公开(公告)号：US10851669B2

公开(公告)日：2020-12-01

申请号：US16598369

申请日：2019-10-10

Applicant: ROLLS-ROYCE plc

Inventor： Emile Raya ,  Lucian Ingley ,  Zahid M. Hussain

IPC: F01D25/14 ,  F02C7/12 ,  F02K3/06 ,  F02C7/32

Abstract: A gas turbine engine for an aircraft is provided. The engine includes an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor. The engine further includes core casings surrounding the engine core. The engine further includes an aerodynamic cowl which surrounds the core casings. The engine further includes a propulsive fan located upstream of the engine core, the fan generating a core airflow which enters the core engine and a bypass airflow which enters a bypass duct surrounding the aerodynamic cowl. The engine further includes one or more engine accessories mounted in a space between the core casings and the aerodynamic cowl.

公开(公告)号：US10858956B2

公开(公告)日：2020-12-08

申请号：US16378847

申请日：2019-04-09

Applicant: ROLLS-ROYCE plc

Inventor： Richard Peace ,  Lucian Ingley

IPC: F01D25/24 ,  F02K3/06 ,  B64D29/08

Abstract: A gas turbine engine for an aircraft is provided. The gas turbine engine comprises an engine core comprising a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor. The gas turbine engine further comprises a fan located upstream of the engine core, the fan comprising a plurality of fan blades, the fan generating a core airflow which enters the engine core and a bypass airflow which flows through a bypass duct surrounding the engine core. The gas turbine engine further comprises a circumferential row of outer guide vanes located in the bypass duct rearwards of the fan, the outer guide vanes extending radially outwardly from an inner ring which defines a radially inner surface of the bypass duct.