Liquid rocket engine injectors
Liquid rocket engine injectors
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液体火箭发动机喷油器
DOI：
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发表时间：
1976
期刊：
影响因子：
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通讯作者：
W. Nurick
中科院分区：
文献类型：
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作者：
G. Gill;W. Nurick
液体火箭发动机中的喷射器将燃料与氧化剂雾化并混合，以产生有效且稳定的燃烧，从而提供所需的推力，而不会危及硬件的耐用性。喷射器通常采用火箭发动机燃烧室头部的穿孔圆盘形式，直径从几英寸到一码多不等。本专著专门论述双组元喷射器，重点放在已研制并用于飞行验证发动机的液/液和液/气喷射器上。所提供的资料对单组元推进剂喷射器和气体/气体推进剂系统的应用有限。关键问题，可能会出现在注射器的发展和成功的设计方法进行了讨论。
The injector in a liquid rocket engine atomizes and mixes the fuel with the oxidizer to produce efficient and stable combustion that will provide the required thrust without endangering hardware durability. Injectors usually take the form of a perforated disk at the head of the rocket engine combustion chamber, and have varied from a few inches to more than a yard in diameter. This monograph treats specifically bipropellant injectors, emphasis being placed on the liquid/liquid and liquid/gas injectors that have been developed for and used in flight-proven engines. The information provided has limited application to monopropellant injectors and gas/gas propellant systems. Critical problems that may arise during injector development and the approaches that lead to successful design are discussed.