Daniel J. DorneyVirginia Commonwealth University, Richmond, Virginia

James P. LakeAFRL/PRRSEdwards Air Force Base, California

Paul I. KingAir Force Institute of TechnologyWright-Patterson Air Force Base, Ohio

David E. AshpisGlenn Research Center, Cleveland, Ohio

Experimental and Numerical Investigation ofLosses in Low-Pressure Turbine Blade Rows

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Prepared for the38th Aerospace Sciences Meeting and Exhibitsponsored by the American Institute of Aeronautics and AstronauticsReno, Nevada, January 10–13, 2000

AIAA–2000–0737

Experimental and Numerical Investigation ofLosses in Low-Pressure Turbine Blade Rows

Daniel J. DorneyVirginia Commonwealth University, Richmond, Virginia

James P. LakeAFRL/PRRSEdwards Air Force Base, California

Paul I. KingAir Force Institute of TechnologyWright-Patterson Air Force Base, Ohio

David E. AshpisGlenn Research Center, Cleveland, Ohio

Acknowledgments

The work of the first author was supported by NASA Glenn Research Center under Grant NCC3–645.

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Experimental and Numerical Investigation of Losses in Low-PressureTurbine Blade Rows

Daniel J. Dorney, James P. Lake, Paul I. King, and David E. Ashpis

Unclassified -UnlimitedSubject Categories: 02, 07, and 34 Distribution: Nonstandard

Prepared for the 38th Aerospace Sciences Meeting and Exhibit sponsored by the American Institute of Aeronautics and Astronautics,Reno, Nevada, January 10–13, 2000. Daniel J. Dorney, Virginia Commonwealth University, Department of Mechanical Engineering,601 West Main Street, P.O. Box 843015, Richmond, Virginia 23284–3015; James P. Lake, AFRL/PRRS, Edwards Air Force Base,California; Paul I. King, Air Force Institute of Technology, Wright-Patterson Air Force Base, Ohio; and David E. Ashpis, NASA GlennResearch Center. Responsible person, David E. Ashpis, organization code 5820, (216) 433–8317.

Boundary layer; Wake; Turbulence; Transition; Separation; Modeling; Turbulencemodeling; Turbine; Turbomachinery

Experimental data and numerical simulations of low-pressure turbines have shown that unsteady blade row interactionsand separation can have a significant impact on the turbine efficiency. Measured turbine efficiencies at takeoff can be asmuch as two points higher than those at cruise conditions. Several recent studies have revealed that the performance oflow-pressure turbine blades is a strong function of the Reynolds number. In the current investigation, experiments andsimulations have been performed to study the behavior of a low-pressure turbine blade at several Reynolds numbers.Both the predicted and experimental results indicate increased cascade losses as the Reynolds number is reduced to thevalues associated with aircraft cruise conditions. In addition, both sets of data show that tripping the boundary layerhelps reduce the losses at lower Reynolds numbers. Overall, the predicted aerodynamic and performance results exhibitfair agreement with experimental data.