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.