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公开(公告)号：US20250163821A1
公开(公告)日：2025-05-22
申请号：US18512681
申请日：2023-11-17
Applicant: Rolls-Royce Corporation
Inventor： Michael Nesteroff , Mark E. Whitlock , Nathanael Cooper , Jonathan Acker
IPC: F01D11/22
Abstract: A compressor assembly for a gas turbine engine comprising an outer case, a shroud arranged circumferentially around the axis to direct compressed air through an impeller, and an actuator coupled with the outer case and the shroud to vary the position of the shroud axially relative to the outer case. The actuator includes a mount arm, an actuator body, and a travel stop. The mount arm is coupled with the outer case. The actuator body is coupled with the mount arm and the shroud to control axial movement of the shroud relative to the outer case. The travel stop is coupled to the mount arm and extends away from the mound arm and is configured to limit a forward most axial position of the shroud relative to the outer case.
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公开(公告)号：US20250163820A1
公开(公告)日：2025-05-22
申请号：US18512672
申请日：2023-11-17
Applicant: Rolls-Royce Corporation
Inventor： Michael Nesteroff , Mark E. Whitlock , Nathanael Cooper , Jonathan Acker
Abstract: A compressor assembly for a gas turbine engine includes a shroud assembly, an outer case assembly, and a plurality of locating bolt assemblies. The shroud assembly extends circumferentially around the engine axis. The outer case assembly includes an outer case that extends circumferentially around the axis and a plurality of fasteners that couple the shroud assembly with the outer case. The plurality of locating bolt assemblies extend into the outer case and abut the shroud assembly at a predetermined axial location to axially locate the shroud assembly.
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公开(公告)号：US12293527B2
公开(公告)日：2025-05-06
申请号：US17932962
申请日：2022-09-16
Applicant: Rolls-Royce Corporation
Inventor： Scott Nelson , Baily Thomas , Abdalla R. Nassar , Jason Scherer , John Grubbs
Abstract: A powder flow monitoring system may include a computing device configured to receive image data representing illuminated powder of a powder stream between a powder delivery device and a build surface of a component, generate a representation of the powder stream based on the image data, and output the representation of the powder stream for display at a display device.
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公开(公告)号：US20250096623A1
公开(公告)日：2025-03-20
申请号：US18470261
申请日：2023-09-19
Inventor： Benedict N. Hodgson , Robert W. Heeter , Alan W. Smith , Hossein Baninajar
Abstract: A stator housing assembly includes a stator housing and a stator sleeve. The stator sleeve including a combination of composite layers with different high strength fibers. The stator housing includes a first end section and a second end section that define a stator cavity configured to contain a pressurized cooling fluid. The stator sleeve defines a longitudinal axis and includes a plurality of layers of composite materials that include more than one high strength fiber material. High strength fibers may include carbon and glass fibers. Portions of the stator sleeve may have different combinations of high strength fiber materials and fiber orientations to optimize sleeve properties.
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公开(公告)号：US12226878B2
公开(公告)日：2025-02-18
申请号：US18150403
申请日：2023-01-05
Applicant: Rolls-Royce Corporation
Inventor： Quinlan Yee Shuck
IPC: B24D18/00 , B22F1/145 , B22F3/00 , B22F7/00 , B22F7/02 , B22F10/00 , B22F10/25 , B22F10/364 , B22F10/38 , B22F12/41
Abstract: A system may include a powder source; a powder delivery device; an energy delivery device; and a computing device. The computing device may be configured to: control the powder source to deliver metal powder to the powder delivery device; control the powder delivery device to deliver the metal powder to a surface of an abrasive coating; and control the energy delivery device to deliver energy to at least one of the abrasive coating or the metal powder to cause the metal powder to be joined to the abrasive coating.
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Patent Agency Ranking
公开(公告)号：US12215593B1
公开(公告)日：2025-02-04
申请号：US18678892
申请日：2024-05-30
Applicant: Rolls-Royce Corporation
Inventor： David J. Thomas , Aaron D. Sippel , Ted J. Freeman , Clark J. Snyder
Abstract: A turbine shroud assembly includes a first shroud segment, a second shroud segment, and a seal assembly. The first shroud segment includes a first carrier segment arranged circumferentially at least partway around a central axis and a first blade track segment supported by the first carrier segment. The second shroud segment is arranged circumferentially adjacent the first shroud segment about the central axis. The seal assembly is configured to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment.
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公开(公告)号：US20250038523A1
公开(公告)日：2025-01-30
申请号：US18358540
申请日：2023-07-25
Applicant: Rolls-Royce Corporation
Inventor： Brian Joseph Huber
Abstract: An example system includes a plurality of transient voltage suppressors (TVSs) that are connected in series across an electrical bus of an aircraft, the electrical bus having a high side and a low side; a plurality of switches, each switch of the plurality of switches configured to selectively shunt a corresponding TVS of the plurality of TVSs to the low side of the electrical bus; and a controller configured to: determine a desired voltage suppression level; and control operation of the plurality of switches such that the plurality of TVSs provides the desired voltage suppression level.
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公开(公告)号：US20250035046A1
公开(公告)日：2025-01-30
申请号：US18361075
申请日：2023-07-28
Inventor： Jeffrey Lawrence , Peter Schenk , Jacob Ward Harral , Brian Joseph Huber
Abstract: An example system includes a first gas-turbine engine configured to propel an aircraft, the first gas-turbine engine comprising: a first air-turbine starter, the first air-turbine starter configured to rotate a spool of the first gas-turbine engine; and a first electric starter, the first electric starter configured to rotate the spool of the first gas-turbine engine; and one or more controllers collectively configured to: cause, during a time period, the first-air turbine starter and the first electric starter to start the first gas-turbine engine while the aircraft is on the ground; measure, during the time period, values of one or more parameters of the first gas-turbine engine; and determine, based on the values of the one or more parameters, whether the first electric starter is available for use in performing mid-air restart of the first gas-turbine engine.
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公开(公告)号：US12209502B1
公开(公告)日：2025-01-28
申请号：US18758996
申请日：2024-06-28
Inventor： Robert W. Heeter , Daniel E. Molnar, Jr. , Jonathan M. Rivers
Abstract: A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.
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公开(公告)号：US12195403B2
公开(公告)日：2025-01-14
申请号：US17302958
申请日：2021-05-17
Applicant: Rolls-Royce Corporation
Inventor： Jeffrey Crutchfield , Christopher Downie
IPC: C04B41/45 , B28B1/52 , B28B7/00 , B28B7/06 , B28B7/32 , B28B7/38 , C04B35/80 , B28B3/00 , B28B7/34
Abstract: A method of forming a bladder cast ceramic matrix composite (CMC) article including infiltrating a CMC substrate positioned in a cavity of a mold body with a slurry. The CMC substrate includes reinforcement material defining inner spaces. The slurry includes solid particles and a carrier material. During infiltration, the slurry at least partially fills at least a portion of the inner spaces of the CMC substrate. The method also includes inflating at least one bladder that is coupled to the mold body and disposed within the cavity such that a surface of the at least one bladder in an inflated configuration contacts at least one surface of the CMC substrate. The method also includes drying the slurry to remove at least a portion of the carrier material form an infiltrated CMC and deflating the at least one bladder.
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