United Technologies Corporation

Scott C Billings

Michael A Weisse

James Olaf Hansen

Ethan C Drew

Edward J Gallagher

Darryl Whitlow

David P Houston

William R Graves

Venkatarama K Seetharaman

Konstantinos Panagiotis Giannakopoulos

Sue-Li Chuang

Jason Elliott

William D Owen

Zhen Wu

Mani Sadeghi

Jay Thomas Abraham

Michael K Gottschalk

Jason Elliot

Ethan Drew

A dovetail root of a fan blade configured for operation within the fan assembly of a gas turbine engine. The dovetail root is imparted with a compressive residual stress layer along the outer faces of the dovetail root preventing crack formation within the dovetail root when the gas turbine engine is in operation. To further protect and structurally enhance the dovetail root, a wear covering is disposed on the dovetail root. The wear covering may consist of a composite laminate layer that is bonded to the metallic core of the dovetail root providing additional cracking protection of the dovetail root when the gas turbine engine is in operation.

Fan blade root

In one exemplary embodiment, an airfoil for a turbine engine includes an airfoil that has pressure and suction sides and extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve that corresponds to a relationship between a leading edge dihedral and a span position. The leading edge dihedral has a portion of the curve with a change in dihedral in the range of 90% to 100% span position of greater than 10&#xb0;. A positive dihedral corresponds to suction side-leaning. A negative dihedral corresponds to pressure side-leaning.

Gas turbine engine airfoil

A fan blade of a gas turbine engine includes an airfoil, a root received in a slot of a hub, and a wear pad covering at least a portion of the root and made of an integrally bonded woven composite laminate.

Wear pad to prevent cracking of fan blade

A fan section for a gas turbine engine includes a fan hub having a slot. A platform is supported by the fan hub. A fan blade has a root that is received in the slot. A wear pad is provided between the fan hub and the root and includes a flap integral with the wear pad to provide a seal relative to the platform. A fan blade for a gas turbine engine includes an airfoil extending from a root. A wear pad is secured to the root and has a free end providing a flap canted toward the root.

Integral fan blade wear pad and platform seal

A turbine rotor balancing system comprises a circumferential array of mounting features. One or more balance weights are each mounted to the respective associated said mounting feature. Each balance weight comprises: a front wall along the forward face of the mounting feature; an aft wall along the aft face of the mounting feature; and a radially inboard wall. One or more fasteners each extend at least partially through holes of the front wall and rear wall of an associated said balance weight and through a hole of the associated said mounting feature. An abutment surface of the rotor is positioned to engage an outboard end of at least one of the front wall and aft wall of each said balance weight to resist outward radial movement of the weight.

Turbomachine rotor balancing system

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Marlborough, CT, United States of America

Scott C Billings