General Electric Company

Ge Marmara Technology Center Muhendislik Hizmetleri Ltd

Benjamin Thomas Van Oflen

Nicholas Joseph Kray

Arthur William Sibbach

Gary Willard Bryant, Jr

Elzbieta Kryj-Kos

Michael John Franks

Nicholas M Daggett

Tod Winton Davis

Li Zheng

Douglas Lorrimer Armstrong

Daryl John Burford

Pawel Pres

Necip Adali

Tomas Muchenik

A turbine engine with an engine core defining an engine centerline and comprising a rotor assembly and a stator assembly. The turbine engine including a primary stage of airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor assembly. A subsidiary stage of airfoils located upstream of the primary stage of airfoils and circumferentially arranged about the engine centerline.

Turbine engine with a primary stage of airfoils and a subsidiary stage of airfoils

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 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 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

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Cincinnati, OH, United States of America

Benjamin Thomas Van Oflen