Patent ID: 9470098
Filing Date: 2016-10-18
CPC Classification: F01D

Claim Text:
1. An axial compressor for a gas turbine engine, the compressor comprising: a rotor disk positioned along a length of a longitudinal axis of the compressor, wherein the rotor disk comprises a slot defined about a radially outer surface of the rotor disk and extending from an upstream end of the rotor disk to a downstream end of the rotor disk, and wherein the slot comprises a slot planar surface facing radially outward 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, wherein the platform comprises a platform sealing edge facing toward the rotor disk, wherein the platform sealing edge is parallel to the slot planar surface, and wherein the platform sealing edge and the slot planar surface are angled radially inward; and a gap defined between the platform sealing edge and the slot planar surface, wherein the gap is configured to control a flow of leakage air from a high-pressure side of the compressor blade to a low pressure side of the compressor blade.