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公开(公告)号：US11358307B2
公开(公告)日：2022-06-14
申请号：US16090963
申请日：2017-03-28
Applicant: ROLLS-ROYCE PLC
Inventor： Giovanni Antonio Marengo
Abstract: There is disclosed a method of manufacturing a composite component comprising a main body and an integral flange, the method comprising applying fibre-reinforcement material on a tool having a main body portion and a flange-forming portion to provide a pre-form comprising a body region and a longitudinally adjacent flange region. The pre-form extends generally longitudinally between two longitudinal ends; and a trailing ply of the pre-form extends generally longitudinally between the longitudinal end closest to the flange region and an inner ply end located in the flange region or partway into the body region. Relative movement between the flange-forming portion and the main body portion causes sliding movement between the trailing ply and the flange-forming portion during a flange forming operation, thereby causing a tension force in at least the flange region of the pre-form of during forming of the flange.
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公开(公告)号：US20220178543A1
公开(公告)日：2022-06-09
申请号：US17550630
申请日：2021-12-14
Applicant: ROLLS-ROYCE plc , ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
Inventor： Luca TENTORIO , Imon-Kalyan BAGCHI
Abstract: A lean burn combustor includes a plurality of lean burn fuel injectors, each including a fuel feed arm and a lean burn fuel injector head with a lean burn fuel injector head tip, wherein the lean burn fuel injector head tip has a lean burn fuel injector head tip diameter, the lean burn fuel injector head including a pilot fuel injector and a main fuel injector, the main fuel injector being arranged coaxially and radially outwards of the pilot fuel injector; and a combustor chamber extending along an axial direction for a length and including a radially inner annular wall, a radially outer annular wall, and a meter panel defining the size and shape of the combustor chamber, wherein the combustor chamber includes primary and secondary combustion zones. A ratio of the combustor chamber length to the lean burn fuel injector head tip diameter is less than 5.
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公开(公告)号：US20220178541A1
公开(公告)日：2022-06-09
申请号：US17367952
申请日：2021-07-06
Applicant: ROLLS-ROYCE PLC , ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
Inventor： Luca TENTORIO , Imon-Kalyan BAGCHI
Abstract: A lean burn combustor includes a plurality of lean burn fuel injectors, each including a fuel feed arm and a lean burn fuel injector head with a lean burn fuel injector head tip, wherein the tip has a lean burn fuel injector head tip diameter, the lean burn fuel injector head including a pilot fuel injector and a main fuel injector, the main fuel injector being arranged coaxially and radially outwards of the pilot fuel injector; and a combustor chamber extending along an axial direction and including a radially inner annular wall, a radially outer annular wall, and a meter panel defining the size and shape of the combustor chamber, which includes a primary combustion zone with a primary combustion zone depth and a secondary combustion zone. A ratio of the primary combustion zone depth to the lean burn fuel injector head tip diameter is less than 2.4.
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公开(公告)号：US20220162953A1
公开(公告)日：2022-05-26
申请号：US17514977
申请日：2021-10-29
Applicant: ROLLS-ROYCE plc
Inventor： Geoffrey B JONES , Edward J SPALTON , Duncan A MACDOUGALL
IPC: F01D9/04
Abstract: A gas turbine engine includes: a fan rotating about an engine main axis; a core duct; an engine core; an Engine Section Stator (ESS) including a plurality of ESS vanes and arranged in the core duct downstream of the fan; and a plurality of variable inlet guide vanes (VIGV) adapted to rotate about a pivot axis and arranged in the core duct downstream of the ESS. The VIGV vanes are arranged angularly rotated with respect to the ESS vanes such that the VIGVs are shielded by the ESS, thereby protecting the VIGVs from icing and from ice shedding from the ESS vanes.
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公开(公告)号：US11339714B2
公开(公告)日：2022-05-24
申请号：US17061057
申请日：2020-10-01
Applicant: ROLLS-ROYCE plc , ROLLS-ROYCE CORPORATION
Inventor： Rory D Stieger , Daniel Swain
Abstract: A gas turbine engine comprises, in fluid flow series, a gas-generator compressor, a combustor, a gas-generator turbine, and a free power turbine. The gas-generator compressor is an axi-centrifugal compressor comprising a plurality of axial compression stages followed by a single centrifugal compression stage, wherein the International Standard Atmosphere, sea-level static (hereinafter ISA SLS) design point pressure ratio of the axi-centrifugal compressor is from 12 to 16, and a ratio of the ISA SLS pressure rise across the axial compression stages to the ISA SLS pressure rise across the centrifugal compression stage is from 0.75 to 1.
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Patent Agency Ranking
公开(公告)号：US11339713B2
公开(公告)日：2022-05-24
申请号：US16398742
申请日：2019-04-30
Applicant: ROLLS-ROYCE plc
Inventor： Richard G Stretton , Michael C Willmot , Nicholas Grech
Abstract: A gas turbine engine for an aircraft includes an engine core including a turbine, a compressor, a core shaft, and a core exhaust nozzle, the core exhaust nozzle having a core exhaust nozzle pressure ratio calculated using total pressure at the core nozzle exit; a fan including a plurality of fan blades; and a nacelle surrounding the fan and the engine core and defining a bypass duct, the bypass duct including a bypass exhaust nozzle, the bypass exhaust nozzle having a bypass exhaust nozzle pressure ratio calculated using total pressure at the bypass nozzle exit;
wherein a bypass to core ratio of: bypass exhaust nozzle pressure ratio core exhaust nozzle pressure ratio is configured to be in the range from 1.1 to 2.0 under aircraft cruise conditions.-
公开(公告)号：US20220154582A1
公开(公告)日：2022-05-19
申请号：US17592226
申请日：2022-02-03
Inventor： Michael J. Whittle , Louise J. Gale , Stephan J. Pattison , Anthony G. Razzell , Ian M. Edmonds , Michael G. Abbott
Abstract: A method of treating a component adapted for use in a gas turbine engine is described herein. The component may comprise ceramic matrix composite materials. The treatment to the ceramic matrix composite component may reduce or eliminate the wear or damage of crack propagation in the ceramic matrix composite component.
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公开(公告)号：US11336151B2
公开(公告)日：2022-05-17
申请号：US16404396
申请日：2019-05-06
Applicant: Rolls-Royce plc , Rolls-Royce Corporation
Inventor： David Scothern , Mark Boden , Don Klemen , William Williamson , Brian Maners
Abstract: An electric starter-generator is described. The generator may comprise a rotor, a housing, two bearings, a stator, and a cooling-fluid flowpath. The cooling-fluid flowpath may comprise a cooling-fluid entrance and exit, and a cooling-fluid channel in fluid communication with the entrance and exit. At least a portion of the channel may be defined by a fluid-tight coupling of the housing and a sleeve radially surrounding the outer race of either the bearings. The portion may form an annulus about the axis. The portion may comprise a radially inner surface defined by the sleeve, a radially outer surface define by said housing, and two axial surfaces. The two axial surfaces may extend a distance from the radially inner to outer surfaces that is less than a distance from one of the two axial surfaces to the other of the two axial surfaces.
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239.发明申请公开(公告)号：US20220143861A1
公开(公告)日：2022-05-12
申请号：US17437689
申请日：2020-03-03
Applicant: ROLLS-ROYCE PLC
Inventor： Paul Warrington
Abstract: There is disclosed a method of providing through-thickness reinforcement in a laminated material. A guide foot is moved to a datum location relative the laminated material, at which the guide foot abuts a reinforcement zone on a surface of the laminated material. An insertion operation is conducted by inserting an insertion element through the guide foot into the laminated material along an insertion direction when the guide foot is in the datum location. The insertion element comprises a needle for forming a hole in the laminated material; a reinforcement rod to be received in the laminated material; or a tamping pin for tamping a reinforcement rod received in the laminated material. A corresponding insertion apparatus is disclosed.
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公开(公告)号：US11326512B2
公开(公告)日：2022-05-10
申请号：US17345588
申请日：2021-06-11
Applicant: ROLLS-ROYCE PLC
Inventor： Craig W Bemment , Pascal Dunning
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, wherein a compressor exit temperature is defined as an average temperature of airflow at the exit from the compressor; and a fan located upstream of the engine core, the fan comprising a plurality of fan blades extending from a hub, each fan blade having a leading edge and a trailing edge, wherein a fan rotor entry temperature is defined as an average temperature of airflow across the leading edge of each fan blade at cruise conditions and a fan tip rotor exit temperature is defined as an average temperature of airflow across a radially outer portion of each fan blade at the trailing edge at cruise conditions. A core to fan tip temperature rise ratio is in the range from 2.845 to 3.8.
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