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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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244.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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Patent Agency Ranking
公开(公告)号：US11320404B2
公开(公告)日：2022-05-03
申请号：US16740859
申请日：2020-01-13
Applicant: ROLLS-ROYCE plc
Inventor： Alejandro Jeketo , Michael Bowyer , Joseph J. Corcoran , Eli Leinov
IPC: G01N29/24 , G01N29/22 , G01N29/265 , G01N29/34
Abstract: An apparatus for ultrasonically inspecting a component of a gas turbine engine at a centre frequency required for ultrasonic inspection of the component. The apparatus comprises an ultrasonic transducer and a waveguide. The ultrasonic transducer and the waveguide are mounted in a holder, the holder is movably mounted in a carrier, and the carrier is movably mounted in a frame. The waveguide has a first end, a second end and a surface. The waveguide is circular in cross-section, the surface of the waveguide between the first end and the second end is concave, and the waveguide reduces in diameter from the first end to the second end. The length of the waveguide is equal to or greater than 0.5 times and equal to or less than 3 times the wavelength of an ultrasonic signal at the centre frequency required for the ultrasonic inspection.
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公开(公告)号：US20220126528A1
公开(公告)日：2022-04-28
申请号：US17431245
申请日：2020-02-04
Applicant: ROLLS-ROYCE PLC
Inventor： Giovanni Antonio Marengo , Kevin Mee
Abstract: There is disclosed a method of manufacturing a composite blade, and the composite blade. The method comprises a lay-up operation comprising laying up fibre reinforcement material on an untwisted lay-up surface to make a blade pre-form and a forming operation comprising forming the blade pre-form to introduce twist in the blade pre-form.
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公开(公告)号：US11313454B2
公开(公告)日：2022-04-26
申请号：US16372972
申请日：2019-04-02
Applicant: ROLLS-ROYCE plc
Inventor： Neil J. Davies
Abstract: A lubrication system for a gas turbine engine, the system comprising: a gearbox, the gearbox comprising a sump; an oil tank; a primary gearbox lubrication system configured to pump oil from the oil tank to lubricate the gearbox with a gearbox primary feed; a secondary gearbox lubrication system, configured to lubricate the gearbox with oil from the sump when the oil level in the sump reaches a predetermined level; wherein the system is configured to increase the oil level in the sump to at least the predetermined level in response to a failure of the primary gearbox lubrication system.
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公开(公告)号：US11306680B2
公开(公告)日：2022-04-19
申请号：US17072492
申请日：2020-10-16
Applicant: ROLLS-ROYCE plc
Inventor： Jack F. Colebrooke
Abstract: There is disclosed an exhaust nozzle for a gas turbine engine. The exhaust nozzle comprises a frame extending along a longitudinal axis, and a convergent petal pivotably attached at a convergent pivot point to the frame and extending axially downstream and radially inward from the frame. The exhaust nozzle comprises a follower roller fixed to the convergent petal on a radially outer side of the convergent petal, and a cam defining a working surface configured to engage the follower roller to react a force from the convergent petal. The cam is movable along a travel in an axial direction to actuate radial movement of the follower roller to pivot the convergent petal. The cam defines a convex working surface such that a contact angle between the follower roller and the cam varies along the travel to thereby vary an axial component of the force reacted by the cam.
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公开(公告)号：US20220112982A1
公开(公告)日：2022-04-14
申请号：US17450519
申请日：2021-10-11
Applicant: Rolls-Royce plc
Inventor： Eric W. DEAN
IPC: F17C1/02
Abstract: An organic composite gas storage tank 100 comprises a hollow central portion 106 which is substantially cylindrical and formed integrally with first and second end portions 102, 104, and which defines a longitudinal tank axis 301. The first end portion comprises a hollow truncated conical region which meets the hollow central portion at a first end thereof, the outer and inner radii of the hollow truncated conical region decreasing in a direction along the longitudinal tank axis away from the hollow central portion. An organic fibre winding 107 extends at least between axial positions which coincide with the hollow truncated conical region of the first end portion and the hollow central portion respectively. The first end portion has a higher axial strength than that achievable for hemispherical end portion of a tank of the prior art.
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