Wear indication sensor designs and methods of integration

A method of detecting blade clearance in a gas turbine engine, the method comprising:

• attaching a wear indication sensor to a first surface of a component of gas turbine engine opposite a blade of the gas turbine engine, wherein the wear indication sensor has two or more resistors from a first terminal to a second terminal located therein,
• wherein the component includes a second surface radially outward from a blade of the gas turbine engine and about concentric to a blade path of the blade, and wherein the first surface is at a non-perpendicular angle with respect to the second surface;
• determining a first resistance between the first terminal and the second terminal;
• operating the gas turbine engine at a first selected speed for a first period of time to remove one or more primary conductive lines from the wear indication sensor, wherein the one of the one or more primary conductive line connects each of the two or more resistors to the first terminal, wherein each of the one or more primary conductive lines is located at a known distance away from the blade;
• measuring a second resistance from the first terminal to the second terminal;
• determining a change in resistance between the second resistance and the first resistance;
• and
• determining an amount of material removed from the wear indication sensor by the blade in response to the change in resistance and the known depth of each of the one or more primary conductive lines.