Factors Affecting Characteristic Length of the Combustion Chamber of Liquid Propellant Rocket Engines

  • Tajwali Khan Department of Aeronautics and Astronautics, Institute of Space Technology, Islamabad, Pakistan
  • Ihtzaz Qamar Department of Aeronautics and Astronautics, Institute of Space Technology, Islamabad, Pakistan

Abstract

Optimum characteristic length of the combustion chamber of liquid rocket engine is very important to get higher energy from the liquid propellants. Characteristic length is defined by the time required for complete burning of fuel. Combustion reactions are very fast and combustion is evaporation dependent. This paper proposes fuel droplet evaporation model for liquid propellant rocket engine and discusses the factors which can affect the required size of characteristic length of the combustion chamber based on proposed model. The analysis is performed for low temperature combustion chamber. A computer code based on proposed model is generated, which solve analytical equations to calculate combustion chamber characteristic length under various input conditions. The analysis shows that characteristic length is affected by combustion chamber temperature, pressure, fuel droplet diameter, chamber diameter, mass flow rate of propellants and relative velocity of the droplet in the combustion chamber.

Published
Jul 1, 2019
How to Cite
KHAN, Tajwali; QAMAR, Ihtzaz. Factors Affecting Characteristic Length of the Combustion Chamber of Liquid Propellant Rocket Engines. Mehran University Research Journal of Engineering and Technology, [S.l.], v. 38, n. 3, p. 729-744, july 2019. ISSN 2413-7219. Available at: <http://publications.muet.edu.pk/index.php/muetrj/article/view/1143>. Date accessed: 19 july 2019.
Section
Articles
This is an open Access Article published by Mehran University of Engineering and Technolgy, Jamshoro under CCBY 4.0 International License