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.

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.

Abstract: 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.

Abstract: A method is provided that involves a wall configured to circumscribe and be radially adjacent a rotor. During this method, a tri-axial capacitance probe is provided that includes a tri-axial conduit with an outer conductor member. The tri-axial capacitance probe is configured to output data indicative of a characteristic of the rotor. The tri-axial capacitance probe is configured within a wall aperture in the wall. The outer conductor member is electrically coupled with the wall. The wall is configured as a housing for the tri-axial capacitance probe.

Abstract: 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.

Abstract: A method is provided that involves a wall configured to circumscribe and be radially adjacent a rotor. During this method, a tri-axial capacitance probe is provided that includes a tri-axial conduit with an outer conductor member. The tri-axial capacitance probe is configured to output data indicative of a characteristic of the rotor. The tri-axial capacitance probe is configured within a wall aperture in the wall. The outer conductor member is electrically coupled with the wall. The wall is configured as a housing for the tri-axial capacitance probe.