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TECHNICAL PAPERS

The Use of Hot-Wire Anemometry to Investigate Unsteady Wake-Induced Boundary-Layer Development on a High-Lift LP Turbine Cascade

[+] Author and Article Information
Stefan Wolff, Stefan Brunner, Leonhard Fottner

Institut für Strahlantriebe, Universität der Bundeswehr München, D-85577 Neubiberg, Germany

J. Turbomach 122(4), 644-650 (Feb 01, 2000) (7 pages) doi:10.1115/1.1311282 History: Received February 01, 2000
Copyright © 2000 by ASME
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References

Schulte, V., 1995, “Unsteady Separated Boundary Layers in Axial-flow Turbomachinery,” PhD thesis, Cambridge University.
Schulte,  V., and Hodson,  H. P., 1998, “Unsteady Wake-Induced Boundary Layer Transition in High Lift LP Turbines,” ASME J. Turbomach., 120, pp. 28–35.
Hodson, H. P., 1998, “Blade Row Interference Effects in Axial Turbomachinery Stages: Bladerow Interactions in Low Pressure Turbines,” VKI Lecture Series 1998-02.
Mayle,  Robert Edward, 1991, “The 1991 IGTI Scholar Lecture: The Role of Laminar–Turbulent Transition in Gas Turbine Engines,” ASME J. Turbo-mach., 113, pp. 590–537.
Halstead,  D. E., Wisler,  D. C., Okiishi,  T. H., Walker,  G. J., Hodson,  H. P., and Shin,  H.-W., 1997, “Boundary Layer Development in Axial Compressors and Turbines: Part 3 of 4—LP Turbines,” ASME J. Turbomach., 119, pp. 225–237.
Schulte,  V., and Hodson,  H. P., 1998, “Prediction of the Becalmed Region for LP Turbine Profile Design,” ASME J. Turbomach., 120, pp. 839–846.
Curtis,  E. M., Hodson,  H. P., Banieghbal,  M. R., Howell,  R. J., and Harvey,  N. W., 1997, “Development of Blade Profiles for Low-Pressure Turbine Applications,” ASME J. Turbomach., 119, pp. 531–538.
Harvey, N. W., Cox, J. C., Schulte, V., Howell, R., and Hodson, H. P., 1999, “The Role of Research in the Aerodynamic Design of an Advanced Low Pressure Turbine,” ImechE Conference Transactions/Vol. A: 3rd European Conference on Turbomachinery, C557/043, pp. 123–132.
Brunner, S., Fottner, L., Schulte, V., and Kappler, G., 1999a, “Investigation of Wake-Induced Transition on a Highly Loaded Low-Pressure Turbine Cascade,” ImechE Conference Transactions/Vol. A: 3rd European Conference on Turbomachinery, C557/068, p. 231 ff.
Schröder, Th., 1991, “Investigations of Blade Row Interaction and Boundary Layer Transition Phenomena in a Multistage Aero Engine Low-Pressure Turbine by Measurements With Hot-Film Probes and Surface-Mounted Hot-Film Gauges,” Von Karman Institute for Fluid Dynamics, Lecture Series 1991-06.
Arndt,  N., 1993, “Blade Row Interaction in a Multistage Low-Pressure Turbine,” ASME J. Turbomach., 115, pp. 137–146.
Banieghbal, M. R., Curtis, E. M., Denton, J. D., Hodson, H. P., Huntsmann, I., and Schulte, V., 1995, “Wake Passing in LP Turbine Blades,” AGARD CP 571, Paper 23.
Acton, P., and Fottner, L., 1996, “The Generation of Instationary Flow Conditions in the High Speed Cascade Wind Tunnel,” 13th Symposium on Measuring Techniques.
Sturm, W., Fottner, L., 1985, “The High-Speed Cascade Wind-Tunnel of the German Armed Forces University Munich,” 8th Symposium on Measuring Techniques.
Pfeil, H., and Eifler, J., 1979, “Turbulenzverhältnisse hinter rotierenden Zylindergittern,” Forschung im Ingenieurwesen, 42 .
Brunner, S., and Fottner, L., 1999, “Untersuchungen zum Einfluß der Rotor–Stator Interaktion auf die saugseitige Transition eines hochbelassteten ungekühlten Niederdruck-Turbinengitters,” DGLR-JT99-078.
Amecke, J., 1967, “Auswertung von Nachlaufmessungen an ebenen Schaufelgittern,” Bericht 67A49, AVA Göttingen.
Ganzert, W., and Pottner, L., 1996, “WINPANDA—an Enhanced PC-Based Data Acquisition System for Wake and Profile Distribution,” 13th Symposium on Measuring Techniques.
Wolff, S., 1999, “Konzeption, Programmierung and Erprobung eines PC-gesteuereten Meßsystems zur Aufnahme und Auswertung von 1-D and 3-D-Hitzdraht-Signalen am Hochgeschwindigkeits-Gitterwindkanal als Ersatz des HP-Systems,” Institute Report WOIB9909.
Brunner, S., Teusch, R., Stadtmüller, P., and Fottner, L., 1998, “The Use of Simultaneous Surface Hot Film Anemometry to Investigate Unsteady Wake Induced Transition in Turbine and Compressor Cascades,” 14th Symposium on Measuring Techniques.

Figures

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High-speed cascade wind tunnel
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Generator of unsteady inlet flow conditions
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HWA data acquisition system
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Aerodynamic design and exemplary sketch
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Wake turbulence intensity and velocity distribution
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Isentropic Mach number distributions
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Boundary layer velocity and turbulence profile
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Time-resolved integral layer parameter
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Ensemble-averaged glue-on hot-film results: (a) rms value; (b) quasi-wall shear stress distribution

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