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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
*
bhupendra.khandelwal@gmail.com
v.sethi@cranfield.ac.uk
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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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