Gas turbine rotor containment

摘要

A gas turbine engine (A) has a spool assembly including a compressor rotor (18) and a turbine rotor (20) connected by a first shaft (24). The first shaft (24) has a forward end connected to the compressor rotor (18) and an aft end connected to the turbine rotor (20). The first shaft (24) extends concentrically around a second shaft (22). The first shaft (24) forward end has a portion (35) with an inner diameter (35a) of close tolerance with the second shaft (22). The second shaft (22) has a region of enlarged diameter (36) located axially aft of the compressor rotor (18) but axially forward of the forward end of the first shaft (24). The region of enlarged diameter (36) has a diameter greater than the inner diameter (35a) of the portion (35) of close tolerance of the forward end of the first shaft (24) to cause the region of enlarged diameter (36) of the second shaft (22) to engage the first shaft (24) in interference in the event that the second shaft (22) is moved axially aft relative to the first shaft (24) more than a pre-selected axial distance.