SYSTEM FOR COMBUSTOR COOLING AND TRIM AIR PROFILE CONTROL

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 and an aft seal is movably engaged with the combustion liner in a seal engagement region. The combustion liner may comprise an inlet formed in an outer s...

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Bibliographische Detailangaben
Hauptverfasser:	DEBRUHL, CHRISTOPHER DWAYNE, ROESLER, TIMOTHY C
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	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 and an aft seal is 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.