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Design and simulation of high temperature rise triple-swirler combustor

Published online by Cambridge University Press:  11 December 2024

D. Wang Open the ORCID record for D. Wang [Opens in a new window] ,
F. Li ,
H. Lin ,
Y. Tan ,
K. Wang ,
D. Wang ,
Y. Zhao ,
K. Zhao  and
T. Zhou
D. Wang
Affiliation:
School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing, China
F. Li*
Affiliation:
School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing, China
H. Lin
Affiliation:
Shenyang Engine Research Institute, Aero Engine Corporation of China, Shenyang, China
Y. Tan
Affiliation:
School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing, China Gas Turbine Establishment, Aero Engine Corporation of China, Chengdu, China
K. Wang
Affiliation:
School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing, China
D. Wang
Affiliation:
School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing, China
Y. Zhao
Affiliation:
School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing, China
K. Zhao
Affiliation:
School of Aviation Operations and Services, Aviation University of Air Force, Changchun, China
T. Zhou
Affiliation:
School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing, China
*
Corresponding author: F. Li; Email: lifeng01@buaa.edu.cn
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Abstract

To meet the development needs of aeroengines for high thrust-to-weight ratios and fuel-air ratios, a high temperature rise triple-swirler main combustor was designed with a total fuel-air ratio of 0.037, utilising advanced technologies including staged combustion, multi-point injection and multi-inclined hole cooling. Fluent software was used to conduct numerical simulations under both takeoff and idle conditions, thereby obtaining the distribution characteristics of the velocity and temperature fields within the combustor, as well as the generation of pollutants. The simulation results indicate that under takeoff conditions, the high temperature rise triple-swirler combustor achieves a total pressure loss coefficient of less than 6% and a combustion efficiency exceeding 99%. Under takeoff conditions, the OTDF and RTDF values are 0.144 and 0.0738, respectively. The mole fraction of NOx emissions is 3,700ppm, while the mole fraction of soot emissions is 2.55×10−5ppm. Under idle conditions, the triple-swirler combustor maintains a total pressure loss coefficient of less than 6% and a combustion efficiency greater than 99.9%. The OTDF and RTDF values are 0.131 and 0.0624, respectively. The mole fractions of CO and UHC emissions are both 0×10−32ppm at the calculation limit of Fluent software.

Keywords

high temperature rise combustortriple-swirler combustormain combustor designcentral staged combustornumerical simulation

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 129 , Issue 1335 , May 2025 , pp. 1320 - 1360
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Copyright
© The Author(s), 2024. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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