Experimental Investigation of Boundary Layer Characteristics on Blade Surface under Different Inlet Flow Conditions
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Abstract
In this paper, an experimental study is conducted on cascade boundary layer under different inlet conditions. New method is used to measure the total pressure in blade surface boundary layer directly using total pressure probe. Total pressure in both suction and pressure surfaces are acquired at different inlet conditions by changing incidence angle and inlet Mach number. In addition, a series of parameters related to boundary layer characteristics are calculated. The objective of the experiment is to investigate the influence of inlet flow conditions on them. The results indicate that influence of incidence angle is significant when other conditions are the same. Displacement thickness, momentum thickness as well as other parameters display some disciplines for variation. In contrast, inlet Mach number has only a small influence in that boundary layer becomes a litter thinner with increasing Mach number. Comparisons of experimental results with theoretical expectations demonstrate that the method in this experiment is effective and reliable.
- S. C. Smith, “Use of Shere-Sentive Liquid Crytals for Surface Flow Visualization,” Journal of Aircraft, Vol. 29, No. 2, 1992, pp. 289-293.
- F. Albano, A. Auletta and F. de Gregorio, “An Expe- rimental Study of Laminar Separation Bubbles on Airfoil at Low Reynolds, ”AIAA2006-3529.
- M. Ali, “Aerodynamics of a Low-Pressure Turbine Airfoil under Steady and Periodically Unsteady Conditions,” Ph.D. Dissertation, University of Carleton, Locus, 2003.
- B. Liu and Y. G. Wang, “Effects of Inlet Flow Conditions on Boundary Flow on Compressor Blade Surface,” Journal of Propulsion Technology, Vol. 20, No. 3, 1999, pp. 64-68.
- X. Y. Nan, B. Liu and J. Jin, “A Progressive Optimization for the Inverse Design of Blade Profile Based on Sequential Quadratic Programming,” Proceed- ings of IMechE. Part C: Journal of Mechanical Engineer- ing Science, Vol. 221, No. 1, 2007, pp. 23-31.
- R. D. Clark, “Boundary Layer Research Using the Millersville University Tethered Balloon Facility,” America Institute of Aeronautics & Astronautics, AIAA 99-3961.
- M. S. Zhao, T. G. Owano and C. S. Kruger, “Boundary layer Diagnostics of an Atmospheric Pressure Plasma Jet,” AIAA 2000-0202.
- B. Hollon and J. Jacob, “Experimental Investigation of Separation on Low Pressure Turbine Blades,” AIAA 2001-0447.
- H. Bhanderi and H. Babinsky, “Improver Boundary Layer Quantities in the Shock Wave Boundary Layer Interaction Region on Bumps,” AIAA 2005-4896.
- Philip P. Geoghegan, William J. Growther, “Measure- ment of Boundary Layer Velocity Profiles by Ultrasonic Tomography for the Prediction of Flow Separation,” AIAA 2006-2805.
- F. Chen, G.-J. Zhao, Y.-P. Song, et al., “Influence of Incidences on the Distribution of Static Pressure of Swept-Curved Compressor Cascades,” Journal of Pro- pulsion Technology, Vol. 25, No. 6, 2004, pp. 521-525.