General Electric Company

Theodore R Ingling

Gary Willard Bryant, Jr

Tod Winton Davis

Max Robert Farson

William Elliot Bachrach

Walter D Howard

Gary B Manharth

Stephanie Glynn Cotten

James Francis Brown

An airfoil assembly for a turbine engine includes an airfoil with an outer wall having a pressure side and a suction side, the airfoil extending axially between a leading edge and a trailing edge to define a chord-wise direction and also extending radially between a root and a tip to define a span-wise direction. An aperture and at least one slot can define at least a portion of a release plane extending through the outer wall.

Turbine engine airfoil assembly

A lightweight, impact-resistant gas turbine blade, such as an aircraft engine fan blade, has a metal solid section, composite or structural/syntactic foam segments, and metal solid spars all attached together to define an airfoil portion. The solid section includes the leading edge, blade tip, and trailing edge. The segments together are bounded in part by the solid section near the leading edge, blade tip, and trailing edge. The solid spars separate and are attached to the segments.

Partially-metallic blade for a gas turbine

In a turbofan engine a fan designed for reduced damage during a blade-out condition wherein the fan blade airfoil is disposed asymmetrically on the platform and includes a forwardly displaced leading edge. The platform is configured to make early contact with a following airfoil upon blade-out.

Fan blade for blade-out protection

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Loveland, OH, United States of America

Theodore R Ingling