GAS TURBINE ENGINE COMPONENTS AND COOLING CAVITIES

摘要

The present disclosure relates to gas turbine engine components (115; 200; 201) including cooling cavities. One embodiment is directed to a component including a forward surface (220; 301), an aft surface (240; 302), at least one inlet (210; 310; 311) on the forward surface and a cavity (205; 206) between the forward surface and the aft surface. The cavity is configured to receive airflow from at least one inlet to provide cooling flow for the component. The cavity includes a plurality of structures (250; 255; 256) within the cavity. The component also includes at least one exit (211; 212) between the forward surface and the aft surface. The plurality of structures are configured to meter air flow within the cavity and to maintain the cooling effectiveness of air flow within the cavity from the at least one inlet to the at least one exit. The component having a cavity may be employed by a combustor (105) of a gas turbine engine (100).