Engine component with abradable material and treatment
AssigneeGeneral Electric Company
InventorsNeelesh Sarawate, Stephan Priebe, Wojciech Sak
Life of this patent
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Abstract
An engine component with an abradable material and treatment is disclosed herein. An example engine component includes a substrate having a first thickness and defining at least a first substrate surface, the substrate extending along an axial direction, an abradable material on the first substrate surface, the abradable material defining a first abradable material surface, a second abradable material surface spaced radially apart from the first abradable material surface and defining a second thickness, and a treatment, the treatment extending from the first abradable material surface through at least a portion of the first thickness of the substrate.
Claims22
An engine component, comprising:
- a substrate having a first thickness and defined by a distance from a first substrate surface to a second substrate surface, the first substrate surface positioned radially inward relative to the second substrate surface, the substrate extending along an axial direction;
- an abradable material applied to the first substrate surface and defining (a) a first abradable material surface in contact with the first substrate surface to define an interface, and (b) a second abradable material surface spaced radially inward from the first abradable material surface;
- and
- a treatment including a groove having:
- a closed end within the substrate;
- an open end within the second abradable material surface;
- and
- lateral walls extending from the open end in the second abradable material surface, through the interface, to the closed end within the substrate, wherein a distance between the lateral walls is equal from the open end to the closed end.
A gas turbine engine comprising:
- an array of rotor blades;
- and
- an engine component including:
- a substrate having at least a first substrate surface and a first thickness;
- an abradable material having:
- a first abradable surface;
- a second abradable surface;
- and
- a second thickness defined between the first abradable surface and the second abradable surface, wherein the first abradable surface is in contact with the first substrate surface to define an interface;
- and
- a treatment separate from the abradable material, the treatment including a plurality of grooves fabricated radially into the abradable material, each groove having:
- an open end at the second abradable surface;
- a closed end opposite the open end, the closed end located in the substrate;
- and
- lateral walls defined between the open end and the closed end, the lateral walls extending radially outward from the second abradable surface through at least a portion of the first thickness such that the lateral walls are continuous at the interface, wherein a distance between the lateral walls is consistent from the open end to the closed end.
An engine component comprising:
- substrate means;
- abradable means positioned on the substrate means;
- and
- treatment means, wherein the treatment means include a groove recessed into the substrate means having the abradable means positioned thereon, the groove including a closed end within the substrate means, an open end opposite the closed end, the open end positioned in the abradable means, and lateral walls defined between the open end and the closed end, wherein a distance between the lateral walls is the same from the open end to the closed end.
Dependencies are inferred from the claim text.