COMBUSTOR LINER COOLING AT TRANSITION DUCT INTERFACE AND RELATED METHOD

A combustor assembly for a turbine includes a combustor and a combustor liner (54); a first flow sleeve (62) surrounding the combustor liner forming a first substantially axially-extending flow annulus (64) radially therebetween. The first flow sleeve (62) has a first plurality of apertures (28) for...

Ausführliche Beschreibung

Bibliographische Detailangaben

Hauptverfasser:	Berry, Jonathan Dwight, Edwards, Kara Johnston, Ostebee, Heath Michael
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING COMBUSTION APPARATUS COMBUSTION PROCESSES ENGINE PLANTS IN GENERAL GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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