| タイトル | Fastrac Gas Generator Testing |
| 本文（外部サイト） | http://hdl.handle.net/2060/20020050413 |
| 著者（英） | Nesman, Tomas E.; Dennis, Jay |
| 著者所属（英） | NASA Marshall Space Flight Center |
| 発行日 | 2001-07-01 |
| 言語 | eng |
| 内容記述 | A rocket engine gas generator component development test was recently conducted at the Marshall Space Flight Center. This gas generator is intended to power a rocket engine turbopump by the combustion of Lox and RP-1. The testing demonstrated design requirements for start sequence, wall compatibility, performance, and stable combustion. During testing the gas generator injector was modified to improve distribution of outer wall coolant and the igniter boss was modified to investigate the use of a pyrotechnic igniter. Expected chamber pressure oscillations at longitudinal acoustic mode were measured for three different chamber lengths tested. High amplitude discrete oscillations resulted in the chamber-alone configurations when chamber acoustic modes coupled with feed-system acoustics modes. For the full gas generator configuration, which included a turbine inlet manifold, high amplitude oscillations occurred only at off-design very low power levels. This testing led to a successful gas generator design for the Fastrac 60,000 lb thrust engine. |
| NASA分類 | Spacecraft Propulsion and Power |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/565259 |
