Ignition and operation of liquid fuel powered rocket engine
AssigneeVenus Aerospace Corp.
InventorsAli Moradi, William Thomas Ross, Vishal Doshi, Eric Wernimont, Andrew Duggleby
Life of this patent
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Abstract
A rocket engine configured to run on a liquid fuel and liquid hydrogen peroxide is started by impinging high pressure streams of a fuel and liquid H2O2 into a combustion chamber under pressure and temperature conditions sufficient to decompose the liquid H2O2 into hot water stream and oxidizer and achieve ignition.
Claims19
A method of initiating startup of a rocket engine configured to run on a liquid fuel and liquid hydrogen peroxide (H2O2) comprising the steps of:
- (a) impinging high pressure streams of a low molecular weight liquid fuel and liquid H2O2 into a combustion chamber of the rocket engine under pressure and temperature conditions sufficient to decompose the liquid H2O2 into hot water steam and oxygen and achieve ignition of the low molecular weight liquid fuel;
- and
- (b) once ignition is initiated, introducing a heavier molecular weight liquid fuel directly into the combustion chamber and discontinuing flow of the low molecular weight fuel.
A method for initiating startup of a rocket engine configured to run on a liquid fuel and liquid H2O2, comprising the steps of:
- impinging a high pressure stream of liquid H2O2 and a high pressurized stream of liquid fuel on one another in a combustion chamber of the rocket engine;
- activating a torch to achieve initial ignition of the fuel/H2O2 mixture;
- deactivating the torch;
- and
- continuing feed of high pressure stream of liquid fuel and liquid H2O2 into the combustion chamber of the rocket.
A rocket system comprising a rocket engine configured to run on liquid fuel and liquid H2O2, said rocket engine comprising:
- a detonation chamber including a mixing section wherein liquid fuel and liquid H2O2 originating from an injection plate are impinged on one another;
- and a detonation section wherein the liquid fuel and liquid H2O2 achieve ignition and detonation, wherein the detonation section includes an annulus extending to a nozzle section of the rocket.
A method of initiating startup of a rocket engine configured to run on a liquid fuel and liquid hydrogen peroxide (H2O2) comprising the steps of:
- (a) impinging high pressure streams of a low molecular weight liquid fuel and decomposed H2O2 into a combustion chamber of the rocket engine under pressure and temperature conditions sufficient to achieve ignition of the liquid fuel;
- and
- (b) once ignition is initiated, introducing liquid H2O2 (in such a way as to cause atomization) into the combustion chamber and discontinuing flow of the decomposed H2O2.
Dependencies are inferred from the claim text.