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research-article

Influence of swirl and primary zone airflow rate on the emissions and performance of a liquid fueled gas turbine combustor

[+] Author and Article Information
Parneeth Lokini

Department of Aerospace Engineering, Indian Institute of Technology, Kanpur, Uttar Pradesh, India
parlok7@gmail.com

Dinesh K Roshan

Department of Aerospace Engineering, Indian Institute of Technology, Kanpur, Uttar Pradesh, India
jsdinesh@iitk.ac.in

Abhijit Kushari

Professor, Department of Aerospace Engineering, Indian Institute of Technology, Kanpur, Uttar Pradesh, India
akushari@iitk.ac.in

1Corresponding author.

ASME doi:10.1115/1.4042410 History: Received September 08, 2018; Revised December 27, 2018

Abstract

This paper presents the results of an experimental study on the influence of swirl number (S) and primary zone airflow rate on the temperature, emission indices of the pollutants and combustion efficiency in an atmospheric pressure liquid fueled gas turbine combustor, equipped with a swirling jet air blast atomizer and operated with Jet A-1 fuel. Experiments were conducted at three primary zone air flow rates and three swirl numbers (0.49, 0.86, 1.32). For all the cases it was found that the NOx emissions were very low (< 2 g/kg of fuel). At all the swirl numbers, an increase in primary zone airflow led to a non-monotonous variation in CO while minimally affecting the NOx emissions. However, increase in the swirl number generated relatively higher NOx and lower CO owing to higher temperature resulting from efficient combustion caused by a superior fuel-air mixing. Also, the UHC was quite high at S = 0.49 because of the unmixedness of fuel and air, and zero at S = 0.86 and 1.32. The combustion efficiency was very low (around 60%) at S = 0.49 while almost 100% at S = 0.86 and 1.32. The study conducted demonstrates a significant dependence of emissions and gas turbine performance on the swirl number governed by the convective time scales and the residence time of the combustible mixture in the combustion zone.

Copyright (c) 2018 by ASME
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