公开(公告)号：US20210108597A1

公开(公告)日：2021-04-15

申请号：US16811368

申请日：2020-03-06

Applicant: General Electric Company

Inventor： David Marion Ostdiek ,  Alan Roy Stuart ,  Daniel Alan Niergarth ,  Gert Johannes van der Merwe ,  Brandon Wayne Miller ,  Stephen William Freund

IPC: F02K3/072 ,  B64D27/10 ,  F02C3/073 ,  F02K3/02 ,  F02K3/075 ,  F02K1/34

Abstract: A propulsion system, the propulsion system comprising a rotating element, a stationary element, and an inlet between the rotating element and the stationary element, wherein the inlet passes radially inward of the stationary element; wherein the inlet passes radially inward of the stationary element; wherein the inlet leads to an inlet duct containing a ducted fan having an axis of rotation and a plurality of blades; and wherein the inlet duct divides into a first duct and a second duct, separate from the first duct. A method of operating a propulsion system, comprising the steps of: operating a first rotating fan assembly to produce a first stream of air; directing a portion of the first stream of air into a second ducted rotating fan assembly; operating the second ducted rotating fan assembly to produce a second stream of air; dividing the second stream of air into a core stream and a fan stream; and directing the core stream into a gas turbine engine core.

公开(公告)号：US20200331622A1

公开(公告)日：2020-10-22

申请号：US16891337

申请日：2020-06-03

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 ,  F02K5/00 ,  F02C7/14 ,  F02C6/20 ,  B64C11/00 ,  B64C21/06 ,  B64D27/10 ,  B64D27/24 ,  F01D15/10 ,  F01D15/12 ,  F02K3/062 ,  F04D29/056 ,  F04D29/063 ,  F04D29/32 ,  F04D29/58

Abstract: A propulsion system for an aircraft having an aft end is provided herein. The propulsion system can include an electric propulsion engine defining a central axis. The electric propulsion engine can include an electric motor, a fan rotatable about the central axis of the electric propulsion engine by the electric motor, a bearing supporting rotation of the fan, and a thermal management system. The thermal management system can include a lubrication oil circulation assembly for providing the bearing with lubrication oil. The lubrication oil circulation assembly can be driven independently of a shaft of the electric propulsion engine.

公开(公告)号：US10804762B2

公开(公告)日：2020-10-13

申请号：US15889619

申请日：2018-02-06

Applicant: General Electric Company

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

IPC: H02K3/42 ,  H02K1/27 ,  H02K1/16 ,  H02K9/22 ,  H02K21/02

Abstract: An axial flux electric machine includes a rotor assembly rotatable about an axis, and a stator assembly. The stator assembly includes a stator face defining an air gap along an axial direction with the rotor assembly, the stator assembly further including a yoke, the yoke including a back surface, the back surface defining an inwardly sloped angle with the radial direction greater than two degrees.

公开(公告)号：US10676205B2

公开(公告)日：2020-06-09

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 ,  F02K5/00 ,  F02C7/14 ,  F02C6/20 ,  B64C11/00 ,  B64C21/06 ,  B64D27/10 ,  B64D27/24 ,  F01D15/10 ,  F01D15/12 ,  F02K3/062 ,  F04D29/056 ,  F04D29/063 ,  F04D29/32 ,  F04D29/58 ,  B64D27/02

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：US10539076B2

公开(公告)日：2020-01-21

申请号：US14937266

申请日：2015-11-10

Applicant: General Electric Company

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

IPC: F02C7/14 ,  F01D25/20 ,  F16N9/02 ,  F01D25/02

Abstract: A self-contained lubrication fluid circulation system for use with a gas turbine engine defining a core air flowpath includes a sump configured to collect lubrication fluid and a heat source coupled in fluid communication with the sump and configured to transfer heat to the lubrication fluid. The system also includes a heat sink positioned within the sump and coupled in fluid communication with the heat source. A lubrication fluid conduit of the system is configured to channel the lubrication fluid between the heat source and the heat sink, wherein the lubrication fluid conduit is positioned entirely within the sump.

公开(公告)号：US20190383564A1

公开(公告)日：2019-12-19

申请号：US16011748

申请日：2018-06-19

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Nicholas Taylor Moore ,  Daniel Alan Niergarth ,  Jeffrey Douglas Rambo ,  Hendrik Pieter Jacobus de Bock ,  William Dwight Gerstler

IPC: F28F1/00 ,  G01M3/32

Abstract: A system for heat exchange and leak detection is generally provided, the system including a heat exchanger including a first wall defining a first passage containing a first fluid. A leak detection enclosure containing a leak detection medium is defined between the first wall and a second wall surrounding the first wall.

公开(公告)号：US10392120B2

公开(公告)日：2019-08-27

申请号：US15132298

申请日：2016-04-19

Applicant: General Electric Company

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

IPC: B64D27/24 ,  B64D27/02 ,  B64D27/18 ,  F02C3/04 ,  F02C7/20 ,  F02C7/36 ,  F02K3/04

Abstract: A propulsion system for an aircraft is provided having a propulsion engine configured to be mounted to the aircraft. The propulsion engine includes an electric machine defining an electric machine tip speed during operation. The propulsion system additionally includes a fan rotatable about a central axis of the electric propulsion engine with the electric machine. The fan defines a fan pressure ratio, RFP, and includes a plurality of fan blades, each fan blade defining a fan blade tip speed. The electric propulsion engine defines a ratio of the fan blade tip speed to electric machine tip speed that is within twenty percent of the equation, 1.68×RFP−0.518, such that the propulsion engine may operate at a desired efficiency.

公开(公告)号：US10392119B2

公开(公告)日：2019-08-27

申请号：US15095249

申请日：2016-04-11

Applicant: General Electric Company

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

IPC: B64D27/24 ,  F04D25/06 ,  F04D19/00 ,  F02K5/00 ,  F04D29/66 ,  B64C21/06 ,  B64D33/02 ,  B64D27/02

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 power gearbox mechanically coupled to an electric motor. The electric propulsion engine further includes a fan rotatable about a central axis of the electric propulsion engine by the electric motor through the power gearbox. Moreover, the electric propulsion engine includes an attachment assembly for mounting at least one of the electric motor or the power gearbox. The attachment assembly includes a torsional damper for accommodating a torsional vibration of the electric motor or the power gearbox.

公开(公告)号：US20190245405A1

公开(公告)日：2019-08-08

申请号：US15889619

申请日：2018-02-06

Applicant: General Electric Company

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

IPC: H02K3/42 ,  H02K1/16 ,  H02K1/27 ,  H02K9/22 ,  H02K21/02

Abstract: An axial flux electric machine includes a rotor assembly rotatable about an axis, and a stator assembly. The stator assembly includes a stator face defining an air gap along an axial direction with the rotor assembly, the stator assembly further including a yoke, the yoke including a back surface, the back surface defining an inwardly sloped angle with the radial direction greater than two degrees.

公开(公告)号：US10374477B2

公开(公告)日：2019-08-06

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 ,  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.