Importance

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Abstract

An expander cycle rocket engine includes a primary nozzle with a heat exchanger formed therein to cool the nozzle and heat up a fluid used to drive a turbo-pump, and a secondary heat exchanger is located within the primary nozzle and includes passages to channel the fluid in order to add additional heat to the fluid used to drive the turbo-pump. The secondary heat exchanger can be a nozzle shaped heat exchanger located within the primary nozzle, and struts that secure the nozzle shaped heat exchanger within the primary nozzle and channel the fluid between nozzles. The concentric arrangement of first and second heat exchangers can transfer more heat from the combustion gases to the fluid that is used to drive the turbo-pump such that higher pressures can be obtained allowing for larger nozzles and much higher thrust than can be obtained with traditional nozzle engines, or provide significantly higher chamber pressures for engines in the prior art thrust class.

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First Claim