Dual fuel nozzle with liquid filming atomization for a gas turbine engine
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United States of America Patent
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Oct 6, 2020
Grant Date -
Jul 21, 2016
app pub date -
Aug 19, 2014
filing date -
Aug 30, 2013
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Abstract
A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, said outer air swirler defines an outer annular air passage between an outer wall and an inner wall, the outer wall defines a convergent-divergent nozzle. An inner air swirler along the axis to define an annular liquid passage therebetween, the annular liquid passage terminates upstream of the convergent-divergent nozzle and an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler.
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