公开(公告)号：US20190047716A1

公开(公告)日：2019-02-14

申请号：US16042328

申请日：2018-07-23

Applicant: General Electric Company

Inventor： Kurt David Murrow ,  Darek Tomasz Zatorski

IPC: B64D33/04 ,  B64C29/00 ,  B64C3/32 ,  B64D27/24

Abstract: An aircraft includes a fuselage; a propulsion system including a power source and a vertical thrust electric fan driven by the power source; and a wing extending from the fuselage. The vertical thrust electric fan is positioned on or within the wing, the wing including a diffusion assembly movable between a first position and a second position and positioned at least partially downstream of the vertical thrust electric fan when in the second position, the diffusion assembly including a first member and a second member, the second member movable generally along the vertical direction relative to the first member such that the first member and second member together define at least in part an exhaust flowpath for the first vertical thrust electric fan when the diffusion assembly is in the second position.

公开(公告)号：US20190023391A1

公开(公告)日：2019-01-24

申请号：US16042487

申请日：2018-07-23

Applicant: General Electric Company

Inventor： Kurt David Murrow

IPC: B64C29/00 ,  B64D27/10 ,  B64D27/24 ,  B64D27/26

Abstract: An aircraft defining a vertical direction and a transverse direction. The aircraft may include a fuselage, a wing extending from the fuselage, and a hybrid-electric propulsion system. The hybrid-electric propulsion system may include a power source, a plurality of vertical thrust electric fans arranged along the wing and driven by the power source, and a forward thrust propulsor. The power source may include a combustion engine and an electric generator. The combustion engine may also define a flowpath for exhausting combustion gases. The forward thrust propulsor may be selectively or permanently mechanically coupled to the combustion engine. The forward thrust propulsor may include a propulsor fan having a plurality of fan blades arranged outside of the flowpath of the combustion engine for exhausting combustion gases.

公开(公告)号：US20180355804A1

公开(公告)日：2018-12-13

申请号：US15417710

申请日：2017-01-27

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Randy M. Vondrell ,  Jeffrey Donald Clements ,  Kurt David Murrow

IPC: F02C9/00 ,  F02C3/04 ,  F01D9/04 ,  F01D5/14

CPC classification number: F02C9/00 ,  F01D5/147 ,  F01D5/284 ,  F01D9/04 ,  F01D9/041 ,  F02C3/04 ,  F02C7/141 ,  F02C7/18 ,  F02C9/18 ,  F02K3/06 ,  F05D2220/3212 ,  F05D2220/323 ,  F05D2240/128 ,  F05D2240/24 ,  F05D2270/02 ,  F05D2300/13 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/673

Abstract: A gas turbine engine includes a compressor section defining a compressor exit temperature, T3. The gas turbine engine also includes a combustion section and a turbine section, with the turbine section defining a turbine inlet temperature, T4. A ratio, T4:T3, of the turbine inlet temperature, T4, to compressor exit temperature, T3, during operation of the gas turbine engine at a rated speed is less than or equal to 1.85.

公开(公告)号：US09957055B2

公开(公告)日：2018-05-01

申请号：US14859523

申请日：2015-09-21

Applicant: General Electric Company

Inventor： Patrick Michael Marrinan ,  Thomas Lee Becker ,  Kurt David Murrow

IPC: B64D29/04 ,  B64D27/10 ,  B64C21/06 ,  F02K3/06 ,  B64C1/16 ,  B64D27/20 ,  B64D33/02

CPC classification number: B64D27/10 ,  B64C1/16 ,  B64C21/06 ,  B64C2230/04 ,  B64D27/20 ,  B64D29/04 ,  B64D33/02 ,  F02K3/06 ,  Y02T50/166 ,  Y02T50/44

Abstract: A propulsion system for an aircraft including a plurality of primary engines is provided. The plurality of primary engines includes at least a first primary engine and a second primary engine, each configured for mounting to a respective one of a pair of wings of the aircraft. The propulsion system additionally includes an aft engine configured for mounting at a tail section of the aircraft. The plurality of primary engines are sized to provide an amount of thrust sufficient for the aircraft to takeoff without use of the aft engine, such that the aft engine may be configured as a non-prime reliable engine.

公开(公告)号：US20180065743A1

公开(公告)日：2018-03-08

申请号：US15259654

申请日：2016-09-08

Applicant: General Electric Company

Inventor： Randy M. Vondrell ,  Matthew Ryan Polakowski ,  Kurt David Murrow ,  Glenn Crabtree ,  Darek Tomasz Zatorski

IPC: B64C29/00 ,  B64D27/24 ,  B64D27/14 ,  B64C21/06 ,  H02P9/04

CPC classification number: B64C29/0033 ,  B64C3/385 ,  B64C21/06 ,  B64C27/28 ,  B64C29/00 ,  B64C29/0008 ,  B64D27/14 ,  B64D27/24 ,  B64D2027/026 ,  B64D2221/00 ,  H02P9/04 ,  Y02T50/64

Abstract: A method for operating a propulsion system of an aircraft includes moving a plurality of forward and aft propulsors to a vertical thrust position. While in the vertical thrust positions, the method also includes providing a first forward to aft ratio of electric power to the plurality of forward and aft propulsors. The method also includes moving the plurality of forward and aft propulsors to a forward thrust position. While in the forward thrust positions, the method also includes providing a second forward to aft ratio of electric power to the plurality of forward and aft propulsors. The first forward to aft ratio of electric power is different than the second forward to aft ratio of electric power to provide certain efficiencies for the aircraft.

公开(公告)号：US20180065739A1

公开(公告)日：2018-03-08

申请号：US15259523

申请日：2016-09-08

Applicant: General Electric Company

Inventor： Randy M. Vondrell ,  Matthew Ryan Polakowski ,  Kurt David Murrow ,  Glenn Crabtree ,  Darek Tomasz Zatorski

IPC: B64C29/00 ,  B64D27/24 ,  B64D27/14

CPC classification number: B64C29/0033 ,  B64D27/14 ,  B64D27/24 ,  B64D2027/026 ,  B64D2221/00

Abstract: An aircraft includes a fuselage and a wing assembly attached to or formed integrally with the fuselage. The aircraft also includes a hybrid electric propulsion system having a port propulsor and a starboard propulsor, with the port and starboard propulsors attached to the wing assembly on opposing sides of the fuselage and rotatable between a forward thrust position and a vertical thrust position. The hybrid electric propulsion system additionally includes an electric power source including a combustion engine and an electric generator, with the electric generator being driven by the combustion engine. The electric generator is in electrical communication with each of the port and starboard propulsors for powering the port and starboard propulsors.

公开(公告)号：US20170253340A1

公开(公告)日：2017-09-07

申请号：US15245257

申请日：2016-08-24

Applicant: General Electric Company

Inventor： Randy M. Vondrell ,  Matthew Ryan Polakowski ,  Kurt David Murrow ,  Glenn Crabtree

IPC: B64D27/18 ,  F01D15/10 ,  B64D41/00 ,  B64D27/24 ,  B64C11/30

CPC classification number: B64D27/18 ,  B64C11/30 ,  B64D27/24 ,  B64D41/00 ,  B64D2027/026 ,  B64D2221/00 ,  F01D15/10 ,  Y02T50/62

Abstract: A propulsion system for an aircraft includes an electric generator and a turbomachine. The turbomachine is configured to be mounted to a first wing of the aircraft and is operable with the electric generator. The propulsion system additionally includes a first propulsor mechanically coupled to a shaft of the turbomachine and a second propulsor assembly configured to be mounted at a location away from the turbomachine and the first propulsor. The electric generator is in electrical communication with the second propulsor assembly for powering the second propulsor assembly.

公开(公告)号：US20170081037A1

公开(公告)日：2017-03-23

申请号：US14859566

申请日：2015-09-21

Applicant: General Electric Company

Inventor： Patrick Michael Marrinan ,  Thomas Lee Becker ,  Kurt David Murrow ,  Jixian Yao

IPC: B64D29/04 ,  B64D27/14

CPC classification number: B64D29/04 ,  B64C1/16 ,  B64C21/06 ,  B64D27/20 ,  B64D33/02 ,  B64D2033/0226 ,  Y02T50/166

Abstract: An aircraft including a fuselage and an aft engine is provided. The fuselage extends from a forward end of the aircraft towards an aft end of the aircraft. The aft engine is mounted to the fuselage proximate the aft end of the aircraft and includes a fan and a nacelle. The fan is rotatable about a central axis of the aft engine and includes a plurality of fan blades. The nacelle of the aft engine surrounds the plurality of fan blades and defines a bottom portion having a forward end. Additionally, the nacelle defines a curved surface at the forward end of the bottom portion, the curved surface including a reference point where the curved surface defines the smallest radius of curvature. The nacelle further defines a normal reference line extending normal from the reference point. The normal reference line defines an angle with the central axis of the aft engine greater than zero to, e.g., allow for a maximum amount of airflow into the aft engine.

公开(公告)号：US20170081034A1

公开(公告)日：2017-03-23

申请号：US14859523

申请日：2015-09-21

Applicant: General Electric Company

Inventor： Patrick Michael Marrinan ,  Thomas Lee Becker ,  Kurt David Murrow

IPC: B64D27/10 ,  B64C21/06 ,  F02K3/06

CPC classification number: B64D27/10 ,  B64C1/16 ,  B64C21/06 ,  B64C2230/04 ,  B64D27/20 ,  B64D29/04 ,  B64D33/02 ,  F02K3/06 ,  Y02T50/166 ,  Y02T50/44

Abstract: A propulsion system for an aircraft including a plurality of primary engines is provided. The plurality of primary engines includes at least a first primary engine and a second primary engine, each configured for mounting to a respective one of a pair of wings of the aircraft. The propulsion system additionally includes an aft engine configured for mounting at a tail section of the aircraft. The plurality of primary engines are sized to provide an amount of thrust sufficient for the aircraft to takeoff without use of the aft engine, such that the aft engine may be configured as a non-prime reliable engine.

公开(公告)号：US20170081013A1

公开(公告)日：2017-03-23

申请号：US14859549

申请日：2015-09-21

Applicant: General Electric Company

Inventor： Patrick Michael Marrinan ,  Thomas Lee Becker ,  Kurt David Murrow ,  Jixian Yao

IPC: B64C1/16 ,  B64D29/00 ,  B64D27/14

CPC classification number: B64C1/16 ,  B64C21/06 ,  B64C2230/00 ,  B64D27/14 ,  B64D27/20 ,  B64D29/00 ,  B64D29/04 ,  B64D33/02 ,  F02K3/04 ,  F05D2220/76 ,  Y02T50/166

Abstract: An aircraft is provided including a fuselage and an aft engine. The fuselage defines a top side, a bottom side, and a frustum located proximate an aft end of the aircraft. The frustum defines a top reference line extending along the frustum at a top side of the fuselage, and a bottom reference line extending along the frustum at a bottom side of the fuselage. The top and bottom reference lines meet at a reference point aft of the frustum. The fuselage further defines a recessed portion located aft of the frustum and indented inwardly from the bottom reference line. The aft engine includes a nacelle extending adjacent to the recessed portion of the fuselage such that the aft engine may be included with the aircraft without interfering with, e.g., a takeoff angle of the aircraft.