Gas turbine engine compressor stator seal

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.

2. A gas turbine engine comprising:

a compressor, a combustor and a turbine, said turbine configured to drive a compressor rotor about an axis;

the compressor rotor including 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 drum has a portion which is generally flat, and spaced by a constant distance from said axis, and said blades being on said flat portion;

wherein there are frustoconical increasing portions positioned upstream and downstream of said flat portion with a larger portion of each frustoconical portion being spaced downstream of a smaller portions; and

said inner surface of said inner ring has a small bump axially aligned with a portion of said plurality of blades.

3. A compressor section comprising:

a plurality of compressor stages configured to rotate about an axis, 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 drum having a portion which is generally flat, and spaced by a constant distance from said axis, and said blades being on said flat portion;

there being frustoconical increasing portions positioned upstream and downstream of said flat portion with a larger portion of each frustoconical portion being spaced downstream of a smaller portion;

said rotor hubs having a generally axially enlarged radially outer portion, and an axially thinner neck portion extending radially inwardly, and said drum being connected to said rotor hubs at said generally enlarged portion; and

said inner surface of said inner ring has a small bump axially aligned with with a portion of said plurality of blades.