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公开(公告)号：US20250042558A1
公开(公告)日：2025-02-06
申请号：US18230609
申请日：2023-08-04
Applicant: General Electric Company
Inventor： Sara Elizabeth Carle , Daniel L. Tweedt , Syed Arif Khalid , Andrew Breeze-Stringfellow , William Bowden
Abstract: The present disclosure is generally related to aircraft having one or more unducted fan propulsors at locations within specific regions relative to an airfoil, such as a wing or horizontal stabilizer. More specifically, the specific regions are located where there is a relatively higher pressure air flow beneath the wings or above a horizontal stabilizer. That higher pressure air flow can be utilized to provide increased thrust from the unducted fan propulsor.
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公开(公告)号：US20250042537A1
公开(公告)日：2025-02-06
申请号：US18652052
申请日：2024-05-01
Applicant: General Electric Company
Inventor： Sara Elizabeth Carle , Daniel L. Tweedt , Syed Arif Khalid , Andrew Breeze-Stringfellow , William Bowden
Abstract: The present disclosure is generally related to aircraft having one or more unducted fan propulsors at locations within specific regions relative to an airfoil, such as a wing or horizontal stabilizer. More specifically, the specific regions are located where there is a relatively higher pressure air flow beneath the wings or above a horizontal stabilizer. That higher pressure air flow can be utilized to provide increased thrust from the unducted fan propulsor.
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公开(公告)号：US11988099B2
公开(公告)日：2024-05-21
申请号：US16900407
申请日：2020-06-12
Applicant: General Electric Company
Inventor： Darek Tomasz Zatorski , Jeffrey Hamel , Andrew Breeze-Stringfellow
IPC: B64C11/00 , B64C11/18 , B64C11/46 , B64C11/48 , F01D9/02 , F01D17/16 , F02C6/20 , F02K1/46 , F02K3/02 , B64D27/00
CPC classification number: F01D17/16 , B64C11/001 , B64C11/18 , B64C11/46 , B64C11/48 , F01D9/02 , F02C6/206 , F02K1/46 , F02K3/025 , B64C11/00 , B64D2027/005 , F05B2240/12 , F05B2260/96 , F05D2220/324 , F05D2220/325 , F05D2250/30 , F05D2250/51 , F05D2250/52 , F05D2260/14 , Y02E10/72 , Y02T50/60
Abstract: An unducted thrust producing system, includes a rotating element, a stationary element. An inlet may be located forward or aft of the rotating element and the stationary element. An exhaust may be located forward, aft, or between the rotating element and the stationary element.
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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：US11262144B2
公开(公告)日：2022-03-01
申请号：US15858453
申请日：2017-12-29
Applicant: General Electric Company
Abstract: A heat exchanger apparatus includes: spaced-apart peripheral walls extending between an inlet and an outlet, the peripheral walls collectively defining a flow channel which includes a diverging portion downstream of the inlet, in which a flow area is greater than a flow area at the inlet; a plurality of spaced-apart fins disposed in the flow channel, each of the fins having opposed side walls extending between an upstream leading edge and a downstream trailing edge, wherein the fins divide at least the diverging portion of the flow channel into a plurality of side-by-side flow passages; and a heat transfer structure disposed within at least one of the fins.
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Patent Agency Ranking
公开(公告)号：US11193377B2
公开(公告)日：2021-12-07
申请号：US16695358
申请日：2019-11-26
Applicant: General Electric Company
Inventor： Aamir Shabbir , Christopher Robert Berndt , Andrew Breeze-Stringfellow
IPC: F01D5/12
Abstract: A method of controlling a transition from a laminar flow to a turbulent flow for an airfoil of a turbomachine includes forming an airfoil. The airfoil defines a span extending between a root and a tip and a chord extending between a leading edge and a trailing edge. The airfoil includes a suction side surface and a pressure side surface, opposite the suction side surface, each extending between the leading edge, the trailing edge, the root, and the tip. The method also includes finishing a majority of the suction and pressure side surfaces in order to form a finished surface. The finished surface defines a first roughness. The method additionally includes leaving at least a portion of the suction side surface and/or pressure side surface unfinished in order to form an unfinished surface. Furthermore, the unfinished surface defines a second roughness greater than the first roughness.
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公开(公告)号：US11124307B2
公开(公告)日：2021-09-21
申请号：US16042403
申请日：2018-07-23
Applicant: General Electric Company
IPC: B64D27/24 , B64C29/00 , B64C3/38 , B64D29/04 , B64C3/10 , B64D27/08 , B64C3/32 , B64D35/02 , B64D33/04 , B64D31/06 , B64D27/02 , B64D27/26 , H02K7/18
Abstract: An aircraft includes a fuselage; a propulsion system including a power source and a plurality of vertical thrust electric fans driven by the power source; and a wing extending from the fuselage. The plurality of vertical thrust electric fans are arranged along the wing, the wing including one or more components being moveable to selectively expose the plurality of vertical thrust electric fans, the wing further including a diffusion assembly positioned downstream of at least one vertical thrust electric fan of the plurality of vertical thrust electric fans, the diffusion assembly defining a diffusion area ratio greater than 1:1 and less than about 2:1.
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公开(公告)号：US20210108595A1
公开(公告)日：2021-04-15
申请号：US17071018
申请日：2020-10-15
Applicant: General Electric Company
Inventor： Syed Arif Khalid , Andrew Breeze-Stringfellow
Abstract: A propulsion system is provided, the propulsion system including a rotor assembly configured to rotate relative to the engine centerline axis, and wherein one or more blades of the rotor assembly are configured to rotate along a blade pitch angle axis. A vane assembly is positioned in aerodynamic relationship with the rotor assembly. The vane assembly includes one or more vanes, wherein each vane includes a vane pitch angle. A controller is configured to execute operations, the operations including moving each blade to a reverse thrust position about its respective blade pitch axis, and adjusting each vane about its respective vane pitch axis when the plurality of blades is in the reverse thrust position to modify an amount of reverse thrust generated by the propulsion system.
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公开(公告)号：US20210107676A1
公开(公告)日：2021-04-15
申请号：US16599430
申请日：2019-10-11
Applicant: General Electric Company
Abstract: An aircraft extending between a forward end and an aft end is provided. The aircraft includes an auxiliary power unit positioned proximate the aft end of the aircraft, the auxiliary power unit having an auxiliary power unit inlet duct and an auxiliary power unit exhaust duct, and a boundary layer ingestion fan positioned proximate the aft end of the aircraft, the boundary layer ingestion fan having a support shaft, wherein the auxiliary power unit exhaust duct extends through a portion of the support shaft of the boundary layer ingestion fan.
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公开(公告)号：US10907495B2
公开(公告)日：2021-02-02
申请号：US16871660
申请日：2020-05-11
Applicant: General Electric Company
IPC: F01D9/02 , F01D17/16 , B64C11/00 , B64C11/18 , F02K1/46 , F02K3/02 , B64C11/46 , F02C6/20 , B64C11/48
Abstract: A unshrouded vane assembly for an unducted propulsion system includes a plurality of vanes which have non-uniform characteristics configured to generate a desired vane exit swirl angle.
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