COMBUSTOR TRANSITION PIECE REAR END COOLING AND ASSOCIATED METHOD

PROBLEM TO BE SOLVED: To provide a means for directly cooling a transition duct having no rear frame structure. SOLUTION: A transition duct 10 for a gas turbine includes a tubular body having the front end and the rear end 12, a plurality of cooling channels 16 formed on an outer surface of the tubu...

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Bibliographische Detailangaben
Hauptverfasser:	MCMAHAN KEVIN W, CHILA RONALD J
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 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 MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	PROBLEM TO BE SOLVED: To provide a means for directly cooling a transition duct having no rear frame structure. SOLUTION: A transition duct 10 for a gas turbine includes a tubular body having the front end and the rear end 12, a plurality of cooling channels 16 formed on an outer surface of the tubular body in the rear end 12, a closing band 32 surrounding the rear end 12 and covering at least a part of the plurality of cooling channels 16, and a seal 37 installed on the closing band 32 and surrounding the rear end of the tubular body. COPYRIGHT: (C)2010,JPO&INPIT