Rocket engine using expander bleed cycle
OwnerKenta YASUDAinventor
Life of this patent
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Abstract
A rocket engine using expander bleed cycle includes an aerospike nozzle to thereby maintain optimal performance even in an environment where the atmospheric pressure varies. A rocket engine includes: a regenerative cooling nozzle; at least one turbine that rotates by fuel vapor vaporized in the regenerative cooling nozzle; a fuel transfer turbopump that is driven by the turbine; an oxidizer transfer turbopump that is driven by the turbine; and a combustion chamber in which an oxidizer and a fuel are mixed and burned. In the rocket engine, the regenerative cooling nozzle is shaped into an aerospike nozzle, and the rocket engine uses an expander bleed cycle that discharges fuel vapor vaporized in the regenerative cooling nozzle, after use, to outside of the combustion chamber.
Claims10
A rocket engine comprising:
- a regenerative cooling nozzle;
- at least one turbine that rotates by fuel vapor vaporized in the regenerative cooling nozzle;
- a fuel transfer turbopump that is driven by the at least one turbine;
- an oxidizer transfer turbopump that is driven by the at least one turbine;
- and
- a combustion chamber in which an oxidizer and fuel are mixed and burned, wherein
- the regenerative cooling nozzle is shaped into an aerospike nozzle shape, and
- the rocket engine uses an expander bleed cycle that discharges fuel vapor vaporized in the regenerative cooling nozzle, after use, to outside of the combustion chamber.
Dependencies are inferred from the claim text.