PREFERENTIAL COOLING OF GAS TURBINE NOZZLES

Turbine nozzle assemblies include a plurality of circumferentially spaced first components (46A, 48A, 50A, 58A, 60A, 68A) and second components (46B, 48B, 50B, 58B, 60B, 68B), which are designed to provide different amounts of cooling. The second components (46B, 48B, 50B, 58B, 60B, 68B), which are generally aligned with an opening of transition pieces (33), are designed to provide more cooling than the first components (46A, 48A, 50A, 58A, 60A, 68A), which are generally aligned with interfaces (52) between the transition pieces (33).