Liquid hydrogen-liquid oxygen fueled powerplant

Patent metadata

Field	Value
Publication number	US-11905914-B2
Application number	US-202217670107-A
Country	US
Kind code	B2
Filing date	Feb 11, 2022
Priority date	Feb 11, 2022
Publication date	Feb 20, 2024
Grant date	Feb 20, 2024

Abstract

A powerplant is provided that includes a pre-burner, a combustor, a power turbine, a mechanical load and a propellant system. The combustor is fluidly coupled with and downstream of the pre-burner. The power turbine is fluidly coupled with and downstream of the combustor. The mechanical load is rotatably driven by the power turbine. The propellant system is configured to direct fluid oxygen and fluid hydrogen to the pre-burner to provide an oxygen rich fuel mixture for combustion within the pre-burner. The propellant system is also configured to direct the fluid hydrogen to the combustor for combustion within the combustor with oxygen within combustion products received from the pre-burner.

First claim

What is claimed is:

1. A powerplant, comprising:
a pre-burner;
a combustor fluidly coupled with and downstream of the pre-burner;
a second pre-burner fluidly coupled with and upstream of the combustor;
a power turbine fluidly coupled with and downstream of the combustor;
a mechanical load rotatably driven by the power turbine; and
a propellant system configured to direct fluid oxygen and fluid hydrogen to the pre-burner to provide an oxygen rich fuel mixture for combustion within the pre-burner, and the propellant system further configured to direct the fluid hydrogen to the combustor for combustion within the combustor with oxygen within combustion products received from the pre-burner; and
the propellant system further configured to direct the fluid oxygen and the fluid hydrogen to the second pre-burner to provide a second oxygen rich fuel mixture for combustion within the second pre-burner, and the propellant system further configured to direct the fluid hydrogen to the combustor for combustion within the combustor with oxygen within second combustion products received from the second pre-burner.

2. The powerplant of claim 1 , wherein
the fluid oxygen directed to the pre-burner comprises liquid oxygen; and
the fluid hydrogen directed to the pre-burner comprises liquid hydrogen.

3. The powerplant of claim 1 , wherein the fluid hydrogen directed to the combustor comprises liquid hydrogen.

4. The powerplant of claim 1 , wherein the fluid hydrogen directed to the combustor comprises hydrogen gas.

5. The powerplant of claim 1 , wherein the propellant system comprises:
an oxygen reservoir; and
an oxygen turbopump including a turbopump turbine and a turbopump pump, the turbopump turbine fluidly coupled with and between the pre-burner and the combustor, the turbopump pump rotatably driven by the turbopump turbine, and the turbopump pump configured to direct the fluid oxygen from the oxygen reservoir to the pre-burner.

6. The powerplant of claim 5 , further comprising an overpressure vent configured to fluidly couple the oxygen reservoir to an environment outside of the powerplant.

7. The powerplant of claim 1 , wherein the propellant system comprises:
a hydrogen reservoir; and
a hydrogen turbopump including a turbopump turbine and a turbopump pump, the turbopump turbine fluidly coupled with and between the pre-burner and the combustor, the turbopump pump rotatably driven by the turbopump turbine, and the turbopump pump configured to direct the fluid hydrogen from the hydrogen reservoir to the pre-burner and to the combustor.

8. The powerplant of claim 1 , wherein the propellant system is configured to direct the fluid oxygen to the power turbine for cooling the power turbine.

9. The powerplant of claim 8 , wherein
an upstream section of the power turbine is cooled using the fluid oxygen; and
a downstream section of the power turbine is uncooled.

10. The powerplant of claim 1 , wherein
the propellant system further comprises a recuperator, and the propellant system is configured to direct the fluid hydrogen to the combustor through the recuperator; and
the recuperator is configured to transfer heat energy from combustion products output from the power turbine to the fluid hydrogen.

11. The powerplant of claim 1 , further comprising a variable area exhaust nozzle fluidly coupled with and downstream of the power turbine.

12. The powerplant of claim 1 , wherein the mechanical load comprises at least one of a propulsor rotor or an electric generator.

13. The powerplant of claim 1 , further comprising:
an electrical generator comprising a fuel cell;
the propellant system further configured to provide the fluid oxygen and the fluid hydrogen to the fuel cell.

14. A powerplant, comprising:
a pre-burner;
a combustor fluidly coupled with and downstream of the pre-burner;
a power turbine fluidly coupled with and downstream of the combustor;
a mechanical load rotatably driven by the power turbine; and
a propellant system configured to direct fluid oxygen and fluid hydrogen to the pre-burner to provide an oxygen rich fuel mixture for combustion within the pre-burner, and the propellant system further configured to direct the fluid hydrogen to the combustor for combustion within the combustor with oxygen within combustion products received from the pre-burner, wherein the propellant system comprises
an oxygen reservoir;
an oxygen turbopump including a turbopump turbine and a turbopump pump, the turbopump turbine fluidly coupled with and between the pre-burner and the combustor, the turbopump pump rotatably driven by the turbopump turbine, and the turbopump pump configured to direct the fluid oxygen from the oxygen reservoir to the pre-burner; and
a heater configured for heating the fluid oxygen within the oxygen reservoir.

15. A powerplant, comprising:
a pre-burner;
a combustor fluidly coupled with and downstream of the pre-burner;
a power turbine fluidly coupled with and downstream of the combustor;
a mechanical load rotatably driven by the power turbine; and
a propellant system configured to direct fluid oxygen and fluid hydrogen to the pre-burner to provide an oxygen rich fuel mixture for combustion within the pre-burner, and the propellant system further configured to direct the fluid hydrogen to the combustor for combustion within the combustor with oxygen within combustion products received from the pre-burner, wherein the propellant system comprises
a hydrogen reservoir;
a hydrogen turbopump including a turbopump turbine and a turbopump pump, the turbopump turbine fluidly coupled with and between the pre-burner and the combustor, the turbopump pump rotatably driven by the turbopump turbine, and the turbopump pump configured to direct the fluid hydrogen from the hydrogen reservoir to the pre-burner and to the combustor; and
a heater configured for heating the fluid hydrogen within the hydrogen reservoir.

16. A powerplant, comprising:
a pre-burner;
a combustor fluidly coupled with and downstream of the pre-burner;
a power turbine fluidly coupled with and downstream of the combustor;
a mechanical load rotatably driven by the power turbine;
a propellant system configured to direct fluid oxygen and fluid hydrogen to the pre-burner to provide an oxygen rich fuel mixture for combustion within the pre-burner, and the propellant system further configured to direct the fluid hydrogen to the combustor for combustion within the combustor with oxygen within combustion products received from the pre-burner, wherein the propellant system comprises
a hydrogen reservoir; and
a hydrogen turbopump including a turbopump turbine and a turbopump pump, the turbopump turbine fluidly coupled with and between the pre-burner and the combustor, the turbopump pump rotatably driven by the turbopump turbine, and the turbopump pump configured to direct the fluid hydrogen from the hydrogen reservoir to the pre-burner and to the combustor;

an exhaust fluidly coupled with and downstream of the power turbine; and
an overpressure vent configured to fluidly couple the hydrogen reservoir to the exhaust.

Assignees

• Raytheon Tech Corp
• Rtx Corp

Inventors

• Ledwith Jr Walter A

Classifications

• F02K9/42 Primary

  using liquid or gaseous propellants (F02K9/72 takes precedence) · CPC title

• B64G1/401

  Liquid propellant rocket engines (Ion or plasma engines B64G1/413; Arcjets and other resistojets B64G1/415) · CPC title

• B64G1/402

  Propellant tanks; Feeding propellants · CPC title

• F02K9/48

  driven by a gas turbine fed by propellant combustion gases {or fed by vaporized propellants or other gases} · CPC title

• F02K9/62

  Combustion or thrust chambers · CPC title