1481617 Gas turbine burners ROLLSROYCE (1971) Ltd 2 Oot 1975 [7 Oct 1974] 43418/74 Heading F4T A gas turbine engine fuel burner 10 comprises a fuel supply 16, having at least one fuel nozzle 18 and a vapourizing and premixing duct 22 for receiving fuel and compressed air, the duct being closed at its -downstream end and having a plurality of slots 32 spaced around the periphery of the duct adjacent the downstream end of the duct. The nozzle assembly is located in a compressed air inlet duct 20 and duct 22 is held within a ring of air swirler vanes 24 located at the entrance to the combustion chamber 26. The spray angle of the nozzle lies within the range 50 to 110 degrees, the air/fuel ratio in the duct is within the range 1 to 7, and the area occupied by slots 32 is 1/3 that of the exterior surface area of cap 30 between the extremities of the slots. The burner may have a pilot fuel nozzle and a main fuel nozzle, or a dual fuel burner may be provided. The duct may terminate in one or more arms at right angles to the duct axis with slots at the end of each arm.
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