United Technologies Corporation

Raytheon Technologies Corporation

Hamilton Sundstrand Corporation

Rtx Corporation

Michael Parkin

Carl Brian Klinetob

Phillip Alexander

Tracy A Propheter-Hinckley

Jonas S Banhos

Steven Clarkson

Thomas J Robertson, Jr

James Olaf Hansen

Colin J Kling

Charles R Watson

Christopher J Hertel

David R Lyders

Micah Beckman

Rajiv A Naik

Brandon A Gates

Brian P Huth

Joseph Rios

Mark Quinn

Osamuyimen A Oyegun

Thomas J Horn

Leland Wiegman

Leland M Wiegman

An assembly for forming a gas turbine engine according to an example of the present disclosure includes, among other things, a layup tool including a main body extending along a longitudinal axis and a flange extending radially from the main body, the flange defining an edge face slopes towards the main body to an axial face. At least one compression tool has a tool body having a first tool section and a second tool section extending transversely from the first tool section. The first tool section is translatable along a retention member in a first direction substantially perpendicular to the edge face such that relative movement causes the second tool section to apply a first compressive force on a composite article trapped between the axial face of the flange and the second tool section. A method of forming a gas turbine engine component is also disclosed.

Method of forming gas turbine engine components

Compression tool and method of forming gas turbine engine components

A method for assembling an airfoil includes pressing a blade body together with at least one of a blade sheath and a blade cover between a plunger and a die base to join the blade body to the blade sheath and/or the blade cover. The method can include transferring heat from the plunger and/or the die base to at least one of the blade body, the blade sheath and the blade cover to cure an adhesive.

Systems and methods for airfoil assembly

A composite article lay up comprising a first layer of resin impregnated fiber material and a second layer of resin impregnated fiber material. An open cell material is layered between the first layer and the second layer. The open cell material has no resin during a first stage of a resin cure cycle. The open cell material has passages configured to flow volatiles formed during the first stage of the resin cure cycle. The open cell material is configured to fill with the resin during a second stage of the resin cure cycle. The open cell material is configured to form an integral structure with the first layer and the second layer as part of the composite article at the completion of the resin cure cycle.

Enhanced volatile removal for composite layup

An airfoil for a gas turbine engine includes a substrate and a sheath providing an edge. A cured adhesive secures the sheath to the substrate. The cured adhesive has a fillet that extends beyond the edge that includes a mechanically worked finished surface. A method of manufacturing the airfoil includes the steps of securing a sheath to a substrate with adhesive, curing the adhesive, and mechanically removing a portion of the adhesive extending beyond the sheath.

Fan blade and method of manufacturing same

A turbine engine fan case () comprises a composite body member () circumscribing an axis () and having an annular mounting portion (), a segmented polymer member () along the annular mounting portion, and integrated therewith.

Fan cases and manufacture methods

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

An airfoil includes an airfoil body made of a first metal with a leading edge, a trailing edge, pressure side and suction side; a sheath with first and second flanks made of a second metal; a first layer of non-conductive material adhesively bonded between a portion of the end of the first flank and the airfoil body and extending beyond the end of the first flank on the pressure side; and a second layer of non-conductive material adhesively between a portion of the end of the second flank and the airfoil body and extending beyond the end of the second flank on the suction side.

Airfoil with galvanic corrosion preventive shim

A duct has: a first non-metallic member extending between a first end and a second end, at least at the first end having an outwardly-projecting flange portion; a metallic flange member having a sleeve extending between a first end and a second end and a flange extending outward from the sleeve and having a first face and a second face; and a second non-metallic member extending between a first end and a second end having an outwardly-projecting flange portion, the first non-metallic member flange portion mounted to the flange first face and the second non-metallic member flange portion mounted to the flange second face.

Composite ducts and methods

A method of forming a fan blade includes the step of positioning a piece of low density filler in a cavity of an inner exposed surface of a fan blade body. An upper surface of the piece of low density filler is located above the inner exposed surface of the fan blade body, and the low density filler has a density lower than a density of a material of the fan blade body. The method further includes the steps of positioning the fan blade body in a lower die of a press and applying pressure to the inner exposed surface of the fan blade body with an upper die of the press to compress the low density filler such that the upper surface of the piece of low density filler is approximately flush with the inner exposed surface of the fan blade body.

Method of securing low density filler in cavities of a blade body of a fan blade

A method of forming a fan blade includes the step of applying an adhesive layer around a leading edge of a fan blade body. The adhesive layer includes an adhesive film supported by a scrim cloth, and the adhesive layer contacts a portion of an inner surface of the fan blade body and a portion of an outer surface of the fan blade body. A leading edge sheath is positioned relative to the fan blade body such that a first flank and a second flank of the leading edge sheath is positioned over the portion of the inner surface and the portion of an outer surface, respectively, of the fan blade body. Pressure is applied to the first flank and the second flank of the leading edge sheath to secure the leading edge sheath to the blade body and curing the adhesive film.

Method of bonding a leading edge sheath to a blade body of a fan blade

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

An intermediate-manufactured composite airfoil includes first and second composite skins each having a plurality of fibers in a polymer matrix. A composite core is removably located between the first and second composite skins. The composite core includes a dry, three-dimensional, woven fiber network. The composite core may alternatively include a three-dimensional, woven fiber network in a fully cured polymer matrix.

Growing community of inventors

South Glastonbury, CT, United States of America

Michael Parkin