Einrichtung und Verfahren zur Reduzierung unterschiedlicher thermischer Ausdehnung bei Gasturbinenschaufeln

In a gas turbine having a plurality of shrouded vane segments (1) and a duct (58) directing a hot gas (19) to flow through the vanes (7) over a first surface (30) of the shroud (3), a containment structure (9) is provided for containing and distributing cooling air (13) which consists of a first lay...

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Bibliographische Detailangaben
Hauptverfasser:	MATARAZZO, JOHN CARMINE, ORLANDO, FLORIDA 32817, US, HULTGREN, KENT GORAN, WINTER PARK, FLORIDA 32789, US
Format:	Patent
Sprache:	ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 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:	In a gas turbine having a plurality of shrouded vane segments (1) and a duct (58) directing a hot gas (19) to flow through the vanes (7) over a first surface (30) of the shroud (3), a containment structure (9) is provided for containing and distributing cooling air (13) which consists of a first layer (17) and a second layer (18) joined to form a laminate structure (9) and which is attached to a second surface (24) of each of said shrouds (3) and has first passageways (59) disposed between the first and second layers (17, 18), in flow communication with a plurality of second passageways (29) formed in said shrouds (3) for directing a portion (26) of said hot gas (19) to said first passageways (59) to minimize differential thermal expansion of the structure.