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公开(公告)号：US20240263565A1
公开(公告)日：2024-08-08
申请号：US18618081
申请日：2024-03-27
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Kishore Ramakrishnan
CPC classification number: F01D25/04 , F01D5/141 , F01D5/145 , F01D5/18 , F01D9/041 , F02K1/827 , G10K11/16 , B64D2033/0226 , F05D2240/121 , F05D2250/184 , F05D2260/96 , F05D2260/961
Abstract: An airfoil is provided defining a spanwise direction, a chordwise direction, a root end, a tip end, a leading edge end, and a trailing edge end. The airfoil includes: a leading edge extending from the leading edge end; a body extending along the spanwise direction between the root end and the tip end, the body including a plurality of cavity walls defining a plurality of cavities, each of the plurality of cavities having an inlet located at the leading edge; and a porous face sheet positioned on at least one inlet of the plurality of cavities.
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公开(公告)号：US20240254883A1
公开(公告)日：2024-08-01
申请号：US18161122
申请日：2023-01-30
Applicant: General Electric Company
Inventor： Kishore Ramakrishnan , Nikolai N. Pastouchenko , Trevor Howard Wood , Thomas William Vandeputte
IPC: F01D5/14
CPC classification number: F01D5/142 , F05D2240/121 , F05D2240/122 , F05D2250/713 , F05D2260/96
Abstract: A turbine airfoil is provided. The turbine airfoil defines a chord line, a spanwise direction, a span along the spanwise direction, and a midpoint along the spanwise direction. The turbine airfoil includes a pressure side and a suction side. The pressure side and the suction side intersecting at a leading edge and a trailing edge. The turbine airfoil further includes a root and a tip at opposing ends along the spanwise direction. In addition, the turbine airfoil defines a leading edge reference line extending from where the leading edge meets the root to where the leading edge meets the tip and a trailing edge reference line extending from where the trailing edge meets the root to where the trailing edge meets the tip. The turbine airfoil includes a lobe positioned at the leading edge or the trailing edge and defines a maximum axially height relative to the leading edge reference line or the trailing edge reference line. The maximum axial height being equal to at least five percent of the chord line of the turbine airfoil.
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公开(公告)号：US20240240571A1
公开(公告)日：2024-07-18
申请号：US18155118
申请日：2023-01-17
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Kishore Ramakrishnan , William Dwight Gerstler , Changjie Sun , Lana Maria Osusky
CPC classification number: F01D25/12 , F01D9/041 , F01D25/04 , F05D2220/32 , F05D2240/12 , F05D2260/202 , F05D2260/96
Abstract: Airfoil include a body extending along a spanwise direction between a root end and a tip end, the body comprising a plurality of acoustic cavities each having an inlet on the airfoil; and at least one cooling channel having an inlet section an outlet section and a middle section within the airfoil extending between the inlet section and the outlet section; and at least one porous face sheet positioned on at least one inlet of the plurality of acoustic cavities.
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公开(公告)号：US20240229741A1
公开(公告)日：2024-07-11
申请号：US18428254
申请日：2024-01-31
Applicant: General Electric Company
CPC classification number: F02K1/48 , F01D25/30 , F05D2220/323 , F05D2240/128 , F05D2260/96
Abstract: An exhaust nozzle for a gas turbine engine. The exhaust nozzle comprises a nozzle body having an upstream end axially spaced from a downstream end with respect to an axial centerline of the nozzle body, and a plurality of chevrons circumferentially spaced apart and extending downstream from the downstream end. Each chevron includes an inner wall radially spaced from an outer wall, a root and a tip axially spaced from the root. At least one chevron of the plurality of chevrons includes a first segment extending axially downstream from the root, a second segment extending axially downstream from the first segment, and a third segment extending axially downstream from the second segment to the tip. The inner wall extends along the first segment, the second segment, and third the segment. The first segment is distinguishable from the second segment and the second segment is distinguishable from the third segment.
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公开(公告)号：US12018838B2
公开(公告)日：2024-06-25
申请号：US17845472
申请日：2022-06-21
Applicant: General Electric Company
Inventor： Kishore Ramakrishnan , Trevor Howard Wood
Abstract: An aerodynamic device defining a thickness direction is provided. The aerodynamic device configured to produce lift or thrust or configured to be a part of an aerodynamic system that produces lift or thrust. The aerodynamic device includes a cowl assembly that defines at least in part an airflow stream. The cowl assembly includes a first cowl and a second cowl moveable relative to the first cowl. The first cowl includes a plurality of first cowl indentations at an end of the first cowl. The second cowl defines an outer surface along the thickness direction and an inner surface along the radial direction. The second cowl includes a plurality of second cowl indentations complementary in shape to the plurality of first cowl indentations. The plurality of second cowl indentations are positioned locally on the outer surface of the second cowl or locally on the inner surface of the second cowl.
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Patent Agency Ranking
公开(公告)号：US12018592B1
公开(公告)日：2024-06-25
申请号：US18086112
申请日：2022-12-21
Applicant: General Electric Company
Inventor： Kishore Ramakrishnan , Ravish Karve , Sara Elizabeth Carle , Trevor Howard Wood
CPC classification number: F01D9/041 , F01D25/28 , F05D2220/323 , F05D2250/37 , F05D2260/961
Abstract: A turbofan engine defining a circumferential direction is provided. The turbofan engine includes: a turbomachine, the turbomachine defining a pylon attachment location along the circumferential direction; an unducted rotor assembly drivingly coupled to the turbomachine, the unducted rotor assembly including a plurality of unducted rotor blades; and a plurality of outlet guide vanes positioned downstream of the plurality of unducted rotor blades, the plurality of outlet guide vanes including NOGV number of outlet guide vanes, the plurality of outlet guide vanes including a first outlet guide vane and a second outlet guide vane adjacent the first outlet guide vane, the first and second outlet guide vanes defining a gap spacing greater than 360 degrees divided by NOGV, and the pylon attachment location positioned outside of between the first and second outlet guide vanes along the circumferential direction.
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公开(公告)号：US12000359B2
公开(公告)日：2024-06-04
申请号：US17890572
申请日：2022-08-18
Applicant: General Electric Company
Inventor： Bugra Han Ertas , Trevor Howard Wood
CPC classification number: F02K1/763 , F02K1/72 , F05D2220/323 , F05D2260/50
Abstract: A cascade thrust reverser assembly is provided for a turbofan engine. The turbofan engine includes a nacelle assembly defining a bypass passage, and the cascade thrust reverser assembly includes at least one cascade assembly configured to be at least partially enclosed by the nacelle assembly. The cascade assembly may further include a plurality of cascade segments and an actuation assembly operably connected to the plurality of cascade segments, wherein the actuation assembly is configured to increase an axial extent of the cascade assembly and rotate the plurality of cascade segments.
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公开(公告)号：US11965425B2
公开(公告)日：2024-04-23
申请号：US17828112
申请日：2022-05-31
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Kishore Ramakrishnan
CPC classification number: F01D25/04 , F01D5/141 , F01D5/145 , F01D5/18 , F01D9/041 , F02K1/827 , G10K11/16 , B64D2033/0226 , F05D2240/121 , F05D2250/184 , F05D2260/96 , F05D2260/961
Abstract: An airfoil is provided defining a spanwise direction, a chordwise direction, a root end, a tip end, a leading edge end, and a trailing edge end. The airfoil includes: a leading edge extending from the leading edge end; a body extending along the spanwise direction between the root end and the tip end, the body including a plurality of cavity walls defining a plurality of cavities, each of the plurality of cavities having an inlet located at the leading edge; and a porous face sheet positioned on at least one inlet of the plurality of cavities.
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公开(公告)号：US20240051673A1
公开(公告)日：2024-02-15
申请号：US17887872
申请日：2022-08-15
Applicant: General Electric Company
Inventor： Kishore Ramakrishnan , Trevor Howard Wood , Harry Kirk Mathews, JR. , Eric Richard Westervelt , Honggang Wang , Timothy Richard DePuy
CPC classification number: B64D31/06 , B64D27/10 , B64D27/24 , B64D2027/026
Abstract: An aircraft engine includes a low pressure spool, a high pressure spool, and an alternative power source. The alternative power source is configured to add power to the high pressure spool. A controller is configured to determine a noise sensitive condition; and control, in response to determining the noise sensitive condition, the alternative power source to add power to the high pressure spool.
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公开(公告)号：US11840987B2
公开(公告)日：2023-12-12
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 , F05D2240/129 , F05D2240/14 , F05D2260/606
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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