Cryogenically assisted exhaust condensation
AssigneeRaytheon Technologies Corporation
InventorsNeil J. Terwilliger, Joseph B. Staubach, Joseph E. Turney
Life of this patent
Estimating the term…
Abstract
Aircraft engines include a burner section and a turbine section arranged along a shaft, wherein an exhaust from the burner section is directed through the turbine section to drive rotation of the turbine section and a core flow path passes through the burner section and then the turbine section. A condenser assembly is arranged downstream of the turbine section along the core flow path. A cryogenic fuel source is configured to supply fuel to the burner section along a fuel line passing through the condenser assembly and the fuel within the fuel line is configured to pick up heat from the exhaust from the burner section and condense water therefrom.
Claims20
An aircraft engine, comprising:
- a burner section and a turbine section arranged along a shaft, wherein an exhaust from the burner section is directed through the turbine section to drive rotation of the turbine section and a core flow path passes through the burner section and then the turbine section;
- a condenser assembly arranged downstream of the turbine section along the core flow path;
- and
- a cryogenic fuel source configured to supply fuel to the burner section along a fuel line,
- wherein the fuel line passes through the condenser assembly and the fuel within the fuel line is configured to pick up heat from the exhaust from the burner section and condense water therefrom.
Dependencies are inferred from the claim text.