Inlet air and fuel flow pressure fluctuation effect on supersonic combustion
Aircraft Engineering and Aerospace Technology
ISSN: 0002-2667
Article publication date: 30 October 2020
Issue publication date: 16 February 2021
Abstract
Purpose
The purpose of this paper is to analyze the effect of pressure fluctuations on the combustion efficiency of the hydrogen fuel injected into the supersonic oxidizing cross flow. The pressure fluctuations are imposed on inlet air flow and also on the fuel flow stream. Two different situations are considered: the combustion chamber once without and again with the inlet standing oblique shock wave.
Design/methodology/approach
The pressure fluctuations are imposed on inlet air flow and also on the fuel flow stream. Two different situations are considered: the combustion chamber once without and again with the inlet standing oblique shock wave. The unsteady turbulent reacting flow solver is developed to simulate the supersonic flow field in the combustion chamber with detail chemical kinetics, to predict the time-variation of the combustion efficiency due to the imposed pressure fluctuations.
Findings
The results show that the response of the reacting flow field depends on both the frequency of fluctuations and the existence of the inlet shock wave. In addition, the inlet standing shock wave has some attenuating role, but the reacting flow shows an amplifying role on imposed oscillations which is also augmented by imposing anti-phase fluctuations on both inlet and fuel flow streams.
Originality/value
This study is performed to analyze the instabilities in the supersonic combustion which has not been considered before in this manner.
Keywords
Citation
Tahsini, A. (2021), "Inlet air and fuel flow pressure fluctuation effect on supersonic combustion", Aircraft Engineering and Aerospace Technology, Vol. 93 No. 1, pp. 115-119. https://doi.org/10.1108/AEAT-12-2019-0268
Publisher
:Emerald Publishing Limited
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