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公开(公告)号：US10921042B2
公开(公告)日：2021-02-16
申请号：US16380665
申请日：2019-04-10
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Eric Donovan , Michael Head , Tim Unton , Eugene Jansen
Abstract: A heat transfer system for high transient heat loads includes a fluid, a heat exchanger; a compressor downstream of the heat exchanger outlet; a condenser downstream of the compressor outlet, and a thermal energy storage (TES) section downstream of the condenser outlet and upstream of the heat exchanger. The TES section may include a first pressure regulating valve downstream of a TES unit; and a second pressure regulating valve upstream of the first pressure regulating valve.
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公开(公告)号：US10906658B2
公开(公告)日：2021-02-02
申请号：US16180570
申请日：2018-11-05
Inventor： Stephen Andrew Long , Andrew Bollman , Michael Adam Zagrodnik , Chandana Jayampathi Gajanayake
Abstract: Energy storage systems for aircraft and methods of operating the same are provided. The energy storage system may include a main battery, a propulsion power bus, a non-critical bus, a critical bus, and an engine starter bus. The propulsion power bus may be configured to convey electricity, which is supplied by the main battery, to an electric propulsion machine configured to provide propulsion for the aircraft. The non-critical bus may be configured to convey electricity to a hotel load on the aircraft. The critical bus may be configured to convey electricity, which is supplied by the main battery, to a critical load on the aircraft. The engine starter bus may be configured to convey electricity, which is supplied by the main battery, to an electric starter for a gas turbine engine, where the gas turbine engine is configured to power the electric propulsion machine.
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公开(公告)号：US10906150B2
公开(公告)日：2021-02-02
申请号：US16380644
申请日：2019-04-10
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Eugene Jansen , Eric Donovan
IPC: B23Q11/14
Abstract: A thermal system may comprise a reservoir, a first fluid flowpath, and a second fluid flowpath. The first fluid flowpath may start at the reservoir and return to the reservoir. The first fluid flowpath may comprise, in a direction of the fluid flow, a first side of a sub-cooler, a liquid pump, a first side of a pre-heater, and a first side of an evaporator. The second fluid flowpath may start at the reservoir and return to the reservoir. The second fluid flowpath may comprise, in a direction of a fluid flow, a pressure regulator, a vapor compressor, a first side of a condenser, and an expansion value.
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104.发明申请公开(公告)号：US20210009282A1
公开(公告)日：2021-01-14
申请号：US16508932
申请日：2019-07-11
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Stephen Long , Dwayne Bevis , Sean Guitar , Michael J. Armstrong
Abstract: A hybrid interchangeable battery evaluation tool (HIBET) is provided. HIBET determines an amount of electrical energy and an amount of jet fuel necessary for a hybrid electric aircraft to complete a flight based on a range of the flight, a payload of the hybrid electric aircraft, an indication of a battery mass limitation of the hybrid electric aircraft, and an optimization of an energy split between the electrical energy and the jet fuel. HIBET causes an indication of the amount of electrical energy to be displayed in a graphical user interface and/or to be otherwise outputted.
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公开(公告)号：US10851996B2
公开(公告)日：2020-12-01
申请号：US16029060
申请日：2018-07-06
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Christopher Dwayne DeBruhl
IPC: F23R3/00
Abstract: Heat shields and methods of cooling a heat shield are provided. A heat shield of a combustor may be cooled. The heat shield comprises a first surface and a second surface, where the first surface is opposite the second surface, and the first surface is configured to face a combustion chamber. The heat shield may be cooled by directing airflow over the heat shield through channels towards an opening of the heat shield and past turbulators located in the channels.
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Patent Agency Ranking
公开(公告)号：US20200332672A1
公开(公告)日：2020-10-22
申请号：US16388152
申请日：2019-04-18
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Douglas David Dierksmeier
Abstract: An assembly is disclosed for adjusting the radial position of a blade track relative to a blade of a turbine stage in a gas turbine engine. The assembly comprises a static turbine casing, a blade track carrier, a blade track support assembly, an actuator, and a blade track. The blade track carrier comprises a pair of radially extending flanges each defining at least one bore in radial and axial alignment with each other forming a pair of bores. The blade track support assembly comprises a portion extending through each bore in a pair of bores, and one or more cam-shaped portions rotatable about an axis of rotation. The blade track has an arcuate flange and a support flange, the support flange being carried by the cam-shaped portion of the blade track support assembly such that rotation of the cam-shaped portion effects radial movement of the blade track.
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公开(公告)号：US20200332671A1
公开(公告)日：2020-10-22
申请号：US16388129
申请日：2019-04-18
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Douglas David Dierksmeier
Abstract: An assembly is disclosed for adjusting the radial position of one or more blade tracks radially encasing the blades of a turbine stage in a gas turbine engine. The assembly comprises a static turbine casing, a plurality of blade track carriers, an annular control ring, an actuator, and a plurality of blade tracks. The blade tracks have a radially inner surface that defines a flowpath boundary of the turbine stage. The blade tracks are carried by the blade track carriers, which are engaged with the annular control ring. Actuation of the actuator moves the control ring in an axial dimension and this movement is translated into an adjustment of the radial position of the blade track.
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公开(公告)号：US10794667B2
公开(公告)日：2020-10-06
申请号：US15398380
申请日：2017-01-04
Inventor： Andrew Eifert , Eric Wilson , Russell White , Mark Jon Blackwelder
Abstract: Systems and methods thermal management of a directed energy weapon are provided. The system may include a controller module executable by a processor to determine a planned energy emission from a light-emitting diode (LED) of the directed energy weapon. The controller module may generate a cooling instruction to influence a temperature of the LED with a cooling fluid in response to the planned energy emission. The controller module may cause the cooling fluid to be applied to the LED in accordance with the cooling instruction prior to a start of the planned energy emission of the LED.
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公开(公告)号：US10787917B2
公开(公告)日：2020-09-29
申请号：US15971356
申请日：2018-05-04
Applicant: Rolls-Royce North American Technologies Inc. , Rolls-Royce High Temperature Composites Inc.
Inventor： Ted J. Freeman , Christopher Barrett
IPC: F01D5/30
Abstract: A multi-piece disk for use in a turbine of a gas turbine engine. The multi-piece disk includes a fore disk segment and an aft disk segment coupled with the fore disk segment for movement with the fore disk segment. The fore disk segment and the aft disk segment are formed to define slots that extend through the disk segments and are configured to receive turbine blades therein.
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公开(公告)号：US10787916B2
公开(公告)日：2020-09-29
申请号：US16016208
申请日：2018-06-22
Inventor： Jun Shi , Ted J. Freeman
Abstract: The present disclosure is related to turbine wheel assemblies for gas turbine engines. Such turbine wheel assemblies may include ceramic matrix composite airfoil components mounted with different types of coupling to a central disc.
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