DILUTION HORN PAIR FOR A GAS TURBINE ENGINE COMBUSTOR
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United States of America Patent
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Issued Date -
Oct 13, 2022
app pub date -
Apr 12, 2021
filing date -
Apr 12, 2021
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Abstract
A combustor for a gas turbine engine has an annular inner liner and an annular outer liner forming a combustion chamber therebetween. A dilution horn pair includes dilution horns that provide a flow of an oxidizer gas into the combustion chamber in a dilution zone. At least one of the dilution horns forming the dilution horn pair is arranged so as to provide a lateral flow component of the flow of oxidizer gas therethrough into the combustion chamber, the lateral flow component having a flow direction extending laterally across and non-orthogonal to an axial flow direction of combustion gases within the combustion chamber.
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