초록 ▼

A dual expander cycle (DEC) rocket engine with an intermediate closed-cycle heat exchanger is provided. A conventional DEC rocket engine has a closed-cycle heat exchanger terhamlly coupled thereto. The heat exchanger utilizes heat extracted from the engine's fuel circuit to drive the engine's oxidi

A dual expander cycle (DEC) rocket engine with an intermediate closed-cycle heat exchanger is provided. A conventional DEC rocket engine has a closed-cycle heat exchanger terhamlly coupled thereto. The heat exchanger utilizes heat extracted from the engine's fuel circuit to drive the engine's oxidizer turbomachinery.

대표청구항 ▼

What is claimed as new and desired to be secured by Letters Patent of the United States is: 1. A rocket engine, comprising: a dual expander cycle rocket engine adapted to have a fuel and an oxidizer supplied thereto, said dual expander cycle rocket engine including a fuel turbine and an oxidizer tu

What is claimed as new and desired to be secured by Letters Patent of the United States is: 1. A rocket engine, comprising: a dual expander cycle rocket engine adapted to have a fuel and an oxidizer supplied thereto, said dual expander cycle rocket engine including a fuel turbine and an oxidizer turbine; and a heat exchanger thermally coupled to said dual expander cycle rocket engine for cooling the fuel that enters said fuel turbine and for heating the oxidizer that enters said oxidizer turbine. 2. A rocket engine as in claim 1 wherein said heat exchanger includes a turbine adapted to have an electric generator coupled thereto. 3. A rocket engine as in claim 1 wherein said heat exchanger has a fluid circulating therethrough that is inert with respect to the fuel and the oxidizer. 4. A rocket engine as in claim 1 wherein said heat exchanger has a fluid circulating therethrough that is selected from the group consisting of nitrogen, helium, xenon, argon and neon. 5. A rocket engine, comprising: a dual expander cycle rocket engine that defines a fuel path and an oxidizer path therethrough wherein said fuel path and said oxidizer path terminate at a main combustion chamber, said fuel path incorporating a fuel turbine heaving an input side and said oxidizer path incorporating an oxidizer turbine having an input side; and a closed cycle heat exchanger having a hot side and a cold side, said hot side thermally coupled to said fuel path at a location therealong forward of said input side of said fuel turbine, said cold side thermally coupled to said oxidizer path at a location therealong forward to said input side of said oxidizer turbine. 6. A rocket engine as in claim 5 wherein said heat exchanger includes a turbine adapted to have an electric generator coupled thereto. 7. A rocket engine as in claim 5 wherein said closed cycle heat exchanger has a fluid circulating therethrough that is inert with respect to the fuel and the oxidizer. 8. A rocket engine as in clime 5 wherein said closed cycle heat exchanger has a fluid circulating therethrough that is selected from the group consisting of nitrogen, helium, xenon, argon and neon. 9. A method of operating a rocket engine, comprising the steps of: providing a dual expander cycle rocket engine that defines a fuel path and an oxidizer path therethrough wherein the fuel path and oxidizer path terminate at a main combustion chamber, the fuel path incorporating a fuel turbine having an input side and the oxidizer path incorporating an oxidizer turbine having an input side; cooling the fuel that flows through the fuel path just prior to the fuel entering the fuel turbine using heat exchange with a fluid that is inert with respect to the fuel and the oxidizer; and heating the oxidizer that flows through the oxidizer path just prior to the oxidizer entering the oxidizer turbine using heat exchanger with the fluid. 10. A method according to claim 9 wherein said steps of cooling and heating comprise the step of thermally coupling a heat exchanger to the dual expander cycle rocket engine, wherein the fluid that is inert with respect to the fuel and the oxidizer circulates through the heat exchanger. 11. A method according to claim 10 wherein said step of thermally coupling comprises the steps of: thermally coupling a hot side of the heat exchanger to the fuel path at a location therealong forward of the input side of the fuel turbine; and thermally coupling a cold side of the heat exchanger to the oxidizer path at a location therealong forward of the input side of the oxidizer turbine.