Patent ID: 8517687
Filing Date: 2013-08-27
Classification: F01D,F05B,F05D,Y10T

Abstract:
1. A gas turbine engine comprising: a compressor section carrying a plurality of compressor rotors; a turbine section carrying a plurality of turbine rotors; said compressor rotors and said turbine rotors being constrained to rotate with a tie shaft; an upstream hub providing an upstream abutment point for said compressor rotors, and a downstream hub abutting said compressor rotors to bias said compressor rotors against said upstream hub, said downstream hub having a rearwardly extending arm, said rearwardly extending arm providing a stop for said turbine rotors, and a downstream first abutment member at a downstream end of a downstream turbine rotor being tightened to force said turbine rotors against said downstream hub to hold said turbine rotors; and both said upstream hub and said downstream hub are provided with threaded members tightened to hold said compressor rotors together, a downstream one of said threaded members being tightened against said rearwardly extending arm.