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US 12,180,914 B1Granted
Boost injection turbine exhaust cycle (BITEC)
AssigneePivotal Space, Inc.
InventorsLloyd J Droppers, Landon Luick
Life of this patent
Estimating the term…
Abstract
A rocket propulsion system that may include a supersonic rocket nozzle with a supersonic divergent section, and a heat transfer system configured to transfer heat from the supersonic rocket nozzle to a propellant where a portion of the propellant may be selectively injected, combusted, and expanded in the supersonic nozzle generating an additional thrust. In examples, the heated propellant may be used to power a pump system to feed the rocket engine.
Claims20
A rocket propulsion system comprising:
- a supersonic rocket nozzle defined by a convergent section, a throat, a supersonic divergent section, and a heat transfer system configured to transfer heat from the supersonic rocket nozzle to a propellant;
- and
- a propellant pump feed system comprising:
- a prime pump configured to pressurize the propellant, the prime pump comprising a prime pressurizing side driven by a prime drive side;
- a boost pump configured to pressurize the propellant, the boost pump comprising a boost pressurizing side driven by a boost drive side;
- and
- a distribution system configured to deliver a portion of the pressurized propellant from the prime pressurizing side to the heat transfer system, from the heat transfer system to the prime drive side, from the prime drive side to the boost drive side, and from the boost drive side to the prime pressurizing side.
4 more elements
A method for operating a rocket engine, comprising:
- pressurizing a propellant with a boost pump to a boost pressure;
- increasing a pressure of the propellant from the boost pressure with a prime pump to a prime pressure;
- directing a first portion of the propellant, at the prime pressure, to a combustion chamber and passing a second portion of the propellant to a heat exchanger;
- transferring heat from the rocket engine to the second portion of the propellant via the heat exchanger, thereby generating a heated propellant;
- transferring the heated propellant to a prime drive side of the prime pump;
- extracting a first portion of energy from the heated propellant by the prime drive side of the prime pump;
- applying the first portion of energy to pressurize the propellant to the prime pressure;
- transferring the heated propellant from the prime drive side to a boost drive side of the boost pump;
- extracting a second portion of energy from the heated propellant by the boost drive side of the boost pump;
- applying the second portion of energy to pressurize the propellant to the boost pressure;
- and
- mixing the heated propellant from the boost drive side with propellant exiting the boost pump directed to the prime pump.
9 more elements
A rocket propulsion system comprising:
- a supersonic rocket nozzle defined by a convergent section, a throat, a supersonic divergent section, and a heat transfer system configured to transfer heat from the supersonic rocket nozzle to a propellant;
- and
- a bipropellant pump feed system comprising:
- a fuel prime pump configured to pressurize fuel, the fuel prime pump comprising a fuel prime pressurizing side driven by a fuel prime drive side;
- a fuel boost pump configured to pressurize the fuel, the fuel boost pump comprising a fuel boost pressurizing side driven by a fuel boost drive side;
- an oxidizer prime pump configured to pressurize oxidizer, the oxidizer prime pump comprising an oxidizer prime pressurizing side driven by an oxidizer prime drive side;
- an oxidizer boost pump configured to pressurize the oxidizer, the oxidizer boost pump comprising an oxidizer boost pressurizing side driven by an oxidizer boost drive side;
- and
- a distribution system configured to deliver a portion of the pressurized fuel from the fuel prime pressurizing side to the heat transfer system, from the heat transfer system to the fuel prime drive side, from the fuel prime drive side to the fuel boost drive side, and from the fuel boost drive side to the fuel boost pressurizing side, and configured to deliver a portion of the pressurized oxidizer from the oxidizer prime pressurizing side to the heat transfer system, from the heat transfer system to the oxidizer prime drive side, from the oxidizer prime drive side to the oxidizer boost drive side, and from the oxidizer boost drive side to the oxidizer boost pressurizing side.
6 more elements
Dependencies are inferred from the claim text.