| タイトル | Experimental Evaluation of a Subscale Gaseous Hydrogen/gaseous Oxygen Coaxial Rocket Injector |
| 本文（外部サイト） | http://hdl.handle.net/2060/20030003786 |
| 著者（英） | Farhangi, Shahram; Sutton, Robert; Smith, Timothy D.; Klem, Mark D.; Breisacher, Kevin J. |
| 著者所属（英） | NASA Glenn Research Center |
| 発行日 | 2002-11-01 |
| 言語 | eng |
| 内容記述 | The next generation reusable launch vehicle may utilize a Full-Flow Stage Combustion (FFSC) rocket engine cycle. One of the key technologies required is the development of an injector that uses gaseous oxygen and gaseous hydrogen as propellants. Gas-gas propellant injection provides an engine with increased stability margin over a range of throttle set points. This paper summarizes an injector design and testing effort that evaluated a coaxial rocket injector for use with gaseous oxygen and gaseous hydrogen propellants. A total of 19 hot-fire tests were conducted up to a chamber pressure of 1030 psia, over a range of 3.3 to 6.7 for injector element mixture ratio. Post-test condition of the hardware was also used to assess injector face cooling. Results show that high combustion performance levels could be achieved with gas-gas propellants and there were no problems with excessive face heating for the conditions tested. |
| NASA分類 | Spacecraft Propulsion and Power |
| レポートNO | E-13652
NAS 1.15:211982
NASA/TM-2002-211982 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/63486 |
