| タイトル | Ceramic Matrix Composite Turbine Disk for Rocket Engines |
| 著者（英） | Kiser, Doug; Genge, Gary; Effinger, Mike |
| 著者所属（英） | NASA Marshall Space Flight Center |
| 発行日 | 2000-01-01 |
| 言語 | eng |
| 内容記述 | 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. |
| NASA分類 | Spacecraft Propulsion and Power |
| 権利 | No Copyright |
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