1999 Turbomachinery Committee Best Paper Award: Development of Advanced Compressor Airfoils for Heavy-Duty Gas Turbines— Part II: Experimental and Theoretical Analysis

[+] Author and Article Information
Bernhard Küsters, Heinz-Adolf Schreiber

German Aerospace Center, Institute of Propulsion Technology, D-51170 Köln, Germany

Ulf Köller, Reinhard Mönig

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

J. Turbomach 122(3), 406-414 (Feb 01, 1999) (9 pages) doi:10.1115/1.1302321 History: Received February 01, 1999
Copyright © 2000 by ASME
Your Session has timed out. Please sign back in to continue.


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, this issue, pp. 397–405.
Drela, M., and Youngren, H., 1991, “Viscous/Inviscid Method for Preliminary Design of Transonic Cascades,” AIAA Paper No. 91-2364.
Youngren, H., 1991, “Analysis and Design of Transonic Cascades With Splitter Vanes,” GTL Report No. 203, Mar., Cambridge, MA.
Drela, M., and Youngren, H. 1996, “A User’s Guide to MISES 2.4,” MIT Computational Aerospace Science Laboratory.
Drela, M., 1995, “Implementation of Modified Abu-Ghannam Shaw Transition Criterion,” MISES User’s Guide, MIT, Cambridge, MA.
Abu-Ghannam,  B. J., and Shaw,  R., 1980, “Natural transition of boundary layers—The effects of turbulence, pressure gradient and flow history,” Journal of Mechanical Engineering Science, 22, No. 5, pp. 213–228.
Schulenberg, Th., Zimmermann, H., 1995, “New Blade Design of Siemens Gas Turbines,” presented at POWER-GEN Europe, May 16–18, Amsterdam.
Köller, U., 1999, “Entwicklung einer fortschrittlichen Profilsystematik für stationäre Gasturbinenverdichter,” Dissertation, Ruhr Universität Bochum, Germany.
Mayle,  E., 1991, “The Role of Laminar–Turbulent Transition in Gas Turbine Engines,” ASME J. Turbomach., 113, pp. 509–537.
Schreiber, H. A., Starken, H., and Steinert, W., 1993, “Transonic and Supersonic Cascades,” AGARDOgraph “Advanced Methods for Cascade Testing,” Ch. Hirsch, ed., AGARD AG 328, pp. 35–59.
Steinert,  W., Fuchs,  R., and Starken,  H., 1992, “Inlet Flow Angle Determination of Transonic Compressor Cascades,” ASME J. Turbomach., 114, No. 3, pp. 487–493.
Eulitz, F., Engel, K., Pokorny, S., 1996, “Numerical Investigation of Inviscid and Viscous Interaction in a Transonic Compressor,” Loss Mechanisms and Unsteady Flows in Turbomachines, AGARD-CP-571, Paper No. 38.
Eulitz, F., Engel, K., Gebing, H., 1996. “Application of a one-equation eddy-viscosity model to unsteady turbomachinery flow,” Engineering Turbulence Modeling and Experiments 3, W. Rodi and G. Bergeles, eds., Elsevier Science B.V. Amsterdam, pp. 741–751.
Spalart, P. R., and Allmaras, S. R., 1992, “A One-Equation Turbulence Model for Aerodynamic Flows,” Paper No. AIAA-92-0439.
Giles M. B., 1990, “UNSFLO: A Numerical Method for the Calculation of the Unsteady Flow in Turbomachinery,” GTL Rept. 205, Gas Turbine Laboratory, MIT, Cambridge, MA.
Küsters,  B., and Schreiber,  H. A., 1998, “Compressor Cascade Flow With Strong Shock-Wave/Boundary-Layer Interaction,” AIAA J., 36, No. 11, pp. 2072–2078.
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; 119, pp. 426–444; 119, pp. 225–237; 119, pp. 128–139.
Steinert,  W., and Starken,  H., 1996, “Off-Design Transition and Separation Behavior of a CDA Cascade,” ASME J. Turbomach., 118, pp. 204–210.
Koch,  C. C., and Smith,  L. H., 1976, “Loss Sources and Magnitudes in Axial-Flow Compressors,” ASME J. Eng. Gas Turbines Power, 98, pp. 411–424.
Schäffler,  A., 1980, “Experimental and Analytical Investigation of the Effects of Reynolds Number and Blade Surface Roughness on Multistage Axial Flow Compressors,” ASME J. Eng. Power, 102, pp. 5–12.


Grahic Jump Location
Experimental and numerical design Mach number distributions of the four test cascades
Grahic Jump Location
Cross section of the DLR Transonic Cascade Tunnel
Grahic Jump Location
Photograph of the test section
Grahic Jump Location
Predicted performance at different Reynolds numbers, cascade C
Grahic Jump Location
Isentropic Mach number distribution at different Reynolds numbers, cascade C
Grahic Jump Location
Boundary layer thickness at different Reynolds numbers, cascade C,M1=0.556,β1=147.3 deg
Grahic Jump Location
Boundary layer form factor at different Reynolds numbers, cascade C,M1=0.556,β1=147.3 deg
Grahic Jump Location
Loss over incidence at design Mach number, experimental and MISES data, Re=0.9–0.7×106,Tu≤1 percent, experimental and design (in brackets) flow angle range
Grahic Jump Location
Experimental and numerical Mach number distributions of test cascade D
Grahic Jump Location
Experimental performance data compared to MISES and Navier–Stokes calculations, cascade B,M1=0.607, AVDR=1.05
Grahic Jump Location
Numerical separation behavior of cascade D, including MISES separation onset
Grahic Jump Location
Oil streak lines on the suction side of cascade D,i=+9 deg, flow direction from top to bottom
Grahic Jump Location
Calculated adiabatic wall temperature on suction side and corresponding isentropic Mach number distribution
Grahic Jump Location
Suction side transition visualized by liquid crystals, influence of turbulence level at Re=2×106
Grahic Jump Location
Experimental (shaded area) and calculated (solid line) suction side transition onset for the profile shown in Fig. 14



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