Electrical resistance wear indicator
In combination a wear indicator and a component of a gas turbine engine is provided. 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 first plate; a second plate opposite the first plate; a plurality of wires extending from first plate to the second plate, wherein the first plate is electrically connected to the second plate through the plurality of wires; and a potting material configured to partially fill the first component and fill voids between the plurality of wires, such that the plurality of wires are electrically insulated from each other by the potting material.
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 first plate;
a second plate opposite the first plate;
a plurality of wires extending from first plate to the second plate, wherein the first plate is electrically connected to the second plate through the plurality of wires; and
a non-conductive potting material configured to partially fill the first component and fill voids between the plurality of wires, the plurality of wires being electrically insulated from each other by the potting material.
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 , further comprising: 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.
4. The combination of claim 1 , wherein the component is a blade outer air seal.
5. The combination of claim 1 , further comprising a measurement device electrically connected to the first plate through a first lead line and electrically connected to the second plate through second lead line, wherein the measurement device is configured to determine the resistance of at least one of the first plate, the second plate, and the plurality of wires.
6. The combination of claim 3 , 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.
7. The combination of claim 1 , wherein the first component has a cylindrical shape.
8. The combination of claim 7 , wherein the first plate and the second plate compose a substantial portion of a curved surface of the cylindrical shape, wherein the first plate and the second plate are separated by a gap in the curved surface.
9. The combination of claim 1 , wherein the first plate further includes a plurality of first orifices and the second plate further includes a plurality of second orifices, and wherein each of the plurality of wires extends from a first orifice to a second orifice.