HYDROGEN FUELED TURBINE ENGINE CONDENSER DUCT

A propulsion system for an aircraft including a gas generating core engine (70) that generates an exhaust gas flow (52) that is expanded through a turbine section (32). A power turbine (38) engine is forward of the core engine (70). A propulsor (22) is coupled to the power turbine (38). A hydrogen f...

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Bibliographische Detailangaben
Hauptverfasser:	STAUBACH, Joseph B, SOBANSKI, Jon Erik
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A propulsion system for an aircraft including a gas generating core engine (70) that generates an exhaust gas flow (52) that is expanded through a turbine section (32). A power turbine (38) engine is forward of the core engine (70). A propulsor (22) is coupled to the power turbine (38). A hydrogen fuel system (96) supplies hydrogen fuel to the combustor (30) through a fuel flow path (80). A condenser (62) extracts water (54) from the exhaust gas flow (52). An evaporator (64) receives a portion of the water (54) that is extracted by the condenser (62) and generates a steam flow (56). The steam flow (56) is injected into the core flow path (C) upstream of the turbine section (32). An inlet duct (66) communicates an inlet airflow (48) to the compressor section (24) aft at a location aft of the turbine section (32). An exhaust duct (68) routes exhaust gas flow (52) through the condenser (62) and into thermal communication with a water flow (86) of water (54) extracted in the condenser (62) in the evaporator (64).