Open AccessValidation of a simplified model for liquid propellant rocket engine combustion chamber design
Author(s) -
Moutaz Hegazy,
Hatem M. Belal,
Ah. El-S. Makled,
M. A. Al-Sanabawy
Publication year - 2020
Publication title -
iop conference series. materials science and engineering
Language(s) - English
Resource type - Journals
eISSN - 1757-899X
pISSN - 1757-8981
DOI - 10.1088/1757-899x/973/1/012003
Subject(s) - propellant , combustion chamber , liquid propellant rocket , thrust , combustion , aerospace engineering , rocket engine , chamber pressure , process (computing) , rocket (weapon) , mechanical engineering , mechanics , automotive engineering , nuclear engineering , computer science , engineering , physics , chemistry , organic chemistry , operating system
The combustion phenomena inside the thrust chamber of the liquid propellant rocket engine are very complicated because of different paths for elementary processes. In this paper, the characteristic length (L*) approach for the combustion chamber design will be discussed compared to the effective length (L eff ) approach. First, both methods are introduced then applied for real LPRE. The effective length methodology is introduced starting from the basic model until developing the empirical equations that may be used in the design process. The classical procedure of L* was found to over-estimate the required cylindrical length in addition to the inherent shortcoming of not giving insight where to move to enhance the design. The effective length procedure was found to be accurate within ± 10%.