Patent ID: 8198356
Filing Date: 2012-06-12
Classification: C08K,Y10T

Abstract:
1. An aircraft engine composite part comprising: from about 40 to about 90 weight percent of a polymer component selected from the group consisting of polyimide, polyamide-imide, polyether imide, polybenzimidazole, and blends thereof; at least about 9 weight percent of a carbonaceous filler component, where said carbonaceous filler consists of powdered graphite or flake graphite optionally, particulate up to about 51 weight percent, where said particulate is selected from the group consisting of talc, mica, wollastonite, kaolinite, and sepiolite; wherein the total of all components of the composite is 100 weight percent; where carbon fibers are excluded from the composite; and wherein the composite has a thermal oxidative weight loss of less than 5% when determined after heating at 700° F. (371° C.) for 100 hours at 70 psi (0.48 MPa) in air, the air being exchanged at a rate of 5 times/hour, and has a dynamic coefficient of friction of less than 0.5 and wherein said composite part is an inner shroud or a segment of an inner shroud.