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Ceramic Matrix Composite Turbine Disk for Rocket EnginesNASA 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.
Document ID
20000036511
Acquisition Source
Marshall Space Flight Center
Document Type
Preprint (Draft being sent to journal)
Authors
Effinger, Mike
(NASA Marshall Space Flight Center Huntsville, AL United States)
Genge, Gary
(NASA Marshall Space Flight Center Huntsville, AL United States)
Kiser, Doug
(NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
September 8, 2013
Publication Date
January 1, 2000
Subject Category
Spacecraft Propulsion And Power
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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