Tripropellant rocket engine

Claim 2

A liquid rocket engine having a combustion chamber, an injector for injecting propellants into said combustion chamber and a source of hydrogen, oxygen and hydrocarbon for use as the propellants, a first turbo-pump for delivering oxygen to said injector, a second turbo-pump for delivering hydrocarbon to said injector and a third turbo-pump for delivering hydrogen to passages disposed in indirect heat exchange with said rocket engine for cooling the casing of said rocket engine, wherein said hydrogen becomes super heated, and conduit means for directing the super heated hydrogen into said injector whereby hydrogen, oxygen and hydrocarbon are concurrently injected into said combustion chamber and means for directing super-heated hydrogen to each of said turbo-pumps for powering said pumps to increase the pressure of said propellants.

Claim 3

A liquid rocket engine as claimed in claim 1 including a gas generator, means for leading oxygen after being pressurized and super-heated hydrogen to said gas generator for combining the said oxygen and hydrogen for producing a product of combustion and means for leading said product of combustion to each of the turbines of said turbo-pumps for powering said turbines.

Claim 4

A liquid rocket engine as claimed in claim 2 including a heat exchanger for placing pressurized hydrogen in indirect heat-exchange relationship with super-heated hydrogen bled from said passages and means for leading the then heated pressurized hydrogen into said injector for being directly injected into said combustion chamber.

Claim 5

A liquid rocket engine having a combustion chamber, an injector for injecting propellants into said combustion chamber and a source of hydrogen, oxygen and hydrocarbon for use as the propellants, a first set of two stages of turbo-pumps for delivering oxygen to said injector, a second set of two stages of turbo-pumps for delivering hydrocarbon to said injector and a third set of two stages of turbo-pumps for delivering hydrogen to passages disposed in indirect heat exchange with said rocket engine for cooling the casing of said rocket engine, wherein said hydrogen becomes super-heated, and conduit means for directing super-heated hydrogen to each of said first stages of turbo pumps for powering said pumps to increase the pressure of said propellants and then to said injector for being directly injected into said combustion chamber, a gas generator for receiving super-heated hydrogen and pressurized oxygen which is combined to form a product of combustion, means for leading said product of combustion to each of the turbines of said second stage turbo pumps, wherein said pumps of said second stage turbo-pumps further pressurize the oxygen and hydrocarbon prior to being injected into said combustion chamber.

Claim 6

A liquid rocket engine having a combustion chamber, an injector for injecting propellants into said combustion chamber and a source of hydrogen, oxygen and hydrocarbon for use as the propellants, a first set of two stages of turbo-pumps for delivering oxygen to said injector, a second set of two stages of turbo-pumps for delivering hydrocarbon to said injector and a third set of two stages of turbo-pumps for delivering hydrogen to passages disposed in indirect heat exchange with said rocket engine for cooling the casing of said rocket engine, wherein said hydrogen becomes super-heated, and conduit means for directing super-heated hydrogen to each of said first stages of turbo pumps for powering said pumps to increase the pressure of said propellants and then to said injector for being directly injected into said combustion chamber, a gas generator for receiving super-heated hydrogen and pressurized oxygen which is combined to form a product of combustion, means for leading said product of combustion to each of the turbines of said second stage turbo pumps, wherein said pumps of said second stage turbo-pumps further pressurize the oxygen and hydrocarbon prior to being injected into said combustion chamber.

Claim 7

A liquid rocket engine as claimed in claim 4 including first conduit means for defining a first circuit for said hydrogen for powering each of said first stage of said turbo pumps by leading super heated hydrogen from said passages at a mid-station of said rocket engine casing, and second conduit means for defining a second circuit for leading super heated hydrogen from said passages at a forward end station of said rocket engine casing.

Claim 8

A liquid rocket engine having a combustion chamber, an injector for injecting propellants into said combustion chamber and a source of hydrogen, oxygen and hydrocarbon for use as the propellants, a first set of two stage turbo-pumps for leading oxygen to said injector, a second set of two stage turbo-pumps for leading hydrocarbon to said injector and a third set of two stage turbo-pumps for leading hydrogen to passages disposed in indirect heat exchange with said rocket engine for cooling the casing of said rocket engine, wherein said hydrogen becomes super-heated, means for directing super heated hydrogen to each of said first stage of said turbo-pumps for powering said pumps to increase the pressure of said propellants, and the oxygen and hydrocarbon being injected directly into said combustion chamber upon being pressurized by the second stage of said first and second turbo-pumps, the hydrogen after powering each of said first stages of said turbo pumps being led directly into said injector wherein hydrogen, oxygen and hydrocarbon are concurrently injected into said combustion chamber, and a gas generator means for producing products of combustion for powering the turbines of said second stages of said turbo-pumps and means for leading super heated hydrogen and pressurized oxygen into said gas generator for combustion thereof.

Claim 9

A liquid rocket engine having a combustion chamber, an injector for injecting propellants into said combustion chamber and a source of hydrogen, oxygen and hydrocarbon for use as the propellants, a first set of two stage turbo-pumps for leading oxygen to said injector, a second set of two stage turbo-pumps for leading hydrocarbon to said injector and a third set of two stage turbo-pumps for leading hydrogen to passages disposed in indirect heat exchange with said rocket engine for cooling the casing of said rocket engine, wherein said hydrogen becomes super-heated, means for directing super heated hydrogen to each of said first stage of said turbo-pumps for powering said pumps to increase the pressure of said propellants, and the oxygen and hydrocarbon being injected directly into said combustion chamber upon being pressurized by the second stage of said first and second turbo-pumps, the hydrogen after powering each of said first stages of said turbo pumps being led directly into said injector wherein hydrogen, oxygen and hydrocarbon are concurrently injected into said combustion chamber, and a gas generator means for producing products of combustion for powering the turbines of said second stages of said turbo-pumps and means for leading super heated hydrogen and pressurized oxygen into said gas generator for combustion thereof.