التفاصيل البيبلوغرافية
| العنوان: |
Numerical Investigation of the Influence of Real World Blade Profile Variations on the Aerodynamic Performance of Transonic Nozzle Guide Vanes. |
| المؤلفون: |
Edwards, R., Asghar, A., Woodason, R., LaViolette, M., Boulama, K. Goni, Allan, W. D. E. |
| المصدر: |
Journal of Turbomachinery; Mar2012, Vol. 134 Issue 2, p21014.1-21014.8, 8p |
| مصطلحات موضوعية: |
AEROFOILS, BOUNDARY layer (Aerodynamics), BLADES (Hydraulic machinery), AERODYNAMICS, COMPUTATIONAL fluid dynamics |
| مستخلص: |
This paper addresses the issue of aerodynamic consequences of small variations in airfoil profile. A numerical comparison offlow field and cascade pressure losses for two representative repaired profiles and a reference new vane were made. Coordinates for the three airfoil profiles were obtained from the nozzle guide vanes of refurbished turboshaft engines using 3D optical scanning and digital modeling. The repaired profiles showed differences in geometry in comparison with the new vane, particularly near the leading and trailing edges. A numerical simulation was conducted using a commercial CFD code, which uses the finite volume approach for solving the governing equations. The computational predictions of the aerodynamic performance were compared with experimental results obtained from a cascade consisting of blades with the same airfoil profiles. The CFD analysis was performed for the cascade at subsonic inlet and transonic exit conditions. Boundary layer growth, wake formation, and shock boundary layer interactions were observed in the two-dimensional computations. The flow field showed the presence of shock waves downstream of the passage throat and near the trailing edges of the blades. A conspicuous change in flow pattern due to subtle variation in airfoil profile was observed. The calculated flow field was compared with the flow pattern visualized in the experimental test rig using the schlieren method. The total pressure calculation for the cascade exit showed an increase in pressure loss for one of the off-design profiles. The pressure loss calculations were also compared with the mnultihole total pressure probe measurement in the transonic cascade rig. [ABSTRACT FROM AUTHOR] |
|
Copyright of Journal of Turbomachinery is the property of American Society of Mechanical Engineers and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.) |
| قاعدة البيانات: |
Supplemental Index |
