Labyrinth seal with variable tooth heights

A labyrinth seal for a gas turbine engine, comprising:

• a stator configured to be 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 configured to be 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 proximate the first side having a first radial height, the first tooth having a first tooth side opposite a second tooth side, the first tooth side facing the fluid flow and spaced apart from the first end, the first tooth side extending at a first angle of less than 90 degrees from a surface of the rotor and the second tooth side extending at a second angle from the surface of the rotor, the first angle and the second angle are included angles and substantially the same, a second tooth between the first tooth and the second side, the second tooth having a second radial height that is less than the first radial height and a third tooth between the first tooth and the second side having a third radial height that is substantially the same as the first radial height, the third tooth is between a fourth tooth and the second side, the fourth tooth having a fourth radial height that is substantially the same as the second radial height, with a first clearance between a first tip of the first tooth and the stator in the radial direction different 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.

A labyrinth seal for a gas turbine engine, comprising:

• a stator configured to be 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 configured to be 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 proximate the first side having a first radial height, a second tooth between the first tooth and the second side, the first tooth having a first tooth side opposite a second tooth side, the first tooth side facing the fluid flow and spaced apart from the first end, the first tooth side extending at an included angle of less than 90 degrees from a surface of the rotor, the second tooth having a second radial height that is less than the first radial height and a third tooth between the first tooth and the second side having a third radial height that is substantially the same as the first radial height, third tooth is between the second tooth and a fourth tooth, the fourth tooth having a fourth radial height that is substantially the same as the second radial height with a first clearance between a first tip of the first tooth and the stator in the radial direction different 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.