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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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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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公开(公告)号：US11319828B1
公开(公告)日：2022-05-03
申请号：US17351741
申请日：2021-06-18
Applicant: Rolls-Royce Corporation
Inventor： Ted J. Freeman , Aaron D. Sippel , David J. Thomas
IPC: F01D11/08
Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier, a seal segment, and a mount assembly. The carrier is configured to be coupled to a turbine case. The seal segment is shaped to define a gas path boundary of the shroud assembly. The mounting assembly is configured to couple the seal segment to the carrier.
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公开(公告)号：US11313324B2
公开(公告)日：2022-04-26
申请号：US16382354
申请日：2019-04-12
Applicant: Rolls-Royce Corporation
Inventor： Jeff Higbie , Robert Heeter , Ben Hodgson , Jon Rivers
Abstract: Systems and methods are presented for acoustic dampening in a rotating machine. The rotating machine has a rotatable shaft defining an axis of rotation and a gas flowpath. A system comprises an acoustic panel affixed to an annular casing. The acoustic panel comprises an acoustic treatment member extending between a radially inner skin and radially outer skin. The radially inner skin extends the full axial and circumferential dimensions of the acoustic panel, and the acoustic treatment member overlays the entirety of the radially inner skin. The acoustic panel is positioned so that the radially outer skin abuts the casing, the abutting surfaces being configured to effect relative axial movement between the surfaces while maintaining contact between the surfaces. The acoustic panel is affixed in position to the casing by one or more fasteners passing through the casing and a portion of the radially outer skin.
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公开(公告)号：US11305363B2
公开(公告)日：2022-04-19
申请号：US16272664
申请日：2019-02-11
Applicant: Rolls-Royce Corporation
Inventor： Raymond Ruiwen Xu , Scott Nelson , Joseph Peter Henderkott
Abstract: A method may include removing a portion of a base component adjacent to a damaged portion of the base component to define a repair portion of the base component. The base component may include a cobalt- or nickel-based superalloy, and the repair portion of the base component may include a through-hole extending from a first surface of the base component to a second surface of the base component. The method also may include forming a braze sintered preform to substantially reproduce a shape of the through-hole. The braze sintered preform may include a Ni- or Co-based alloy. The method additionally may include placing the braze sintered preform in the through-hole and heating at least the braze sintered preform to cause the braze sintered preform to join to the repair portion of the base component and change a microstructure of the braze sintered preform to a brazed and diffused microstructure.
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Patent Agency Ranking
公开(公告)号：US11300008B2
公开(公告)日：2022-04-12
申请号：US16591388
申请日：2019-10-02
Inventor： Kerry J. Lighty , Phillip Burnside
Abstract: A lubricant scavenging system for a turbine engine having a pair of concentric, counter-rotating shafts. The system comprises a lubricant sump housing having a radially inner surface, a pair of pedestal mounts each adapted to receive a bearing assembly from a respective shaft, a lubricant collection point axially disposed between the pedestal mounts, and a pair of axial channels adapted to guide lubricant toward the lubricant collection point.
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公开(公告)号：US20220097184A1
公开(公告)日：2022-03-31
申请号：US17444952
申请日：2021-08-12
Applicant: Rolls-Royce Corporation
Inventor： Joseph Peter Henderkott , Robert Frederick Proctor
Abstract: An assembly for a dual-walled component of a gas turbine engine and methods of forming and repairing a dual-walled component. The assembly includes a cold section part having an outer surface that defines a plurality of impingement apertures, a hot section part including a pre-sintered preform, the hot section part positioned over the outer surface of the cold section part, and a plurality of support structures including the pre-sintered preform, the plurality of support structures positioned between the hot section part and the cold section part, the plurality of support structures separating the hot section part from the cold section part to define at least one cooling channel therebetween.
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公开(公告)号：US11286798B2
公开(公告)日：2022-03-29
申请号：US16545791
申请日：2019-08-20
Inventor： Michael J. Whittle , Daniel K. Vetters , Ted J. Freeman , Eric Koenig , Jeff Crutchfield , Jeffrey A. Walston , David J. Thomas
Abstract: An airfoil assembly includes a vane that includes an outer platform, an inner platform, and an airfoil. The outer platform defines an outer boundary of a gas path. The inner platform is spaced apart axially from the outer platform relative to an axis and defines an inner boundary of the gas path. The airfoil extends axially between and interconnects the outer platform and the inner platform. Force loads caused by gases interacting with the airfoil are configured to be transmitted from the airfoil assembly to a case arranged around the airfoil assembly.
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公开(公告)号：US11255265B2
公开(公告)日：2022-02-22
申请号：US16291681
申请日：2019-03-04
Applicant: Rolls-Royce Corporation
Inventor： John R. Gebhard
Abstract: An air-oil separation system for a gas turbine engine system comprises a housing that extends circumferentially around an axis to define an interior chamber of the housing and a separation unit located in the chamber. The housing is formed to include an inlet configured to receive a mixture of air and oil, an oil outlet configured to conduct oil to exit the housing, and an air outlet configured to conduct air to exit the housing. The air-oil separation unit separates air from the oil.
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公开(公告)号：US11231044B2
公开(公告)日：2022-01-25
申请号：US16176250
申请日：2018-10-31
Applicant: Rolls-Royce Corporation
Inventor： Bronwyn Power
Abstract: An apparatus comprises a gas turbine engine having a compressor for increasing a total pressure of a working fluid prior to delivery to a combustor for mixing with fuel. The compressor has a plurality of airfoil members that extend between a first flow surface and a second flow surface. The plurality of airfoil members have a first camber shape at a tip portion that provides a cumulative integral according to the relationship 0.4
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