Temperature mixing enhancement with locally co-swirling quench jet pattern for gas turbine engine combustor
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United States of America Patent
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Apr 26, 2016
Grant Date -
Jan 31, 2013
app pub date -
Jul 29, 2011
filing date -
Jul 29, 2011
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Abstract
A combustor for a turbine engine includes a first liner defined about an axis with a first row of first combustion air holes, one of the first combustion air holes is defined along each of a multiple of fuel injector zero pitch lines. A second liner defined about the axis with a second row of second combustion air holes, each of the second combustion air holes circumferentially offset relative to each of the multiple of fuel injector zero pitch lines.
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