| タイトル | Evaluation of Vortex Chamber Concepts for Liquid Rocket Engine Applications |
| 本文（外部サイト） | http://hdl.handle.net/2060/20010020208 |
| 著者（英） | Knuth, Williams; Turner, James E.; Michaels, Scott; Trinh, Huu Phuoc |
| 著者所属（英） | NASA Marshall Space Flight Center |
| 発行日 | 2000-01-01 |
| 言語 | eng |
| 内容記述 | Rocket-based combined-cycle engines (RBBC) being considered at NASA for future generation launch vehicles feature clusters of small rocket thrusters as part of the engine components. Depending on specific RBBC concepts, these thrusters may be operated at various operating conditions including power level and/or propellant mixture ratio variations. To pursue technology developments for future launch vehicles, NASA/Marshall Space Flight Center (MSFC) is examining vortex chamber concepts for the subject cycle engine application. Past studies indicated that the vortex chamber schemes potentially have a number of advantages over conventional chamber methods. Due to the nature of the vortex flow, relatively cooler propellant streams tend to flow along the chamber wall. Hence, the thruster chamber can be operated without the need of any cooling techniques. This vortex flow also creates strong turbulence, which promotes the propellant mixing process. Consequently, the subject chamber concepts not only offer the system simplicity but they also would enhance the combustion performance. The test results showed that the chamber performance was markedly high even at a low chamber length-to- diameter ratio (L/D). This incentive can be translated to a convenience in the thrust chamber packaging. |
| NASA分類 | Spacecraft Propulsion and Power |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/226417 |
