Heat induced high pressure lox pump rocket engine cycle
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机译:热诱导高压熏氧泵火箭发动机循环
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摘要
A liquid hydrogen-liquid oxygen (LH.sub.2 -LOX) rocket engine system wherein a conventional oxidizer turbo pump is replaced with a jet pump--a jet oxidizer pump. Beneficial features of the jet oxidizer pump system, over a conventional oxidizer turbo pump system, include: 1) it does not require a complicated seal system, 2) it has no moving parts, and 3) it is lighter. All these features improve the operational reliability of the rocket engine while decreasing its manufacturing cost.
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