| タイトル | Ultra high tip speed (670.6 m/sec) fan stage with composite rotor: Aerodynamic and mechanical design |
| 本文（外部サイト） | http://hdl.handle.net/2060/19770013157 |
| 著者（英） | Halle, J. E.; Burger, G. D.; Dundas, R. E. |
| 著者所属（英） | Pratt and Whitney Aircraft |
| 発行日 | 1977-03-01 |
| 言語 | eng |
| 内容記述 | A highly loaded, single-stage compressor having a tip speed of 670.6 m/sec was designed for the purpose of investigating very high tip speeds and high aerodynamic loadings to obtain high stage pressure ratios at acceptable levels of efficiency. The design pressure ratio is 2.8 at an adiabatic efficiency of 84.4%. Corrected design flow is 83.4 kg/sec; corrected design speed is 15,200 rpm; and rotor inlet tip diameter is 0.853 m. The rotor uses multiple-circular-arc airfoils from 0 to 15% span, precompression airfoils assuming single, strong oblique shocks from 21 to 43% span, and precompression airfoils assuming multiple oblique shocks from 52% span to the tip. Because of the high tip speeds, the rotor blades are designed to be fabricated of composite materials. Two composite materials were investigated: Courtaulds HTS graphite fiber in a Kerimid 601 polyimide matrix and the same fibers in a PMR polyimide matrix. In addition to providing a description of the aerodynamic and mechanical design of the 670.0 m/sec fan, discussion is presented of the results of structural tests of blades fabricated with both types of matrices. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 77N20101
PWA-5487
NASA-CR-135122 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/182827 |
