0
TECHNICAL PAPERS

Effects of Reynolds Number and Free-Stream Turbulence on Boundary Layer Transition in a Compressor Cascade

[+] Author and Article Information
Heinz-Adolf Schreiber, Wolfgang Steinert

German Aerospace Center (DLR), Institute of Propulsion Technology, 51170 Köln, Germany

Bernhard Küsters

Siemens AG, Power Generation (KWU), 45466 Mülheim a.d. Ruhr, Germany

J. Turbomach 124(1), 1-9 (Feb 01, 2000) (9 pages) doi:10.1115/1.1413471 History: Received February 01, 2000
Copyright © 2002 by ASME
Your Session has timed out. Please sign back in to continue.

References

Dong,  Y., and Cumptsy,  N., 1990, “Compressor Blade Boundary Layers: Part 2—Measurements With Incident Wakes,” ASME J. Turbomach., 112, pp. 231–240.
Teusch, R., Fottner, L., and Swoboda, M., 1999, “Experimental Investigation of Wake-Induced Transition in a Linear Compressor Cascade With Controlled Diffusion Blading,” 14th ISABE Conference, Florence, Sept., Paper No. 99-7057.
Solomon, W. J., and Walker, G. J., 1995, “Observation of Wake-Induced Transition on an Axial Compressor Blade,” ASME Paper No. 95-GT-381.
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 1–4,” ASME J. Turbomach., 119, pp. 114–127; 1997119, pp. 426–444; 1997119, pp. 225–237; 1997119, pp. 128–139.
Pieper, S., Schulte, J., Hoynacki, A., and Gallus, H.E., 1996, “Experimental Investigation of a Single Stage Axial Flow Compressor With Controlled Diffusion Airfoils,” ASME Paper No. 96-GT- 81.
Cumpsty, N. A., Dong, Y., and Li, Y. S., 1995, “Compressor Blade Boundary Layers in the Presence of Wakes,” ASME Paper No. 95- GT-443.
Hourmouziadis, J., 1989, “Aerodynamic Design of Low Pressure Turbines,” AGARD Lecture Series No. 167.
Köller,  U., Mönig,  R., Küsters,  B., and Schreiber,  H. A., 2000, “Development of Advanced Compressor Airfoils for Heavy-Duty Gas Turbines, Part I: Design and Optimization,” ASME J. Turbomach., 122, pp. 397–405.
Küsters,  B., Schreiber,  H. A., Köller,  U., and Mönig,  R., 1999, “Development of Advanced Compressor Airfoils for Heavy Duty Gas Turbines, Part II: Experimental and Analytical Analysis,” ASME J. Turbomach., 122, pp. 406–414.
Wisler,  D. C., 1985, “Loss Reduction in Axial-Flow Compressors Through Low Speed Model Testing,” ASME J. Eng. Gas Turbines Power, 107, pp. 354–363.
Abu-Ghannam,  B. J., and Shaw,  R., 1980, “Natural Transition of Boundary Layers—The Effect of Turbulence, Pressure Gradient and Flow History,” J. Mech. Eng. Sci., 22, No. 5, pp. 213–228.
Gostelow,  J. P., and Bluden,  A. R., 1989, “Investigation of Boundary Layer Transition in an Adverse Pressure Gradient,” ASME J. Turbomach., 111, pp. 366–375.
Mayle,  R. E., 1991, “The 1991 GTI Scholar Lecture: The Role of Laminar–Turbulent Transition in Gas Turbine Engines,” ASME J. Turbomach., 113, pp. 509–537.
Blair,  M. F., 1982, “Influence of Free-Stream Turbulence on Boundary Layer Transition in Favorable Pressure Gradients,” ASME J. Eng. Power, 104, pp. 743–750.
Drela, M., and Youngren, H., 1991, “Viscous/Inviscid Method for Preliminary Design of Transonic Cascades,” AIAA Paper No. 91-2364.
Drela, M., 1995, “Implementation of Modified Abu-Ghannam Shaw Transition Criterion,” MISES User’s Guide, MIT, Computational Aerospace Science Lab., Cambridge, MA.
Schreiber, H. A., Starken, H., and Steinert, W., 1993, “Transonic and Supersonic Cascades,” AGARDOgraph “Advanced Methods for Cascade Testing,” AGARD AG 328, pp. 35–59.
Steinert,  W., and Starken,  H., 1996, “Off-Design Transition and Separation Behavior of a CDA Cascade,” ASME J. Turbomach., 118, pp. 204–210.
Bize, D., Lempereur, C., Mathe, J. M., Mignosi, A., Seraudie, A., and Serrot, G., 1998, “Transition Analysis by Surface Temperature Mapping Using Liquid Crystals,” Aerospace Sci. Tech., Paris, No. 7, pp. 439–449.
Mick, W. J., 1987, “Transition and Heat Transfer in Highly Accelerated Rough-Wall Boundary Layers,” Ph.D. Thesis, Rensselaer Polytechnic Institute, Troy, NY.
Schäffler,  A., 1980, “Experimental and Analytical Investigation of the Effect of Reynolds Number and Blade Surface Roughness on Multistage Axial Flow Compressors,” ASME J. Eng. Power, 102, pp. 5–12.

Figures

Grahic Jump Location
Typical blade chord Reynolds number of a heavy-duty gas turbine compressor
Grahic Jump Location
Influence of Reynolds number and free-stream turbulence on suction side transition onset (MISES simulation)
Grahic Jump Location
Acceleration parameter for suction and pressure side for two different Reynolds numbers
Grahic Jump Location
Test section of the DLR Transonic Cascade Tunnel
Grahic Jump Location
Photograph of cascade and endwalls
Grahic Jump Location
Oil streak lines on suction side, M1=0.6,Re=0.8×106
Grahic Jump Location
Mach number distribution and oil streak lines at Re=0.7×106 and Tu≈2.5–3 percent, 1 tick approximately 10 percent of chord
Grahic Jump Location
Mach number distribution and oil streak lines at Re=2.1×106 and Tu≈3 percent, 1 tick approximately 10 percent of chord
Grahic Jump Location
Predicted blade Mach number distribution and calculated adiabatic wall temperature on suction side
Grahic Jump Location
Simulated surface temperature distribution on blade suction side, influence of free-stream turbulence on temperature discontinuity near transition for M1=0.6 and Re=2.6×106
Grahic Jump Location
Mach number distribution and liquid crystal picture of suction side at Re=0.9×106 and Tu≈0.7 percent showing laminar separation and turbulent reattachment
Grahic Jump Location
Mach number distribution and liquid crystal picture of suction surface at Re=2.2×106 and Tu≈0.7 percent (no screen)
Grahic Jump Location
Mach number distribution and liquid crystal picture of suction surface at Re=2.0×106 and Tu≈2.5–3 percent (screen 1.9)
Grahic Jump Location
Liquid crystal picture of suction surface at Re=2.0×106 and Tu≈3–3.5 percent (screen 1.9+4)
Grahic Jump Location
Liquid crystal picture of suction surface at Re≈2.0×106 and Tu≈4–5 percent (screen 2.6)
Grahic Jump Location
Liquid crystal picture of suction surface at M1=0.7,Re=3.1×106 and Tu≈3–3.5 percent
Grahic Jump Location
Experimental (shaded area) and predicted (solid line) suction side transition onset at Re=2×106
Grahic Jump Location
Momentum thickness Reynolds number Reθ calculated for three different roughness heights in comparison to Reθ transition (dashed line from 20) against the roughness parameter θ/kS

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In