United Technologies Corporation

Raytheon Technologies Corporation

Jason Leroux

Gregory E Reinhardt

John C DiTomasso

Carl Brian Klinetob

Thomas B Hyatt

Steven D Roberts

Andrew Pope

Weston Behling

William Richard Ganoe

Robert B Fuller

John P Lucashu

Douglas J Morgan

Steven L Conner

David J Yudichak

Brian Klinetob

Integrally bladed rotors (IBRs) are described. The IBRs include a central hub, an outer rim defining an outer circumference of the central hub, the outer rim defining a plurality of platforms, a plurality of circumferentially distributed blades, wherein a blade extends from each of the plurality of platforms, a rotor slot arranged between two adjacent blades, wherein the rotor slot is defined by a cut within the outer rim, and a rotor slot insert installed within the rotor slot, the rotor slot insert sized and shaped to fit within the rotor slot and prevent air leakage from a first side of the central hub to a second side of the central hub through the rotor slot during operation of the integrally bladed rotor.

Inserts for slotted integrally bladed rotor

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 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

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 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

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Kensington, CT, United States of America

Jason Leroux