公开(公告)号：US20190120138A1

公开(公告)日：2019-04-25

申请号：US16134062

申请日：2018-09-18

Applicant: ROLLS-ROYCE plc

Inventor： John R. WELLS ,  Christopher A. MOSLEY ,  Nicholas GRECH

IPC: F02C3/04 ,  F02C9/18 ,  F01D25/24

Abstract: A turbofan engine comprises a nacelle and an engine core having a core cowling. The internal surface of the nacelle and the external surface of the core cowling define a bypass duct having an exhaust end defining a bypass duct exit plane generally normal to the longitudinal axis of the engine. The core cowling extends aft of the bypass duct exit plane and has an annular or partly-annular exit ventilation nozzle located aft of a first longitudinal position and fore of a second longitudinal position, the first and second longitudinal positions being respectively fore of and either aft of or coincident with the bypass duct exit plane, the core cowling otherwise being free of exit ventilation nozzles fore of the second longitudinal position. The engine has a lower specific fuel consumption than an equivalent engine having an exit ventilation nozzle in a conventional position aft of the second longitudinal position.

公开(公告)号：US20180334993A1

公开(公告)日：2018-11-22

申请号：US15887343

申请日：2018-02-02

Applicant: ROLLS-ROYCE plc

Inventor： John R. WELLS

IPC: F02K1/48 ,  F01D25/24 ,  B64D33/04 ,  F02K3/06

CPC classification number: F02K1/48 ,  B64D33/04 ,  F01D25/24 ,  F02K1/46 ,  F02K3/06 ,  F05D2250/61 ,  F05D2250/611 ,  F05D2260/96

Abstract: A gas turbine engine includes a core engine having a working gas annulus which ends in a core exhaust nozzle for exit of hot gas from the core engine. The engine further includes a bypass duct which ends in a bypass exhaust nozzle for exit of bypass air from the bypass duct, the bypass exhaust nozzle being forward of the core exhaust nozzle, and the bypass duct having an inner wall which forms a surrounding cowl of the core engine and ends at the bypass exhaust nozzle. The engine further includes a core cowl after-body which provides a frustoconical air-washed surface continuing unbroken, on a longitudinal section through the engine, the line of the bypass duct inner wall downstream of the bypass exhaust nozzle. The air-washed surface of the core cowl after-body has plural axially-spaced circumferentially extending corrugations which locally disturb the flow of air over the surface.

公开(公告)号：US20180119639A1

公开(公告)日：2018-05-03

申请号：US15593674

申请日：2017-05-12

Applicant: ROLLS-ROYCE plc

Inventor： John R. WELLS

IPC: F02K1/09

Abstract: A fan nacelle for an aircraft gas turbine engine. The nacelle includes an aft nacelle portion including a radially outer surface and a radially inner surface, the radially outer and inner surfaces defining an internal cavity therebetween. The nacelle further includes an aft nacelle segment translatable along a translation vector having an axial component, wherein the aft nacelle segment is configured to translate between a forward deployed position in which the nacelle defines a first primary fan nozzle exit area (A1) and a clean position in which the nacelle defines a second primary fan nozzle exit area (A2) less than the first primary fan nozzle exit area A1, wherein in the forward deployed position, the aft nacelle segment is at least partly located within the internal cavity.