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公开(公告)号：US20250146424A1
公开(公告)日：2025-05-08
申请号：US18933153
申请日：2024-10-31
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Neil Backus , Stanford Clemens
Abstract: A power-generation system includes an electrical system, a turbine engine, and a pump. The turbine engine includes a compressor configured to receive and compress a working fluid, a heat source that transfers heat to the compressed working fluid, a turbine fluidly connected with the compressor to extract work from the heated working fluid, and a first heat-exchanger fluidly connected with the turbine to transfer heat away from the heated working fluid to provide a cooled working fluid. The pump conducts a portion of the cooled working fluid from the first heat-exchanger to the electrical system to cool components of the electrical system.
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公开(公告)号：US12292056B2
公开(公告)日：2025-05-06
申请号：US18600610
申请日：2024-03-08
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Robert W. Heeter , Daniel E. Molnar, Jr. , Gregory J. Hebert
Abstract: A fan assembly for a gas turbine engine includes a fan duct, a fan, and an outlet guide vane assembly located in the fan duct axially downstream of the fan. The outlet guide vane assembly includes a first variable leading edge outlet guide vane that extends radially relative to the central axis and includes a leading edge portion and a fixed aft portion, the leading edge portion including a tip segment configured to rotate about a leading edge pitch axis and a hub segment located radially inward of and separate from the tip segment, the hub segment configured to independently rotate about the leading edge pitch axis relative to the tip segment. The assembly further includes two unique gear assemblies each configured to rotate one of the tip and hub segments.
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公开(公告)号：US12281615B1
公开(公告)日：2025-04-22
申请号：US18377643
申请日：2023-10-06
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Patrick Gore
Abstract: A system includes a hydrogen fuel delivery system for an engine. The hydrogen fuel delivery system includes a pump configured to pump hydrogen from a tank storing the hydrogen in a liquid state through the hydrogen fuel delivery system, and an evaporator configured to convert at least some of the hydrogen in the liquid state to a gaseous state. The system also includes a heat source thermally coupled with the hydrogen fuel delivery system and fluidly uncoupled from the hydrogen fuel delivery system. The hydrogen fuel delivery system is configured to supply the hydrogen to the engine for combustion and cool the heat source using the hydrogen.
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公开(公告)号：US20250122847A1
公开(公告)日：2025-04-17
申请号：US19000553
申请日：2024-12-23
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Kenneth M. Pesyna , Andrew M. Simonich
Abstract: A propulsion unit includes a gas turbine engine and an exhaust nozzle coupled to an aft end of the gas turbine engine. The exhaust nozzle is configured to interact with exhaust gases exiting the gas turbine engine in an aft direction. The exhaust nozzle includes an outer nozzle case and an inner plug that cooperate to define an exhaust flow path therebetween. The exhaust nozzle is configured to manipulate the exhaust gases to provide different thrust capabilities for the gas turbine engine. The exhaust nozzle includes a thrust reverser configured to be retained by the inner plug.
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公开(公告)号：US20250101914A1
公开(公告)日：2025-03-27
申请号：US18371812
申请日：2023-09-22
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： James C. Loebig
Abstract: A vortex particle separator adapted for use with a gas turbine engine includes a vortex tube, a plurality of swirl vanes, and an outlet tube. The vortex tube receives atmospheric air laden with particles. The plurality of swirl vanes are arranged within the vortex tube and separate the atmospheric air into a first flow of air having the particles and a second flow of air that is relatively free of the particles. The outlet tube extends into the vortex tube to define a scavenge passageway between the outlet tube and the vortex tube that receives the first flow of air. The outlet tube defines an intake passageway that receives the second flow of air. The vortex particle separator further includes a layer of material having a low coefficient of restitution on at least one of an interior surface of the vortex tube and a surface of the swirl vanes.
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Patent Agency Ranking
公开(公告)号：US12258874B2
公开(公告)日：2025-03-25
申请号：US18347722
申请日：2023-07-06
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Eric Engebretsen , Aaron Weishaar , Jonathan Acker , Brett Hartnagel
Abstract: A gas turbine engine includes: an inlet guide vane; an inlet channel extending from a location downstream of the inlet guide vane to a stem manifold; and an outlet channel extending to an outlet port, the outlet port configured to dump anti-ice air overboard, wherein the inlet guide vane includes an anti-ice cavity in fluid communication with the inlet channel and the outlet channel such that anti-ice air, flowing from a downstream location within a core flow of the gas turbine, flows from the inlet channel, through the inlet guide vane, and to the outlet channel.
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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：US20250092825A1
公开(公告)日：2025-03-20
申请号：US18469252
申请日：2023-09-18
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Timothy Unton , Eric S. Donovan
Abstract: A cooling system may comprise a vapor cycle system. The cooling system may comprise a gas turbine engine. The vapor cycle system may include a compressor, a heat exchanger downstream from the compressor, and a heat load downstream from the heat exchanger and upstream of the compressor. The cooling system may comprise a bleed air conduit. The bleed air conduit may be configured to receive bleed air from the gas turbine engine. The cooling system may comprise a bleed turbine driven by the bleed air supplied from the bleed air conduit. The bleed turbine may be configured to drive the compressor of the vapor cycle system. The compressor may be connected to a bleed turbine via a shaft. The cooling system may comprise a throttle valve to control a flow of the bleed air through the bleed air conduit.
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公开(公告)号：US12228096B1
公开(公告)日：2025-02-18
申请号：US18233671
申请日：2023-08-14
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Kenneth M. Pesyna , Andrew M. Simonich
Abstract: A propulsion unit includes a gas turbine engine and an exhaust nozzle coupled to an aft end of the gas turbine engine. The exhaust nozzle is configured to interact with exhaust gases exiting the gas turbine engine in an aft direction. The exhaust nozzle includes an outer nozzle case and an inner plug that cooperate to define an exhaust flow path therebetween. The exhaust nozzle is configured to manipulate the exhaust gases to provide different thrust capabilities for the gas turbine engine.
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公开(公告)号：US20250043695A1
公开(公告)日：2025-02-06
申请号：US18228258
申请日：2023-07-31
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Kerry J. Lighty , William Williamson , Michel Smallwood
Abstract: A heat-exchanger assembly includes a shroud, a heat exchanger, and a mounting system. The shroud is configured to direct a flow of air through the heat-exchanger assembly. The heat exchanger is configured to transfer heat. The mounting system is configured to couple the shroud with the heat exchanger.
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