公开(公告)号：US11905887B2

公开(公告)日：2024-02-20

申请号：US17988504

申请日：2022-11-16

Applicant: ROLLS-ROYCE plc

Inventor： Gareth E Moore ,  Paul R Davies ,  Stephen M Husband ,  David R Trainer ,  David P Scothern ,  Luke George ,  Douglas M M Herbert

IPC: F02C7/262 ,  F01D15/10

CPC classification number: F02C7/262 ,  F01D15/10 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2260/85 ,  F05D2270/092 ,  F05D2270/093

Abstract: Multi-engine aircraft power and propulsion systems and methods of restarting an engine of a multi-engine aircraft during fight are provided. One such method comprises: determining a condition to the effect that a flame in the combustion equipment of the second gas turbine engine has been extinguished; responsive to the determination, supplying electrical power from the electrical energy storage system to one or more of the electric machines of the second gas turbine engine and operating said one or more electric machines as motors to limit a reduction in a speed of the one or more spools of the second gas turbine engine following extinguishment of the flame in its combustion equipment; and restarting the second gas turbine engine by relighting the combustion equipment of the second gas turbine engine.

公开(公告)号：US11236678B2

公开(公告)日：2022-02-01

申请号：US16914827

申请日：2020-06-29

Applicant: ROLLS-ROYCE plc

Inventor： Paul R Davies

IPC: F02C7/36 ,  F02C7/32 ,  B64D27/02

Abstract: An aircraft gas turbine engine includes a main engine shaft, a main engine shaft bearing arrangement for rotatably supporting the main engine shaft, and an electric machine including a rotor and a stator. The rotor is mounted to the main engine shaft and is rotatably supported by a further electric machine bearing arrangement extending between the rotor and the stator, and the stator is mounted to static structure of the gas turbine engine.

公开(公告)号：US11067035B2

公开(公告)日：2021-07-20

申请号：US16162860

申请日：2018-10-17

Applicant: ROLLS-ROYCE plc

Inventor： Edward C Gower ,  Paul R Davies

IPC: F02K1/82 ,  F02C7/18 ,  B64D33/04 ,  B64D33/08 ,  F02K1/38

Abstract: A gas turbine engine includes a main gas flow exhaust nozzle having an annular inner surface which, in use, bounds a flow of exhaust gas. The gas turbine engine further includes cooling passages having respective outlets therefrom to provide a flow of cooling air over a surface of the engine or an adjacent airframe component, thereby protecting the cooled surface from the exhaust gas flow. Adjacent cooling passages of the or each pair of the nested cooling passages are separated from each other by a respective dividing wall. The outlets from the nested cooling passages are staggered in the axial direction of the exhaust nozzle such that cooling air flowing out of an inner one of the adjacent cooling passages of the or each pair of the nested cooling passages flows over the dividing wall separating the adjacent passages.