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公开(公告)号：US11753939B2
公开(公告)日：2023-09-12
申请号：US16280531
申请日：2019-02-20
Applicant: General Electric Company
Inventor： Alan Roy Stuart , Tsuguji Nakano , Thomas Ory Moniz , Andrew Breeze-Stringfellow , Richard Schmidt
IPC: F01D5/06
CPC classification number: F01D5/06 , F05D2220/32
Abstract: A gas turbine engine is provided including a turbine section including a turbine having a plurality of first speed turbine rotor blades; a compressor section including a compressor having a plurality of first speed compressor rotor blades and a plurality of second speed compressor rotor blades; a gearbox; and a first spool rotatable by the plurality of first speed turbine rotor blades, the first spool coupled to the plurality of first speed compressor rotor blades for driving the plurality of first speed compressor rotor blades in a first direction and to the plurality of second speed compressor rotor blades across the gearbox for driving the plurality of second speed compressor rotor blades in a second direction, opposite the first direction.
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公开(公告)号：US20230279779A1
公开(公告)日：2023-09-07
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 , 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：US11300003B2
公开(公告)日：2022-04-12
申请号：US16234892
申请日：2018-12-28
Applicant: General Electric Company
IPC: F01D17/16 , F02K1/46 , B64C11/00 , B64C11/18 , B64C11/46 , F02K3/02 , F02C6/20 , B64C11/48 , F01D9/02
Abstract: An unducted thrust producing system has a rotating element with an axis of rotation and a stationary element. The rotating element includes a plurality of blades, each having a blade root proximal to the axis, a blade tip remote from the axis, and a blade span measured between the blade root and the blade tip. The rotating element has a load distribution such that at any location between the blade root and 30% span the value of ΔRCu in the air stream is greater than or equal to 60% of the peak ΔRCu in the air stream.
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公开(公告)号：US20210239132A1
公开(公告)日：2021-08-05
申请号：US17227529
申请日：2021-04-12
Applicant: General Electric Company
IPC: F04D29/56 , F01D9/04 , F01D5/14 , F01D5/34 , F02K3/06 , F02C3/04 , F04D19/02 , F04D25/04 , F04D29/32 , F04D29/54
Abstract: A variable-cycle compressor includes: an axial-flow compressor, a flowpath downstream of the compressor, and at least one variable-cycle device operable to vary a choked flow capacity of the downstream flowpath. The compressor includes: a rotor having at least one rotor stage including a rotatable disk defining a rotor flowpath surface and an array of axial-flow rotor airfoils extending outward from the flowpath surface; at least one stator stage including a wall defining a stator flowpath surface, and an array of axial-flow stator airfoils extending away from the stator flowpath surface. At least one stage includes splitter airfoils alternating with the rotor or stator airfoils of the corresponding stage. At least one of a chord dimension of the splitter airfoils and a span dimension of the splitter airfoils is less than the corresponding dimension of the airfoils of the at least one stage.
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公开(公告)号：US10822101B2
公开(公告)日：2020-11-03
申请号：US15699349
申请日：2017-09-08
Applicant: General Electric Company
Inventor： Kurt David Murrow , Darek Tomasz Zatorski , Andrew Breeze-Stringfellow , Randy M. Vondrell , Dominic Barone
IPC: B64D27/24 , B64C3/32 , B64C29/00 , B64C3/38 , B64D29/04 , B64D27/08 , B64D35/02 , B64D33/04 , B64D31/06 , B64D27/02 , B64D27/26 , H02K7/18
Abstract: An aircraft includes a fuselage; a wing coupled to, and extending from, the fuselage; and a hybrid-electric propulsion system. The hybrid-electric propulsion system includes a power source including a combustion engine and an electric generator; a plurality of vertical thrust electric fans integrated into the wing and oriented to generate thrust along the vertical direction, the plurality of vertical thrust electric fans arranged along a length of the wing and driven by the power source; and a forward thrust propulsor. The forward thrust propulsor it is selectively or permanently mechanically coupled to the combustion engine.
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Patent Agency Ranking
公开(公告)号：US20200308979A1
公开(公告)日：2020-10-01
申请号：US16900407
申请日：2020-06-12
Applicant: General Electric Company
Inventor： Darek Tomasz Zatorski , Jeffrey Hamel , Andrew Breeze-Stringfellow
IPC: F01D17/16 , B64C11/46 , F02K3/02 , F02C6/20 , F02K1/46 , B64C11/00 , B64C11/18 , B64C11/48 , F01D9/02
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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公开(公告)号：US10737797B2
公开(公告)日：2020-08-11
申请号：US15699315
申请日：2017-09-08
Applicant: General Electric Company
IPC: B64D27/24 , B64C29/00 , B64C3/32 , B64D27/08 , B64D29/04 , B64D35/02 , B64C3/38 , B64D33/04 , B64D31/06 , B64D27/02 , B64D27/26 , H02K7/18
Abstract: An aircraft includes a fuselage; a wing coupled to, and extending from, the fuselage; and a propulsion system. The propulsion system includes a plurality of electric fans integrated into the wing and oriented to generate thrust along a vertical direction, the plurality of electric fans arranged along a length of the wing and including an outer-most electric fan along a transverse direction relative to the fuselage. The outer-most electric fan is at least one of a variable pitch fan or a variable speed fan to provide increased stability to the aircraft.
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公开(公告)号：US10704410B2
公开(公告)日：2020-07-07
申请号：US14438006
申请日：2013-10-23
Applicant: General Electric Company
Inventor： Darek Tomasz Zatorski , Jeffrey Hamel , Andrew Breeze-Stringfellow
IPC: B64C11/00 , F01D17/16 , B64C11/46 , F02K3/02 , F02C6/20 , F02K1/46 , B64C11/18 , B64C11/48 , F01D9/02
Abstract: An unducted thrust producing system has a rotating element with an axis of rotation and a stationary element. The rotating element includes a plurality of blades, and the stationary element has a plurality of vanes configured to impart a change in tangential velocity of the working fluid opposite to that imparted by the rotating element acted upon by the rotating element. The system includes an inlet forward of the rotating element and the stationary element.
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公开(公告)号：US10106265B2
公开(公告)日：2018-10-23
申请号：US15191586
申请日：2016-06-24
Applicant: General Electric Company
Inventor： Jixian Yao , Andrew Breeze-Stringfellow
IPC: B64D27/20 , B64C5/02 , B64C1/26 , B64D27/18 , B64C7/02 , B64C21/00 , B64D27/12 , B64D27/14 , B64D27/26 , B64D33/02
Abstract: An aerodynamic stabilizer assembly for stabilizing an aft fan mounted to a fuselage of an aircraft is presented. The stabilizer assembly includes one or more generally horizontal stabilizers for mounting to a nacelle of the aft fan and the fuselage so as to stabilize the aft fan. Each of the generally horizontal stabilizers includes an inner portion and an outer portion. The inner portions are mounted to a nacelle of the aft fan and the fuselage at a predetermined downward angle with respect to a central axis of the aft fan so as to direct airflow upwards and into the aft fan, the outer portion being mounted to the inner portion.
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公开(公告)号：US20180195527A1
公开(公告)日：2018-07-12
申请号：US15402536
申请日：2017-01-10
Applicant: General Electric Company
Abstract: A containment structure comprising an annular structure configured to provide close tolerance to a rotation structure. The containment structure includes a first abradable structure, a second abradable structure, and a shroud that is defined in part by the first abradable structure and in part by the second abradable structure. An annular surface of the shroud is defined by the first abradable structure and by the second abradable structure. The first abradable structure is harder than the second abradable structure.
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