US Patent 10082033 Gas turbine blade with platform cooling

A component for a gas turbine engine is provided. The component having: a platform secured to the component, the platform having an exterior surface in fluid communication with an internal cooling pocket of the platform via a plurality of cooling openings located in the platform; a channel in fluid communication with the internal cooling pocket; an internal cooling cavity in fluid communication with the channel via a feed opening extending through an internal wall of the component, wherein a portion of the channel and the feed opening are located below the internal cooling pocket; and a cover plate sealing the internal cooling pocket and the channel.