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公开(公告)号：US20200025099A1
公开(公告)日：2020-01-23
申请号：US16376129
申请日：2019-04-05
Applicant: ROLLS-ROYCE plc
Inventor： David P. SCOTHERN
Abstract: A gas turbine engine for an aircraft, comprising: an engine core; a covering configured to cover at least part of the engine core; and an engine accessory that interacts with the engine core or a component of the engine core; wherein the engine accessory is outside the covering.
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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
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.
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公开(公告)号：US20200025092A1
公开(公告)日：2020-01-23
申请号：US16255384
申请日：2019-01-23
Applicant: Rolls-Royce Deutschland Ltd & Co KG , Rolls-Royce plc
Inventor： Christoph RICHTER , Tom HILTON
IPC: F02C7/24
Abstract: A gas turbine engine for an aircraft includes: a flow path boundary, which delimits the flow path through the engine radially on the outside, and a lining, which lines the flow path boundary on the inside, at least along an axial section. Here, the lining includes a plurality of panels, which, in the circumferential direction of the flow path boundary, adjoin each other and which together line a circumferential area of 360°, wherein each panel has two end faces, which each adjoin an end face of an adjacent panel. The panels are of beveled design at their end faces, such that two mutually adjoining panels form a V-shaped gap between them, the minimum clearance of which is realized at the inside of the panels. The panels can be sound-absorbing panels. Also disclosed is a panel for a gas turbine engine.
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公开(公告)号：US20200025033A1
公开(公告)日：2020-01-23
申请号：US16291019
申请日：2019-03-04
Applicant: ROLLS-ROYCE plc
Inventor： Samuel W. WHITE , William A. MALEWICZ , Sebastian RAY , Cristina DIAZ GARCIA
Abstract: A gas turbine engine for an aircraft comprises: an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor. The gas turbine engine further comprises a core casing surrounding the engine core. The gas turbine engine further comprises a core cowl surrounding the engine core and the core casing. The gas turbine engine further comprises an engine accessory gearbox driven by a take-off from the core shaft. The gas turbine engine further comprises an oil system having one or more oil pumps powered by the engine accessory gearbox for circulating lubricating oil around components of the engine including the engine accessory gearbox, and having an oil tank for receiving and storing oil scavenged from the engine components before recirculation thereto. The gas turbine engine further comprises an oil fill line which extends from the engine accessory gearbox to an inlet port accessible from the core cowl, the oil tank being fillable from the inlet port via the fill line and the engine accessory gearbox.
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公开(公告)号：US20200024961A1
公开(公告)日：2020-01-23
申请号：US16211840
申请日：2018-12-06
Applicant: ROLLS-ROYCE plc
Inventor： Thomas MELIA
IPC: F01D5/18
Abstract: An aerofoil, comprises: a wall comprising an external surface, and an internal surface defining a cavity for receiving a cooling fluid in use; a first trench formed in the external surface, and a second trench formed in the external surface; a first passageway extending from a first passageway inlet in the cavity to a first passageway outlet in the first trench, and a second passageway extending from a second passageway inlet in the cavity to a second passageway outlet in the second trench; wherein the first passageway and second passageway intersect within the wall.
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Patent Agency Ranking
公开(公告)号：US20200023963A1
公开(公告)日：2020-01-23
申请号：US16451734
申请日：2019-06-25
Applicant: ROLLS-ROYCE plc
Inventor： Darren JAMES , Anmol A. MANOHAR , David FILLINGHAM , Marko BACIC
Abstract: An aircraft defining longitudinal, lateral and vertical directions the aircraft comprising: a main wing and a tail, each being pivotable about the lateral direction (B); a plurality of main propellers mounted to the main wing, and configured to pivot with the main wing; at least one cruise propeller mounted to the tail, and configured to pivot with the tail; each main propeller being stowable from a deployed position to a stowed position; wherein each main propeller has a fixed pitch, and each cruise propeller has a variable pitch.
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公开(公告)号：US20200023460A1
公开(公告)日：2020-01-23
申请号：US16445359
申请日：2019-06-19
Applicant: ROLLS-ROYCE plc
Inventor： John H BOSWELL , Michael J WALLIS
Abstract: A method of diffusion bonding two components together comprises providing a first component having a first bonding surface, and a second component having a second bonding surface. Each of the first bonding surface and the second bonding surface is etched. A cold working process is applied to each of the first bonding surface and the second bonding surface. Each of the first bonding surface and the second bonding surface is then etched. The first component is positioned adjacent to the second component with the first bonding surface abutting against the second bonding surface, to define a joint surface between the first component and the second component. A peripheral edge of the joint surface is sealed. The first bonding surface is diffusion bonded to the second bonding surface.
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公开(公告)号：US20200018333A1
公开(公告)日：2020-01-16
申请号：US16449507
申请日：2019-06-24
Applicant: ROLLS-ROYCE plc
Inventor： Simon P. WEBB
IPC: F15D1/12
Abstract: A low drag surface is provided for a fluid washed object, the low drag surface comprising an aerodynamic surface comprising a cut-out region, and a continuously translatable surface comprising a surface portion. The surface portion is positioned in the cut-out region such that the aerodynamic surface and the surface portion form a fluidwash surface, and the surface portion is translatable relative to the aerodynamic surface.
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公开(公告)号：US20200011250A1
公开(公告)日：2020-01-09
申请号：US16437907
申请日：2019-06-11
Applicant: ROLLS-ROYCE plc
Inventor： Alan R. MAGUIRE , Richard G. STRETTON
Abstract: Apparatus for a gas turbine engine, the apparatus comprising: a core engine casing having a longitudinal axis and including: an inner wall defining at least part of a core airflow path through the gas turbine engine; an outer wall defining an external surface of the core engine casing, a first cavity being defined between the inner wall and the outer wall of the core engine casing; a plurality of guide vanes extending radially from the outer wall of the core engine casing; a torque box defined within the first cavity of the core engine casing and at least partially overlapping axially with the plurality of guide vanes, the torque box defining a second cavity; and an accessory gear box positioned within the second cavity of the torque box.
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公开(公告)号：US20200011238A1
公开(公告)日：2020-01-09
申请号：US16411347
申请日：2019-05-14
Applicant: ROLLS-ROYCE plc
Inventor： Michael O. HALES , Craig W. BEMMENT , Stephane M. M. BARALON , Benjamin J. SELLERS , Christopher BENSON , Benedict R. PHELPS , Mark J. WILSON
Abstract: A gas turbine engine has a cycle operability parameter β in a defined range to achieve improved overall performance, taking into account fan operability and/or bird strike requirements as well as engine efficiency. The defined range of cycle operability parameter β may be particularly beneficial for gas turbine engines in which the fan is driven by a turbine through a gearbox.
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