A labyrinth seal for a gas turbine engine , comprising: a stator coupled to a non-rotating portion of the gas turbine engine and fixed in an axial direction and a radial direction, the stator including a layer of abradable material extending uniformly in the axial direction from a first stator side to an opposite second stator side ; and a rotor coupled to a rotating portion of the gas turbine engine so as to be spaced apart from the stator in the radial direction, the rotor having a first side adapted to receive a fluid flow and an opposite second side , the rotor including a first tooth at the first side having a first radial height, a second tooth between the first tooth and the second side, the second tooth having a second radial height that is greater than the first radial height, a third tooth between the first tooth and the second side having a third radial height that is the same as the first radial height, the third tooth between the second tooth and a fourth tooth , and the fourth tooth has a fourth radial height that is the same as the second radial height, a first clearance between a first tip of the first tooth and the stator in the radial direction is greater than a second clearance between a second tip of the second tooth and the stator in the radial direction, a third clearance between a third tip of the third tooth and the stator in the radial direction is substantially the same as the first clearance and a fourth clearance between a fourth tip of the fourth tooth and the stator is substantially the same as the second clearance, wherein during an operation of the gas turbine engine , the second tooth and the fourth tooth are configured to contact and abrade the layer of abradable material until a rub depth is defined in the layer of abradable material , wherein the difference of the radial heights is the expected rub depth. a stator coupled to a non-rotating portion of the gas turbine engine and fixed in an axial direction and a radial direction, the stator including a layer of abradable material extending uniformly in the axial direction from a first stator side to an opposite second stator side ; and a rotor coupled to a rotating portion of the gas turbine engine so as to be spaced apart from the stator in the radial direction, the rotor having a first side adapted to receive a fluid flow and an opposite second side , the rotor including a first tooth at the first side having a first radial height, a second tooth between the first tooth and the second side, the second tooth having a second radial height that is greater than the first radial height, a third tooth between the first tooth and the second side having a third radial height that is the same as the first radial height, the third tooth between the second tooth and a fourth tooth , and the fourth tooth has a fourth radial height that is the same as the second radial height, a first clearance between a first tip of the first tooth and the stator in the radial direction is greater than a second clearance between a second tip of the second tooth and the stator in the radial direction, a third clearance between a third tip of the third tooth and the stator in the radial direction is substantially the same as the first clearance and a fourth clearance between a fourth tip of the fourth tooth and the stator is substantially the same as the second clearance, wherein during an operation of the gas turbine engine , the second tooth and the fourth tooth are configured to contact and abrade the layer of abradable material until a rub depth is defined in the layer of abradable material , wherein the difference of the radial heights is the expected rub depth. <EOS>