Cold flow studies in a vortex thrust chamber
Aircraft Engineering and Aerospace Technology
ISSN: 0002-2667
Article publication date: 6 November 2018
Issue publication date: 30 January 2019
Abstract
Purpose
The purpose of this paper is to estimate the chamber pressure and flow behaviour in a vortex thrust chamber (VTC) during the cold flow with hydrogen and oxygen as propellants.
Design/methodology/approach
Experiments are carried out in a VTC with a different mixture ratio of hydrogen and oxygen. The pressures developed inside the VTC are measured. Numerical simulations are carried out to understand the flow patterns of fuel and oxidizer inside the VTC.
Findings
The chamber pressure is influenced by the type of injection of propellant and mixture ratio. Tangential injection of propellant is the key parameter for an increase of the chamber pressure of the VTC.
Research limitations/implications
The pressure measurements are carried out in cold flow conditions without combustion happening in the VTC.
Practical implications
The practical implication is that when the combustion in the VTC ceases, the thrust generated due to the propellants in cold flow conditions can be assessed.
Originality/value
The VTC with the tangential injection of propellant generates higher chamber pressure.
Keywords
Acknowledgements
The authors would like to thank Dr Praveen Nair, Sujith Kumar R, Dr Ganesh P, Ravi S and scientists/technical experts at the Indian Space Research Organisation (ISRO) for their invaluable suggestions and consistent discussions while carrying out this research study.
Citation
T.N., R., Sarvoththama Jothi, T.J. and T., J. (2020), "Cold flow studies in a vortex thrust chamber", Aircraft Engineering and Aerospace Technology, Vol. 91 No. 1, pp. 69-77. https://doi.org/10.1108/AEAT-07-2017-0167
Publisher
:Emerald Publishing Limited
Copyright © 2018, Emerald Publishing Limited