| タイトル | An integral equation solution for multistage turbomachinery design calculations |
| 本文（外部サイト） | http://hdl.handle.net/2060/19930006332 |
| 著者（英） | Mcfarland, Eric R. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1993-01-01 |
| 言語 | eng |
| 内容記述 | A method was developed to calculate flows in multistage turbomachinery. The method is an extension of quasi-three-dimensional blade-to-blade solution methods. Governing equations for steady compressible inviscid flow are linearized by introducing approximations. The linearized flow equations are solved using integral equation techniques. The flows through both stationary and rotating blade rows are determined in a single calculation. Multiple bodies can be modelled for each blade row, so that arbitrary blade counts can be analyzed. The method's benefits are its speed and versatility. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 93N15521
NASA-TM-105970
E-7493
NAS 1.15:105970 |
| 権利 | No Copyright |
