公开(公告)号：US20200079513A1

公开(公告)日：2020-03-12

申请号：US16126269

申请日：2018-09-10

Applicant: General Electric Company

Inventor： Nikolai N. Pastouchenko ,  Randy M. Vondrell ,  Kurt David Murrow ,  Jixian Yao ,  Brandon Wayne Miller ,  Patrick Michael Marrinan ,  Daniel Alan Niergarth ,  Narendra Digamber Joshi

IPC: B64D27/02 ,  B64D27/12 ,  B64D27/24 ,  F02K5/00 ,  F01D9/02 ,  F02K1/18 ,  F02C6/14

Abstract: A method for operating an electric fan of an aircraft propulsion system includes driving a plurality of fan blades of the electric fan with an electric machine to generate thrust for the aircraft; and driving the electric machine with the plurality of fan blades of the electric fan to generate electrical power subsequent to driving the plurality of fan blades of the electric fan with the electric machine to generate thrust for the aircraft.

公开(公告)号：US10533436B2

公开(公告)日：2020-01-14

申请号：US14932661

申请日：2015-11-04

Applicant: General Electric Company

Inventor： Daniel Alan Niergarth ,  Brandon Wayne Miller ,  Darek Tomasz Zatorski

IPC: F01D7/00 ,  F01D5/12 ,  F01D5/02 ,  F01D15/00

Abstract: A method and system for controlling a pitch of blades of a fan assembly having a centerline axis of rotation is provided. The system includes a pitch change mechanism (PCM) including a hydraulic actuator positioned axisymmetric with respect to the fan assembly and configured to angularly displace the blades of the fan assembly between a first position and a second position. The PCM further includes a plurality of hydraulic fluid supply lines coupled in flow communication between the hydraulic actuator and a hydraulic fluid transfer sleeve, the hydraulic fluid transfer sleeve configured to transfer a flow of pressurized hydraulic fluid across a gap between a stationary member of the hydraulic fluid transfer sleeve and a rotatable member of the hydraulic fluid transfer sleeve.

公开(公告)号：US20190257247A1

公开(公告)日：2019-08-22

申请号：US15899831

申请日：2018-02-20

Applicant: General Electric Company

Inventor： Kishanjit Pal ,  Arnab Sen ,  Pranav R. Kamat ,  Brandon Wayne Miller ,  Daniel Alan Niergarth

IPC: F02C7/18 ,  F02C3/04 ,  F02C9/18

Abstract: A method of operating a thermal management system for a gas turbine engine includes determining the gas turbine engine is in a first operating mode; transferring heat from a first heat source exchanger to a heat sink system in response to determining the gas turbine engine is in the first operation mode, the first heat source exchanger thermally coupled to a first system/component of the gas turbine engine; determining the gas turbine engine is in a second operating mode, the second operating mode being different than the first operating mode; and transferring heat from a second heat source exchanger to the heat sink system in response to determining the gas turbine engine is in the second operation mode, the second heat source exchanger thermally coupled to a second system/component of the gas turbine engine, the second system/component being different than the first system/component.

公开(公告)号：US20190249599A1

公开(公告)日：2019-08-15

申请号：US15895336

申请日：2018-02-13

Applicant: General Electric Company

Inventor： Arnab Sen ,  Brandon Wayne Miller ,  Bhaskar Nanda Mondal ,  Kishanjit Pal ,  Daniel Alan Niergarth

IPC: F02C6/18 ,  F02C3/04 ,  F02C7/18 ,  F02K3/02

CPC classification number: F02C6/18 ,  F02C3/04 ,  F02C7/18 ,  F02K3/02 ,  F05D2210/20 ,  F05D2220/323 ,  F05D2220/62 ,  F05D2220/76 ,  F05D2260/213

Abstract: An aeronautical gas turbine engine includes a turbomachine including a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order. The aeronautical gas turbine engine additionally includes a closed cycle heat engine including a compressor configured to compress a working fluid; a primary heat exchanger in thermal communication with the turbomachine and the working fluid, the primary heat exchanger configured to transfer heat from the turbomachine to the working fluid; an expander coupled to the compressor for expanding the working fluid; and an output shaft driven by the expander.

公开(公告)号：US20190217963A1

公开(公告)日：2019-07-18

申请号：US16366453

申请日：2019-03-27

Applicant: General Electric Company

Inventor： Thomas Kupiszewski ,  Brandon Wayne Miller ,  Daniel Alan Niergarth ,  Randy M. Vondrell

IPC: B64D27/24 ,  F02C7/32 ,  F02K3/06 ,  F04D19/02 ,  B64D27/12 ,  H02K1/27 ,  F04D25/06 ,  F02K5/00 ,  F01D25/18 ,  F01D15/10 ,  F02C7/24 ,  H02K7/18

CPC classification number: B64D27/24 ,  B64D27/12 ,  B64D2027/026 ,  F01D15/10 ,  F01D25/183 ,  F02C7/24 ,  F02C7/32 ,  F02K3/06 ,  F02K5/00 ,  F04D19/02 ,  F04D25/06 ,  F05D2220/323 ,  F05D2220/768 ,  F05D2260/98 ,  H02K1/27 ,  H02K7/1823

Abstract: A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. A cavity wall defines at least in part a buffer cavity surrounding at least a portion of the electric machine to thermally insulate the electric machine, e.g., from the relatively high temperatures within the core air flowpath.

公开(公告)号：US10316856B2

公开(公告)日：2019-06-11

申请号：US14955327

申请日：2015-12-01

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Andrew Michael Tompkins ,  Daniel Alan Niergarth

IPC: F02C7/06 ,  F01D9/06 ,  F04D29/063 ,  F04D25/04 ,  F04D29/52 ,  F01D25/18 ,  F16N31/00 ,  F02K3/06 ,  F01M1/12

Abstract: A casing for use in a turbofan engine is provided. The casing includes an inner hub including a first fluid opening defined at bottom dead center of the casing. The casing also includes an intermediate casing positioned radially outward from the inner hub, an outer casing positioned radially outward from the intermediate casing, and struts spaced circumferentially about the inner hub and extending between the inner hub and the outer casing. The struts include a first strut and a second strut positioned on opposing sides of bottom dead center of the casing such that a first fluid sump is defined between the inner hub, the intermediate casing, and the first and second struts. At least one of said first and second struts includes a flow channel extending therethrough such that a fluid flow path is defined from the first fluid opening, through the first fluid sump, and through the flow channel.

公开(公告)号：US10221706B2

公开(公告)日：2019-03-05

申请号：US14943059

申请日：2015-11-17

Applicant: General Electric Company

Inventor： Daniel Alan Niergarth ,  Darek Tomasz Zatorski ,  Brandon Wayne Miller

IPC: F01D7/00 ,  B64C11/32 ,  F02C7/32 ,  F01D17/12 ,  F01D7/02 ,  F02C9/58 ,  F02C3/10 ,  F02C7/04 ,  F02K3/06

Abstract: A gas turbine engine including a core having in serial flow order a compressor, a combustor, and a turbine—the compressor, combustor, and turbine together defining a core air flowpath. The gas turbine engine additionally includes a fan section mechanically coupled to the core, the fan section including a plurality of fan blades, and each of the plurality fan blades defining a pitch axis. An actuation device is operable with the plurality fan blades for rotating the plurality fan blades about their respective pitch axes, the actuation device including an actuator located outward of the core air flowpath to, e.g., simplify the gas turbine engine.

公开(公告)号：US10113633B2

公开(公告)日：2018-10-30

申请号：US15008907

申请日：2016-01-28

Applicant: General Electric Company

Inventor： Daniel Alan Niergarth ,  Brandon Wayne Miller ,  Bugra Han Ertas ,  Donald Albert Bradley ,  Joseph Robert Dickman

IPC: F16H57/00 ,  F02C7/36 ,  F16H57/08 ,  F16H57/04 ,  F16C27/04

Abstract: An epicyclic gearing arrangement includes a planet gear rotatable on a planet bearing that is mounted via a support pin to a carrier of the epicyclic gearing arrangement. A spring film damper is disposed between the cylindrical outer surface of the support pin and the opposing inner surface of the inner ring of the planet bearing and includes an annular gap.

公开(公告)号：US20180269737A1

公开(公告)日：2018-09-20

申请号：US15461654

申请日：2017-03-17

Applicant: General Electric Company

Inventor： Daniel Alan Niergarth ,  Darek Tomasz Zatorski ,  David William Crall

IPC: H02K1/30 ,  F01D15/10 ,  F01D1/00 ,  F04D19/00 ,  H02K7/18 ,  H02K1/27

CPC classification number: H02K1/30 ,  F01D1/00 ,  F01D15/10 ,  F04D19/002 ,  F05D2220/32 ,  H02K1/2793 ,  H02K7/1823 ,  H02K21/24

Abstract: The present disclosure is directed to an electric machine defining a longitudinal direction, a radial direction, and a circumferential direction, and an axial centerline defined along the longitudinal direction. The electric machine includes a rotor assembly that includes a plurality of carriers arranged along the circumferential direction. Each pair of carriers defines a carrier gap therebetween along the circumferential direction, and each carrier includes a rotor magnet. The rotor assembly further includes an outer ring radially outward of and surrounding the plurality of carriers along the circumferential direction, the outer ring defining a unitary structure.

公开(公告)号：US20180138766A1

公开(公告)日：2018-05-17

申请号：US15354370

申请日：2016-11-17

Applicant: General Electric Company

Inventor： Nicholas Taylor Moore ,  Daniel Alan Niergarth ,  Brandon Wayne Miller ,  Paul Robert Gemin

IPC: H02K1/27 ,  H02K1/18

Abstract: An electric machine is provided which includes a rotor disk extending along a radial direction and having a rotor flange attached to or formed integrally with the rotor disk and extending substantially along the axial direction. A plurality of rotor magnets are mounted on the rotor disk and supported by the rotor flange such that the rotor flange absorbs centrifugal loads exerted on the magnets and enables high speeds of operation.