초록 ▼

A bi-propellant self-contained propulsion system is provided for powering rockets. A plurality of turbopump assemblies are provided to take liquid propellants from low pressure storage tanks to a substantially higher pressure thrust chamber. Substantially all of the liquid propellants are pressurize

A bi-propellant self-contained propulsion system is provided for powering rockets. A plurality of turbopump assemblies are provided to take liquid propellants from low pressure storage tanks to a substantially higher pressure thrust chamber. Substantially all of the liquid propellants are pressurized and gasified within the plurality of turbopumps. Substantially all of the gasified propellants are then used to drive the turbopumps that pressurize the liquid propellants. Gasification preferably occurs within a preburner internal to the turbopump assembly that combines a small portion of one of the propellants with a substantial portion of the other. The proportions are selected so that gasification of all of the propellants is ensured yet relatively low preburner temperatures are maintained. A multi-stage pintle assembly may be provided to vary the exit-to-throat area ratio of the nozzle. The total thrust and the mixture ratio may be controlled by shutting down some of the turbopumps. Actuation of the pintle is preferably coordinated with the shutting down of turbopumps to maintain a relatively constant thrust chamber pressure. A nozzle skirt insert is provided to enhance the low altitude performance of the rocket engine and the high altitude performance of the rocket engine.

대표청구항 ▼

In a liquid rocket propulsion system that includes at least two liquid propellants in the form of an oxidant stored in an oxidant tank and a fuel stored in a fuel tank apart from said oxidant, combustion means for mixing and burning said propellants to produce combustion products, said combustion me

In a liquid rocket propulsion system that includes at least two liquid propellants in the form of an oxidant stored in an oxidant tank and a fuel stored in a fuel tank apart from said oxidant, combustion means for mixing and burning said propellants to produce combustion products, said combustion means including a thrust chamber wherein at least a portion of the burning occurs, and a nozzle assembly for expelling the combustion products from the propulsion system to produce thrust, the improvement comprising delivery means for supplying the propellants to the combustion means and for enhanced expulsion from the combustion means, the delivery means comprising: a plurality of turbopumps for pumping the liquid propellants to operational pressures, each said turbopump including, a pump impeller for pumping one of the propellants to an operational pressure, a preburner for combusting a portion of the fuel with a portion of the oxidant to produce a gasified fluid flowstream, and a turbine wheel for extracting energy from the gasified flowstream to drive the pump impeller; means for carrying the fluid flowstreams from said turbopumps to said combustion means; and wherein said plurality of turbopumps gasify substantially all of the propellants prior to delivery of the propellants to the combustion means, and the plurality of turbopumps include at least one oxidant turbopump, each said oxidant turbopump combining and combusting a small portion of the fuel with a substantial portion of the oxidant within its preburner to produce a gasified oxidizer-rich flowstream, and at least one fuel turbopump, each said fuel turbopump assembly combining and combusting a small portion of the oxidizer with a substantial portion of the fuel within its preburner to produce a gasified fuel-rich flowstream.