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：US20180003076A1

公开(公告)日：2018-01-04

申请号：US15200686

申请日：2016-07-01

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Matthew Robert Cerny ,  Nicholas Taylor Moore

IPC: F01D25/12 ,  F28F9/007 ,  F01D25/14 ,  F28F9/02 ,  F28D1/03 ,  F28D21/00 ,  F28D1/02

CPC classification number: F01D25/12 ,  F01D9/041 ,  F01D9/042 ,  F01D25/14 ,  F02C7/14 ,  F05D2250/38 ,  F05D2260/208 ,  F05D2260/213 ,  F05D2260/22141 ,  F28D1/0308 ,  F28D1/0358 ,  F28D9/0012 ,  F28D2001/0273 ,  F28D2021/0026 ,  F28F9/0075 ,  F28F9/02 ,  Y02T50/672 ,  Y02T50/676

Abstract: An annular duct including a modular annular heat exchanger for a gas turbine engine is provided, where the modular annular heat exchanger includes a plurality of radial modules in circumferentially adjacent arrangement. Each radial module includes a cooled fluid inlet plenum segment, a plurality of blades, and a cooled fluid outlet plenum segment. The plurality of blades is configured in circumferentially adjacent arrangement and defines an angular space that is conformal between each circumferentially adjacent blade. The cooled fluid inlet plenum segment, the plurality of blades, and the cooled fluid outlet plenum segment are in serial axial flow arrangement and define an internal cooled fluid flowpath and an external cooling fluid flowpath parallel to the internal cooled fluid flowpath. Each radial module further includes an inner annular ring segment and an outer annular ring segment. The inner annular ring segment and the outer annular ring segment define a plurality of blade retainers. The blade retainers define an axial, radial, and circumferential position of the blades, the cooled fluid inlet plenum segment, and the cooled fluid outlet plenum segment.

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.

公开(公告)号：US20170284304A1

公开(公告)日：2017-10-05

申请号：US15084898

申请日：2016-03-30

Applicant: General Electric Company

Inventor： Brian Francis Nestico ,  Brian K. Kestner ,  Brandon Wayne Miller

IPC: F02C9/18 ,  F02C3/13

CPC classification number: F02C9/18 ,  F02C3/13 ,  F02C6/08 ,  F02C7/047 ,  F04D27/0215 ,  F05D2260/96

Abstract: Systems and methods for adjusting airflow distortion in a gas turbine engine using a valved airflow passage assembly are provided. A gas turbine engine can include a compressor section, a combustion section, and a turbine section in series flow and defining at least in part an engine airflow path. The compressor section can include a compressor. The gas turbine engine can further include a valved airflow passage assembly comprising a valve and a duct, the duct defining an inlet in airflow communication with the engine airflow path at a location downstream of the compressor and an outlet in airflow communication with the engine airflow path at a location upstream of the compressor, the duct comprising an airflow passage extending between the inlet and outlet. The valve can be operable with the airflow passage for controlling an airflow through the airflow passage to adjust airflow distortion.

公开(公告)号：US20170284296A1

公开(公告)日：2017-10-05

申请号：US15084966

申请日：2016-03-30

Applicant: General Electric Company

Inventor： Brian Francis Nestico ,  Brian K. Kestner ,  Brandon Wayne Miller

IPC: F02C7/057 ,  B64D31/06 ,  B64D27/10 ,  F02C3/14 ,  F02C3/06

CPC classification number: F02C7/057 ,  B64D27/10 ,  B64D31/06 ,  F02C3/06 ,  F02C3/14 ,  F02C7/042 ,  F05D2210/44 ,  F05D2220/323 ,  F05D2270/101 ,  F05D2270/102 ,  F05D2270/3011 ,  F05D2270/44 ,  F05D2270/54

Abstract: Systems and methods for adjusting airflow distortion in a gas turbine engine using a secondary airflow passage assembly are disclosed. A gas turbine engine can include a compressor section, a combustion section, and a turbine section in series flow and defining at least in part an engine airflow path. A casing can enclose the gas turbine engine and be at least partially exposed to a bypass airflow. The gas turbine engine can further include a secondary airflow passage assembly comprising a door and a duct, the duct defining an inlet located on the casing, the duct defining an outlet in airflow communication with the engine airflow path, the duct comprising an airflow passage extending between the inlet and outlet. The door can be moveable between an open and closed position to allow a portion of the bypass airflow to flow through the airflow passage to adjust airflow distortion.

公开(公告)号：US20170219079A1

公开(公告)日：2017-08-03

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

CPC classification number: F16H57/0006 ,  F02C7/36 ,  F05D2260/40311 ,  F05D2260/96 ,  F16C19/28 ,  F16C27/045 ,  F16C2361/61 ,  F16H57/0471 ,  F16H57/08 ,  F16H57/082 ,  F16H2057/085

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：US20170190409A1

公开(公告)日：2017-07-06

申请号：US14984758

申请日：2015-12-30

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Ian Francis Prentice ,  Trevor Wayne Goerig ,  Trevor Howard Wood ,  Kishore Ramakrishnan ,  Andrew Breeze-Stringfellow

IPC: B64C1/40 ,  B64D27/12

CPC classification number: B64C1/40 ,  B64C11/00 ,  B64D27/12 ,  B64D27/14 ,  B64D2027/005 ,  Y02T50/66

Abstract: An aircraft and method of operating the aircraft are provided. The aircraft includes a fuselage including a nose, a tail, and a hollow, elongate body extending therebetween, a wing extending laterally away from the fuselage, the wing including a leading edge in a direction of motion of the aircraft during normal flight and a trailing edge on an opposing edge of the wing, and an engine configured to drive a bladed rotatable member, the engine coupled to at least one of the wing and the fuselage. The aircraft further includes at least one of a forward chine member and an aft chine member extending from the fuselage at a point forward of the engine aftward to a point aft of the bladed rotatable member.

公开(公告)号：US20170184020A1

公开(公告)日：2017-06-29

申请号：US14982793

申请日：2015-12-29

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Narendra Digamber Joshi ,  Ian Francis Prentice ,  Kurt David Murrow

IPC: F02C3/107 ,  F04D29/32 ,  F01D5/02 ,  F01D25/30 ,  F02C7/04 ,  F02C7/36

Abstract: A gas turbine engine system and method of operating gas turbine engines are provided. The gas turbine engine assembly includes a gas turbine engine includes a power shaft configured to rotate about an axis of rotation. The gas turbine engine assembly also includes a first fan and a second fan coupled to the power shaft coaxially with the gas turbine engine. The gas turbine engine assembly also includes a first fan duct configured to direct a first stream of air to the first fan. The gas turbine engine assembly also includes a second fan duct configured to direct a second stream of air to the second fan. The gas turbine engine assembly also includes an exhaust duct configured to direct a stream of exhaust gases of the gas turbine engine in a direction of the axis of rotation.

公开(公告)号：US20170167382A1

公开(公告)日：2017-06-15

申请号：US14963419

申请日：2015-12-09

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Christopher James Kroger ,  Matthew Robert Cerny

IPC: F02C7/14 ,  F02C7/06 ,  F01D11/24 ,  F02C3/04

CPC classification number: F02C7/14 ,  B64D15/06 ,  B64D33/02 ,  B64D2033/0233 ,  F01D11/24 ,  F02C3/04 ,  F02C7/047 ,  F02C7/06 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2260/213 ,  F05D2260/98 ,  Y02T50/676

Abstract: A thermal management system for a gas turbine engine and/or an aircraft is provided including a thermal transport bus having a heat exchange fluid flowing therethrough. The thermal management system also includes one or more heat source exchangers and a deicing module. The one or more heat source exchangers and the deicing module are each in thermal communication with the heat exchange fluid in the thermal transport bus. The one or more heat source exchangers are configured to transfer heat from one or more accessory systems to the heat exchange fluid, and the deicing module is located downstream of the one or more heat source exchangers for transferring heat from the thermal transfer fluid to a surface of one or more components of the gas turbine engine and/or the aircraft.

公开(公告)号：US20170152859A1

公开(公告)日：2017-06-01

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: F04D29/063 ,  F04D29/52 ,  F04D25/04

CPC classification number: F04D29/063 ,  F01D9/065 ,  F01D25/18 ,  F01M2001/126 ,  F02C7/06 ,  F02K3/06 ,  F04D25/045 ,  F04D29/526 ,  F05B2260/602 ,  F05D2260/40311 ,  F05D2260/602 ,  F16N31/00 ,  Y02T50/671

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.