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

IPC: F01D25/12 ,  F01D9/04 ,  F01D25/04

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.

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

Inventor： Kishore Ramakrishnan ,  Steven B. Morris ,  Nikolai N. Pastouchenko ,  Trevor Howard Wood

IPC: F02K1/48 ,  F01D25/30

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.

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

IPC: F23R3/04 ,  B64C9/24 ,  B64D29/06 ,  F02C7/04 ,  F02K1/34

CPC classification number: F23R3/04 ,  B64D29/06 ,  F02C7/04 ,  B64C9/24 ,  B64D33/06 ,  F05D2220/36

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.

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

IPC: F01D9/04 ,  F01D25/28

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.

公开(公告)号：US11987008B2

公开(公告)日：2024-05-21

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 ,  B22F10/28 ,  B22F10/366 ,  B22F12/45 ,  B28B1/00 ,  B28B17/00 ,  B29C64/153 ,  B29C64/268 ,  B29C64/277 ,  B33Y10/00 ,  B33Y30/00 ,  B33Y50/02 ,  B22F10/80

CPC classification number: B29C64/393 ,  B22F10/28 ,  B22F10/366 ,  B22F12/45 ,  B28B1/001 ,  B28B17/0081 ,  B29C64/153 ,  B29C64/268 ,  B29C64/277 ,  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.

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

IPC: F01D5/18 ,  F01D5/14 ,  F01D9/04 ,  F01D25/04 ,  F02K1/82 ,  G10K11/16 ,  B64D33/02

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.

公开(公告)号：US20240052780A1

公开(公告)日：2024-02-15

申请号：US17819426

申请日：2022-08-12

Applicant: General Electric Company

Inventor： Nikolai Pastouchenko ,  Kishore Ramakrishnan ,  Trevor H. Wood ,  Timothy Richard DePuy

IPC: F02C7/045 ,  F01D25/04

CPC classification number: F02C7/045 ,  F01D25/04 ,  F05D2220/32 ,  F05D2260/96

Abstract: An inlet duct for a nacelle of a ducted fan engine includes an inlet portion at an upstream end of the inlet duct, an acoustic liner arranged downstream of the inlet portion, and a fan section arranged downstream of the acoustic liner. The inlet portion and the acoustic liner are coupled together at an inlet-acoustic liner interface extending circumferentially about the inner surface of the inlet duct, and the acoustic liner and the fan section are coupled together at a fan section hardwall-acoustic liner interface extending circumferentially about the inner surface of the inlet duct. At least one of the acoustic liner, the inlet-acoustic liner interface, and the fan section hardwall-acoustic liner interface having a structure that circumferentially alters a magnitude and a phase of an acoustic wave reflection of the inlet duct to attenuate flutter bite of a fan.

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

IPC: B64D31/06 ,  B64D27/10 ,  B64D27/24

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.

公开(公告)号：US11852161B1

公开(公告)日：2023-12-26

申请号：US18138442

申请日：2023-04-24

Applicant: General Electric Company

Inventor： Jixian Yao ,  Trevor H. Wood ,  Kishore Ramakrishnan ,  William J. Solomon ,  Giridhar Jothiprasad ,  Aaron J. King

IPC: F01D5/14 ,  F04D29/38 ,  F04D19/00

CPC classification number: F04D29/384 ,  F04D19/002

Abstract: A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. The fan includes fan blades that extend radially outwardly toward the annular casing. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.

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

IPC: F02K1/72 ,  F02K1/76

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.