Effect of Propellant-Supply Pressure on Liquid Rocket Engine Performance

被引：0

作者：

Cho, Won Kook ^{[1
]}

Park, Soon Young ^{[1
]}

Nam, Chang Ho ^{[1
]}

Kim, Chul Woong ^{[1
]}

机构：

[1] Korea Aerosp Res Inst, Rocket Engine Dept, Daejeon, South Korea

来源：

TRANSACTIONS OF THE KOREAN SOCIETY OF MECHANICAL ENGINEERS B | 2010年 / 34卷 / 04期

关键词：

Liquid Rocket Engine; Combustion Pressure; Mixture Ratio; Gas Generator Cycle; Sensitivity;

D O I：

10.3795/KSME-B.2010.34.4.443

中图分类号：

TH [机械、仪表工业];

学科分类号：

0802 ;

摘要：

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.

引用

页码：443 / 448

页数：6