Investigation of the Boundary Layer Behavior on Turbine Airfoils.

Han, L. S.; Cox, W. R.; Chait, Arnon

doi:10.21236/ada075501

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Cascade and Instrumentation1

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1982

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Cited by 1 publication

(3 citation statements)

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“…The same cascade arrangement has been used in an earlier work [5] by the authors in which the wake velocity profiles were surveyed. It was conducted along the exit plane, indicated by the dashed line in Figure 1, with a hotwire probe.…”

Section: Resultsmentioning

confidence: 99%

“…Figure 1 depicts schematically the cascade arrangement. Details of the experimental apparatus and accessories can be found in Reference [5] from which a portion of the material in this paper is excerpted.…”

Section: Cascade and Instrumentationmentioning

confidence: 99%

“…Airfoil Wake Velocity Distributions.influence of the vortex system on the order of 1 kHz in affecting the wake velocity 2 Measured value. Reference[5] reported a value of 0.73 inches calculated from smoothed coordinates.…”

mentioning

confidence: 99%

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A Visual Study of Turbine Blade Pressure-Side Boundary Layers

Han

Cox

1982

Volume 1: Turbomachinery

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Boundary layer characteristics on the pressure-side of a turbine airfoil were investigated experimentally in a three-blade cascade tunnel. The blades had a chord length of 21 in. to facilitate flow visualization and high-speed photography. The investigation revealed the existence of the Gortler’s vortices appearing in spurts in regions of severe curvature. In the trailing edge region, Karman vortices were detected and found to interact strongly with the Gortler’s vortices convected thereto.

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Section: Resultsmentioning

confidence: 99%

Section: Cascade and Instrumentationmentioning

confidence: 99%