Cooling features for a gas turbine engine transition duct
A gas engine turbine has a transition duct (100) that has improved cooling features and a method for forming the cooling features. A continuous exit section cooling channel (130) is formed through the transition duct panel (112), the exit frame (114) and the connection (116). The continuous exit section cooling channel (130) reduces the need for effusion channels in the transition duct. The continuous exit section cooling channel (130) further reduces costs and improves the emissions associated with the transition duct (100) of the gas engine turbine.
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Manish Daniel
Kumar Cassar