Abstract: Disclosed herein is a composite part for an airplane engine comprising polymer selected from polyimide, polyamide-imide, polyether imides, polybenzimidazole, or blends thereof, and carbonaceous filler, which in combination provides thermal stability and wear resistance. Optionally, the composite may comprise particulate.

Abstract: Disclosed herein is a composite part for an airplane engine comprising polymer selected from polyimide, polyamide-imide, polyether imides, polybenzimidazole, or blends thereof, and carbonaceous filler, which in combination provides thermal stability and wear resistance. Optionally, the composite may comprise particulate.

Abstract: This invention relates to a composite ring or segment of a ring, having use as a shroud of an airplane engine, comprising about 20 to about 70 weight percent of the thermoplastic polymer and about 30 to about 80 weight percent of the carbon fiber, and having a heat deflection temperature of at least 230° C. at 1.8 MPa as determined according to ASTM D648, and which provides thermal stability and wear resistance.

Abstract: The present invention is an improved composite clamp having a greatly reduced profile, eliminating most of the block portion of the prior art clamp to substantially reduce the weight. The composite clamp of the present invention can be appropriately described as a “composite strap clamp”. The clamping sections are molded in an arcuate shape without the presence of block material. To provide high strength, reinforcing fibers comprising structural woven carbon fiber cloth are used together with a thermoplastic, thermoset, or thermosettable polymer. Continuous reinforcing fibers extend longitudinally through the clamping sections to provide high strength and low delamination.