| タイトル | Investigation of the Performance of an Axial-Flow-Pump Stage Designed by the Blade-Element Theory: Blade-Element Data |
| 本文（外部サイト） | http://hdl.handle.net/2060/19980228119 |
| 著者（英） | Soltis, Richard F.; Crouse, James E.; Montgomery, John C. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1961-12-01 |
| 言語 | eng |
| 内容記述 | An axial-flow-pump stage was designed by utilizing blade-element methods in conjunction with axial-flow-compressor blade-element theory. This report presents the blade-element data of the pump stage in both the noncavitating and cavitating conditions. The noncavitating blade- element performance is compared with design rules. The results indicated that some modification of the compressor design equations for computing minimum-loss incidence and deviation angles may be necessary for application to an axial-flow-pump design. Minimum values of observed rotor loss were slightly lower than anticipated from compressor results. At the design flow coefficient the rotor-blade elements were not operating at the reference incidence angles, and the experimental efficiency was lower than the design value. The observed head rise was very close to the design. An attempt was made to estimate the potential of this rotor by using the minimum measured values of loss coefficient and observed energy input at the design flow. Performance of the pump at a suction specific speed of approximately 13,000 (cavitation number k approximately equals 0.12) showed only a slight dropoff in performance in the cavitation inception region from the noncavitating results. The observed performance at a suction specific speed of approximately 16,000 (k approximately equals 0.09) is also presented for comparison. |
| NASA分類 | Mechanical Engineering |
| レポートNO | NASA-TN-D-1109
E-1127 |
| 権利 | No Copyright |
|
