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公开(公告)号：US20240368997A1
公开(公告)日：2024-11-07
申请号：US18410290
申请日：2024-01-11
Applicant: General Electric Company
IPC: F01D17/16 , B64C11/00 , B64C11/18 , B64C11/46 , B64C11/48 , B64D27/00 , F01D9/02 , F02C6/20 , F02K1/46 , F02K3/02
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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32.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：US11859515B2
公开(公告)日：2024-01-02
申请号：US17686843
申请日：2022-03-04
Applicant: General Electric Company
Inventor： Tsuguji Nakano , Darek Zatorski , Andrew Breeze-Stringfellow
CPC classification number: F01D9/041 , F01D5/145 , F01D9/02 , F01D9/04 , F01D25/28 , F05D2240/126 , F05D2240/129
Abstract: There is provided apparatuses and methods for a gas turbine engine. The embodiments include a core section with a flow path. The flow path includes a stator vane array having outlet vanes. Each outlet vane has a trailing edge. A strut has a leading edge that is upstream of the trailing edges. Alternatively, the flow path includes a stator vane array having inlet vanes. Each inlet vane has a leading edge. The strut has a trailing edge that is downstream of the leading edges. There also is increased spacing between adjacent vanes and rotor blades.
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公开(公告)号：US20220063796A1
公开(公告)日：2022-03-03
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
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：US11208912B2
公开(公告)日：2021-12-28
申请号：US16219059
申请日：2018-12-13
Applicant: General Electric Company
Inventor： Paul Hadley Vitt , Andrew Breeze-Stringfellow
Abstract: A shroud assembly for a gas turbine engine includes: at least one shroud hanger; an annular array of shroud segments carried by the child hanger at least one and arrayed about an engine centerline axis, each of the shroud segments having a flowpath side defining a portion of a primary engine flowpath, and an opposed backside facing the at least one shroud hanger, wherein the shroud segment is mounted to the at least one shroud hanger such that it is movable in a radial direction between an inboard position and an outboard position, in response to a balance of gas pressures prevailing on the flowpath side and the backside; and biasing means which urge each of the shroud segments towards one of the positions.
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Patent Agency Ranking
公开(公告)号：US20210339879A1
公开(公告)日：2021-11-04
申请号：US17366749
申请日：2021-07-02
Applicant: General Electric Company
IPC: B64D27/24 , B64D29/04 , B64C3/10 , B64C29/00 , B64D27/08 , B64C3/32 , B64D35/02 , B64C3/38 , B64D33/04 , B64D31/06
Abstract: An aircraft defines a vertical direction and includes a fuselage and a propulsion system comprising a power source and a plurality of vertical thrust electric fans driven by the power source. A wing extends from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing along a lengthwise direction of the wing. The wing comprises a diffusion assembly along the lengthwise direction of the wing and includes a first diffusion member positioned downstream of at least one of the plurality of vertical thrust electric fans. The first diffusion member defines a curved shape relative to a longitudinal direction of the aircraft. The longitudinal direction is generally perpendicular to the lengthwise direction of the wing.
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公开(公告)号：US20210222575A1
公开(公告)日：2021-07-22
申请号：US17061594
申请日：2020-10-02
Applicant: General Electric Company
Inventor： Andrew Breeze-Stringfellow , Syed Arif Khalid
Abstract: A single unducted rotor engine is provided. The single unducted rotor engine defines an axial direction and a radial direction, the engine including: a power source; a casing surrounding the power source; an unducted rotor assembly driven by the power source comprising a single row of rotor blades; and an outlet guide vane assembly comprising a plurality of pairs of outlet guide vanes, each pair of the plurality of pairs of outlet guide vanes including first outlet guide vane extending from the casing at a location downstream from the single row of rotor blades of the unducted rotor assembly and a second outlet guide vane also positioned downstream from the single row of rotor blades of the unducted rotor assembly; wherein the first outlet guide vane of each pair of outlet guide vanes defines a first geometry, wherein the second outlet guide vane of each pair of outlet guide vanes defines a second geometry, and wherein the first geometry is not equal to the second geometry.
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公开(公告)号：US20210156258A1
公开(公告)日：2021-05-27
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：US20210108572A1
公开(公告)日：2021-04-15
申请号：US17071271
申请日：2020-10-15
Applicant: General Electric Company
Inventor： Syed Arif Khalid , Andrew Breeze-Stringfellow
Abstract: A method is provided of operating a single unducted rotor engine, the single unducted rotor engine comprising a single stage of unducted rotor blades. The method includes operating the single unducted rotor engine to define a flight speed, V0, in a length unit per second and an angular speed, n, in revolutions per second, the single stage of unducted rotor blades defining a diameter, D, in the length unit; wherein operating the single unducted rotor engine comprises operating the single unducted rotor engine to define an advance ratio greater than 3.8 while operating the single unducted rotor engine at a net efficiency of at least 0.8, the advance ratio defined by the equation V0/(n×D).
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公开(公告)号：US10788053B2
公开(公告)日：2020-09-29
申请号：US16170254
申请日：2018-10-25
Applicant: General Electric Company
Inventor： Arun Kumar , Nitesh Jain , Nicholas Joseph Kray , Thomas Ory Moniz , Andrew Breeze-Stringfellow
Abstract: A noise reducing airfoil defining a span extending between a root and a tip and a chord at each point along the span extending between a leading edge and a trailing edge. The airfoil includes a pressure side, a suction side, and a trailing edge sheath including an outer surface coupled to the trailing edge of the airfoil. The trailing edge sheath extends at least partially along the chord on the pressure and suction sides at each point along the span within the trailing edge sheath. The trailing edge sheath defines a fluid passageway extending along at least a portion of the span. Further, the trailing edge sheath defines at least one aperture on at least one of the pressure side, the suction side, or trailing edge fluidly coupling the fluid passageway to the outer surface.
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