Electrical resistance wear indicator
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.
1. 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.
2. The combination of claim 1 , wherein the first component is configured to delaminate when impacted by a blade of the gas turbine engine.
3. The combination of claim 1 , wherein the component is a blade outer air seal.
4. The combination of claim 1 , further comprising a measurement device electrically connected to the first end of the ribbon wire through a first lead line and electrically connected to the second end of the ribbon wire through a second lead line, wherein the measurement device is configured to determine a resistance of the ribbon wire.
5. The combination of claim 1 , wherein:
the post is cylindrical in shape.
6. The combination of claim 1 , wherein:
the ribbon wire is wrapped around an outer surface of the post.
7. The combination of claim 1 , wherein:
the ribbon wire is wrapped around an inner surface of the post.
8. 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.
9. The method of claim 8 , further comprising:
determining a clearance between the blade and the inner surface in response to the amount of material removed from the wear indicator.
10. 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.
11. The combination of claim 10 , wherein the component is a blade outer air seal.
12. The combination of claim 10 , further comprising a measurement device electrically connected to the first end of the ribbon wire through a first lead line and electrically connected to the second end of the ribbon wire through a second lead line, wherein the measurement device is configured to determine a resistance of the ribbon wire.
13. The combination of claim 10 , wherein:
the post is cylindrical in shape.
14. The combination of claim 10 , wherein:
the ribbon wire is wrapped around an outer surface of the post.
15. The combination of claim 10 , wherein:
the ribbon wire is wrapped around an inner surface of the post.