| A wear indicator (100) for detecting blade clearance in a gas turbine engine includes a capacitor (102) connected to a first conductor and a second conductor. The capacitor (102) includes a multiple of layers (104) arranged transverse to a rub direction, each layer (104) separated by an insulator (106) and including a first plate (108), a second plate (110), and a dielectric (112) between the first plate (108) and the second plate (110). A method of detecting blade clearance in a gas turbine engine (20), includes determining a change in capacitance between the first and second capacitance and determining an amount of material removed from the wear indicator (100) by the blade (84) corresponding to the change in capacitance. |
