Gas turbine engine and combustor having air inlets and pilot burner
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United States of America Patent
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Jul 5, 2022
Grant Date -
Oct 10, 2019
app pub date -
May 23, 2018
filing date -
Apr 6, 2018
priority date (Note) -
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Abstract
A combustor includes a circumferential main combustion chamber and a plurality of air inlets, the plurality of air inlets dispersing air into the circumferential main combustion chamber. The combustor also includes at least one swirl-stabilized pilot burner, which disperses combustion gases into the circumferential main combustion chamber. The air inlets and the swirl-stabilized pilot burner are aligned at least partially in a radial direction and at least partially in a circumferential direction.
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