CONDENSER FOR HYDROGEN STEAM INJECTED TURBINE ENGINE

A propulsion system (20) for an aircraft includes a hydrogen fuel system (52) suppling hydrogen fuel to a combustor (30) through a fuel flow path . A condenser (80) extracts water (116) from a high energy gas flow (55). The condenser (80) includes a plurality of rotating passages (100) that are disp...

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Bibliographische Detailangaben
1. Verfasser:	ALAHYARI, Abbas A
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 ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PERFORMING OPERATIONS PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL SEPARATION STEAM ENGINES TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	A propulsion system (20) for an aircraft includes a hydrogen fuel system (52) suppling hydrogen fuel to a combustor (30) through a fuel flow path . A condenser (80) extracts water (116) from a high energy gas flow (55). The condenser (80) includes a plurality of rotating passages (100) that are disposed within a collector (112) and are configured to rotate about a condenser axis (110) to generate a transverse pressure gradient to direct water (116) out of the high energy gas flow (55) toward the collector (112).