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http://dx.doi.org/10.3795/KSME-B.2010.34.4.443

Effect of Propellant-Supply Pressure on Liquid Rocket Engine Performance  

Cho, Won-Kook (Rocket Engine Dept., Korea Aerospace Research Institute)
Park, Soon-Young (Rocket Engine Dept., Korea Aerospace Research Institute)
Nam, Chang-Ho (Rocket Engine Dept., Korea Aerospace Research Institute)
Kim, Chul-Woong (Rocket Engine Dept., Korea Aerospace Research Institute)
Publication Information
Transactions of the Korean Society of Mechanical Engineers B / v.34, no.4, 2010 , pp. 443-448 More about this Journal
Abstract
In this paper, the changes in performance parameters, e.g., the combustor pressure, turbine power, engine mixture ratio, temperature of gas generator, and product gas, of a liquid rocket engine employing gas generator cycle with the variations in propellant-supply pressure have been described. Engine performance is numerically calculated using the 13 major system-level variables of the rocket engine. The combustor pressure and turbine power increase with an increase in the oxidizer-supply pressure and decrease with an increase in fuel-supply pressure. The lower mixture ratio of gas generator for increased fuel mass flow rate decreases the gas generator gas temperature and deteriorates the gas material properties as the turbine working fluid. The turbine power decreases with an increase in fuel-supply pressure; this results in a decrease in the main-combustor pressure, which is directly proportional to engine thrust.
Keywords
Liquid Rocket Engine; Combustion Pressure; Mixture Ratio; Gas Generator Cycle; Sensitivity;
Citations & Related Records
Times Cited By KSCI : 3  (Citation Analysis)
Times Cited By SCOPUS : 0
연도 인용수 순위
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