General Electric Company

Ge Marmara Technology Center Muhendislik Hizmetleri Ltd

Gary Willard Bryant, Jr

Nicholas Joseph Kray

Arthur William Sibbach

Tod Winton Davis

Elzbieta Kryj-Kos

Benjamin Thomas Van Oflen

Brandon Wayne Miller

Michael John Franks

Douglas Lorrimer Armstrong

David Raju Yamarthi

Bhaskar Nanda Mondal

Nitesh Jain

Wei Wu

Frank Worthoff

Abhijeet Jayshingrao Yadav

Paul Mathew

Nicholas M Daggett

Li Zheng

Vishnu Vardhan Venkata Tatiparthi

Vaishnav Raghuvaran

Max Robert Farson

Balaraju Suresh

Raghuveer Chinta

Daryl John Burford

Phani Nandula

Vasanth Kumar Balaramudu

Srinivas Nuthi

Pawel Pres

Stephanie Glynn Cotten

Theodore R Ingling

Nuthi Srinivas

Necip Adali

Tomas Muchenik

Gregory Allen Platz, Jr

James Francis Brown

Matthew Robert Hastings

Justin Jeffrey Kral

A gas turbine engine includes: a turbomachine comprising a drive turbine and defining a working gas flowpath and an inlet to the working gas flowpath; a fan having a fan blade formed of a composite material, the fan blade defining a leading edge fan radius Rand a trailing edge fan radius R, and the fan defining a leading edge hub radius Rand a trailing edge hub radius R, the gas turbine engine defining a bypass ratio during operation of the gas turbine engine in a cruise operating mode; and a reduction gearbox mechanically coupling the drive turbine of the turbomachine to the fan; wherein the gas turbine engine defines a Fan Leading Edge to Trailing Edge Compression Factor (FLTCF) greater than or equal to 1.05 and less than or equal to 1.8.

Gas turbine engine having composite fan blades

A composite airfoil assembly has a composite airfoil, a spar, and a wrap. The composite airfoil has an outer wall and a composite skin. The outer wall extends between a root and a tip. The outer wall defines an interior. The composite skin at least partially defines the outer wall. The spar having a spar centerline axis, a stem, a base, and a transition interconnecting the base and the stem.

Composite airfoil assembly having a composite airfoil and spar

A composite airfoil assembly for a gas turbine engine. The composite airfoil assembly includes a composite airfoil having opposite pressure and suction sides and opposite leading and trailing edges. The pressure side and the suction side extend axially between the leading edge and the trailing edge. The composite airfoil has a laminate skin that is applied to at least a portion of a core. A first cladding and a second cladding, having adjacent segments, are located on the pressure side or the suction side of the composite airfoil.

Composite airfoil assembly for a turbine engine

A composite airfoil for a turbine engine, the composite airfoil having at least one airfoil body element. The at least one airfoil body element includes a core and a composite wrap, where the composite wrap overlies at least a portion of the core. The core includes a set of composite plies.

Composite airfoil for a turbine engine

An airfoil assembly for a turbine engine having a composite spar, a sleeve, and a set of lobes. The composite spar includes an exterior spar portion, where at least part of the exterior spar portion of the composite spar is received at a sleeve inner surface of the sleeve. The set of lobes extends from the composite spar and is received by a set of recesses at the sleeve inner surface.

Airfoil assembly having a composite spar

A fan assembly includes a disk having a disk forward surface, a disk aft surface, and a radially outer surface. The disk defines a plurality of disk posts and a plurality of disk slots in the radially outer surface. At least one of the plurality of disk posts includes a post slot. The fan assembly also includes a fan having a plurality of fan blades and a plurality of platforms extending between adjacent fan blades of the plurality of fan blades. Each of the plurality of fan blades is received within one of the plurality of disk slots via a respective blade root. Further, the fan assembly includes at least one fan retention member having a body portion and a protrusion extending from the body portion. The protrusion is received within the post slot such that the at least one fan retention member supports one of the plurality of platforms.

Fan retention member for supporting a blade platform of a fan assembly

A gas turbine engine is provided having: a turbomachine; a fan rotatable by the turbomachine, the fan comprising a fan blade, the fan blade defining an outer tip along the radial direction, a trailing edge at the tip, and a length, L, at the tip along the axial direction; and an outer nacelle surrounding the fan and surrounding at least in part the turbomachine, the outer nacelle comprising a stage of pre-swirl inlet guide vanes located upstream of the fan, the stage of pre-swirl inlet guide vanes having a pre-swirl inlet guide vane, the outer nacelle further comprising an inner surface along the radial direction and an acoustic treatment coupled to or integrated with the inner surface.

Outer nacelle with inlet guide vanes and acoustic treatment

A composite airfoil assembly for a gas turbine engine. The composite airfoil assembly includes a composite airfoil defined by a core and a skin. The composite airfoil assembly further includes cladding. The core defines a core exterior, where the skin is applied to at least a portion of the core exterior. The cladding is prepared before being coupled or adhered to the composite airfoil.

Composite airfoil assembly and method of forming a composite airfoil assembly

A turbine engine including a fan section, a compressor section, a combustion section, a turbine section, and an airfoil assembly. The airfoil assembly comprising a spar, a trunnion and a stress relief. The trunnion having an upper edge with an open top, and a socket extending from the open top. The spar extending through the open top and into the socket. A junction being formed between the spar and a portion of the upper edge defining the open top.

Turbine engine having an airfoil assembly with a trunnion and a spar

A turbine engine having a disk and a composite airfoil assembly. The disk having a slot. The composite airfoil assembly having an airfoil portion, a dovetail portion, and a roll snubber. The dovetail portion having a radially inner surface. The roll snubber being provided on the radially inner surface. The radially inner surface spaced from the slot to define a gap therebetween.

Turbine engine including a composite airfoil assembly having a dovetail portion

A composite blade assembly for a turbine engine. The composite blade assembly having a core, a first skin and a second skin. The core having a composite structure. The first skin having at least one composite ply. The second skin having at least one composite ply. The first skin having a first radius. The second skin having a second radius.

Composite airfoil assembly having a dovetail portion

A turbine engine having a disk, a composite airfoil assembly and a pitch snubber. The disk having a slot. The composite airfoil assembly having an airfoil portion and a dovetail portion. The dovetail portion having a radially inner surface spaced from the slot to define a gap therebetween. The pitch snubber being provided on one of the slot or the radially inner surface of the dovetail portion.

Turbine engine with a composite-airfoil assembly having a dovetail portion

A guide vane assembly for a nacelle of a gas turbine engine includes a forward vane and an aft vane. The aft vane is located aft of the forward vane and forward of a plurality of fan blades. The forward vane defines a fixed pitch angle and the aft vane is movable between a first pitch angle and a second pitch angle.

Guide vane assembly with fixed and variable pitch inlet guide vanes

A blade is provided. The blade comprises a plurality of a first composite fiber plies and a plurality of a second composite fiber plies. Ends of the second fiber plies are staggered such that interlock between the first composite fiber plies and the second composite fiber plies is formed in a region where the second composite fiber plies end and meet with the first composite fiber plies. The blades are used for an engine of an aircraft.

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Loveland, OH, United States of America

Gary Willard Bryant, Jr