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- W84130147 abstract "NASA has recently completed testing of a ceramic matrix composite (CMC), integrally bladed disk (blisk) for rocket engine turbopumps. The turbopump's main function is to bring propellants from the tank to the combustion chamber at optimal pressures, temperatures, and flow rates. Advantages realized by using CMC blisks are increases in safety by increasing temperature margins and decreasing costs by increasing turbopump performance. A multidisciplinary team, involving materials, design, structural analysis, nondestructive inspection government, academia, and industry experts, was formed to accomplish the 4.5 year effort. This article will review some of the background and accomplishments of the CMC Blisk Program relative to the benefits of this technology." @default.
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- W84130147 date "2000-01-01" @default.
- W84130147 modified "2023-09-23" @default.
- W84130147 title "Ceramic Matrix Composite Turbine Disk for Rocket Engines" @default.
- W84130147 hasPublicationYear "2000" @default.
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