Turbine engine with mass rejection
AssigneeRaytheon Technologies Corporation
InventorsNeil J. Terwilliger, Joseph E. Turney, Joseph B. Staubach
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Abstract
Aircraft engines include a turbine engine comprising a compressor section, a burner section, and a turbine section arranged along a shaft, with a core flow path through the turbine engine such that exhaust from the burner section passes through the turbine section, a condensing assembly arranged downstream of the turbine section of the turbine engine along the core flow path, and an exhaust compressor arranged downstream of the condensing assembly along the core flow path. The condensing assembly is configured to reduce a mass flow of the exhaust compressor by condensing water vapor from the core flow and removing liquid water from the core flow.
Claims20
An aircraft engine, comprising:
- a turbine engine comprising a compressor section, a burner section, and a turbine section arranged along a shaft, with a core flow path through the turbine engine such that exhaust from the burner section passes through the turbine section;
- a condensing assembly arranged downstream of the turbine section of the turbine engine along the core flow path;
- and
- an exhaust compressor arranged downstream of the condensing assembly along the core flow path,
- wherein the condensing assembly is configured to reduce a mass flow of the exhaust compressor by condensing water vapor from a core flow exhausted from the turbine section and removing liquid water from the core flow.
Dependencies are inferred from the claim text.