Abstract: A method for assembling a fan platform for a gas turbine engine is provided. The method includes determining an area of vulnerability to impact and erosion damage across the platform, forming a sheet of cladding metal to substantially conform to a contour of the identified area of vulnerability of the platform, and bonding the cladding metal to the identified area of vulnerability.

Abstract: A composite article, for example a blading member of a gas turbine engine, comprising a plurality of stacked layers of in-plane reinforcing fibers bonded together with a matrix resin is provided with enhanced resistance to impact cracking, material loss and/or delamination through use of a plurality of spaced apart reinforcing pins disposed into the article at an angle to the stacked layers, in one form disposed in a selected article region generally to resist strain energy generated during operation of the region. In another form, enhanced resistance is provided through the combination of a matrix resin including properties comprising a tensile strain property of at least 5% and a K1c toughness of at least about 850 psi-inch1/2, and a plurality of spaced apart reinforcing pins disposed into the article at an angle to the stacked layers.

Abstract: A composite article, for example a blading member of a gas turbine engine, comprising a plurality of stacked layers of in-plane reinforcing fibers bonded together with a matrix resin is provided with enhanced resistance to impact cracking, material loss and/or delamination through use of a plurality of spaced apart reinforcing pins disposed into the article at an angle to the stacked layers, in one form disposed in a selected article region generally to resist strain energy generated during operation of the region. In another form, enhanced resistance is provided through the combination of a matrix resin including properties comprising a tensile strain property of at least 5% and a K1c toughness of at least about 850 psi·inch1/2, and a plurality of spaced apart reinforcing pins disposed into the article at an angle to the stacked layers.

Abstract: Increased impact resistance capability is achieved in a cost and weight efficient manner by providing a spinner made of a 3-D orthogonal woven composite material. The spinner defines a generally conical shell having a plurality of axial rib stiffeners and at least one circumferential rib stiffener integrally formed thereon. The combination of the integral rib stiffeners with the 3-D orthogonal woven composite material results in a substantially greater torsional stiffness. The use of the 3-D orthogonal woven composite material also eliminates delamination found in laminated composite spinners.

Abstract: A rotator member, for example an airfoil of a rotating blade, is provided with additional stiffness in a radially outer portion of the member by including in the outer portion at least one corrugation extending generally along the width, for example chordwise, of the member.

Abstract: A method and apparatus for achieving a fluid tight seal of a fluid coupling having an axis, wherein a spring interposed between a coupling nut and an inner member of a first coupling element is compressed when the coupling nut is engaged with a second coupling element and rotated in a tightening direction such that complementary sealing surfaces between the first and second coupling elements are axially pre-loaded to achieve a fluid tight seal. A fluid tight seal is dependent on the axial compression of the spring, indicated by the axial location of the coupling nut with respect to the inner member and second coupling element, and is visually indicated by the rotational relationship of the coupling nut and the second coupling element.

Abstract: A one piece inner cowling for a bifurcated fan duct is provided having an integral core cowl and radially extending bifurcation sidewalls for use in a bifurcated fan bypass duct of a turbofan engine. In the preferred embodiment the sidewalls extend substantially to the end of the fan duct and the core cowl extends substantially between the fan and turbine frames. The cowling is preferably made of a composite material, preferably graphite/PMR-15 and provisions are made for mechanically attaching the sidewalls to an outer cowl. The inner cowling and outer cowl assembly form one half of a bifurcated fan duct assembly for being pivotally attached to a turbofan mounting pylon and includes suitable latching apparatus for accessing the core engine by pivotally opening the mirror image bifurcated fan duct assemblies on either side of the engine.