| タイトル | Experimental evaluation of a cooled radial-inflow turbine |
| 著者（英） | Dicicco, L. D.; Nowlin, Brent C.; Tirres, Lizet |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1993-06-01 |
| 言語 | eng |
| 内容記述 | Two 14.4 inch tip diameter rotors were installed and tested in the Small Engines Component Turbine Facility (SECTF) at NASA Lewis Research Center. The rotors, a solid and a cooled version of a radial-inflow turbine, were tested with a 15 vane stat or over a set of rotational speeds ranging from 80 to 120 percent design speed (17,500 to 21,500 rpm). The total-to-total stage pressure ratios ranged from 2.5 to 5.5. The data obtained at the equivalent conditions using the solid version of the rotor are presented with the cooled rotor data. A Reynolds number of 381,000 was maintained for both rotors, whose stages had a design mass flow of 4.0 lbm/sec, a design work level of 59.61 Btu/lbm, and a design efficiency of 87 percent. The results include mass flow data, turbine torque, turbine exit flow angles, stage efficiency, and rotor inlet and exit surveys. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 93A49685
AIAA PAPER 93-1795 |
| 権利 | Copyright |
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