Boundary layer transition and development on a turbomachinery blade is subjected to highly periodic unsteady turbulent flow, pressure gradient in longitudinal as well as lateral direction, and surface curvature. To study the effects of periodic unsteady wakes on the concave surface of a turbine blade, a curved plate was utilized. On the concave surface of this plate, detailed experimental investigations were carried out under zero and negative pressure gradient. The measurements were performed on an unsteady flow research facility using a rotating cascade of rods positioned upstream of the curved plate. Boundary layer measurements using a hot-wire probe were analyzed by the ensemble-averaging technique. The results presented in the temporal-spatial domain display the transition and further development of the boundary layer, specifically the ensemble-averaged velocity and turbulence intensity. As the results show, the turbulent patches generated by the wakes have different leading and trailing edge velocities and merge with the boundary layer resulting in a strong deformation and generation of a high turbulence intensity core. After the turbulent patch has totally penetrated into the boundary layer, pronounced becalmed regions were formed behind the turbulent patch and were extended far beyond the point they would occur in the corresponding undisturbed steady boundary layer.
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ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition
June 13–16, 1994
The Hague, Netherlands
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-7883-5
PROCEEDINGS PAPER
Effects of Periodic Unsteady Wake Flow and Pressure Gradient on Boundary Layer Transition Along the Concave Surface of a Curved Plate Free
M. T. Schobeiri,
M. T. Schobeiri
Texas A&M University, College Station, TX
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R. E. Radke
R. E. Radke
Texas A&M University, College Station, TX
Search for other works by this author on:
M. T. Schobeiri
Texas A&M University, College Station, TX
R. E. Radke
Texas A&M University, College Station, TX
Paper No:
94-GT-327, V001T01A106; 14 pages
Published Online:
February 18, 2015
Citation
Schobeiri, MT, & Radke, RE. "Effects of Periodic Unsteady Wake Flow and Pressure Gradient on Boundary Layer Transition Along the Concave Surface of a Curved Plate." Proceedings of the ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition. Volume 1: Turbomachinery. The Hague, Netherlands. June 13–16, 1994. V001T01A106. ASME. https://doi.org/10.1115/94-GT-327
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