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app pub date -
Dec 28, 2016
filing date -
Dec 29, 2015
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Abstract
An injection assembly for a combustor of a gas turbine has an outer body provided with inlet passages for comburent air, a conical tubular portion housed inside the outer body and delimiting partly an inner duct and an outer annular duct; a first and a second supply means for supplying a liquid fuel into the inner duct and, respectively, into the outer annular duct; at least one circumferential annular seat formed being carried by one of the tubular portion and the outer body, so as to collect a mass of liquid fuel advancing in the outer annular duct and make uniform the flow of liquid flowing out of the circumferential annular seat.
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