A new transport equation for the intermittency factor was proposed to predict separated and transitional boundary layers under low-pressure turbine airfoil conditions. The intermittent behavior of the transitional flows is taken into account and incorporated into computations by modifying the eddy viscosity, with the intermittency factor, γ. Turbulent quantities are predicted by using Menter’s two-equation turbulence model (SST). The intermittency factor is obtained from a transport equation model, which not only can reproduce the experimentally observed streamwise variation of the intermittency in the transition zone, but also can provide a realistic cross-stream variation of the intermittency profile. In this paper, the intermittency model is used to predict a recent separated and transitional boundary layer experiment under low pressure turbine airfoil conditions. The experiment provides detailed measurements of velocity, turbulent kinetic energy and intermittency profiles for a number of Reynolds numbers and freestream turbulent intensity conditions and is suitable for validation purposes. Detailed comparisons of computational results with experimental data are presented and good agreements between the experiments and predictions are obtained.
Skip Nav Destination
Article navigation
July 2003
Technical Papers
Predictions of Separated and Transitional Boundary Layers Under Low-Pressure Turbine Airfoil Conditions Using an Intermittency Transport Equation
Y. B. Suzen, Senior Engineer Associate,
Y. B. Suzen, Senior Engineer Associate
Department of Mechanical Engineering, University of Kentucky, Lexington, KY 40506-0503
Search for other works by this author on:
P. G. Huang, Professor,
P. G. Huang, Professor
Department of Mechanical Engineering, University of Kentucky, Lexington, KY 40506-0503
Search for other works by this author on:
Lennart S. Hultgren, Aerospace Engineer, Mem. ASME,
Lennart S. Hultgren, Aerospace Engineer, Mem. ASME
National Aeronautics and Space Administration, Glenn Research Center at Lewis Field, Cleveland, OH 44135
Search for other works by this author on:
David E. Ashpis, Aerospace Engineer
David E. Ashpis, Aerospace Engineer
National Aeronautics and Space Administration, Glenn Research Center at Lewis Field, Cleveland, OH 44135
Search for other works by this author on:
Y. B. Suzen, Senior Engineer Associate
Department of Mechanical Engineering, University of Kentucky, Lexington, KY 40506-0503
P. G. Huang, Professor
Department of Mechanical Engineering, University of Kentucky, Lexington, KY 40506-0503
Lennart S. Hultgren, Aerospace Engineer, Mem. ASME
National Aeronautics and Space Administration, Glenn Research Center at Lewis Field, Cleveland, OH 44135
David E. Ashpis, Aerospace Engineer
National Aeronautics and Space Administration, Glenn Research Center at Lewis Field, Cleveland, OH 44135
Contributed by the International Gas Turbine Institute for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received by the IGTI July 9, 2001; revised manuscript received March 10, 2003. Associate Editor: S. Sjolander.
J. Turbomach. Jul 2003, 125(3): 455-464 (10 pages)
Published Online: August 27, 2003
Article history
Received:
July 9, 2001
Revised:
March 10, 2003
Online:
August 27, 2003
Citation
Suzen, Y. B., Huang, P. G., Hultgren, L. S., and Ashpis, D. E. (August 27, 2003). "Predictions of Separated and Transitional Boundary Layers Under Low-Pressure Turbine Airfoil Conditions Using an Intermittency Transport Equation ." ASME. J. Turbomach. July 2003; 125(3): 455–464. https://doi.org/10.1115/1.1580159
Download citation file:
Get Email Alerts
The Cooling Effect of Combustor Exit Louver Scheme on a Transonic Nozzle Guide Vane Endwall
J. Turbomach (July 2025)
Aerodynamic Performance Evaluation of Subsonic Compressor Cascade Blade With Leading-Edge Damage
J. Turbomach (July 2025)
Thermohydraulic Performance and Flow Structures of Diamond Pyramid Arrays
J. Turbomach (July 2025)
Related Articles
Calculation of High-Lift Cascades in Low Pressure Turbine Conditions Using a Three-Equation Model
J. Turbomach (July,2011)
On the Physics of Flow Separation Along a Low Pressure Turbine Blade Under Unsteady Flow Conditions
J. Fluids Eng (May,2005)
Predicting Transition in Turbomachinery—Part II: Model Validation and Benchmarking
J. Turbomach (January,2007)
Separation Control on a Very High Lift Low Pressure Turbine Airfoil Using Pulsed Vortex Generator Jets
J. Turbomach (October,2011)
Related Proceedings Papers
Related Chapters
Cavitating Structures at Inception in Turbulent Shear Flow
Proceedings of the 10th International Symposium on Cavitation (CAV2018)
Boundary Layer Analysis
Centrifugal Compressors: A Strategy for Aerodynamic Design and Analysis
Aerodynamic Performance Analysis
Axial-Flow Compressors