MULTI-SIDED DIFFUSER FOR A VENTURI IN A FUEL INJECTOR FOR A GAS TURBINE

A combustor for a gas turbine includes a main fuel injector for receiving compressor discharge air and mixing the air with fuel for flow to a downstream catalytic section. The main fuel injector includes an array of venturis each having an inlet, a throat and a diffuser. A main fuel supply plenum be...

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Bibliographische Detailangaben
Hauptverfasser:	DINU CONSTANTIN A, STOREY JAMES M, HU IRIS Z
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING COMBUSTION APPARATUS COMBUSTION PROCESSES GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A combustor for a gas turbine includes a main fuel injector for receiving compressor discharge air and mixing the air with fuel for flow to a downstream catalytic section. The main fuel injector includes an array of venturis each having an inlet, a throat and a diffuser. A main fuel supply plenum between forward and aft plates supplies fuel to secondary annular plenums having openings for supplying fuel into the inlets of the venturis upstream of the throats. Each diffuser transitions from a circular cross-section at the throat to multiple discrete angularly related side walls at the diffuser exit. Gaps between circumferentially and radially spaced diffusers at their exits are eliminated. With this arrangement, uniform flow distribution of the fuel/air, velocity and temperature is provided at the catalyst inlet.