| タイトル | Air-Cooled Turbine Blades with Tip Cap For Improved Leading-Edge Cooling |
| 本文（外部サイト） | http://hdl.handle.net/2060/19980228322 |
| 著者（英） | Morgan, William C.; Meyer, Andre J., Jr.; Calvert, Howard F. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1959-02-01 |
| 言語 | eng |
| 内容記述 | An investigation was conducted in a modified turbojet engine to determine the cooling characteristics of the semistrut corrugated air- cooled turbine blade and to compare and evaluate a leading-edge tip cap as a means for improving the leading-edge cooling characteristics of cooled turbine blades. Temperature data were obtained from uncapped air-cooled blades (blade A), cooled blades with the leading-edge tip area capped (blade B), and blades with slanted corrugations in addition to leading-edge tip caps (blade C). All data are for rated engine speed and turbine-inlet temperature (1660 F). A comparison of temperature data from blades A and B showed a leading-edge temperature reduction of about 130 F that could be attributed to the use of tip caps. Even better leading-edge cooling was obtained with blade C. Blade C also operated with the smallest chordwise temperature gradients of the blades tested, but tip-capped blade B operated with the lowest average chordwise temperature. According to a correlation of the experimental data, all three blade types 0 could operate satisfactorily with a turbine-inlet temperature of 2000 F and a coolant flow of 3 percent of engine mass flow or less, with an average chordwise temperature limit of 1400 F. Within the range of coolant flows investigated, however, only blade C could maintain a leading-edge temperature of 1400 F for a turbine-inlet temperature of 2000 F. |
| NASA分類 | Aircraft Propulsion and Power |
| レポートNO | NASA-MEMO-2-9-59E |
| 権利 | No Copyright |
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