Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory(NAL)
雑誌名
航空宇宙技術研究所報告
雑誌名(英)
Technical Report of National Aerospace Laboratory TR-642
巻
642
ページ
23
発行年
1980-12
抄録（英）
A liquid propellant rocket engine is usually supplied with a propellant at high pressure by the use of high speed pumps. These pumps are generally driven by a hot-gas turbine, and the hot gas is usually obtained from bipropellant gas generators. The gas generator has its own problems, like hot streaking and combustion instability at an exceedingly low mixture ratio, which are different from those of the thrust chamber of a liquid rocket engine. In the present study, several kinds of Lox/Kerosene gas generators have been investigated to clearly define their performance. The major results of the present study were summarized as follows: (1)Characteristic exhaust velocity C is little influenced by any temperature distribution of hot gas at the exit of gas generators. This shows that C of gas generators is not so significant as that of thrust chambers. (2)Improvement in the temperature efficiency of gas generators must be considered in relation to their size and weight. (3)Bends better contribute to temperature uniformity at the exit of gas generators than turbulence rings or a splash ring. (4)The ratio of the pressure difference in propellant injection to the combustion chamber pressure is also an important factor in the low-frequency combustion instability of gas generators.
An Experimental Investigation of Lox/Kerosene Gas Generators for Liquid Propellant Rockets
naltr00642.pdf
(3.61MB)
