General Electric Company

General Electric Renovables Espana, S.l.

Nikolai N Pastouchenko

Kishore Ramakrishnan

Trevor Howard Wood

Lawrence Chih-hui Cheung

Jixian Yao

Ivan Malcevic

Brandon Wayne Miller

Patrick Michael Marrinan

Daniel Alan Niergarth

Randy M Vondrell

Timothy Richard DePuy

Umesh Paliath

Wendy Wenling Lin

Robert William Davidoff

Hongbin Ju

Carlos Enrique Diaz

David Herman

Narendra Digamber Joshi

Kurt David Murrow

Darren John Danielsen

Thomas William Vandeputte

Richard David Cedar

David Perveiler

Narendra Joshi

Steven B Morris

Patrick John Lonneman

Changjin Yoon

Martin Stettner

Gottfried Schuon

Marc Canal

Jason A Lee

Valentina Motta

Marianne Luise Susanne Hartung

Ivan K Malcevic

Lawrence Chih-Hui Cheung

Bart Jan Veldkamp

An acoustic core may include an array of resonant cells configured as a plurality of resonant cell groups. The resonant cell groups may include a plurality of resonant cells configured as a partitioned resonant cell that include a converging resonant cell and a diverging resonant cell. The converging resonant cell and the diverging resonant cell may be defined by a plurality of cell walls integrally formed with one another and a partition integrally formed with the plurality of cell walls. The partition may at least partially delimit the converging resonant cell from the diverging resonant cell. The converging resonant cell may define an upper resonant space delimited by the partition and a top face of the array of resonant cells. The diverging resonant cell may define a lower resonant space delimited by the partition and a bottom face of the array of resonant cells.

Tools and methods for forming acoustic cores

A turbine airfoil is provided. The turbine airfoil defines a chord line, a spanwise direction, a span along the spanwise direction, and a midpoint along the spanwise direction. The turbine airfoil includes a pressure side and a suction side. The pressure side and the suction side intersecting at a leading edge and a trailing edge. The turbine airfoil further includes a root and a tip at opposing ends along the spanwise direction. In addition, the turbine airfoil defines a leading edge reference line extending from where the leading edge meets the root to where the leading edge meets the tip and a trailing edge reference line extending from where the trailing edge meets the root to where the trailing edge meets the tip. The turbine airfoil includes a lobe positioned at the leading edge or the trailing edge and defines a maximum axially height relative to the leading edge reference line or the trailing edge reference line. The maximum axial height being equal to at least five percent of the chord line of the turbine airfoil.

Turbine airfoils

A propulsion system is provided, wherein the propulsion system includes an afterburner assembly. The afterburner assembly including: an exhaust section and a fuel injector assembly that is operable to inject fuel in the exhaust section. The fuel injector assembly includes a plurality of fuel injection members. The plurality of fuel injection members defines a hot zone and a cold zone. The cold zone is positioned to provide a noise insulation barrier for the hot zone.

Propulsion system for jet noise reduction

An inlet duct for a nacelle of a ducted fan engine includes an inlet portion at an upstream end of the inlet duct, an acoustic liner arranged downstream of the inlet portion, and a fan section arranged downstream of the acoustic liner. The inlet portion and the acoustic liner are coupled together at an inlet-acoustic liner interface extending circumferentially about the inner surface of the inlet duct, and the acoustic liner and the fan section are coupled together at a fan section hardwall-acoustic liner interface extending circumferentially about the inner surface of the inlet duct. At least one of the acoustic liner, the inlet-acoustic liner interface, and the fan section hardwall-acoustic liner interface having a structure that circumferentially alters a magnitude and a phase of an acoustic wave reflection of the inlet duct to attenuate flutter bite of a fan.

Nacelle inlet duct for a ducted fan engine

A proactive method and related wind turbine system are provided for reducing vibrations in the rotor blades when the rotor hub is locked against rotation. The method includes determining an initial blade orientation to wind direction and wind parameters for wind impacting the rotor blades. Based on the wind parameters and blade orientation, an angle of attack is determined for the rotor blades that will at least reduce vibrations expected to be induced in the blades from the current wind conditions. With a controller, the rotor blades are pitched to achieve the angle of attack using a pitch control system. The angle of attack is determined and the rotor blades are pitched from the initial blade orientation to the new angle of attack prior to vibrations being induced in the rotor blades.

System and method for controlling blade pitch on wind turbine rotor blades to reduce vibrations and limit loads in a locked condition of the turbine rotor

Acoustic cores and tools and methods for forming the same

An exhaust nozzle for a gas turbine engine. The exhaust nozzle comprises a nozzle body having an upstream end axially spaced from a downstream end with respect to an axial centerline of the nozzle body, and a plurality of chevrons circumferentially spaced apart and extending downstream from the downstream end. Each chevron includes an inner wall radially spaced from an outer wall, a root and a tip axially spaced from the root. At least one chevron of the plurality of chevrons includes a first segment extending axially downstream from the root, a second segment extending axially downstream from the first segment, and a third segment extending axially downstream from the second segment to the tip. The inner wall extends along the first segment, the second segment, and third the segment. The first segment is distinguishable from the second segment and the second segment is distinguishable from the third segment.

Gas turbine exhaust nozzle noise abatement

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.

Propulsion engine for an aircraft

An acoustic core includes an array of resonant cells. The array may include a plurality of coupled resonant cells respectively defining an antecedent resonant space and a subsequent resonant space, with at least one cell wall having one or more wall-apertures defining a pathway between the antecedent resonant space and the subsequent resonant space. The array may include a plurality of high-frequency resonant cells respectively defining a high-frequency resonant space and being matched with respective ones of the plurality of coupled resonant cells. A cross-sectional dimension of the one or more wall-apertures defining the pathway between the antecedent resonant space and the subsequent resonant space may be less than a cross-sectional dimension of the antecedent resonant space and/or a cross-sectional dimension of the subsequent resonant space. The array may include a plurality of partitioned resonant cells that have a partition integrally formed with at least one of a corresponding one or more cell walls and transecting the corresponding resonant space with at least one surface of the partition having an interface angle that is oblique or perpendicular relative to a plane parallel to a top face and/or a bottom face of the array of resonant cells.

Acoustic liners with low-frequency sound wave attenuating features

An aircraft includes a fuselage extending between a forward end and an aft end; a propulsor mounted to the fuselage at the aft end of the fuselage, the propulsor comprising an outer nacelle, the outer nacelle defining an inlet to the propulsor; and a deployable assembly attached to at least one of the fuselage or the outer nacelle and moveable between a stowed position and an engaged position. The deployable assembly alters an airflow towards the propulsor or into the propulsor through the inlet defined by the outer nacelle when in the engaged position. The propulsor further comprises a tail cone, wherein the outer nacelle defines an exhaust with the tail cone, and wherein the plurality of nacelle panels are movable generally along the axial centerline to a position at least partially aft of the exhaust of the outer nacelle when in the engaged position.

Deployable assembly for a propulsor

An aircraft is provided including a fuselage that extends along a longitudinal direction between a forward end and an aft end. A boundary layer ingestion fan is mounted to the fuselage at the aft end and is configured for ingesting boundary layer airflow off the surface of the fuselage. The fuselage defines a profile proximate the boundary layer ingestion fan that is optimized for ingesting a maximum amount of boundary layer air and improving propulsive efficiency of the aircraft. More specifically, the fuselage defines a cross sectional profile upstream of the boundary layer ingestion fan that has more cross sectional area in a top half relative to a bottom half as defined relative to a centerline of the boundary layer ingestion fan.

Aircraft having an aft engine

A propulsion system for an aircraft includes an electric propulsion engine configured to be mounted at an aft end of the aircraft. The electric propulsion engine includes an electric motor and a fan rotatable about a central axis, the fan driven by the electric motor. The electric propulsion system additionally includes a cooling system operable with an airflow over the aft end the aircraft when the electric propulsion system is mounted to the aircraft. The cooling system is configured to cool the electric motor during operation of the electric propulsion engine.

Thermal management system for an electric propulsion engine

A method for operating an electric fan of an aircraft propulsion system includes driving a plurality of fan blades of the electric fan with an electric machine to generate thrust for the aircraft; and driving the electric machine with the plurality of fan blades of the electric fan to generate electrical power subsequent to driving the plurality of fan blades of the electric fan with the electric machine to generate thrust for the aircraft.

An aircraft includes a boundary layer ingestion fan defining a centerline and including a plurality of fan blades rotatable about the centerline. The aircraft also includes a fuselage extending between a forward end and an aft end along a longitudinal direction, the boundary layer ingestion fan positioned within the fuselage at the aft end of the fuselage, the fuselage defining an inlet upstream of the boundary layer ingestion fan extending at least about 180 degrees around the centerline of the boundary layer ingestion fan, the fuselage further defining an exhaust downstream of the boundary layer ingestion fan.

Aircraft having an AFT engine

A propulsion system for an aircraft includes a gas turbine engine and an electric propulsion engine defining a central axis. The electric propulsion engine includes an electric motor and a fan rotatable about the central axis of the electric propulsion engine by the electric motor. The electric propulsion engine additionally includes a bearing supporting rotation of the fan and a thermal management system including a thermal fluid circulation assembly. The thermal fluid circulation assembly is in thermal communication with at least one of the electric motor or the bearing and is further in thermal communication with a heat exchanger of a thermal management system of the gas turbine engine.

Growing community of inventors

Glenville, NY, United States of America

Nikolai N Pastouchenko