公开(公告)号：US11053886B2

公开(公告)日：2021-07-06

申请号：US16456870

申请日：2019-06-28

Applicant: ROLLS-ROYCE plc

Inventor： John R Whurr ,  Conor Hickey

IPC: F02K1/08 ,  F02K3/06 ,  F02K1/38 ,  F02K1/12 ,  F02K1/15

Abstract: A turbofan engine having: an engine core having a centre axis and including in flow series a compressor, a combustor and a turbine; and a bypass duct surrounding the engine core, the bypass duct has a bypass duct exit area at its downstream end. The engine further includes an exhaust nozzle assembly including: coaxially arranged inner mixer and outer exhaust nozzles, the exhaust nozzle being axially downstream of said mixer nozzle; a core flow duct defined by the mixer nozzle, the core flow duct having a core exit area; and an exhaust duct defined at least in part by the exhaust nozzle downstream of the mixer nozzle, the exhaust duct having an exhaust throat area.

公开(公告)号：US11378017B2

公开(公告)日：2022-07-05

申请号：US16448214

申请日：2019-06-21

Applicant: ROLLS-ROYCE plc

Inventor： Rory D Stieger ,  Conor Hickey

IPC: F02C9/20 ,  B64D31/06 ,  B64D33/02 ,  B64D33/04 ,  F02C9/54 ,  F02K3/06

Abstract: A turbofan engine has an engine core including in flow series a compressor, a combustor and a turbine. The engine further has a fan located upstream of the engine core, has a supersonic intake for slowing down incoming air to subsonic velocities at an inlet to the fan formed by the intake, has a bypass duct surrounding the engine core, wherein the fan generates a core airflow to the engine core and a bypass airflow through the bypass duct, and has a mixer for mixing an exhaust gas flow exiting the engine core and bypass airflow exiting bypass duct. The engine further has a thrust nozzle rearwards of the mixer for discharging mixed flows, the thrust nozzle having a variable area throat. The engine further has a controller controlling the thrust produced by the engine over a range of flight operations including on-the-ground subsonic take-off and subsequent off-the-ground subsonic climb.

公开(公告)号：US11313322B2

公开(公告)日：2022-04-26

申请号：US16446690

申请日：2019-06-20

Applicant: ROLLS-ROYCE plc

Inventor： Jonathan V. Watson ,  Conor Hickey

IPC: F02K1/46 ,  F02K1/06

Abstract: An exhaust nozzle assembly for a gas turbine engine. The assembly includes concentrically arranged inner mixer and outer exhaust nozzles, the exhaust nozzle extending axially downstream of said mixer nozzle. A centre-body is axially mounted within and extends axially downstream from the mixer nozzle. A core flow duct is defined by the mixer nozzle and the centre-body, the core flow duct having a core exit area. An exhaust duct is defined at least in part by the exhaust nozzle downstream of the mixer nozzle, the exhaust duct having an exhaust exit area. The mixer nozzle includes a mixer cowl which is axially-translatable along the centre axis and the exhaust nozzle includes an exhaust cowl which is either axially-translatable along or angularly-adjustable relative to the centre axis. The assembly further includes an actuation mechanism and the mixer cowl and exhaust cowl are movable by the actuation mechanism.