公开(公告)号：US20190003335A1

公开(公告)日：2019-01-03

申请号：US16014071

申请日：2018-06-21

Applicant: ROLLS-ROYCE plc

Inventor： Peter A. EVANS ,  Adam CARPENTER

IPC: F01D25/12 ,  F02C7/18 ,  F02C3/10 ,  F02C7/06 ,  F01D5/08 ,  F01D11/02

Abstract: A cooling arrangement for cooling a bearing in a gas turbine engine, the gas turbine engine comprising a compressor section, a combustor section and a turbine section, the turbine section comprising a low pressure (LP) sub-section and a high pressure (HP) sub-section, a first shaft for carrying rotors of the compressor section and of the HP turbine sub-section and a second shaft for carrying rotors of the LP turbine sub-section the second shaft coaxially aligned with and located within the first shaft, and the bearing arranged downstream of the HP turbine sub-section and upstream of the LP turbine sub-section and arranged for rotatably mounting the second shaft with respect to a support structure. The cooling arrangement comprising a first bleed taken off from the compressor, one or more inlet holes in the second shaft located upstream of the combustor and one or more outlet holes in the second shaft located downstream of the HP turbine sub-section and upstream of the bearing, and an air guide for guiding flow from the first bleed to the one or more inlet holes whereby to separate the flow from the first bleed from a coolant flow directed to cool discs of the turbine section.