公开(公告)号：US20190252929A1

公开(公告)日：2019-08-15

申请号：US15892962

申请日：2018-02-09

Applicant: General Electric Company

Inventor： Nicholas Taylor Moore ,  Daniel Alan Niergarth ,  Paul Robert Gemin ,  Arthur Vorwerk Radun ,  Hao Huang

IPC: H02K1/16 ,  H02K1/27 ,  H02K21/24 ,  H02K15/02

CPC classification number: H02K1/165 ,  H02K1/2793 ,  H02K15/024 ,  H02K21/24 ,  H02K2201/03

Abstract: An electric machine includes a stator assembly including a first stator segment and a second stator segment, the first and second stator segments each including a plurality of laminations extending generally along a circumferential direction, each pair of adjacent laminations of the first and second stator segments defining a gap therebetween. The first and second stator segments are assembled together such that the laminations of the first stator segment are arranged at least partially in the gaps between the laminations of the second stator segment.

公开(公告)号：US20190203644A1

公开(公告)日：2019-07-04

申请号：US15861802

申请日：2018-01-04

Applicant: General Electric Company

Inventor： Daniel Alan Niergarth ,  Brandon Wayne Miller ,  Raymond Floyd Martell ,  Jeffrey Douglas Rambo ,  Ryan James Matthys ,  Joel Francis Kirk

IPC: F02C7/143 ,  F02C7/18 ,  F01D5/08 ,  F02C3/06 ,  F23R3/28 ,  F01D9/06

CPC classification number: F02C7/143 ,  F01D5/085 ,  F01D9/065 ,  F01D25/12 ,  F02C3/06 ,  F02C7/12 ,  F02C7/185 ,  F02C7/22 ,  F05D2220/3216 ,  F05D2240/12 ,  F05D2260/201 ,  F05D2260/213 ,  F23R3/283

Abstract: A gas turbine engine includes a turbomachine including a compressor section, a combustion section, a turbine section, and an exhaust section arranged in serial flow order and together defining at least in part a core air flowpath. The gas turbine engine also includes a thermal management system including a flowpath heat exchanger coupled to, or integrated into, one or more components of the compressor section, the combustion section, the turbine section, or the exhaust section such that the flowpath heat exchanger is directly thermally coupled to an airflow through the core air flowpath.

公开(公告)号：US10100736B2

公开(公告)日：2018-10-16

申请号：US14927536

申请日：2015-10-30

Applicant: General Electric Company

Inventor： Daniel Alan Niergarth ,  Brandon Wayne Miller ,  Christopher James Kroger

IPC: F02C7/14 ,  F02C7/10 ,  F01D25/18

Abstract: A gas turbine engine includes a compressor section in series flow with a turbine section. The compressor section includes one or more compressors and the turbine section includes one or more turbines, the compressor section and turbine section together defining a core air flowpath. A sump is positioned inward of the core air flowpath for containing and collecting lubrication oil. Additionally, a heat exchanger is positioned in direct thermal communication with the sump for removing heat from lubrication oil contained therein to reduce a size and/or amount of heat exchangers located radially outward of the core air flowpath.

公开(公告)号：US10072510B2

公开(公告)日：2018-09-11

申请号：US14873382

申请日：2015-10-02

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Ian Francis Prentice ,  Daniel Alan Niergarth

IPC: F01D7/00 ,  F01D25/24 ,  F01D9/04 ,  F01D17/10 ,  F02C3/04 ,  F01D5/02 ,  F01D7/02 ,  F04D29/32

CPC classification number: F01D7/00 ,  F01D5/02 ,  F01D7/02 ,  F01D9/041 ,  F01D17/105 ,  F01D25/24 ,  F02C3/04 ,  F04D29/323 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/35 ,  F05D2260/71 ,  F05D2260/74

Abstract: A gas turbine engine is provided. The gas turbine engine includes a core and a variable pitch fan arranged in flow communication with the core. The variable pitch fan has a disk and at least nine fan blades coupled to the disk for rotation together with the disk. The gas turbine engine further includes a rotatable nacelle covering the disk such that the engine has a fan hub radius ratio of between about 0.1 and about 0.4.

公开(公告)号：US20180138767A1

公开(公告)日：2018-05-17

申请号：US15354422

申请日：2016-11-17

Applicant: General Electric Company

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

IPC: H02K1/27 ,  H02K1/16 ,  H02K7/14 ,  H02K7/18 ,  B64D27/18

Abstract: An electric machine is provided which includes a rotor disk extending along a radial direction and a having a rotor magnet embedded within the rotor disk. The electric machine further includes a stator assembly in axial or radial magnetic flux communication with the rotor magnets to generate a torque.

公开(公告)号：US20180138761A1

公开(公告)日：2018-05-17

申请号：US15354323

申请日：2016-11-17

Applicant: General Electric Company

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

IPC: H02K1/18 ,  H02K1/27

CPC classification number: H02K1/187 ,  H02K1/2786 ,  H02K16/00 ,  H02K21/22 ,  H02K2201/03 ,  H02K2213/09

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 positioned against the rotor flange. The electric machine includes a stator assembly including a tracking tooth in magnetic flux communication with the rotor magnets across an air gap. The stator assembly further includes an actuator operable with the tracking tooth to move the tracking tooth along the radial direction to adjust a height of the air gap.

公开(公告)号：US09932858B2

公开(公告)日：2018-04-03

申请号：US14809560

申请日：2015-07-27

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Richard Schmidt ,  Daniel Alan Niergarth

IPC: F01D25/16 ,  F02C7/32 ,  F01D25/20 ,  F01D25/18 ,  F01D9/06

CPC classification number: F01D25/164 ,  F01D9/065 ,  F01D25/162 ,  F01D25/18 ,  F01D25/20 ,  F02C7/32 ,  F05D2260/98 ,  Y02T50/671

Abstract: A gas turbine engine is provided including a shaft coupling a compressor of a compressor section to a turbine of a turbine section. An aft bearing assembly, including at least two bearings, is positioned at least partially in an aft sump and supports the shaft within the turbine section. The aft sump is configured to receive lubrication oil from a lubrication oil supply extending through at least a portion of a turbine center frame of the turbine section, and provide such lubrication to the at least two bearings of the aft bearing assembly.

公开(公告)号：US20180050810A1

公开(公告)日：2018-02-22

申请号：US15241157

申请日：2016-08-19

Applicant: General Electric Company

Inventor： Daniel Alan Niergarth ,  Randy M. Vondrell ,  Brandon Wayne Miller ,  Patrick Michael Marrinan ,  Lawrence Chih-hui Cheung ,  Nikolai N. Pastouchenko

IPC: B64D33/08 ,  B64C21/06 ,  B64D27/10 ,  B64D27/24 ,  F01D15/10 ,  F01D15/12 ,  F02K3/062 ,  F04D29/32 ,  F04D29/056 ,  F04D29/063 ,  F04D29/58

Abstract: A propulsion system for an aircraft includes an electric propulsion engine. The electric propulsion engine includes an electric motor and a fan rotatable about a central axis of the electric propulsion engine by the electric motor. The electric propulsion engine also includes a bearing supporting rotation of the fan and a thermal management system. The thermal management system includes a lubrication oil circulation assembly and a heat exchanger thermally connected to the lubrication oil circulation assembly. The lubrication oil circulation assembly is configured for providing the bearing with lubrication oil. Such an electric propulsion engine may be a relatively self-sufficient engine.

公开(公告)号：US09869190B2

公开(公告)日：2018-01-16

申请号：US14708353

申请日：2015-05-11

Applicant: General Electric Company

Inventor： Daniel Alan Niergarth ,  Brandon Wayne Miller ,  Donald Albert Bradley

IPC: F02C3/04 ,  F01D7/02 ,  F01D21/08 ,  F01D5/02

CPC classification number: F01D7/02 ,  F01D5/02 ,  F01D21/08 ,  F02C3/04 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/30 ,  F05D2260/53 ,  F05D2260/77 ,  F05D2260/79 ,  F05D2270/021 ,  F05D2270/09 ,  F05D2270/58 ,  Y02T50/673

Abstract: A pitch control mechanism includes: a rotor structure configured for rotation about a longitudinal axis; a row of blades carried by the rotor structure, each blade having an airfoil and a trunnion mounted for pivoting movement relative to the rotor structure, about a trunnion axis which is perpendicular to the longitudinal axis; a unison ring interconnecting the blades; an actuator connected to the unison ring and the rotor structure, operable to move the unison ring relative to the rotor structure; at least one moveable counterweight carried by the rotor structure, remote from the blades; and an interconnection between the blades and the counterweight, such that movement of the counterweight causes a change in the pitch angle of the blades.

公开(公告)号：US20170291693A1

公开(公告)日：2017-10-12

申请号：US15095262

申请日：2016-04-11

Applicant: General Electric Company

Inventor： Daniel Alan Niergarth ,  Randy M. Vondrell ,  Brandon Wayne Miller ,  Patrick Michael Marrinan

IPC: B64C21/06 ,  B64D27/24 ,  F02K5/00 ,  B64D27/18

CPC classification number: B64C21/06 ,  B64C2230/04 ,  B64D27/24 ,  B64D33/02 ,  B64D2027/026 ,  B64D2033/0226 ,  F02K5/00 ,  Y02T50/166 ,  Y02T50/62

Abstract: A propulsion system for an aircraft includes an electric propulsion engine configured to be mounted to the aircraft at an aft end of the aircraft. The electric propulsion engine includes a fan rotatable about a central axis of the electric propulsion engine. The fan includes a fan shaft mechanically coupled to a power gearbox. The electric propulsion engine also includes an electric motor having a driveshaft, with the electric motor coupled to the power gearbox through the drive shaft. The electric motor rotates the fan through the power gearbox. The driveshaft includes a flexible element for accommodating a misalignment of the electric motor and the power gearbox.