General Electric Company

United States of America as Represented by the Secretary of the Air Force

Heidi J Stegemiller

Mark Joseph Mielke

Ahmad P Zahedi

James R Jamieson

Stephen W Mak

Aaron M Gilbert

Kohki Nishida

Steven R Manwaring

A turbine engine for an aircraft. The turbine engine includes a vane support and a vane. The vane support has a vane-facing surface. A first hook and a second hook extend from the vane-facing surface and define a channel therebetween. The vane includes an airfoil and an outer band connected to the airfoil. The outer band is positioned in the channel to form a gap between a support-facing surface of the outer band and the vane-facing surface under assembly conditions of the turbine engine. The vane-facing surface and the support-facing surface are shaped to form a contact configuration that occurs when, under an operating condition of the turbine engine, the vane flexes and at least a portion of the support-facing surface contacts the vane-facing surface over a contacting region to eliminate the gap over the contacting region.

Turbine engine including a vane support and a vane

An airfoil assembly for a turbo machine, the airfoil assembly including an airfoil defining a leading edge and a trailing edge, and further defining ends separated along a span of the airfoil; a shaft extended from the end of the airfoil; and a button surrounding at least a portion of the end of the airfoil, the button comprising a composite material.

Airfoil for a turbo machine

Vibrations within ceramic matrix and metal matrix composite materials are controlled by applying an excitation voltage to an array of piezoelectric actuators mounted to the surface of such materials. The actuators are driven in response to the phase shift of monochromatic light transmitted through a grid of optical fibers embedded within the composite materials. Applications include active vibration suppression, de-icing, and on-line structural integrity monitoring.

System and method for controlling deformation of a structure having a

A first hollow titanium MMC driveshaft portion is diffusion bonded to a third portion which in turn is fastened to a second superalloy portion via circumferentially positioned pins which are tightly fitted within aligned holed formed in the second and third driveshaft portions. The first, second and third portions are concentric with respect to the driveshaft centerline, and the pins are retained by means of a concentric retaining cylinder.

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Franklin, OH, United States of America

Heidi J Stegemiller