Abstract: Metal darts are captured either in bonded assembly or in riveted assembly with composite airfoil skins. The darts have a thin fin extending rearward with a dam at its rear end forming a hot air duct on either side of the fin. As hot compressor bleed air is diverted down through the fin duct, heat is transferred forward to the dart leading edge. The fin may contain ripples or other perturbances to improve heat transfer if necessary. Sufficient heat should be transferred to inhibit ice buildup on the final coating that covers the entire airfoil and further provides FOD protection by having a metal leading edge.

Abstract: A flush mounting fastener system for threadably attaching a threaded member to a plate or shell structure is described which comprises in one representative embodiment an internally threaded bushing flanged on a first end for attachment to the housing within a hole of preselected size in the housing, a plurality of circumferentially spaced crenelations of preselected size and spacing on the second end of the bushing, an insert threaded on the outer surface for threadably engaging the bushing and on the inner surface for threadably attaching a threaded member to the housing structure, and a plurality of tangs on one end of the insert corresponding in size and spacing with the spaced crenelations in the bushing and being radially outwardly bendable into spaces between the crenelations to lock the insert within the bushing.

Abstract: A fluid-cooled article, such as a turbomachinery blading member, is provided with a fluid passage by a method of depositing a first material on a work surface of a mandrel by low pressure plasma deposition. A first member thus generated is separated from the mandrel. In one form, an inner surface of the first member is provided with a surface groove. After depositing a sacrificial material in the groove, a cover material is applied to entrap the sacrificial material. Removal of the sacrificial material provides the fluid passage.

Abstract: A fan for use as a front fan or in the lift fan system with aircraft jet engines having blades supported by a segmented hub platform and a segmented tip platform which are supported by hub support hoops and tip support hoops. The blades are secured to the hub platform segments and tip platform segments by composite pre-preg pin stock which is inserted in holes in the tip platform, the hub platform and fan blades. The pins are placed under axial compression to expand the pin diameter to provide a precise fit. Channel members are provided between the tip hoops and the blades. Some of the channels have extensions which form seals.

Abstract: A wheel comprising a plurality of wheel plies, each wheel ply including concentric inner and outer hoops and a plurality of circumferentially spaced spoke loops therebetween, wherein each of the spoke loops is entrapped within the hoops. In one embodiment the wheel comprises a laminate of alternating wheel plies and intermediate plies bonded together. A spoked frame comprising one or more of the wheels is provided, the frame including fairing means to substantially envelope the spokes and retain the individual wheels in their proper spacial relationship.