General Electric Company

Unison Industries, Inc.

Balaraju Suresh

Abhijeet Jayshingrao Yadav

Nicholas Joseph Kray

Nitesh Jain

Gordon Tajiri

Yanzhe Yang

Dattu G V Jonnalagadda

Daniel Dyer

Sebastian Merin

Narayanan Payyoor

Frank Worthoff

Gary Willard Bryant, Jr

Suryarghya Chakrabarti

Nicholas M Daggett

Gary W Bryant

Abhishek Goverdhan

Amarnath Kakarla

Illya Emmanuel Arcos Perez

Ashish Rajput

Ricardo Hernandez Pandeli

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

An engine for an aircraft. The engine includes a rotating airfoil assembly, at least one actuator, a torque producing system, and a controller. The rotating airfoil assembly includes a rotation axis and a plurality of rotating airfoils configured to rotate about the rotation axis in a plane of rotation. The at least one actuator is operable to change the plane of rotation of the plurality of rotating airfoils. The torque producing system is coupled to the rotating airfoil assembly and configured to rotate the rotating airfoil assembly about the rotation axis of the rotating airfoil assembly. The controller is configured to determine that the aircraft has an angle of attack and to operate the at least one actuator to change the plane of rotation of the plurality of rotating airfoils based on the angle of attack.

Rotating airfoil assembly for an aircraft engine

A strengthened component includes a sacrificial material mold of the component having an outer surface, an insert having an inner surface and an outer surface opposite and spaced from the inner surface such that the strengthening insert inner surface abuts the mold outer surface, and a metallic layer deposited over the exposed mold outer surface and the exposed strengthening insert outer surface, where the sacrificial material mold is removed from the strengthened component.

Methods of forming a strengthened component

A component and blade assembly for a turbine engine, the component having a wall bounding an interior and defining an exterior surface extending radially between a leading edge and a trailing edge to define a chordwise direction, and between a hub and a tip to define a spanwise direction. A metallic spar extending from the hub in the spanwise direction into the interior, the metallic spar defining a socket. A composite spar extending in the spanwise direction between a spar root and a spar tip, the spar root received in the socket. The component further having a stiffener.

Component with spar assembly for a turbine engine

An airfoil for a turbine engine having a spar assembly. The spar assembly including a composite spar, a metallic hub, and a composite body. The metallic hub can receive a portion of the composite spar at an interior surface to define an overlapping region. The composite body is located at the overlapping region.

Airfoil having a spar assembly for a turbine engine

A method of forming a strengthened component includes forming a sacrificial material into a mold of the component having an outer surface, disposing an insert having an inner surface and an outer surface opposite and spaced from the inner surface such that the strengthening insert inner surface abuts the mold outer surface, forming the component by way of electrodisposition of a metallic layer over the exposed mold outer surface and the exposed strengthening insert outer surface, and removing the sacrificial material from the component.

Growing community of inventors

Bengaluru, India

Balaraju Suresh