| タイトル | Fuel and oxidizer turbine loss analysis |
| 本文（外部サイト） | http://hdl.handle.net/2060/19850018589 |
| 著者（英） | Haas, J. E. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1985-04-01 |
| 言語 | eng |
| 内容記述 | The turbine losses for the fuel and oxidizer turbines at the FPL condition were assessed by a quasi-3D loss analysis method. This loss analysis method uses two flow codes - MERIDL and TSONIC - to calculate the flow velocities along the blade surfaces and endwalls. The velocities are then used as input to the boundary layer code - BLAYER - to calculate the friction losses due to incidence, secondary flow, and tip clearance. The loss analysis for the fuel turbine indicated an overall two-stage efficiency of about 90%. The largest loss was due to rotor tip clearance. The loss analysis for the oxidizer turbine is nearly completed. Results for the first stage of the two-stage design indicates an efficiency of about 80%, with high losses due to rotor incidence and blade and endwall friction. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 85N26900 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/566945 |
