GAS TURBINE COMBUSTION SYSTEM COOLING ARRANGEMENT

PROBLEM TO BE SOLVED: To provide cooling for a gas turbine combustion system. SOLUTION: The gas turbine combustion system includes a first member, such as a liner, having exterior and interior surfaces that define a wall therebetween and a central area. A second member, such as a cap, is located adj...

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Bibliographische Detailangaben
Hauptverfasser:	BYRNE WILLIAM, CHILLAR DAVID, BERKMAN MERT
Format:	Patent
Sprache:	eng
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:	PROBLEM TO BE SOLVED: To provide cooling for a gas turbine combustion system. SOLUTION: The gas turbine combustion system includes a first member, such as a liner, having exterior and interior surfaces that define a wall therebetween and a central area. A second member, such as a cap, is located adjacent that interior surface. A source of cooling gas is in fluid communication with the exterior surface of the first member. An open space, in which a hula seal is located, is located between the interior surface of the first member and the second member. At least one opening in the wall of the first member provides a passageway for the cooling gas from the exterior surface of the first member to the open space. The passageway has a directional axis along which the cooling gas flows and is discharged into the open space. The directional axis is substantially oriented in a direction other than a direction towards the central area of the first member. COPYRIGHT: (C)2010,JPO&INPIT