Cover plate for a component of a gas turbine engine

A gas turbine engine, comprising:

• a compressor section;
• a combustor section in fluid communication with said compressor section;
• a turbine section in fluid communication with said combustor section;
• wherein one of said compressor section and said turbine section includes at least one component, said at least one component including a platform and an airfoil extending from said platform, wherein said platform includes a non-gas path side and a cover plate positioned at said non-gas path side, wherein said cover plate includes a first plurality of openings that communicate a first portion of a cooling air to a first cooling cavity of said platform and a second plurality of openings that communicate a second portion of said cooling air to a second cooling cavity of said platform that is separate from said first cooling cavity, and each of said first cooling cavity and said second cooling cavity include a plurality of augmentation features, said cover plate configured as a single cover plate configured to cover both said first cooling cavity and said second cooling cavity;
• said first plurality of openings are impingement holes configured to direct said first portion of said cooling air for impingement cooling said first cooling cavity;
• and
• said second plurality of openings are core feed holes configured to direct said second portion of said cooling air for providing metered cooling within said second cooling cavity.

A component for a gas turbine engine, comprising:

• a platform having a non-gas path side and a gas path side;
• an airfoil extending from said gas path side of said platform;
• and
• a cover plate positioned adjacent to said non-gas path side of said platform, said cover plate including:
• a plurality of impingement holes configured to communicate a first portion of a cooling air for cooling said platform in an area encompassed by a first cooling cavity of said platform;
• a plurality of core feed holes configured to communicate a second portion of said cooling air for cooling said platform in an area encompassed by a second cooling cavity of said platform;
• and
• a hole aligned with an opening of an internal core of said airfoil, said hole configured to communicate a third portion of said cooling air into said internal core for cooling said airfoil.