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公开(公告)号：US20220018401A1
公开(公告)日：2022-01-20
申请号：US17449370
申请日：2021-09-29
Applicant: Rolls-Royce Corporation
Inventor： Donald Klemen
IPC: F16D27/112 , F16D27/06 , F16D27/115
Abstract: An electromagnetic clutch assembly may include a first clutch plate, a second clutch plate, and a synchronizer. The second clutch plate may define an aperture. A portion of the synchronizer may be configured to extend through the aperture. In the absence of a magnetic field, the first clutch plate and the first surface of the second clutch plate may define an air gap and the portion of the synchronizer may extend into the air gap. In response to a first magnetic field, the portion of the synchronizer may contact the first clutch plate. In response to a second magnetic field, the portion of the synchronizer may translate in the aperture toward the second clutch plate and the first clutch plate and the second clutch plate may close the air gap.
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公开(公告)号：US20210277961A1
公开(公告)日：2021-09-09
申请号：US16813242
申请日：2020-03-09
Applicant: Rolls-Royce Corporation
Inventor： Donald Klemen
IPC: F16D27/115 , F16D27/06
Abstract: An electromagnetic clutch assembly may include a first clutch plate, a second clutch plate, and a synchronizer. The second clutch plate may define an aperture. A portion of the synchronizer may be configured to extend through the aperture. In the absence of a magnetic field, the first clutch plate and the first surface of the second clutch plate may define an air gap and the portion of the synchronizer may extend into the air gap. In response to a first magnetic field, the portion of the synchronizer may contact the first clutch plate. In response to a second magnetic field, the portion of the synchronizer may translate in the aperture toward the second clutch plate and the first clutch plate and the second clutch plate may close the air gap.
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公开(公告)号：US11015476B2
公开(公告)日：2021-05-25
申请号：US16410837
申请日：2019-05-13
Applicant: Rolls-Royce Corporation
Inventor： Donald Klemen , Russell E. White , Eric E. Wilson
Abstract: In examples, a propulsion and electrical generation system including a gas turbine engine including a compressor and a bleed air outlet from the compressor, wherein the compressor is configured to compress a fluid, wherein a portion of the compressed fluid is directed out of the bleed air outlet to define bleed air from the compressor; and a turbo-generator including a combustor, wherein the combustor includes a fuel inlet and a bleed air inlet, wherein the bleed air inlet is in fluid communication with the bleed air outlet from the compressor, wherein the combustor is configured to receive the bleed air via the bleed air inlet from the bleed air outlet of the gas turbine engine and receive fuel via the fuel inlet, wherein the combustor is configured to combust the received fuel with the received bleed air, wherein the turbo-generator is configured to generate electrical energy via the combustion of the fuel by the combustor.
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公开(公告)号：US10323606B2
公开(公告)日：2019-06-18
申请号：US14853757
申请日：2015-09-14
Inventor： Eric E. Wilson , Donald Klemen , Geoffrey L. Gatton
Abstract: A vehicle includes an engine, an oil circuit for providing oil to the engine, a fuel supply line, and an air-oil separating unit. The air-oil separating unit is configured to receive aerated oil from the engine via the oil circuit, flow the aerated oil in approximately a helical direction to de-aerate the oil, receive fuel from the fuel supply line, cool the aerated oil with the fuel while the aerated oil flows in the approximately helical direction, causing the fuel to heat, and pass the cooled and de-aerated oil and pass the heated fuel to the engine.
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公开(公告)号：US11453488B2
公开(公告)日：2022-09-27
申请号：US16588695
申请日：2019-09-30
Applicant: Rolls-Royce Corporation
Inventor： Donald Klemen
IPC: B64C29/00 , B64D27/10 , B64D27/16 , B64D33/04 , B64D27/24 , B60L50/10 , B64D27/02 , F02C3/04 , F02C7/22 , H02K7/18
Abstract: A lightweight lift system for VTOL/VSTOL operation running in parallel with an existing turbine. This system distributes LP power by switching compressor flow and fuel proportionally over to the lift turbine module. As forward thrust is demanded, some of the power is transitioned back to the flight LP turbine, which can drive a variable propeller, fan or can supply jet thrust. As flight motion occurs, the power to the lift fan can be reduced to zero and lift closed off.
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Patent Agency Ranking
公开(公告)号：US11196320B2
公开(公告)日：2021-12-07
申请号：US16690510
申请日：2019-11-21
Applicant: Rolls-Royce plc , Rolls-Royce Corporation
Inventor： Mark Boden , Donald Klemen , Jonathan Terrell , Brian Maners
Abstract: A rotor of an electric machine includes a main rotor body having a longitudinal axis, the main rotor body comprising: a hollow cylinder body with a first end and a second end; an integral end flange at the first end; a separate end flange disposed at the second end of the cylinder body; and laminations disposed on an outer surface of the cylinder body, the laminations comprising magnetic material.
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公开(公告)号：US11009085B2
公开(公告)日：2021-05-18
申请号：US16415580
申请日：2019-05-17
Applicant: Rolls-Royce Corporation
Inventor： Donald Klemen , Brian S. Maners , Erik A. Munevar
Abstract: A gearbox rigidly coupled to a static structure; a driven component rigidly coupled to another static structure; a clutch assembly floating between and coupled to the gearbox and driven component. The clutch may have aligned output and input shafts, defining an engagement surface, a bearing, and a magnetic friction plate coupled and rotating with the input shaft. The plate may have a friction-engagement face, and a magnetic flux generator. The magnetic flux generator may be rigidly coupled to a static housing and partially surrounded in the radial direction by a structure configured to reduce leakage of a magnetic flux, by defining a plurality of voids, which direct multiple passes of the magnetic flux through the engagement surface of the output shaft. The magnetic flux generator may create the magnetic flux that creates a magnetic force between the engagement face and the magnetic friction plate that causes them to engage.
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公开(公告)号：US10676198B2
公开(公告)日：2020-06-09
申请号：US15601969
申请日：2017-05-22
Applicant: Rolls-Royce Corporation
Inventor： Donald Klemen , Michael James Armstrong
Abstract: A system includes at least one compressor, at least two turbines, and at least two combustors, each fluidically coupled to a respective turbine of the at least two turbines and configured to receive compressed fluid from the at least one compressor. The system further includes at least two motor-generators, each operably coupled to a respective turbine of the at least two turbines and configured to convert electrical energy to mechanical energy to drive a respective propulsor to which the respective motor-generator is operably coupled and to convert mechanical energy from the respective turbine to electrical energy. The system further includes at least two propulsors, each operably coupled to a respective turbine of the at least two turbines and configured to be driven by the respective turbine, a respective motor-generator to which the respective propulsor is operably coupled via the respective turbine, or both the respective turbine and the respective motor-generator.
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公开(公告)号：US20150288253A1
公开(公告)日：2015-10-08
申请号：US14679432
申请日：2015-04-06
Applicant: Rolls-Royce Corporation
Inventor： Eric E. Wilson , Donald Klemen
CPC classification number: H02K9/04 , F01D15/10 , F01D25/08 , F02C6/08 , F05D2220/76 , F05D2260/20 , H02K7/1823 , H02K9/00 , H02K19/38 , Y02T50/671 , Y02T50/676
Abstract: A turbine engine includes an electrical system having at least two generator circuits, one coupled to a high pressure portion of a gas turbine engine and the other coupled to a low pressure portion of the gas turbine engine. The electrical system actively cools an electrical generator during operation in order to ensure proper operation as well as extend the lifespan of the generator.
Abstract translation: 涡轮发动机包括具有至少两个发电机电路的电气系统，一个耦合到燃气涡轮发动机的高压部分，另一个联接到燃气涡轮发动机的低压部分。 电气系统在运行期间主动冷却发电机，以确保正常运行以及延长发电机的使用寿命。
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公开(公告)号：US11718395B2
公开(公告)日：2023-08-08
申请号：US16570590
申请日：2019-09-13
Applicant: Rolls-Royce Corporation
Inventor： Donald Klemen
IPC: B64C29/00 , B64D27/24 , B60L50/60 , B60L53/20 , B64D35/04 , B64D35/02 , B60L50/15 , B64D27/02 , H02J7/16
CPC classification number: B64C29/0025 , B60L50/15 , B60L50/60 , B60L53/20 , B64D27/24 , B64D35/02 , B64D35/04 , B60L2200/10 , B64D2027/026 , H02J7/16 , H02J2207/20
Abstract: A vertical takeoff and landing aircraft system includes a gas turbine engine coupled to a variable pitch propeller. The gas turbine engine is also coupled to a power split device including a first motor generator, a second motor generator, and a planetary module therebetween. The planetary module includes a sun gear, a ring gear, and a planet carrier. The motor generators are coupled to inverters, a DC bus and a battery. The battery is configured to power balance fans disposed on wings and horizontal stabilizers of the aircraft system. The balance fans can be closed off after vertical lift has been achieved.
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