Steam-injected engine heat exchanger arrangement
AssigneeRtx Corporation
InventorsAbbas A. Alahyari, Neil J. Terwilliger
Life of this patent
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Abstract
An aircraft propulsion system includes a core engine including a compressor, combustor, and turbine section. An inlet airflow is compressed communicated to the combustor, mixed with fuel, and ignited to generate an exhaust gas flow that is expanded through the turbine section. A water recovery system includes a series of condensers that include a series of passages for water containing exhaust gas flow. The series of passages are defined circumferentially about the propulsor axis such that recovered water drains downward in a direction of gravity through the series of passages.
Claims20
An aircraft propulsion system comprising:
- a core engine including a compressor, combustor, and turbine section, wherein an inlet airflow is compressed communicated to the combustor, mixed with fuel, and ignited to generate an exhaust gas flow that is expanded through the turbine section;
- a propulsor driven about a propulsor axis by the core engine;
- a water recovery system comprising a condenser configured to recover water from the exhaust gas flow, the condenser includes a passage that is disposed such that the recovered water drains downward in a direction of gravity through the passage;
- and
- an evaporator where a steam flow is generated from water separated from the exhaust gas flow and communicated to the combustor.
A water recovery system for an aircraft propulsion system comprising:
- a series of condensers comprising a series of passages for an exhaust gas flow, the series of passage are defined such that recovered water drains downward in a direction of gravity through the series of passages;
- and
- an evaporator where a steam flow is generated from water separated from the exhaust gas flow for communication to a core engine.
Dependencies are inferred from the claim text.