Burner for a gas turbine

A burner for a gas turbine has a series of atomiser nozzles 12 located around a periphery of a swirler 4 on its downstream side, liquid fuel issuing from the nozzles being atomised by high-pressure air introduced into a conduit 10 in which the nozzles are situated. Holes 14 in the swirler wall oppos...

Ausführliche Beschreibung

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Bibliographische Detailangaben
1. Verfasser:	MAHMOUD KOWKABI
Format:	Patent
Sprache:	eng
Schlagworte:	AIR BLASTING BURNERS COMBUSTION APPARATUS COMBUSTION PROCESSES GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING LIGHTING MECHANICAL ENGINEERING METHODSOR APPARATUS FOR COMBUSTION USING FLUID FUELOR SOLID FUEL SUSPENDED IN WEAPONS
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Beschreibung
Zusammenfassung:	A burner for a gas turbine has a series of atomiser nozzles 12 located around a periphery of a swirler 4 on its downstream side, liquid fuel issuing from the nozzles being atomised by high-pressure air introduced into a conduit 10 in which the nozzles are situated. Holes 14 in the swirler wall opposite the nozzle outlets allow the atomised fuel through to the swirler air passages where the air-fuel mixture is mixed with further air. In a dual-fuel version of the invention, the conduit may be used to introduce gas fuel into the swirler instead of liquid fuel, the gas being allowed through by means of the same holes.