COMPOSITE PARTS FOR AIRPLANE ENGINES

摘要

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.