| タイトル | The Effect of Vane-Blade Spacing on Transonic Turbine Stage Performance |
| 著者（英） | Griffin, J. W.; Delaney, R. A.; Kelecy, F. J. |
| 著者所属（英） | Allison Engine Co. |
| 発行日 | 1996-01-01 |
| 言語 | eng |
| 内容記述 | This paper presents the results of a computational study on the effect of axial spacing between the vane and blade rows of a transonic turbine stage. The study was performed on the mid-span section of a high-pressure turbine stage using a quasi-3D, unsteady Navier-Stokes solver that provides a fully interactive vane-blade unsteady flow solution. Three different cases were considered, corresponding to axial spacings of 20%, 40%, and 60% of the vane axial chord. The calculated vane and blade pressure distributions for the 40 percent case were found to compare favorably with experimental measurements acquired in a short-duration shock tunnel. In addition, the analysis shows a marked increase in the amplitude of the unsteady pressure fluctuations on the vane and blade surfaces as the spacing decreases. Time-averaged stage adiabatic efficiency predictions for each case are presented to show the effect of spacing on aerodynamic performance. |
| NASA分類 | Aircraft Propulsion and Power |
| レポートNO | 96N26968 |
| 権利 | Copyright, Distribution within the U.S. granted by agreement |
|
