Ceramic Matrix Composites for Rocket Engine Turbine Applications

[+] Author and Article Information
T. P. Herbell, A. J. Eckel

Lewis Research Center, Cleveland, OH 44135

J. Eng. Gas Turbines Power 115(1), 64-69 (Jan 01, 1993) (6 pages) doi:10.1115/1.2906687 History: Received February 04, 1992; Online April 24, 2008


A program to establish the potential for introducing fiber-reinforced ceramic matrix composites (FRCMC) in future rocket engine turbopumps was instituted in 1988. A brief summary of the overall program (both contract and in-house research) is presented. Tests at NASA Lewis include thermal upshocks in a hydrogen/oxygen test rig capable of generating heating rates up to 2500°C/s. Post-thermal upshock exposure evaluation includes the measurement of residual strength and failure analysis. Test results for monolithic ceramics and several FRCMCs are presented. Hydrogen compatibility was assessed by isothermal exposure of monolithic ceramics in high-temperature gaseous hydrogen plus water vapor.

Copyright © 1993 by The American Society of Mechanical Engineers
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