公开(公告)号：US12044194B2

公开(公告)日：2024-07-23

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: F02K3/077 ,  B64D27/10 ,  F02C3/073 ,  F02K1/34 ,  F02K3/02 ,  F02K3/072 ,  F02K3/075

CPC classification number: F02K3/072 ,  B64D27/10 ,  F02C3/073 ,  F02K1/34 ,  F02K3/025 ,  F02K3/075 ,  F02K3/077

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：US20240110522A1

公开(公告)日：2024-04-04

申请号：US17959336

申请日：2022-10-04

Applicant: General Electric Company

Inventor： Arthur William Sibbach ,  Brandon Wayne Miller ,  Andrew Hudecki

IPC: F02C7/36 ,  F16D1/10

CPC classification number: F02C7/36 ,  F16D1/10 ,  F05D2220/323 ,  F05D2240/60

Abstract: A gas turbine engine includes a rotatably driven engine component including a shaft coupling. The shaft coupling defines a first axial centerline and includes an inner surface. The inner surface includes a plurality of internal splines extending radially inwardly from the inner surface with respect to the first axial centerline. The engine further includes a driving member having a driving end portion and defining a second axial centerline. The driving end portion includes an outer surface and a plurality of external splines extending radially outwardly from the outer surface with respect to the second axial centerline. The plurality of external splines is drivingly engaged with the plurality of internal splines. The plurality of internal splines or the plurality of external splines comprises bowed splines.

公开(公告)号：US20240110518A1

公开(公告)日：2024-04-04

申请号：US18071743

申请日：2022-11-30

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Andrew Hudecki ,  Eric Barre

IPC: F02C7/18 ,  F02C6/08

CPC classification number: F02C7/185 ,  F02C6/08 ,  F05D2220/323 ,  F05D2260/213

Abstract: A gas turbine engine is provided. The gas turbine engine includes: a fan; a turbomachine drivingly coupled to the fan and defining in part a working gas flowpath, the gas turbine engine defining a bypass passage over the turbomachine, the turbomachine defining an annular cooling passage extending between a CP inlet and a CP outlet, the CP inlet in airflow communication with the working gas flowpath and the CP outlet in airflow communication with the bypass passage; and a variable bleed assembly including a variable bleed duct extending between a VB inlet and a VB outlet, the VB inlet in airflow communication with the working gas flowpath at a location downstream of the CP inlet and the VB outlet in airflow communication with the annular cooling passage for urging an airflow through the cooling passage.

公开(公告)号：US20240110515A1

公开(公告)日：2024-04-04

申请号：US18071722

申请日：2022-11-30

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Andrew Hudecki ,  Steven Douglas Johnson ,  Eric Barre ,  John Carl Glessner ,  Efren Souza Chavez

IPC: F02C7/18 ,  F01D25/12

CPC classification number: F02C7/18 ,  F01D25/12 ,  F05D2220/323 ,  F05D2260/232

Abstract: A gas turbine engine including: a fan assembly comprising a fan; and a turbomachine drivingly coupled to the fan and including a compressor section, a combustion section, and a turbine section arranged in serial flow order and defining in part a working gas flowpath, the gas turbine engine defining a bypass passage over the turbomachine; the turbomachine further including a heat exchanger and defining an annular cooling passage extending between an inlet and an outlet, the inlet in airflow communication with the working gas flowpath at a location upstream of the compressor section and the outlet in airflow communication with the bypass passage, the heat exchanger in thermal communication with an airflow through the cooling passage.

公开(公告)号：US20230407795A1

公开(公告)日：2023-12-21

申请号：US17844863

申请日：2022-06-21

Applicant: General Electric Company

Inventor： Arthur William Sibbach ,  Brandon Wayne Miller ,  Jeffrey Douglas Rambo

IPC: F02C7/36

CPC classification number: F02C7/36 ,  F05D2260/4023

Abstract: A shaft power transfer system includes a first mechanical clutch mechanism operably coupling a high-pressure shaft to a low-pressure shaft. The first mechanical clutch mechanism transfers power from the high-pressure shaft to the low-pressure shaft at a predefined first speed transient condition. The system further includes a second mechanical clutch mechanism that operably couples the low-pressure shaft to the high-pressure shaft. The second mechanical clutch mechanism transfers power from the low-pressure shaft to the high-pressure shaft at a predefined second speed transient condition where the predefined first speed transient condition is different than the predefined second speed transient condition.

公开(公告)号：US11815024B2

公开(公告)日：2023-11-14

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 ,  F28F27/02

CPC classification number: F02C7/224 ,  F02C7/14 ,  F02C7/141 ,  F28F23/00 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2260/213 ,  F28F27/02 ,  F28F2250/06

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：US11814174B2

公开(公告)日：2023-11-14

申请号：US17071379

申请日：2020-10-15

Applicant: General Electric Company

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

IPC: F01D9/04 ,  F01D5/30 ,  F01D5/14 ,  F01D5/18 ,  F01D7/00 ,  F01D15/10 ,  F01D15/12 ,  F02K5/00 ,  F02K3/06 ,  F02C6/20 ,  F02C9/00 ,  F02C9/22 ,  F02C7/26 ,  F02C7/32 ,  F02C7/36 ,  F02C3/113 ,  B32B7/022 ,  B64C1/38 ,  B64D45/00 ,  F01D17/16 ,  F01D25/12 ,  F02C7/264 ,  F02K1/66 ,  F02K1/76

CPC classification number: B64D45/00 ,  B32B7/022 ,  B64C1/38 ,  F01D5/146 ,  F01D5/187 ,  F01D5/30 ,  F01D5/3007 ,  F01D7/00 ,  F01D9/041 ,  F01D15/10 ,  F01D15/12 ,  F01D17/162 ,  F01D25/12 ,  F02C6/206 ,  F02C7/264 ,  F02C7/32 ,  F02C7/36 ,  F02C9/00 ,  F02C9/22 ,  F02K1/66 ,  F02K1/76 ,  B32B2307/558 ,  B32B2307/72 ,  B32B2307/732 ,  B32B2571/02 ,  B32B2605/18 ,  F02C3/113 ,  F05D2220/323 ,  F05D2220/325 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2240/24 ,  F05D2240/60 ,  F05D2250/37 ,  F05D2260/201 ,  F05D2260/30 ,  F05D2260/4031 ,  F05D2260/70 ,  F05D2270/05 ,  F05D2270/051 ,  F05D2270/121 ,  F05D2270/304 ,  F05D2270/71 ,  F05D2270/81

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 a plurality of rotor blades; and a fuselage shield attached to or formed integrally with the fuselage at a location in alignment with the plurality of rotor blades along the lateral direction, the fuselage shield comprising a first layer defining a first density and a second layer defining a second density, the first density being different than the second density.

公开(公告)号：US20230287837A1

公开(公告)日：2023-09-14

申请号：US17691222

申请日：2022-03-10

Applicant: General Electric Company

Inventor： Arthur William Sibbach ,  Brandon Wayne Miller ,  Tsuguji Nakano ,  Stefan Joseph Cafaro

IPC: F02C9/26

CPC classification number: F02C9/26 ,  F05D2220/323 ,  F05D2270/051

Abstract: A gas turbine engine and a method of operating the gas turbine engine is provided. The gas turbine engine includes a fan having a plurality of fan blades, a turbomachine operably coupled to the fan for driving the fan, a nacelle surrounding and at least partially enclosing the fan, the nacelle defining an inlet and a longitudinal axis, and an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle. The method includes determining, by one or more computing devices, a thrust demand for the gas turbine engine, and in response to the thrust demand, controlling, by the one or more computing devices, a rotational speed of the fan and an angle of the inlet pre-swirl feature with respect to the longitudinal axis of the nacelle.

公开(公告)号：US11725584B2

公开(公告)日：2023-08-15

申请号：US15873605

申请日：2018-01-17

Applicant: General Electric Company

Inventor： Daniel Alan Niergarth ,  Brandon Wayne Miller ,  Jeffrey Douglas Rambo ,  Matthew Robert Cerny

IPC: F02C7/14 ,  F02C9/18 ,  F02C7/18

CPC classification number: F02C7/14 ,  F02C7/185 ,  F02C9/18 ,  F05D2260/213 ,  F05D2270/301 ,  F05D2270/303

Abstract: A heat engine comprising a compressor providing a flow of compressed air from a core flowpath of the heat engine; a cooled cooling air (CCA) heat exchanger system to which the flow of compressed air is provided from the compressor; a coolant supply system providing a flow of coolant to the CCA heat exchanger in thermal communication with the flow of compressed air at the CCA heat exchanger, in which the coolant supply system and CCA heat exchanger together define a CCA circuit through which the compressed air flows in thermal communication with the coolant; and a hot section disposed downstream of the compressor section along the core flowpath through which combustion gases flow, in which the hot section defines a secondary flowpath through which the flow of compressed air from the CCA heat exchanger is provided.

公开(公告)号：US11702958B2

公开(公告)日：2023-07-18

申请号：US17483251

申请日：2021-09-23

Applicant: General Electric Company

Inventor： Scott Alan Schimmels ,  Daniel Alan Niergarth ,  Arthur William Sibbach ,  Brandon Wayne Miller

IPC: F01D25/12 ,  F01D25/10 ,  F02C7/12

CPC classification number: F01D25/10 ,  F01D25/12 ,  F02C7/12 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2260/213

Abstract: A method of regulating pressure in a thermal transport bus of a gas turbine engine, the method including: operating the gas turbine engine with the thermal transport bus having an intermediary heat exchange fluid flowing therethrough, the thermal transport bus including one or more heat source heat exchangers and one or more heat sink heat exchangers in thermal communication through the intermediary heat exchanger fluid; and adjusting a flow volume of the thermal transport bus using a variable volume device in fluid communication with the thermal transport bus in response to a pressure change associated with the thermal transport bus.