Patent ID: 9291070
Filing Date: 2016-03-22
CPC Classification: F01D,F05D

Claim Text:
1. A gas turbine engine comprising at least one spool assembly including at least a compressor rotor and a turbine rotor connected by a first shaft, the first shaft having a forward end connected to the compressor rotor and an aft end connected to the turbine rotor, the first shaft extending concentrically around a second shaft, the second shaft having a region of enlarged diameter located axially aft of the compressor rotor but axially forward of the forward end of the first shaft; the region of enlarged diameter having a diameter greater than an inner diameter of at least a portion of the forward end of the first shaft to cause the region of enlarged diameter of the second shaft to axially engage the first shaft in interference in the event that the second shaft is moved axially aft relative to the first shaft more than a pre-selected axial distance, wherein a bell shape support extends forwardly from the forward end of the first shaft, and wherein the first shaft is provided with a collar at the forward end thereof, the collar providing an axially arresting surface for the second shaft.