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公开(公告)号：US20220034259A1
公开(公告)日：2022-02-03
申请号：US17360653
申请日：2021-06-28
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Ryan C. Humes , Andrew J. Eifert
Abstract: A compressor adapted for use in a gas turbine engine includes an impeller, a diffuser, and a deswirler. The impeller is arranged circumferentially about an axis and configured to rotate about the axis. The diffuser is arranged circumferentially around the impeller to receive the air from the impeller. The deswirler is configured to receive the air from the diffuser and to conduct the air into a combustion chamber.
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公开(公告)号：US20220034227A1
公开(公告)日：2022-02-03
申请号：US16983695
申请日：2020-08-03
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Douglas David Dierksmeier , Michael A. Karam
Abstract: A turbine wheel for a gas turbine engine including a compressor impeller and a radial inflow turbine integral to or attached to the compressor impeller is provided. A compressor turbine wheel including features to increase surface area of a surface of the compressor impeller and/or the radial inflow turbine and/or a passage to flow air between the compressor impeller and the radial inflow turbine is further provided. Methods for cooling radial inflow turbines integral to compressor impellers are further provided.
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73.发明申请公开(公告)号：US20220018310A1
公开(公告)日：2022-01-20
申请号：US16928586
申请日：2020-07-14
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Ryan Humes
Abstract: A compressor adapted for use in for a gas turbine engine includes a diffuser and a housing. The diffuser is arranged circumferentially around an axis and includes a fore plate, an aft plate spaced apart axially from the fore plate to define a flow path therebetween, and a plurality of vanes that extend between the fore plate and the aft plate. The housing is arranged circumferentially about the axis and located adjacent the diffuser.
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公开(公告)号：US11225881B2
公开(公告)日：2022-01-18
申请号：US16184725
申请日：2018-11-08
Inventor： Stephen Andrew Long
Abstract: An example hybrid aircraft propulsion system includes one or more parallel propulsion units, each of the parallel propulsion units comprising: a first propulsor; a gas turbine engine configured to drive the first propulsor; and an electrical machine selectively configurable to: generate, for output via one or more electrical busses, electrical energy using mechanical energy derived from the first propulsor or the gas turbine engine; and drive the first propulsor using electrical energy received via the one or more electrical busses; and one or more series propulsion units, each of the series propulsion units comprising: a second propulsor; and an electrical machine selectively configurable to: generate, for output via the one or more electrical busses, electrical energy using mechanical energy derived from the second propulsor or the gas turbine engine; and drive the second propulsor using electrical energy received from one or more electrical busses.
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公开(公告)号：US11212948B1
公开(公告)日：2021-12-28
申请号：US17196700
申请日：2021-03-09
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Douglas J. Snyder , Timothy Unton
Abstract: A thermal management system for tightly controlling temperature of a thermal load (e.g., onboard an aircraft) includes: a pressurized tank for storing an expendable coolant; a control valve downstream of the pressurized tank for controlling a flow rate of the expendable coolant; a heat exchanger downstream of the control valve for transferring heat from a thermal load to the expendable coolant at a predetermined temperature; a back pressure regulator (BPR) downstream of the heat exchanger, the BPR having a set point controlled to maintain the expendable coolant at the predetermined temperature in the heat exchanger; optionally, a sensor or orifice downstream of the heat exchanger for determining vapor quality at an exit of the heat exchanger; and a system exit downstream of the BPR for removing some or all of the expendable coolant from the thermal management system after transferring heat from the thermal load to the expendable coolant.
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Patent Agency Ranking
公开(公告)号：US11162388B1
公开(公告)日：2021-11-02
申请号：US16991611
申请日：2020-08-12
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Douglas J. Snyder , Timothy Unton
Abstract: Thermal management systems for cooling high-power, low-duty-cycle thermal loads that include at least three thermally coupled, closed subsystems are provided. Thermal management systems provided herein include a main thermal energy storage loop including a cold-temperature tank and a warm-temperature tank. Thermal management systems provided herein also include a multi-stage compression system or a cascaded architecture of a low-temperature vapor compression system and a high-temperature vapor compression system. Methods of transferring heat from one or more thermal loads to an ambient environment are also provided.
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公开(公告)号：US11162377B2
公开(公告)日：2021-11-02
申请号：US16428319
申请日：2019-05-31
Applicant: Rolls-Royce High Temperature Composites Inc. , Rolls-Royce North American Technologies Inc.
Inventor： Robert J. Shinavski , Thomas Tran , Kevin Lukhard , Ted J. Freeman , Steffan Brown
Abstract: A turbine vane comprising ceramic matrix composite materials. The turbine vane includes an vane support core, an airfoil, and a pair of end walls that are spaced apart from one another to define a gas path. The turbine vane is formed from a plurality of ceramic plies or preforms that are infiltrated with ceramic matrix material to form a one-piece ceramic matrix composite turbine vane.
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78.发明申请公开(公告)号：US20210332714A1
公开(公告)日：2021-10-28
申请号：US16857988
申请日：2020-04-24
Inventor： Shaling H. Starr , Aaron D. Sippel , Ted J. Freeman , David J. Thomas
Abstract: A turbine shroud assembly is adapted to extend around a turbine wheel mounted for rotation about a central reference axis of a gas turbine engine. The turbine shroud assembly includes a carrier segment made from metallic materials and a blade track segment made from ceramic matrix composite materials. The carrier extends at least partway about the axis. The blade track segment is supported by the carrier radially relative to the axis to define a portion of a gas path of the assembly.
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公开(公告)号：US20210332713A1
公开(公告)日：2021-10-28
申请号：US16856752
申请日：2020-04-23
Inventor： Keith Sadler , Ted J. Freeman , Aaron D. Sippel , Alexandra Baucco
Abstract: An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment. The carrier extends at least partway about an axis. The blade track segment is supported by the carrier radially relative to the axis to define a portion of a gas path of the assembly.
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公开(公告)号：US11155339B2
公开(公告)日：2021-10-26
申请号：US16158472
申请日：2018-10-12
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： David Russell Trawick
Abstract: A first assembly can be configured to exert mechanical control forces on a second assembly through a tensioned and inelastic cable including steel. An electrical power source can be in electric communication with a first portion of the cable. An electrical power consumer can be in electric communication with a second portion of the cable. The cable can be a wire rope.
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