Axial compressor and method for controlling stage-to-stage leakage therein

A method of controlling stage-to-stage leakage in an axial compressor of a gas turbine engine, the method comprising:

• passing a flow of compressed air over a compressor blade from a low-pressure side of the compressor blade to a high-pressure side of the compressor blade;
• passing a flow of leakage air between a platform of the compressor blade and a rotor disk from the high-pressure side of the compressor blade to the low-pressure side of the compressor blade;
• and
• controlling the flow of leakage air with a gap defined between a platform sealing edge and a slot planar surface defined about a radially outer surface of the rotor disk.

An axial compressor for a gas turbine engine, the compressor comprising:

• a rotor disk positioned along an axis of the compressor, wherein the rotor disk comprises a slot defined about a radially outer surface of the rotor disk, and wherein the slot comprises a first slot planar surface and a second slot planar surface each facing away from the rotor disk;
• a compressor blade coupled to the rotor disk via the slot, wherein the compressor blade comprises a platform positioned over the radially outer surface of the rotor disk, and wherein the platform comprises a first platform sealing edge and a second platform sealing edge each facing toward the rotor disk;
• a first gap defined between the first platform sealing edge and the first slot planar surface;
• and
• a second gap defined between the second platform sealing edge and the second slot planar surface;
• wherein the first gap and the second gap each are configured to control a leakage flow of air from a high-pressure side of the compressor blade to a low pressure side of the compressor blade.