公开(公告)号：US20200025093A1

公开(公告)日：2020-01-23

申请号：US16284191

申请日：2019-02-25

Applicant: ROLLS-ROYCE plc

Inventor： Lucian INGLEY ,  Emile RAYA

IPC: F02C7/24 ,  F01D25/14

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 a core casings surrounding the engine core. The engine further includes one or more engine accessories mounted adjacent to and vertically beneath the core casings. The engine further includes a heatshield positioned between the one or more engine accessories and the core casings. The heatshield contains one or more ventilation holes for channelling convectively driven flows of ventilation air around the one or more engine accessories on engine shutdown.

公开(公告)号：US20200141274A1

公开(公告)日：2020-05-07

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 ,  F02C7/32 ,  F02K3/06

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.