In order to investigate the unsteady effect on transition in film cooling, an 11-m long Ludwieg Tube, consisting of a test section placed between the high pressure and low pressure sections of a shock tube, has been constructed. With this device, a controlled unsteady, low subsonic flow lasting for a period of several milliseconds is obtained. The transition Reynolds Number is determined from the output of thin film heat flux transducers having a response time of a fraction of a microsecond. The results indicate that, in the case of flow without gas injection into the boundary layer, the transition Reynolds Number is one order of magnitude smaller than the critical Reynolds Number for steady wedge flow with the same pressure gradient. With injection, the transition Reynolds Number is small near the injection slot; far downstream, it increases asymptotically to the value for flow without injection.
Skip Nav Destination
ASME 1981 International Gas Turbine Conference and Products Show
March 9–12, 1981
Houston, Texas, USA
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-7963-4
PROCEEDINGS PAPER
Experimental Determination of Transition Reynolds Number for Unsteady Film Cooling
F. K. Tsou,
F. K. Tsou
Drexel University, Philadelphia, PA
Search for other works by this author on:
L. T. Smith,
L. T. Smith
University of Hartford, West Hartford, CT
Search for other works by this author on:
S. J. Chen
S. J. Chen
Drexel University, Philadelphia, PA
Search for other works by this author on:
F. K. Tsou
Drexel University, Philadelphia, PA
L. T. Smith
University of Hartford, West Hartford, CT
S. J. Chen
Drexel University, Philadelphia, PA
Paper No:
81-GT-94, V003T09A012; 9 pages
Published Online:
April 15, 2015
Citation
Tsou, FK, Smith, LT, & Chen, SJ. "Experimental Determination of Transition Reynolds Number for Unsteady Film Cooling." Proceedings of the ASME 1981 International Gas Turbine Conference and Products Show. Volume 3: Heat Transfer; Electric Power. Houston, Texas, USA. March 9–12, 1981. V003T09A012. ASME. https://doi.org/10.1115/81-GT-94
Download citation file:
166
Views
Related Proceedings Papers
Related Articles
Heat Transfer Through a Pressure-Driven Three-Dimensional Boundary Layer
J. Heat Transfer (May,1991)
Heat Transfer Characteristics Analysis on a Fully Cooled Vane With Varied Density Ratios
J. Thermal Sci. Eng. Appl (January,2022)
Blast Wave Reflection From Wedges
J. Fluids Eng (May,2003)
Related Chapters
Boundary Layer Analysis
Centrifugal Compressors: A Strategy for Aerodynamic Design and Analysis
Cavitating Structures at Inception in Turbulent Shear Flow
Proceedings of the 10th International Symposium on Cavitation (CAV2018)
Introduction
Design and Analysis of Centrifugal Compressors