Patent ID: 8402764
Filing Date: 2013-03-26
Classification: F01D,Y02T

Abstract:
1. A transition duct for a gas turbine engine to channel a hot gas flow from a combustor into a turbine, the transition duct comprising: a cone section and an intermediate exit piece, the cone section forming an inlet end for the transition duct and the intermediate exit piece forming an outlet end for the transition duct; the cone section having an outer section and an inner section that form a cooling air passage from an inlet to an outlet of the cone section; the inner section having an outer surface with a plurality of inner ribs that form cooling air channels, the inner ribs being at an angle to a longitudinal direction of the transition duct; and, the outer section having an inner surface with a plurality of outer ribs that form cooling air channels, the outer ribs being at an angle to a longitudinal direction of the transition duct such that the cooling air channels that form by the plurality of inner ribs counter flow to the cooling air channels that form by the plurality of outer ribs for the cooling air.