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公开(公告)号：US11808161B2
公开(公告)日：2023-11-07
申请号：US17717387
申请日：2022-04-11
Applicant: General Electric Company
Inventor： Jixian Yao , Kishore Ramakrishnan , Trevor Howard Wood , Mustafa Dindar
CPC classification number: F01D25/24 , B64C21/02 , B64C21/06 , F05D2220/323 , F05D2240/14 , F05D2260/60
Abstract: A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; and a nacelle that circumferentially surrounds the fan, the nacelle comprising an annular wall having an exterior surface and an interior surface, the exterior surface comprising a first exterior portion, and the interior surface comprising a first interior portion, wherein a first exterior portion is formed of a first structure defining an exterior surface porosity, and wherein a first interior portion is formed of a second structure defining an interior surface porosity.
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公开(公告)号：US20230323791A1
公开(公告)日：2023-10-12
申请号：US17717387
申请日：2022-04-11
Applicant: General Electric Company
Inventor： Jixian Yao , Kishore Ramakrishnan , Trevor Howard Wood , Mustafa Dindar
CPC classification number: F01D25/24 , B64C21/06 , F05D2220/323 , F05D2240/14 , F05D2260/60
Abstract: A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; and a nacelle that circumferentially surrounds the fan, the nacelle comprising an annular wall having an exterior surface and an interior surface, the exterior surface comprising a first exterior portion, and the interior surface comprising a first interior portion, wherein a first exterior portion is formed of a first structure defining an exterior surface porosity, and wherein a first interior portion is formed of a second structure defining an interior surface porosity.
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公开(公告)号：US20230313754A1
公开(公告)日：2023-10-05
申请号：US17713597
申请日：2022-04-05
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Kishore Ramakrishnan , Justin John Gambone, JR. , Darren Lee Hallman , Thomas Malkus , Jixian Yao , Keith Edward James Blodgett
CPC classification number: F02K1/72 , F02K1/766 , F05D2220/323 , F05D2240/14 , F05D2260/606 , F05D2240/129
Abstract: A cascade thrust reverser assembly for a gas turbine engine includes a nacelle assembly defining a bypass passage. The cascade thrust reverser assembly includes a cascade assembly configured to be at least partially enclosed by the nacelle assembly, the cascade assembly comprising one or more cascade members, the one or more cascade members movable between a stowed configuration wherein the one or more cascade members define a first radial extent and a deployed configuration wherein the one or more cascade members define a second radial extent, wherein the one or more cascade members form a cascade segment in the deployed configuration, and wherein the second radial extent is greater than the first radial extent.
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114.发明公开公开(公告)号：US20230219298A1
公开(公告)日：2023-07-13
申请号：US17573068
申请日：2022-01-11
Applicant: General Electric Company , Concept Laser GmbH , GE Additive Germany GmbH
Inventor： Benedikt Roidl , Kishore Ramakrishnan , Changjin Yoon , Andrey I. Meshkov , Peter Pontiller-Schymura
IPC: B29C64/393 , B29C64/153 , B29C64/268 , B29C64/277 , B22F10/28 , B22F10/366 , B22F12/45 , B28B1/00 , B28B17/00 , B33Y10/00 , B33Y30/00 , B33Y50/02
CPC classification number: B29C64/393 , B29C64/153 , B29C64/268 , B29C64/277 , B22F10/28 , B22F10/366 , B22F12/45 , B28B1/001 , B28B17/0081 , B33Y10/00 , B33Y30/00 , B33Y50/02
Abstract: A method of additively manufacturing a three-dimensional object may be performed using an irradiation sequence that is based at least in part on a predicted location of one or more fume plumes emitted from the powder material when irradiated by a plurality of energy beams. An exemplary method may include determining, with a computing device, an irradiation sequence for selectively consolidating powder material using an energy beam system of an additive manufacturing machine, and providing control commands, from the computing device to the energy beam system, configured to cause the energy beam system to emit a plurality of energy beams to selectively consolidate the powder material.
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公开(公告)号：US20230150681A1
公开(公告)日：2023-05-18
申请号：US17526383
申请日：2021-11-15
Applicant: General Electric Company
Inventor： Kishore Ramakrishnan , Trevor Howard Wood , Stefan Joseph Cafaro , Robert Jon McQuiston , David Marion Ostdiek , Timothy Richard DePuy , Trevor Goerig , Eric Richard Westervelt
CPC classification number: B64D31/06 , B64D27/12 , B64C2220/00
Abstract: Systems and methods for controlling an unducted turbofan engine to limit noise. The unducted turbofan engine may include an unducted fan drivingly coupled with a low-pressure turbine and a plurality of unducted outlet guide vanes. The unducted fan may include a plurality of fan blades and a pitch angle of the fan blades may be variable. A pitch angle of the unducted outlet guide vanes may be variable. A controller is configured to control the engine to limit noise based on a noise sensitive condition.
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Patent Agency Ranking
公开(公告)号：US11649834B2
公开(公告)日：2023-05-16
申请号：US17582931
申请日：2022-01-24
Applicant: General Electric Company
Inventor： Trevor Wood , Kishore Ramakrishnan
CPC classification number: F04D29/544 , F01D9/042 , F04D29/667 , F02C3/04 , F05D2220/323 , F05D2230/80 , F05D2240/121 , F05D2240/122 , F05D2260/96
Abstract: Disclosed examples include a retrofit fan frame assembly, comprising: a leading edge adjustment component coupleable to an airfoil, the leading edge adjustment component of variable chord length, the variable chord length to increase and then decrease along a radial length from a hub end of the airfoil to an opposite tip end of the airfoil; and an attachment mechanism configured to couple the leading edge adjustment component to a leading edge of the airfoil.
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公开(公告)号：US20220389882A1
公开(公告)日：2022-12-08
申请号：US17338073
申请日：2021-06-03
Applicant: General Electric Company
Inventor： Wendy Wenling Lin , David Herman , Trevor Howard Wood , Nikolai N. Pastouchenko , Kishore Ramakrishnan , Timothy Richard DePuy , Robert William Davidoff
IPC: F02K1/82 , G10K11/172 , F03D80/00 , G10K11/16
Abstract: An acoustic core may include an array of resonant cells configured as a plurality of resonant cell groups. The resonant cell groups may include a plurality of resonant cells configured as a partitioned resonant cell that include a converging resonant cell and a diverging resonant cell. The converging resonant cell and the diverging resonant cell may be defined by a plurality of cell walls integrally formed with one another and a partition integrally formed with the plurality of cell walls. The partition may at least partially delimit the converging resonant cell from the diverging resonant cell. The converging resonant cell may define an upper resonant space delimited by the partition and a top face of the array of resonant cells. The diverging resonant cell may define a lower resonant space delimited by the partition and a bottom face of the array of resonant cells.
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公开(公告)号：US11485481B2
公开(公告)日：2022-11-01
申请号：US16279244
申请日：2019-02-19
Applicant: General Electric Company
Abstract: An aircraft includes a fuselage extending between a forward end and an aft end; a propulsor mounted to the fuselage at the aft end of the fuselage, the propulsor comprising an outer nacelle, the outer nacelle defining an inlet to the propulsor; and a deployable assembly attached to at least one of the fuselage or the outer nacelle and moveable between a stowed position and an engaged position. The deployable assembly alters an airflow towards the propulsor or into the propulsor through the inlet defined by the outer nacelle when in the engaged position. The propulsor further comprises a tail cone, wherein the outer nacelle defines an exhaust with the tail cone, and wherein the plurality of nacelle panels are movable generally along the axial centerline to a position at least partially aft of the exhaust of the outer nacelle when in the engaged position.
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公开(公告)号：US11136109B2
公开(公告)日：2021-10-05
申请号：US16550868
申请日：2019-08-26
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Trevor Howard Wood , Kishore Ramakrishnan
Abstract: In some embodiments, an airfoil comprises a proximal end; a distal end opposite said proximal end; a distal portion extending adjacent said distal end; an edge extending between said proximal end and said distal end; and a surface extending between said proximal end and said distal end, said edge and said surface defining a sweep and a cahedral through said distal portion, wherein the distal portion extends over an acoustically active portion of the airfoil.
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公开(公告)号：US11105340B2
公开(公告)日：2021-08-31
申请号：US15241137
申请日：2016-08-19
Applicant: General Electric Company
Inventor： Lawrence Chih-hui Cheung , Nikolai N. Pastouchenko , Kishore Ramakrishnan , Brandon Wayne Miller
IPC: F04D29/58 , B64D27/24 , B64D33/08 , B64C21/06 , F04D25/06 , H02K7/18 , H02K9/19 , H02K7/14 , F04D25/02 , B64D33/10 , B64D27/20 , B64D29/04 , B64D33/02 , B64D27/02
Abstract: A propulsion system for an aircraft includes an electric propulsion engine configured to be mounted at an aft end of the aircraft. The electric propulsion engine includes an electric motor and a fan rotatable about a central axis, the fan driven by the electric motor. The electric propulsion system additionally includes a cooling system operable with an airflow over the aft end the aircraft when the electric propulsion system is mounted to the aircraft. The cooling system is configured to cool the electric motor during operation of the electric propulsion engine.
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