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US 10,458,291 B2Granted
Cover plate for a component of a gas turbine engine
AssigneeUnited Technologies Corporation
InventorsBrandon W. Spangler, Russell J. Bergman
Life of this patent
Estimating the term…
Abstract
A component for a gas turbine engine includes a platform having a non-gas path side and a gas path side, an airfoil extending from the gas path side of the platform, and a cover plate positioned adjacent to the non-gas path side of the platform. The cover plate can include a first plurality of openings that communicate a first portion of a cooling air to a first cooling cavity of the platform and a second plurality of openings that can communicate a second portion of the cooling air to the second cooling cavity that is separate from the first cooling cavity. Each of the first cooling cavity and the second cooling cavity can include a plurality of augmentation features.
Claims23
A component for a gas turbine engine, comprising:
- a platform having a non-gas path side and a gas path side, and said platform having a leading edge rail and a trailing edge rail extending outwardly from said non-gas path side;
- an airfoil extending from said gas path side of said platform;
- a cover plate positioned adjacent to said non-gas path side of said platform, said cover plate including 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 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, and said cover plate is a single cover plate configured to cover both of 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;
- 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;
- and
- wherein said second cooling cavity radially extends between said trailing edge rail and said gas path side of the component.
4 more elements
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;
- a cover plate positioned adjacent to said non-gas path side of said platform, said cover plate including 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 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, and said cover plate is a single cover plate configured to cover both of 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;
- 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;
- and
- wherein said core feed holes are configured to communicate said second portion of said cooling air radially through said second plurality of openings, and then axially within said second cooling cavity, and then circumferentially within said second cooling cavity.
4 more elements
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 gas path side and a cover plate positioned at said non-gas path side, said platform having a leading edge rail and a trailing edge rail extending outwardly from 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;
- 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;
- and
- wherein said second cooling cavity radially extends between said trailing edge rail and said gas path side of said at least one component.
5 more elements
A component for a gas turbine engine, comprising:
- a platform having a non-gas path side and a gas path side, and said platform having a leading edge rail and a trailing edge rail extending outwardly from said non-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, wherein said second cooling cavity radially extends between said trailing edge rail and said gas path side of the component;
- 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.
5 more elements
Dependencies are inferred from the claim text.