| タイトル | Study of controlled diffusion stator blading |
| 本文（外部サイト） | http://hdl.handle.net/2060/19850009749 |
| 著者（英） | Canal, E.; Brooky, J. D.; Behlke, R. F. |
| 著者所属（英） | Pratt and Whitney Aircraft Group |
| 発行日 | 1983-03-01 |
| 言語 | eng |
| 内容記述 | Tests were conducted on a high tip speed, highly loaded front compressor stage having low aspect ratio rotor and stator airfoils. The stator airfoils were designed by the controlled diffusion procedure recently developed by P&WA for designing transonic cascade airfoils. The rotor blades consisted of multiple-circular-arc airfoil sections. The stage had a tip speed of 442 m/sec (1450 ft/sec), a hub/tip ratio of 0.597, a rotor aspect ratio of 1.3, and a stator aspect ratio of 1.45. At design speed the rotor-stator stage achieved an adiabatic efficiency of 89.1% at design flow and pressure ratio. Surge margin was 14%. The stage efficiency exceeded the design goal by 0.6 percentage points. The rotor efficiency was 92.4%, exceeding design by 0.3 percentage points. The controlled diffusion stator demonstrated a lower minimum loss over the multiple-circular-arc stator from the root to 70 percent span. A surge diffusion factor of 0.72 was reached at both the rotor tip and the stator root. The NAS3-22008 program demonstrated its intent: high efficiency and loading levels with low aspect ratio blades and the controlled diffusion stator in the unfavorable front stage environment. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 85N18058
NAS 1.26:167995
PWA-5698-77
NASA-CR-167995 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/157271 |
