Patent ID: 7707836
Filing Date: 2010-05-04
Classification: F23R,Y02T

Abstract:
1. A combustor for a gas turbine comprising: a nozzle assembly located at a first end of the combustor; a combustion chamber defined within the combustor, downstream of the nozzle assembly; a venturi positioned within the combustor and defining a transition between the first end and the combustion chamber, the venturi having an internal passageway therein, the internal passageway having a first portion extending towards the first end and a second portion extending towards the combustion chamber; a compressed air source directed into a cooling inlet, the cooling inlet in fluid communication with the first and second portions of the internal passageway, the internal passageway directing the compressed air from the source in opposite directions along the first portion and second portion for cooling the venturi; and a secondary passageway communicating with a downstream end of the second portion of the internal passageway, wherein the air flow moving through the second portion of the internal passageway into the secondary passageway is reversed in direction and directed towards the first end of the combustor.