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US 11,111,802 B2Granted
Seal for a gas turbine engine
AssigneeRaytheon Technologies Corporation
InventorsTracy A. Propheter-Hinckley, Egon Salimusaj
Life of this patent
Estimating the term…
Abstract
A component for a gas turbine engine includes a first platform that has a first pair of circumferential surfaces and a first axially aft surface. A first axially extending seal slot is located in each of the first pair of circumferential surfaces and the first axially aft surface. A first cover plate is attached to the first axially aft surface and encloses at least a portion of the first axially extending seal slots.
Claims19
A component for a gas turbine engine comprising:
- a first platform having a first pair of circumferential surfaces that are circumferentially opposing, a first axially aft surface, and a surface defining a core gas flow path;
- a first axially extending seal slot located in each of the first pair of circumferential surfaces and the first axially aft surface;
- and
- a first cover plate attached to the first axially aft surface enclosing at least a portion of the first axially extending seal slot located in each of the first pair of circumferential surfaces, wherein a radial direction and a circumferential direction are defined with respect to a central longitudinal axis of the gas turbine engine.
1 more element
A gas turbine engine comprising:
- a compressor section upstream of a combustor section;
- and
- a turbine section downstream of the combustor section wherein at least one of the compressor section or the turbine section includes a component having:
- a first platform having a first pair of circumferential surfaces that are circumferentially opposing and a first axially aft surface;
- a first axially extending seal slot located in each of the first pair of circumferential surfaces and the first axially aft surface;
- and
- a first cover plate attached to the first axially aft surface enclosing at least a portion of the first axially extending seal slot located in each of the first pair of circumferential surfaces;
- an airfoil having a first end adjacent the first platform and a second end adjacent a second platform, the second platform having a second pair of opposing circumferential surfaces and a second axially aft surface and a second axially extending seal slot located in each of the second pair of circumferential surfaces and the second axially aft surface, wherein a radial direction and a circumferential direction are defined with respect to a central longitudinal axis of the gas turbine engine.
5 more elements
A method of forming a seal slot in a component including the steps of:
- forming a first axially extending seal slot through each of a pair of first circumferential surfaces and through a first axially aft surface on a first platform, wherein the pair of first circumferential surfaces are circumferentially opposed, the first platform includes a surface defining a core flow path, and a circumferential direction is defined with respect to a central longitudinal axis of a gas turbine engine;
- and
- enclosing a portion of the first axially extending seal slot located in each of the pair of first circumferential surfaces with a cover plate attached to the first axially aft surface.
Dependencies are inferred from the claim text.