United Technologies Corporation

Raytheon Technologies Corporation

Hamilton Sundstrand Corporation

Sikorsky Aircraft Corporation

Rtx Corporation

Rajiv A Naik

John D Riehl

Larry Foster

Darin S Lussier

Sreenivasa R Voleti

Thomas J Robertson, Jr

Mark W Costa

Carl Brian Klinetob

Phillip Alexander

Michael Parkin

Jinkyu Choi

Brian P Huth

Steven Clarke

Steven R Clarke

A gas turbine engine and a composite apparatus is disclosed. The gas turbine engine includes a composite apparatus body formed from a composite material, the composite material including a three dimensional preform, the three dimensional preform including a plurality of warp fibers disposed in a warp direction in a first plane, a plurality of fill fibers disposed in a fill direction, wherein the fill direction is perpendicular to the warp direction in the first plane, a plurality of z-yarn fibers disposed in a z-yarn direction, wherein the z-yarn direction intersects the warp direction through the first plane, and a plurality of bias fibers disposed in a bias direction, wherein the bias direction is not aligned with the warp direction and the fill direction.

Gas-turbine engine composite components with integral 3-D woven off-axis reinforcement

A composite article including a multiple of composite layers impregnated with a polymer matrix; and a nanotube material that facilitates a mechanical interlock between at least two of the multiple of composite layers. A method of manufacturing a composite article including a multiple of composite layers within a polymer matrix; and distributing a nanotube material between at least two of the multiple of composite layers to facilitate a mechanical interlock between the at least two of the multiple of composite layers adjacent an otherwise relatively low strength interlaminar interface region of the composite article.

Nanotube enhancement of interlaminar performance for a composite component

A coating bond test method includes, attaching with an adhesive a pull-off bar to a coating on a planar surface of a substrate for which a normal bond strength between the coating and the substrate is sought, reducing a first area defined by an interface between the substrate and the coating to a value less than a second area defined by an interface between the adhesive and the coating, urging the pull-off bar away from the substrate in a direction normal to the planar surface until failure occurs, and recording a load at which failure occurred.

Coating bond test method and method of making a specimen for testing bond strength of a coating

A fan case for a gas turbine engine includes an outer case defined about an engine axis and a hard ballistic liner defined about the engine axis, the hard ballistic liner within the outer case.

Case with ballistic liner

A composite blade has a root and a tip in a spanwise direction and a leading edge and a trailing edge in a chordwise direction. The composite blade includes a three-dimensional woven preform having weft yarns and warp yarns. The weft yarns extend in the spanwise direction of the composite blade. The warp yarns interweave the weft yarns and extend in the chordwise direction of the blade.

Three-dimensionally woven composite blade with spanwise weft yarns

A fan case for a gas turbine engine includes a composite fan containment case having an outer surface, a front and a rear. An attachment flange and a mounting ring are respectively provided on the front and the rear. A bolt attachment is supported on the outer surface. The composite fan containment case has a containment area that is configured to be axially aligned with a fan blade. A ballistic liner is arranged in the containment area.

Composite fan containment case assembly

A composite blade includes a preform and a binder. The preform is a preform of yarns woven in three-dimensions and has a tip region, a root region and an intermediate region. The intermediate region is positioned between the tip region and the root region. The yarns comprise warp yarns and weft yarns. The warp yarns form a longitudinal axis. The weft yarns are positioned at a 90 degree angle to the warp yarns. The weft yarns increase in yarn size as determined by filament count along the longitudinal axis to change the thickness of the preform. The binder maintains the relative positions of the preform yarns.

Integrally woven composite fan blade using progressively larger weft yarns

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.

Growing community of inventors

Glastonbury, CT, United States of America

Rajiv A Naik