Dual pilot ring for a gas turbine engine

Details Dual pilot ring for a gas turbine engine Dual pilot ring for a gas turbine engine

1995-03-29

1997-09-09

Thorpe, Timothy S.

Power plants

Combustion products used as motive fluid

Combined with regulation of power output feature

60 3936, 4151745, F02C 728

Patent

active

056644132

ABSTRACT:
A gas turbine engine having a compressor rotor and turbine rotor in back-to-back relation and annular groove therebetween. A nonrotating seal is disposed in the groove. A dual pilot ring is disposed at the radial inner end of the groove. The dual pilot ring includes an inner annular ring and an outer annular ring radially spaced apart to define a clearance gap. The inner ring is mounted to radially facing piloting surfaces on both the compressor and turbine rotors and maintains concentricity between the two rotors as they grow at different thermal rates. The outer annular ring transfers axial loads between the rotors.

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