 2015, 229, (9), pp 1631–1639.Google Scholar
10. Anselmi, E. et al. Assessment of the low pressure turbine exhaust design challenges in a geared intercooled reversed flow core engine, ISABE-2015-20200, ISABE 2015 Conference, October 2015, Phoenix, Arizona, US.Google Scholar
11. Zhao, X. and Grönstedt, T. Conceptual design of a two-pass cross-flow aeroengine intercooler, Proceedings of the Institution of Mechanical Engineers, Part G: J Aerospace Engineering, 2015, vol. 229, no. (11), pp 2006–2023.Google Scholar
12. Walsh, P.P. and Fletcher, P. Gas Turbine Performance, 2nd ed, 2004, Blackwell Science Ltd, Oxford, UK. ISBN: 9780632064342.Google Scholar