公开(公告)号：US20220289394A1

公开(公告)日：2022-09-15

申请号：US17571752

申请日：2022-01-10

Applicant: General Electric Company

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

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

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：US20220252008A1

公开(公告)日：2022-08-11

申请号：US17170116

申请日：2021-02-08

Applicant: General Electric Company

Inventor： Arthur William Sibbach ,  Brandon Wayne Miller ,  David Marion Ostdiek

IPC: F02C6/20 ,  F02C3/06

Abstract: Propulsion systems and methods of operation are provided. An exemplary propulsion system comprises a rotating element; a stationary element; an inlet duct having an inlet between the rotating and stationary elements, the inlet passing radially inward of the stationary element; a ducted fan disposed in the inlet duct downstream of the inlet and having an axis of rotation and a plurality of blades; a gas turbine engine core having a high pressure compressor, a combustor, and a high pressure turbine in serial relationship; and a booster compressor disposed between the ducted fan and the gas turbine engine core. At least one of the ducted fan and the booster compressor is driven by a variable speed power source such that the rotational speed of the ducted fan and/or booster compressor is controllable independently from the rotational speed of any rotor of the propulsion system.

公开(公告)号：US11300365B2

公开(公告)日：2022-04-12

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：US11225975B2

公开(公告)日：2022-01-18

申请号：US16503929

申请日：2019-07-05

Applicant: General Electric Company

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

IPC: F04D29/32 ,  F01D25/16 ,  F04D29/26 ,  F02C7/06

Abstract: A gas turbine engine includes a core turbine engine and a fan mechanically coupled to the core turbine engine. The fan includes a plurality of fan blades, each fan blade defining a base and an inner end along a radial direction of the gas turbine engine. The fan also includes a hub covering the base of each of the plurality of fan blades. Further, the fan includes one or more bearings for supporting rotation of the plurality of fan blades. The one or more bearings define a fan bearing radius along a radial direction of the gas turbine engine. Similarly, the hub defines a hub radius along the radial direction of the gas turbine engine. The ratio of the hub radius to the fan bearing radius is less than about three, providing for desired packaging of the various components within the fan of the gas turbine engine.

公开(公告)号：US20210340914A1

公开(公告)日：2021-11-04

申请号：US17375489

申请日：2021-07-14

Applicant: General Electric Company

Inventor： Daniel Alan Niergarth ,  Adon Delgado, JR. ,  Brandon Wayne Miller ,  Hendrik Pieter Jacobus de Bock

IPC: F02C7/224 ,  F02C7/141 ,  F28F23/00 ,  F02C7/14

Abstract: A gas turbine engine includes a turbomachine and a thermal management system. The thermal management system includes a heat source heat exchanger configured to collect heat from the turbomachine during operation; a heat sink heat exchanger; and a thermal transport bus having a heat exchange fluid configured to flow therethrough at a pressure within an operational pressure range. The thermal management system defines an operational temperature range for the heat exchange fluid, the operational temperature range having a lower temperature limit less than about zero degrees Fahrenheit at a pressure within the operational pressure range and an upper temperature limit of at least about 1000 degrees Fahrenheit at a pressure within the operational pressure range.

公开(公告)号：US20210339846A1

公开(公告)日：2021-11-04

申请号：US17071308

申请日：2020-10-15

Applicant: General Electric Company

Inventor： David William Crall ,  Nicholas Joseph Kray ,  Douglas Duane Ward ,  Brandon Wayne Miller

IPC: B64C1/38

Abstract: An aircraft defining a longitudinal direction and a lateral direction is provided. The aircraft includes a fuselage; an engine mounted at a location spaced from the fuselage of the aircraft, the engine comprising rotor blades; and at least one fuselage shield removably coupled to the fuselage at a location in alignment with the rotor blades along the lateral direction.

公开(公告)号：US11156128B2

公开(公告)日：2021-10-26

申请号：US16108732

申请日：2018-08-22

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Randy M. Vondrell ,  Darek Tomasz Zatorski ,  Christopher Charles Glynn

IPC: F01D25/28 ,  B64D27/10 ,  F01D15/10 ,  B64D27/02

Abstract: A method is provided for maintaining a gas turbine engine installed on an aircraft, the gas turbine engine including an electric machine mounted at least partially inward of a core air flowpath of the gas turbine engine. The method includes removing a rotor mount connecting a rotor of the electric machine to a rotary component of the gas turbine engine; removing a stator mount connecting a stator of the electric machine to a stationary component of the gas turbine engine; and removing in situ the electric machine.

公开(公告)号：US11143104B2

公开(公告)日：2021-10-12

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 ,  F02C9/00 ,  F02C7/143

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：US11098647B2

公开(公告)日：2021-08-24

申请号：US16256629

申请日：2019-01-24

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Duane Howard Anstead ,  Mohammed El Hacin Sennoun ,  Ning Fang ,  Kyle Robert Snow

IPC: F02C7/00 ,  F02C7/224 ,  F02C7/06 ,  F02C7/14 ,  B64D37/02 ,  B64D37/34 ,  B64D27/12 ,  F02C7/236

Abstract: A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500° F. The system additionally includes a fuel system having a deoxygenation unit for deoxygenating fuel in the fuel system, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system and the fuel in the fuel system for transferring heat from the oil in the first engine system to the fuel in the fuel system.

公开(公告)号：US11085310B2

公开(公告)日：2021-08-10

申请号：US16188373

申请日：2018-11-13

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.