Two-stage combustor for gas turbine engine
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United States of America Patent
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Nov 24, 2015
Grant Date -
Jun 13, 2013
app pub date -
Dec 7, 2011
filing date -
Dec 7, 2011
priority date (Note) -
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Abstract
A combustor for a gas turbine engine comprises an inner annular liner and an outer annular liner. First and second combustion stages are defined between the liners. Each combustion stage has a plurality of fuel injection bores distributed in a liner wall defining the respective stage. A lobed mixer extends into the combustor, the lobed mixer arranged to receive combustion gases from each combustion stage for mixing flows of said combustion gases.
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