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公开(公告)号：US20190205500A1
公开(公告)日：2019-07-04
申请号：US15861647
申请日：2018-01-03
Applicant: General Electric Company
Inventor： Brendan Michael Freely , Kevin Klasing , Eric Ruggiero , Daniel Endecott Osgood
CPC classification number: G06F17/5095 , F05D2220/32 , F05D2230/60 , G06Q10/06 , G06Q10/0635 , G06Q10/20 , G06Q50/04
Abstract: Systems, computer-implemented methods and/or computer program products that facilitate selecting components for aviation engines. In one embodiment, a computer-implemented method comprises: calculating, by a system operatively coupled to a processor, standard deviation between components for aviation engines based on a statistical distribution of measured manufacturing characteristics; selecting, by the system, a subset of components based on the calculated standard deviation; and analyzing, by the system, the subset of components at respective standard deviation to determine a standard deviation and period of time for trading that maximizes durability performance.
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公开(公告)号：US12149154B2
公开(公告)日：2024-11-19
申请号：US17382722
申请日：2021-07-22
Applicant: General Electric Company
Inventor： Brendan Michael Freely , Pablo Gabriel Piazza Galarza , Fabian Isaza , Paul Robert Gemin , Darek Tomasz Zatorski , John Russell Yagielski , Andrew Michael Watson
Abstract: An electric machine having a hybrid insulative-conductive manifold is disclosed. In one aspect, an electric machine includes a manifold that includes an insulative plate and a conductive backplate positioned adjacent to the insulative plate. The insulative plate and the backplate define a first channel and a second channel therebetween. The electric machine also includes a prime winding and a secondary winding electrically isolated from the prime winding. The prime winding and the secondary winding are both in fluid communication with the first channel and the second channel. A terminal conductor extends through the backplate and insulative plate and is electrically coupled with the prime winding. The terminal conductor is electrically isolated from the backplate and provides cooling fluid to the prime winding and the first channel so that cooling fluid flows between the terminal conductor and the prime winding and between the terminal conductor and the first channel.
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公开(公告)号：US20230415883A1
公开(公告)日：2023-12-28
申请号：US18466922
申请日：2023-09-14
Applicant: General Electric Company
Inventor： Brendan Michael Freely , Kurt David Murrow , Michael James McMahon
CPC classification number: B64C11/305 , F01D5/12 , F02C6/20 , F02C9/00 , F05D2220/323
Abstract: A method of operating an aircraft engine coupled to a wing of an aircraft including: setting a pitch of a plurality of rotor blades of a rotor assembly of the aircraft engine at non-uniform pitch angles along a circumferential direction of the aircraft engine such that the plurality of rotor blades define a first pitch at a first position and a second pitch at a second position, wherein the second position is 180 degrees offset from the first position, and wherein the first pitch is different from the second pitch.
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公开(公告)号：US20220063793A1
公开(公告)日：2022-03-03
申请号：US17007503
申请日：2020-08-31
Applicant: General Electric Company
Inventor： Brendan Michael Freely , Kurt David Murrow , Michael James McMahon , Andrew Breeze-Stringfellow
Abstract: An aircraft equipped with a distributed unducted fan propulsion system is provided. In one aspect, an aircraft includes a body defining a lateral centerline that separates the body into a first side and a second side. One or more first unducted fans are mounted to the first side of the body. The one or more first unducted fans are rotatable in a first direction. One or more second unducted fans are mounted to the second side of the body. The one or more second unducted fans are rotatable in a second direction that is opposite the first direction.
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公开(公告)号：US11182514B2
公开(公告)日：2021-11-23
申请号：US15861647
申请日：2018-01-03
Applicant: General Electric Company
Inventor： Brendan Michael Freely , Kevin Klasing , Eric Ruggiero , Daniel Endecott Osgood
Abstract: Systems, computer-implemented methods and/or computer program products that facilitate selecting components for aviation engines. In one embodiment, a computer-implemented method comprises: calculating, by a system operatively coupled to a processor, standard deviation between components for aviation engines based on a statistical distribution of measured manufacturing characteristics; selecting, by the system, a subset of components based on the calculated standard deviation; and analyzing, by the system, the subset of components at respective standard deviation to determine a standard deviation and period of time for trading that maximizes durability performance.
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Patent Agency Ranking
公开(公告)号：US11834186B2
公开(公告)日：2023-12-05
申请号：US17006965
申请日：2020-08-31
Applicant: General Electric Company
Inventor： Brendan Michael Freely , Kurt David Murrow , Michael James McMahon , Andrew Breeze-Stringfellow
CPC classification number: B64D27/02 , B64C23/00 , B64D27/24 , B64D31/12 , F04D25/166
Abstract: An aircraft equipped with a distributed fan propulsion system and methods of operating such aircraft are provided. In one aspect, an aircraft includes a wing having a top surface and a bottom surface. The aircraft also has a distributed propulsion system that includes a suction fan array having one or more fans mounted to the wing and a pressure fan array having one or more fans mounted to the wing. The fans of the suction fan array are each positioned primarily above the top surface of the wing and the fans of the pressure fan array are each positioned primarily below the bottom surface of the wing. The fans of the suction fan array are controllable independent of the fans of the pressure fan array so that the air pressure above and/or below the wing can be locally controlled, allowing for adjustment of lift on the wing.
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公开(公告)号：US20220063792A1
公开(公告)日：2022-03-03
申请号：US17383031
申请日：2021-07-22
Applicant: General Electric Company
Inventor： Brendan Michael Freely , Kurt David Murrow , Michael James McMahon
Abstract: A method of operating an aircraft engine coupled to a wing of an aircraft including: setting a pitch of a plurality of rotor blades of a rotor assembly of the aircraft engine at non-uniform pitch angles along a circumferential direction of the aircraft engine such that the plurality of rotor blades define a first pitch at a first position and a second pitch at a second position, wherein the second position is 180 degrees offset from the first position, and wherein the first pitch is different from the second pitch.
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8.发明公开公开(公告)号：US20240051670A1
公开(公告)日：2024-02-15
申请号：US18495871
申请日：2023-10-27
Applicant: General Electric Company
Inventor： Brendan Michael Freely , Kurt David Murrow , Michael James McMahon , Andrew Breeze-Stringfellow
CPC classification number: B64D27/02 , B64C23/00 , B64D27/24 , B64D31/12 , F04D25/166
Abstract: An aircraft equipped with a distributed fan propulsion system and methods of operating such aircraft are provided. In one aspect, an aircraft includes a wing having a top surface and a bottom surface. The aircraft also has a distributed propulsion system that includes a suction fan array having one or more fans mounted to the wing and a pressure fan array having one or more fans mounted to the wing. The fans of the suction fan array are each positioned primarily above the top surface of the wing and the fans of the pressure fan array are each positioned primarily below the bottom surface of the wing. The fans of the suction fan array are controllable independent of the fans of the pressure fan array so that the air pressure above and/or below the wing can be locally controlled, allowing for adjustment of lift on the wing.
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公开(公告)号：US11814154B2
公开(公告)日：2023-11-14
申请号：US17383031
申请日：2021-07-22
Applicant: General Electric Company
Inventor： Brendan Michael Freely , Kurt David Murrow , Michael James McMahon
CPC classification number: B64C11/305 , F01D5/12 , F02C6/20 , F02C9/00 , F05D2220/323
Abstract: A method of operating an aircraft engine coupled to a wing of an aircraft including: setting a pitch of a plurality of rotor blades of a rotor assembly of the aircraft engine at non-uniform pitch angles along a circumferential direction of the aircraft engine such that the plurality of rotor blades define a first pitch at a first position and a second pitch at a second position, wherein the second position is 180 degrees offset from the first position, and wherein the first pitch is different from the second pitch.
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公开(公告)号：US20230024956A1
公开(公告)日：2023-01-26
申请号：US17382722
申请日：2021-07-22
Applicant: General Electric Company
Inventor： Brendan Michael Freely , Pablo Gabriel Piazza Galarza , Fabian Isaza , Paul Robert Gemin , Darek Tomasz Zatorski , John Russell Yagielski , Andrew Michael Watson
Abstract: An electric machine having a hybrid insulative-conductive manifold is disclosed. In one aspect, an electric machine includes a manifold that includes an insulative plate and a conductive backplate positioned adjacent to the insulative plate. The insulative plate and the backplate define a first channel and a second channel therebetween. The electric machine also includes a prime winding and a secondary winding electrically isolated from the prime winding. The prime winding and the secondary winding are both in fluid communication with the first channel and the second channel. A terminal conductor extends through the backplate and insulative plate and is electrically coupled with the prime winding. The terminal conductor is electrically isolated from the backplate and provides cooling fluid to the prime winding and the first channel so that cooling fluid flows between the terminal conductor and the prime winding and between the terminal conductor and the first channel.
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