United Technologies Corporation

Raytheon Technologies Corporation

Thomas B Hyatt

Carl Brian Klinetob

William Richard Ganoe

Jason Leroux

Gregory E Reinhardt

Steven J Feigleson

Andrew Pope

Paul Thomas Rembish

John P Lucashu

Douglas J Morgan

Steven L Conner

Brian Klinetob

William Richard Ganoe Jr

A structural guide vane may include a first root, a second root positioned radially outward from the first root and a truss extending between the first root and second root. The truss may be made of a first material. The guide vane may further include an overmold made of a second material that surrounds the truss to form an airfoil.

Gas turbine engine structural guide vanes

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 method of forming a guide vane is disclosed. The method includes forming a vane blank with sufficient material to fabricate the guide vane in accordance with any one of a plurality of different vane classes. The vane blank is inspected for material inconsistencies, and material is removed from the vane blank to form a desired guide vane in accordance with one of the plurality of vane classes. The inspection process includes disregarding at least one material inconsistency in a region of the vane blank that is removed to form the guide vane.

Structural guide vane sonic shape and inspection

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 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 fastener includes a fastening portion including a head, a threaded portion having a first diameter, and a shank having a second diameter that is less than the first diameter. The shank is located between the head and the threaded portion. A sleeve surrounds the shank. The sleeve and the shank are uncoupled.

Pitch diameter shank bolt with shear sleeve

An example method of assembling a particle damped gas turbine engine component according to an exemplary aspect of the present disclosure includes, among other things, holding damping media within a cavity of a gas turbine engine component using magnetic force.

Retention of damping media

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 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

No flange damage wedge lock washers are disclosed. The washers may comprise an upper washer and a lower washer. The lower washer may have a generally smooth bottom surface and at least one means for securement. The at least one means for securement may be arranged to keep together the lower washer and a flange without causing damage to the flange. A locking fastener assembly which comprises no flange damage wedge lock washers is also disclosed. The locking fastener assembly may include a lower washer having a generally smooth bottom surface and at least one means for securement. A method of manufacturing a locking fastener assembly which comprises no flange damage wedge lock washers is also disclosed. The locking fastener assembly of the method may include a lower washer having a generally smooth bottom surface and at least one means for securement.

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Cromwell, CT, United States of America

Thomas B Hyatt