United Technologies Corporation

Hamilton Sundstrand Corporation

Raytheon Technologies Corporation

Carl Brian Klinetob

Gregory E Reinhardt

Steven J Feigleson

John C DiTomasso

Thomas B Hyatt

Phillip Alexander

Jason Leroux

Michael Parkin

Andrew Pope

William Richard Ganoe

Brian P Huth

Douglas J Morgan

David R Lyders

Steven Clarkson

Christopher John Feeney

Thomas D Kasprow

Rajiv A Naik

Nicholas D Stilin

Myron Klein

Paul Thomas Rembish

Peter Ventura

John H Vontell, Sr

John P Lucashu

Steven L Conner

Christian A Carroll

James Allen Eley

Stephen J Lindahl

Allan J Brockett

David J Yudichak

Myron L Klein

Jr William Richard Ganoe

A vibration damping assembly and a method of damping vibration in a gas turbine engine are disclosed. The vibration damping assembly includes a strut configured to couple a fan case and turbine engine case of a turbine engine, a strut cavity disposed within the strut, and vibration damping media disposed in the strut cavity.

Vibration damping assembly and method of damping vibration in a gas turbine engine

A turbofan engine structural guide vane is mounted to a forward bulkhead of a core engine case structure at an inner end and to a fan case at an outer end. A plurality of shear pins extend from the aft portion of the structural guide vane into a corresponding plurality of openings defined in the bulkhead for bearing circumferential loads.

Structural guide vane circumferential load bearing shear pin

A guide vane includes an airfoil with a first end and a second end. A platform is disposed at a first end of the airfoil, and a K-gusset is disposed on the platform opposite the airfoil. The K-gusset includes four bosses and ribs extending between the bosses in a 'K' configuration.

Structural guide vane outer diameter K gussets

An airfoil array includes a plurality of airfoils that differ in geometry over a plurality of geometry classes. An airfoil can include an airfoil body that has a first distinct piece and a second distinct piece that seats together with the first distinct piece. The first distinct piece and the second distinct piece include a mistake-proof feature configured such that the second distinct piece fully seats with the first distinct piece.

Airfoil array with airfoils that differ in geometry according to geometry classes

A guide vane for use in a gas turbine engine fan section has an airfoil extending between a radially inner platform and a radially outer platform. The radially inner platform has a radially outwardly facing surface from which the airfoil extends and a radially inwardly facing underside. The airfoil has a trailing edge extending to a leading edge. The underside is attached to a mount bracket and a main rib extending from the underside of the platform adjacent the trailing edge and in a direction generally towards the leading edge, and merging into a top surface on the mount bracket. A pair of shoulders is formed on each of two circumferential sides of the rib. Each of the shoulders is spaced from each other at a point on the shoulders connected into the top surface of the mount bracket. The shoulders extend circumferentially toward each other and the under surface.

Structural guide vane for gas turbine engine

A stationary guide vane includes a top platform, a bottom platform, and a vane body located between the top platform and the bottom platform. The vane body includes one or more cavities formed on a side wall of the vane body. One or more of the cavities are filled with vibration damping material and a vane cover is bonded to the vane body over the one or more containers.

Vibration damping for structural guide vanes

A structural guide vane for use in a gas turbine engine has a leading edge section, a trailing edge, a pressure surface and a suction surface. An erosion coating such as polyurethane resin is on the pressure surface and the suction surface. The leading edge of the vane is without the erosion coating and is bare metal. The vane is formed to include a plurality of pockets and bond shelves in the pressure surface side, and an epoxy bond line on the bond shelves holding a cover plate protected by the erosion coating.

Structural guide vane leading edge

A barrel washer comprising a convex portion, a concave portion, the concave portion configured to mate with the convex portion, such that the convex portion is only capable of rocking along a single axis within the concave portion. The barrel washer may be configured to prevent a bolt from rotating within the barrel washer. The barrel washer may be configured to relieve bending stress on the bolt as well as extraction of the bolt from the barrel washer. A surface of the concave portion may be coated with a lubricant. A surface of the convex portion may be coated in a lubricant. The barrel washer may be configured to couple a bolt to a flange that is couple to another flange. The convex portion may comprise a rocker. The barrel washer may be configured relieve bending stress on the bolt as a first flange moves relative to a second flange.

Moment relief barrel washer

A composite airfoil includes a core that has a three-dimensional network of fibers. The core defines an airfoil section and a root section. A composite skin covers a portion of the core excluding the root section.

Composite airfoil and turbine engine

A fan blade includes an airfoil and a dovetail at a radially inner end of the airfoil. The dovetail extends between first and second axial ends, and has outer circumferential faces. The dovetail is formed of relatively rigid composite material. Compliant material is placed on each outer circumferential face of the dovetail. The compliant material is less rigid than the composite material for forming the dovetail. In a second embodiment, the compliant layer may be positioned within the disk slots in a disk, such that the compliant layer will come in contact with circumferentially outer faces of the dovetail.

Fan blade dovetail with compliant layer

A disclosed structural guide vane for a gas turbine engine includes a strut defining a plurality of channels and a cover attached over the plurality of channels. The strut includes a first side defining a first surface of an airfoil and a second side including a plurality of channels. At least one of the plurality of channels defines a wall thickness of a portion of the first side that varies in a chord wise direction.

Structural guide vane internal topology

A device for providing a grounding path between an outer surface of a gas turbine aircraft engine and an inner surface of a gas turbine aircraft engine uses a structural guide vane (SGV) with a nonconductive coating on the surface. Bolts are put in bolt holes that have a bolt receiving cavity without the nonconductive coating. A washer and bolt are used so that attachment of the SGV to a surface provides a ground path from the SGV through the bolt, washer and nut for electrical engagement with a surface to which the bolt attaches the SGV.

Selective coating removal or masking for ground path

A composite fan blade having an airfoil with a leading edge and a trailing edge and a dovetail root includes a first pressure face and second pressure face, a lower horizontal face connecting the pressure faces at the bottom of the dovetail and a first and a second dovetail runout fillet connecting the pressure faces to the airfoil. The pressure faces are each angled outward at about 65 degrees to about 75 degrees from horizontal.

Composite fan blade dovetail root

The disclosed composite airfoil includes a three-dimensional composite core extending longitudinally and having a chord-wise direction. The core has a core in-plane thickness extending between opposing sides in a through-plane direction generally perpendicular to the chord-wise and longitudinal directions. A composite skin covers the opposing sides and has an exterior surface providing an airfoil contour. The skin includes a total skin in-plane thickness corresponding to a sum of thicknesses through the skin in the through-plane direction from each of the opposing sides to their adjoining exterior surface. A sum of the core in-plane and total skin in-plane thicknesses at a central portion of the composite airfoil is a total in-plane thickness. The total skin in-plane thickness at the central portion is less than 50% of the total in-plane thickness.

Gas turbine engine composite blade

A sheath for a fan airfoil having a leading edge, a trailing edge, a tip, a root, a suction side and a pressure side includes a solid portion to wrap around the airfoil lead edge and over the airfoil tip and means for securing the solid portion to the airfoil.

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East Haddam, CT, United States of America

Carl Brian Klinetob