Patent ID: 9169849
Filing Date: 2015-10-27
Classification: F01D,F04D,Y02T

Abstract:
1. A compressor section for use in a gas turbine engine comprising: a plurality of compressor stages, each of said compressor stages provided with a rotor hub, and each said rotor hub mounting a plurality of compressor blades; a rotor drum extending between said adjacent rotor hubs; a plurality of stator vanes having a radially outer ring and a radially inner ring, with a plurality of vanes extending between said outer and inner rings, and an inner surface of said inner ring being spaced by a gap from an outer surface of said rotor drum; said rotor drum being provided with a plurality of blades having a general airfoil shape to resist leakage across said gap; said inner surface of said inner ring has a small bump axially aligned with a portion of said plurality of blades; said drum has a portion which is generally flat, and spaced by a constant distance from what will be a center of rotation of said rotor hubs, and said blades being on said flat portion; and wherein there are frustoconical portions positioned upstream and downstream of said flat portion with a larger portion of each frustoconical portion being spaced downstream of a smaller portion.