SUPERCRITICAL OR MIXED PHASE MULTI-PORT FUEL INJECTOR

The invention relates to an apparatus, comprising: a fuel supply (102) for a turbine engine; a means (202) for maintaining a specified pressure in the fuel supply (102), the means (202) disposed within a body (302), the specified pressure at or greater than a critical pressure of a fuel of the fuel...

Ausführliche Beschreibung

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Bibliographische Detailangaben
1. Verfasser:	ROESLER, TIMOTHY, C
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 LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	The invention relates to an apparatus, comprising: a fuel supply (102) for a turbine engine; a means (202) for maintaining a specified pressure in the fuel supply (102), the means (202) disposed within a body (302), the specified pressure at or greater than a critical pressure of a fuel of the fuel supply; and a plurality of fueling passages (204) fluidly coupling the means (202) for maintaining the specified pressure to a plurality of nozzle exits (214), wherein each of the fueling passages (204) has a corresponding inlet (309) and a corresponding one of the nozzle exits (214), the inlets (309) of the fueling passages (204) are positioned on a surface of a plate (306) within the body (302), the surface exposed to the means (202) for maintaining the specified pressure, each of the inlets (309) is positioned on the surface to receive a portion of fuel received from the means (202) for maintaining the specified pressure.