SYSTEM FOR COMBUSTOR COOLING AND TRIM AIR PROFILE CONTROL
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United States of America
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Issued Date -
Jan 9, 2020
app pub date -
Jul 6, 2018
filing date -
Jul 6, 2018
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Abstract
Systems and methods may be provided in which a combustion liner is configured to be included in an aft end of a combustor for a gas turbine engine. An aft seal may be movably engaged with the combustion liner in a seal engagement region. The combustion liner may comprise an inlet formed in an outer surface of the combustion liner to receive a cooling fluid, and an outlet in fluid communication with the inlet via a passageway formed within the combustion liner, the outlet disposed in an inner surface of the combustion liner in the seal engagement region.
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