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Preliminary design and performance analysis of a low emission aero-derived gas turbine combustor

Part of: Sustainable Aerospace

Published online by Cambridge University Press:  27 January 2016

B. Khandelwal ,
A. Karakurt ,
V. Sethi ,
R. Singh  and
Z. Quan
B. Khandelwal*
Affiliation:
School of Engineering, Cranfield University, Cranfield, Bedfordshire, UK
A. Karakurt
Affiliation:
School of Engineering, Cranfield University, Cranfield, Bedfordshire, UK
V. Sethi*
Affiliation:
School of Engineering, Cranfield University, Cranfield, Bedfordshire, UK
R. Singh
Affiliation:
School of Engineering, Cranfield University, Cranfield, Bedfordshire, UK
Z. Quan
Affiliation:
China Gas Turbine Establishment, Aviation Industry of China, Chengdu, Sichuan, China
*
[email protected]
[email protected]
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Abstract

Modern gas turbine combustor design is a complex task which includes both experimental and empirical knowledge. Numerous parameters have to be considered for combustor designs which include combustor size, combustion efficiency, emissions and so on. Several empirical correlations and experienced approaches have been developed and summarised in literature for designing conventional combustors. A large number of advanced technologies have been successfully employed to reduce emissions significantly in the last few decades. There is no literature in the public domain for providing detailed design methodologies of triple annular combustors.

The objective of this study is to provide a detailed method designing a triple annular dry low emission industrial combustor and evaluate its performance, based on the operating conditions of an industrial engine. The design methodology employs semi-empirical and empirical models for designing different components of gas turbine combustors. Meanwhile, advanced DLE methods such as lean fuel combustion, premixed methods, staged combustion, triple annular, multi-passage diffusers, machined cooling rings, DACRS and heat shields are employed to cut down emissions. The design process is shown step by step for design and performance evaluation of the combustor.

The performance of this combustor is predicted, it shows that NOx emissions could be reduced by 60%-90% as compared with conventional single annular combustors.

Type
Research Article
Information
The Aeronautical Journal , Volume 117 , Issue 1198 , December 2013 , pp. 1249 - 1271
Copyright
Copyright © Royal Aeronautical Society 2013 

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References

1. Lefebvre, A.H. and Dilip, R.B. Gas Turbine Combustion: Alternative Fuels and Emissions, 3rd ed, Taylor & Francis Group, LLC, New York, USA, 2010.Google Scholar
2. Mellor, A.M. Design of Modern Turbine Combustors, Combustion Treatise, Academic Press Inc, San Diego, USA, 1990.Google Scholar
3. Singh, R. Gas Turbine Application, non-public course notes, Cranfield University, 2010.Google Scholar
4. Joshi, N.D., Epstein, M.J., Durlak, S. Marakovits, S. and Sabla, P.E. Development of a Fuel-Air Premixer for Aero-Derivative Dry Low Emissions Combustor, ASME Paper 92-GT-253,1994.Google Scholar
5. Poeschl, G., Ruhkamp, W. and Pfost, H. Combustion with Low Pollutant Emissions of Liquid Fuel in Gas Turbine by Premixing and Prevaporization, ASME Paper 92-GT-443, 1994.Google Scholar
6. Group 1, Aero-derivative Industrial Gas Turbine Engine Based on AVIC Team-1 2009 Year’s Core Engine, MSc Thesis, Cranfield University, 2010.Google Scholar
7. Pilidis, P. Gas Turbine Theory and Performance, Unpublished Lecture Notes, Cranfield University, UK, 2010.Google Scholar
8. Mohammad, B.S. and Jeng, S.M. Design procedures and a Developed Computer Code for Preliminary Single Annular Combustor Design, University of Cincinnati, Cincinnati, USA, 2009.Google Scholar
9. Khandelwal, B., Yan, M., Hegde, G. and Sethi, V. ET AL Design procedure of a reverse flow combustor for a helicopter engine with high temperature rise, SAE Technical Paper 2011-01-2562, 2011, doi: 10.4271/2011-01-2562.Google Scholar
10. Cochran, D.L. and Kline, S.J. The Use of Short Flat Vanes as a Means for Producing Effcient Wide-Angle Two-Dimensional Subsonic Diffuser, NACA TN 4309,1958.Google Scholar
11. Joshi, N.D., Ekstedt, E.E. and Epstein, M.J. Air Fuel Mixer for Gas Turbine Combustor, US Patent Number 5251447, General Electric Company, 1992.Google Scholar
12. Ekstedt, E.E., Joshi, N.D. and Ablett, A.M. Triple Annular Combustor for Gas Turbine Engine, U.S. Patent Number 5323604, General Electric Company, 1994.Google Scholar
13. Lefebvre, A.H. Fuel effects on gas turbine combustion-liner temperature, pattern factor, and pollutant emissions, J Aircr, 1984, 21, (11), pp 887–98.Google Scholar
14. Odgers, J. and Kretscgmer, D. The Prediction of Thermal NO x in Gas Turbine, ASME Paper 85-1GT-126, 1985.Google Scholar
15. Lewis, G.D. A New Understanding of NO x Formation, Tenth International Symposium on Air-Breathing Engines, ISABE 91-7064, Nottingham, UK, AIAA, 1991,Washington, DC, USA, pp 625-9.Google Scholar
16. Frazier, T.R., Foglesong, R.E., Coverdill, R.E., Peters, J.E. and Lucht, R.P. Fuel-Air Mixing and Flame Structure Measurements for Advanced Low Emission Gas Turbine Combustors, Accession Number ADA386682, University of Illinois, Illinois USA, 2001.Google Scholar
17. Badeer, G.H., GE Aeroderivative Gas Turbine – Design and Operating Features, GE IAD, GE Power System, Evendale, OH, USA, GER-3695E.Google Scholar
18. Rizk, N.K. and Mongia, H.C. Emission Predictions of Different Gas Turbine Combustors, AIAA Paper 92-0118, 1994.Google Scholar