Electrical resistance wear indicator
AssigneeRaytheon Technologies Corporation
InventorsEli Cole Warren, Corey A. Benoit, Ian F. Agoos, Edward F. Dreger, III
Life of this patent
Estimating the term…
Abstract
In combination a wear indicator and a component of a gas turbine engine. The wear indicator is secured to a surface of the component of the gas turbine engine. The wear indicator including: a first component including: a post; and a ribbon wire having a first end and a second end opposite the first end. The first end is operably connected to the post and the ribbon wire is wrapped around the post.
Claims15
In combination a wear indicator and a component of a gas turbine engine, wherein the wear indicator is secured to a surface of the component of the gas turbine engine, the wear indicator comprising:
- a first component including:
- a post;
- and
- a ribbon wire having a first end and a second end opposite the first end, wherein the first end is operably connected to the post, and wherein the ribbon wire is wrapped around the post;
- and
- a second component of the wear indicator having a blind hole partially enclosing the first component, wherein the wear indicator is secured to a surface of the component of the gas turbine engine through the second component,
- wherein the second component further comprises:
- a first side that delaminates when impacted by a blade of the gas turbine engine;
- a second side parallel to the first side, the second side being secured to the component of the gas turbine engine;
- and
- a mid-section interposed between the first side and the second side;
- wherein the mid-section is conical frustum in shape.
A method of detecting blade clearance in a gas turbine engine, the method comprising:
- attaching a wear indicator to an inner surface of a gas turbine engine opposite a blade of the gas turbine engine, the wear indicator comprising a first plate, a second plate opposite to the first plate, and a plurality of wires extending from the first plate to the second plate, wherein the first plate is electrically connected to the second plate through the plurality of wires;
- measuring a first resistance of the first plate, the second plate, and the plurality of wires;
- operating the gas turbine engine at a first selected speed for a first period of time to remove material from the wear indicator;
- measuring a second resistance of the first plate, the second plate, and the plurality of wires after material is removed from the wear indicator;
- determining a change in resistance between the second resistance and the first resistance;
- and
- determining an amount of material removed from the wear indicator by the blade in response to the change in resistance.
In combination a wear indicator and a component of a gas turbine engine, wherein the wear indicator is secured to a surface of the component of the gas turbine engine, the wear indicator comprising:
- a first component including:
- a post;
- and
- a ribbon wire having a first end and a second end opposite the first end, wherein the first end is operably connected to the post, and wherein the ribbon wire is wrapped around the post;
- and
- a second component of the wear indicator having a blind hole partially enclosing the first component, wherein the wear indicator is secured to a surface of the component of the gas turbine engine through the second component,
- wherein the second component further comprises:
- a first side that delaminates when impacted by a blade of the gas turbine engine;
- a second side parallel to the first side, the second side being secured to the component of the gas turbine engine;
- and
- a mid-section interposed between the first side and the second side,
- wherein the mid-section is conical frustum in shape.
Dependencies are inferred from the claim text.