| タイトル | Orbital transfer vehicle oxygen turbopump technology. Volume 1: Design, fabrication, and hydrostatic bearing testing |
| 本文（外部サイト） | http://hdl.handle.net/2060/19910009861 |
| 著者（英） | Lorenc, S. A.; Sabiers, R. L.; Buckmann, P. S.; Hayden, W. R.; Shimp, N. R. |
| 著者所属（英） | GenCorp Aerojet |
| 発行日 | 1990-12-01 |
| 言語 | eng |
| 内容記述 | The design, fabrication, and initial testing of a rocket engine turbopump (TPA) for the delivery of high pressure liquid oxygen using hot oxygen for the turbine drive fluid are described. This TPA is basic to the dual expander engine which uses both oxygen and hydrogen as working fluids. Separate tasks addressed the key issue of materials for this TPA. All materials selections emphasized compatibility with hot oxygen. The OX TPA design uses a two-stage centrifugal pump driven by a single-stage axial turbine on a common shaft. The design includes ports for three shaft displacement/speed sensors, various temperature measurements, and accelerometers. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 91N19174
NAS 1.26:185175
AEROJET-2459-54-2-VOL-1
AD-A234629
NASA-CR-185175 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/133774 |
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