Validation of a simplified model for liquid propellant rocket engine combustion chamber design
Hegazy, M., Abdalla, H., Makled, A., Al-Sanabawy, M. (2020). Validation of a simplified model for liquid propellant rocket engine combustion chamber design. EKB Journal Management System, 19(19th International Conference on Applied Mechanics and Mechanical Engineering.), 1-14. doi: 10.1088/1757-899X/973/1/012003
M Hegazy; H M Abdalla; A Makled; M A Al-Sanabawy. "Validation of a simplified model for liquid propellant rocket engine combustion chamber design". EKB Journal Management System, 19, 19th International Conference on Applied Mechanics and Mechanical Engineering., 2020, 1-14. doi: 10.1088/1757-899X/973/1/012003
Hegazy, M., Abdalla, H., Makled, A., Al-Sanabawy, M. (2020). 'Validation of a simplified model for liquid propellant rocket engine combustion chamber design', EKB Journal Management System, 19(19th International Conference on Applied Mechanics and Mechanical Engineering.), pp. 1-14. doi: 10.1088/1757-899X/973/1/012003
Hegazy, M., Abdalla, H., Makled, A., Al-Sanabawy, M. Validation of a simplified model for liquid propellant rocket engine combustion chamber design. EKB Journal Management System, 2020; 19(19th International Conference on Applied Mechanics and Mechanical Engineering.): 1-14. doi: 10.1088/1757-899X/973/1/012003

Validation of a simplified model for liquid propellant rocket engine combustion chamber design

The International Conference on Applied Mechanics and Mechanical Engineering
Volume 19, 19th International Conference on Applied Mechanics and Mechanical Engineering., July 2020, Page 1-14  XML
Document Type: Original Article
DOI: 10.1088/1757-899X/973/1/012003
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Authors
M Hegazy1; H M Abdalla2; A Makled3; M A Al-Sanabawy2
1M.Sc. Student, Rocket Department, Military Technical College, Egypt.
2Associate Professor. Rocket Department, Military Technical College, Egypt.
3Associate Professor. Zagazig University, Egypt.
Abstract
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 (Leff) 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%.
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