公开(公告)号：US20200224554A1

公开(公告)日：2020-07-16

申请号：US16720068

申请日：2019-12-19

Applicant: ROLLS-ROYCE plc

Inventor： Alan R. MAGUIRE ,  Stewart T. THORNTON ,  Philip C. BOND ,  Glenn A. KNIGHT

IPC: F01D25/16

Abstract: A gas turbine engine for an aircraft. The gas turbine engine comprises a rotatable shaft defining a rotational axis extending between rearward and forward ends of the gas turbine engine and a compressor drum surrounding, and coupled to, the shaft so as to define an annular gap therebetween. The gas turbine engine further comprises an intermediate case arranged axially rearward of the compressor drum and comprising a bearing support element extending into the annular gap, and a forward bearing mounted between the bearing support element and the shaft proximate a forward end of the compressor drum.