General Electric Company

Concept Laser Gmbh

Ge Additive Germany Gmbh

Kishore Ramakrishnan

Trevor Howard Wood

Nikolai N Pastouchenko

Jixian Yao

Timothy Richard DePuy

Mohammed Mounir Shalaby

Thomas Malkus

Ramakrishna Venkata Mallina

Giridhar Jothiprasad

Peter Pontiller-Schymura

Davide Giacché

Wendy Wenling Lin

Shashwat Swami Jaiswal

Robert William Davidoff

Lawrence Chih-hui Cheung

Shourya Prakash Otta

Sara Elizabeth Carle

Eric Edward Halla

Ravish Karve

Brandon Wayne Miller

Nicholas Joseph Kray

Ian Francis Prentice

Daniel Lawrence Tweedt

Li Zheng

William Joseph Solomon

Rene Du Cauze De Nazelle

Christian Thomas Wakelam

Ivan Malcevic

David Herman

Rathakrishnan Bhaskaran

Valeria Andreoli

Nicholas Bown

Angela Knepper

Jens Stammberger

Thomas Ory Moniz

Bugra Han Ertas

Harry Kirk Mathews, Jr

William Dwight Gerstler

Honggang Wang

Andrew Breeze-Stringfellow

Bhaskar Nanda Mondal

Christian Lee Vandervort

Darren Lee Hallman

Scott Roger Finn

Changjie Sun

Patrick Michael Marrinan

Eric Richard Westervelt

Justin John Gambone, Jr

Thomas William Vandeputte

Egbert Geertsema

Lana Maria Osusky

Mustafa Dindar

Vinod Shashikant Chaudhari

Andrey Meshkov

Steven B Morris

Keith Edward James Blodgett

Trevor Wayne Goerig

Ahmed Mostafa ELKady

Umesh Paliath

Adam G Susong

Kishanjit Pal

Sushilkumar Shevakari

Changjin Yoon

Benedikt Roidl

Aaron J King

Angela Marie Knepper

Ivan K Malcevic

Nicholas William Bown

An aircraft defines a longitudinal direction, a vertical direction, and a transverse direction. The aircraft includes a fuselage; and a wing extending from the fuselage generally along the transverse direction and defining an outer end along the transverse direction. The wing includes a wing tip assembly at the outer end of the wing, the wing tip assembly defining an axis substantially parallel to the longitudinal direction of the aircraft and a circumferential direction extending about the axis, the wing tip assembly including at least three stationary guide vanes spaced along the circumferential direction from one another.

Aerodynamic tip feature

A turbofan engine defining a circumferential direction is provided. The turbofan engine includes: a turbomachine, the turbomachine defining a pylon attachment location along the circumferential direction; an unducted rotor assembly drivingly coupled to the turbomachine, the unducted rotor assembly including a plurality of unducted rotor blades; and a plurality of outlet guide vanes positioned downstream of the plurality of unducted rotor blades, the plurality of outlet guide vanes including Nnumber of outlet guide vanes, the plurality of outlet guide vanes including a first outlet guide vane and a second outlet guide vane adjacent the first outlet guide vane, the first and second outlet guide vanes defining a gap spacing greater than 360 degrees divided by N, and the pylon attachment location positioned outside of between the first and second outlet guide vanes along the circumferential direction.

Outlet guide vane assembly for a turbofan engine

A rotary component for a gas turbine engine includes a plurality of rotor blades operably coupled to a rotating shaft extending along the central axis and an outer casing arranged exterior to the plurality of rotor blades in a radial direction of the gas turbine engine. The outer casing defines a gap between a blade tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features formed into an interior surface thereof. Each of the plurality of features includes one or more design parameters that are perturbed about a mean design parameter for stall performance so as to provide a circumferential variation in wake strengths associated with the plurality of rotor blades, thereby reducing operational noise of the gas turbine engine.

Circumferentially varying fan casing treatments for reducing fan noise effects

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

An aircraft having a fuselage, an aircraft body, at least one aircraft engine system and a feature. The fuselage defining a longitudinal centerline. The at least one aircraft engine system defining an axial centerline. The at least one aircraft engine system having a nacelle and at least one rotatable propeller. The at least one rotatable propeller having a free end that is spaced radially outward from the nacelle with respect to the axial centerline. The feature shaped to alter a flow of air between the aircraft body and the at least one rotatable propeller. The feature having a continuous rounded contour when viewed along a vertical plane normal to the longitudinal centerline and intersecting the feature.

Aircraft having an aircraft body including a feature

An airfoil assembly for a gas turbine engine includes a first blade having a first leading edge and a first trailing edge, and a second blade circumferentially spaced from the first blade where the second blade has a second leading edge and a second trailing edge. The first blade includes a feature formed on the first leading edge where the first blade includes a chord extending from the first leading edge to the first trailing edge. The chord is located radially where a projection of a line normal to an intersection of the chord with the first trailing edge intersects the second leading edge. At least a portion of the feature is radially located at or inboard of the chord.

Airfoil assembly

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

Airfoil include a body extending along a spanwise direction between a root end and a tip end, the body comprising a plurality of acoustic cavities each having an inlet on the airfoil; and at least one cooling channel having an inlet section an outlet section and a middle section within the airfoil extending between the inlet section and the outlet section; and at least one porous face sheet positioned on at least one inlet of the plurality of acoustic cavities.

Airfoils for turbofan engines

A turbofan engine may include a variable pitch fan rotatable about an axis and operable in a forward thrust mode by generating flow opposite a direction of travel and in a reverse thrust mode by generating flow in the direction of travel. In reverse thrust mode, a nacelle assembly defines an intermediate opening disposed aft of the variable pitch fan. A flow guide assembly is configured to guide a first fluid flow opposite the direction of travel within a bypass passage from a forward opening to an aft opening of the nacelle assembly in forward thrust mode, and to redirect a second fluid flow from outside the bypass passage opposite the direction of travel to inside the bypass passage in the direction of travel through the intermediate opening in reverse thrust mode. One or more flow channels are defined for generating at least one fluidic injection pressurized by a core.

Reverse thrust turbofan engine

An aircraft engine includes a low pressure spool, a high pressure spool, and an alternative power source. The alternative power source is configured to add power to the high pressure spool. A controller is configured to determine a noise sensitive condition; and control, in response to determining the noise sensitive condition, the alternative power source to add power to the high pressure spool.

Gas turbine engine noise reduction

A turbofan engine defining a circumferential direction is provided. The turbofan engine includes a turbomachine; an unducted rotor assembly drivingly coupled to the turbomachine, the unducted rotor assembly including a plurality of unducted rotor blades; and a plurality of outlet guide vanes positioned downstream of the plurality of unducted rotor blades, the plurality of outlet guide vanes each defining a span, the spans of the plurality of outlet guide vanes being nonuniform along the circumferential direction.

An airfoil is provided defining a spanwise direction, a chordwise direction, a root end, a tip end, a leading edge end, and a trailing edge end. The airfoil includes: a leading edge extending from the leading edge end; a body extending along the spanwise direction between the root end and the tip end, the body including a plurality of cavity walls defining a plurality of cavities, each of the plurality of cavities having an inlet located at the leading edge; and a porous face sheet positioned on at least one inlet of the plurality of cavities.

Airfoil for a turbofan engine

A propulsor is provided having a power source; a fan section coupled to the power source and configured to provide thrust opposite a downstream direction; and a cowl assembly at least partially enclosing the power source and the fan section, the cowl assembly including: a forward cowl component; a first aft cowl component disposed in the downstream direction relative to the forward cowl component and movable to vary a first aft cowl displacement from the forward cowl component in the downstream direction; and a second aft cowl component disposed in the downstream direction relative to the first aft cowl component and movable to vary a second aft cowl intermediate displacement from the first aft cowl component.

Cowl assembly for a propulsor

A turbofan engine and an outlet guide vane structure for the turbofan engine is provided. The outlet guide vane structure includes a non-uniform plurality of outlet guide vanes utilized in a bypass duct and between a radially inward wall and a radially outward wall. The non-uniform plurality of outlet guide vanes have varying chord lengths at the base of the outlet guide vanes along the radially inward wall. The non-uniform plurality of outlet guide vanes may include structural outlet guide vanes, non-structural outlet guide vanes, and cut-out outlet guide vanes. The non-uniform plurality of outlet guide vanes include at least one outlet guide vane integrated with a pylon and/or a bifurcation of the turbofan engine. The cut-out outlet guide vane may be integrated with the pylon and/or bifurcation. The cut-out may include a leading edge and a trailing edge disposed in front of a leading edge of the pylon.

Turbofan engine including integrated pylon and fan outlet guide vane with noise reduction features

An unducted airfoil assembly includes an airfoil having spaced-apart pressure and suction sides extending radially in span from a root to a tip, and extending axially in chord between spaced apart leading and trailing edges. The airfoil defines a forward-most axial point and is arranged around a longitudinal axis and rotates about the longitudinal axis in a rotational direction. A tip leading edge of the airfoil is circumferentially offset in a direction opposite the rotational direction relative to a circumferential location of the forward-most axial point.

Unducted airfoil assembly

Growing community of inventors

Rexford, NY, United States of America

Kishore Ramakrishnan