COOLED COMBUSTOR FOR A GAS TURBINE ENGINE
Abstract:
A combustor for a gas turbine engine comprises a combustion liner to define a combustion chamber for burning fuel to drive to turbine. The combustion liner comprises a plurality of nugget holes for providing cooling fluid to create a cooling film over the surface of the combustion liner adjacent the combustion chamber. The nugget holes can be circumferentially angled relative to the engine centerline to provide the flow of cooling fluid in an angled manner to align with a local streamline for the flow of fluid from the combustor.
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