Near full hoop electrical axial shift wear indication sensor
A wear indication sensor comprising: a resistor strip configured to be operably attached to the surface of an engine component, the resistor strip including a first end and second end; a plurality of lead wires comprising: a first lead wire electrically connected to the first end proximate an aft end of the engine component; a second lead wire electrically connected to the first end proximate a forward end of the engine component; a third lead wire electrically connected to the second end proximate the aft end of the engine component; and a fourth lead wire electrically connected to the second end proximate the forward end of the engine component; and a measurement device electrically connected to each of the plurality of lead wires, wherein the measurement device is configured to measure a resistance of the resistor strip between each of the plurality of lead wires.
1. A wear indication sensor, the wear indication sensor comprising:
a resistor strip configured to be operably attached to the surface of an engine component, the resistor strip including a first end and a second end;
a plurality of lead wires comprising:
a first lead wire electrically connected to the first end of the resistor strip proximate an aft end of the resistor strip;
a second lead wire electrically connected to the first end of the resistor strip proximate a forward end of the resistor strip;
a third lead wire electrically connected to the second end of the resistor strip proximate the aft end of the resistor strip; and
a fourth lead wire electrically connected to the second end of the resistor strip proximate the forward end of the resistor strip; and
a measurement device electrically connected to each of the plurality of lead wires, wherein the measurement device is configured to measure a resistance of the resistor strip between each of the plurality of lead wires.
2. The wear indication sensor of claim 1 , wherein the engine component is a blade outer air seal.
3. The wear indication sensor of claim 2 , wherein the blade outer air seal includes a first surface and a second surface opposite the first surface, wherein the first surface is located radially outward from blades of the gas turbine engine, wherein the first surface is located opposite the blades, wherein the wear indication sensor attaches to the first surface.
4. The wear indication sensor of claim 3 , wherein the first surface is about concentric to a blade path of the blades.
5. The wear indication sensor of claim 1 , wherein the first end and the second end are electrically insulated from each other.
6. The wear indication sensor of claim 1 , wherein the resistor strip is located such that when the blade extends radially outward to a selected depth the resistor strip is cut into a first resistor strip and a second resistor strip, wherein the second resistor strip is electrically insulated from the first resistor strip.
7. The wear indication sensor of claim 1 , wherein the resistor strip is configured to abrade when impacted by a blade of the gas turbine engine.
8. An engine component of a gas turbine engine, comprising:
a surface;
a wear indication sensor comprising:
a plurality of resistor strips operably attached to the surface, each of the plurality of resistor strips including a first end and a second end, wherein the plurality of resistor strips are staggered intermittently between a forward end of the engine component and an aft end of the engine component;
a plurality of lead wires, wherein each of the plurality of resistor strips includes one of the plurality of lead wires attached to the first end and one of the plurality of lead wires attached to the second end: and
a measurement device electrically connected to each of the plurality of lead wires, wherein the measurement device is configured to measure a resistance of each of the plurality of resistor strips between the first end and the second end.
9. The engine component of claim 8 , wherein the engine component is a blade outer air seal.
10. The engine component of claim 9 , wherein the blade outer air seal includes a first surface and a second surface opposite the first surface, wherein the first surface is located radially outward from blades of the gas turbine engine, wherein the first surface is located opposite the blades, wherein the wear indication sensor attaches to the first surface.
11. The engine component of claim 10 , wherein the first surface is about concentric to a blade path of the blades.
12. The engine component of claim 8 , wherein each of the plurality of resistor strips are electrically insulated from each other.
13. The engine component of claim 8 , wherein each of the plurality of resistor strips is configured to abrade when impacted by a blade of the gas turbine engine.
14. The engine component of claim 8 , wherein each of the plurality of resistor strips includes: a first resistor strip located proximate the aft end, a second resistor strip, a third resistor strip, and a fourth resistor strip located proximate the forward end, wherein the fourth resistor strip is located forward of the third resistor strip, the third resistor strip is located forward of the second resistor strip, and the second resistor strip is located forward of the first resistor strip.
15. The engine component of claim 14 , wherein the plurality of lead wires further comprises:
a first lead wire electrically connected to the first end of the first resistor strip;
a second lead wire electrically connected to the first end of the second resistor strip;
a third lead wire electrically connected to the first end of the third resistor strip;
a fourth lead wire electrically connected to the first end of the fourth resistor strip;
a fifth lead wire electrically connected to the second end of the first resistor strip;
a sixth lead wire electrically connected to the second end of the second resistor strip;
a seventh lead wire electrically connected to the second end of third the resistor strip; and
an eighth lead wire electrically connected to the second end of fourth the resistor strip.
16. A method of detecting at least one of blade clearance and blade axial shift in a gas turbine engine, the method comprising:
measuring a first resistance of each of one or more resistor strips, the one or more resistor strips attached to an inner surface of a gas turbine engine component opposite a blade of the gas turbine engine, wherein each of the one or more resistor strips includes a first end and a second end, and wherein the one or more resistor strips are staggered intermittently between a forward end of the gas turbine engine component and an aft end of the gas turbine engine component;
operating the gas turbine engine at a first selected speed for a first period of time;
measuring a second resistance of each of the one or more resistor strips after the first period of time;
determining a change in resistance between the second resistance and the first resistance for each of the one or more resistor strips; and
determining an amount of material removed from each of the one or more resistor strips by the blade in response to the change in resistance.
17. The method of claim 16 , wherein:
the first resistance and the second resistance of each of the one or more resistor strips is measured from the first end to the second end of each of the one or more resistor strips.
18. The method of claim 16 , wherein:
the first resistance and the second resistance of each of the one or more resistor strips is measured between a location on the first end proximate an aft end and a location on the first end proximate a forward end.
19. The method of claim 16 , further comprises:
determining at least one of an axial shift of the blade and a clearance between the blade and the inner surface in response to the amount of material removed from each of the one or more resistor strips.