0
TECHNICAL PAPERS

Investigation of the Unsteady Rotor Aerodynamics in a Transonic Turbine Stage

[+] Author and Article Information
R. Dénos, T. Arts, G. Paniagua

Von Karman Institute for Fluid Dynamics, Rhode Saint Genèse, Belgium

V. Michelassi

Department of Mechanical and Industrial Engineering, University of Rome, Tre, Italy

F. Martelli

Energetics Department “Sergio Stecco,” University of Florence, Florence, Italy

J. Turbomach 123(1), 81-89 (Feb 01, 2000) (9 pages) doi:10.1115/1.1314607 History: Received February 01, 2000
Copyright © 2001 by ASME
Your Session has timed out. Please sign back in to continue.

References

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.
Harvey, N. W., Cox, J. C., Schulte, V., Howell, R., and Hodson, H. P., 1999, “The Role of Research in the Aerodynamic Design of Advanced Low-Pressure Turbine,” Trans. 3rd European Conference on Turbomachinery, pp 123–132.
Garside, T., Moss, R. W., Ainsworth, R. W., Dancer, S. N., and Rose, M. G., 1994, “Heat Transfer to Rotating Turbine Blades in a Flow Undisturbed by Wakes,” ASME Paper No. 94-GT-94.
Dénos, R., 1996, “Investigation of the Unsteady Aerothermal Flow Field in the Rotor of a Transonic Turbine,” Ph.D. thesis, IVK—University of Poitiers.
Jung, A. R., Mayer, J. F., and Stetter, H., 1996, “Simulation of 3D-Unsteady Stator-Rotor Interaction in Turbomachinery Stages of Arbitrary Pitch Ratio,” ASME Paper No. 96-GT-69.
Gundy-Burlet, K. L., and Dorney, D. J., 1996, “Three-Dimensional Simulations of Hot Streak Clocking in a 1-1/2 Stage Turbine,” presented at 32nd IAA/ASME/SAE/ASEE Joint Propulsion Conference, Lake Buena Vista, FL, July 1–3.
Hilditch, M. A., Smith, G. C., and Singh, U. K., 1998 “Unsteady Flow in a Single Turbine Stage,” ASME Paper No. 98-GT-531.
Emunds,  R., Jennions,  I. K., Bohn,  D., and Gier,  J., 1999, “The Computation of Adjacent Blade-Row Effects in a 1.5-Stage Axial Flow Turbine,” ASME J. Turbomach., 121, pp. 1–10.
Giles, M. B., 1991, “UNSFLO: A Numerical Method for the Calculation of Unsteady Flow in Turbomachinery,” GTL Rep. No. 205, MIT Gas Turbine Laboratory.
DeRango,  S., and Zing,  D. W., 1997, “Improvements to a Dual-Time Stepping Method for Computing Unsteady Flows,” AIAA J., 35, No. 9, pp. 1548–1550.
Doorly,  D. J., and Oldfield,  M. L. G., 1985, “Simulation of the Effect of Shock Wave Passing on a Turbine Rotor Blade,” ASME J. Eng. Gas Turbines Power, 107, pp. 998–1006.
Ashworth,  D. A., LaGraff,  J. E., Shultz,  D. L., and Grindrod,  K. J., 1985, “Unsteady Aerodynamic and Heat Transfer Processes in a Transonic Turbine Stage,” ASME J. Eng. Gas Turbines Power, 107, pp. 1022–1030.
Giles, M. B., 1988, “Stator/Rotor Interaction in a Transonic Turbine,” AIAA Paper No. 88-3093.
Saxer,  A. P., and Giles,  M. B., 1994, “Predictions of Three-Dimensional Steady and Unsteady Inviscid Transonic Stator/Rotor Interaction With Inlet Radial Temperature Nonuniformity,” ASME J. Turbomach., 116, pp. 347–357.
Moss, R. W., Sheldrake, C. D., Ainsworth, R. W., Smith A. D., and Dancer, S. N., 1996, “Unsteady Pressure and Heat Transfer Measurements on a Rotating Blade Surface in a Transient Flow Facility,” 85th Propulsion and Energetic Panel Symposium on Loss Mechanism and Unsteady Flows in Turbomachines, Derby, UK, AGARD CP No. 571.
Rao,  K. V., Delaney,  R. A., and Dunn,  M. G., 1994, “Vane–Blade Interaction in a Transonic Turbine. Part 1: Aerodynamics. Part 2: Heat Transfer,” AIAA J. Propulsion Power, 10, No. 3, pp. 305–317.
Guenette,  G. R., Epstein,  A. H., Giles,  M. B., Haimes,  R., and Norton,  R. J. G., 1989, “Fully Scaled Transonic Turbine Rotor Heat Transfer Measurements,” ASME J. Turbomach., 111, pp. 1–7.
Michelassi,  V., Martelli,  F., Dénos,  R., Arts,  T., and Sieverding,  C. H., 1999, “Unsteady Heat Transfer in Stator–Rotor Interaction by Two Equation Turbulence Model,” ASME J. Turbomach., 121, pp. 436–447.
Dénos,  R., Sieverding,  C. H., Arts,  T., Brouckaert,  J. F., Paniagua,  G., and Michelassi,  V., 1999, “Experimental Investigation of the Unsteady Rotor Aerodynamics of a Transonic Turbine Stage,” IMechE J. Power Energy, 23, No A4, pp. 327–338.
Sieverding, C. H., Vanhaeverbeek, C., and Schulze, G., 1992, “An Opto-Electronic Data Transmission System for Measurements on Rotating Turbomachinery Components,” ASME Paper No. 92-GT-337.
Byrne, C. M., and Davies, M. R. D., 1996, “Data Transmission Systems for a Transient Gas Turbine Rotor,” ASME Paper No. 96-GT-514.
Ainsworth, R., 1995, “Recent Development in Fast Response Aerodynamic Technology,” Von Karman Institute Lecture Series 1995-01 on Measurement Techniques.
Jameson, A., 1991, “Time Dependent Calculations Using a Multigrid With Applications to Unsteady Flows Past Airfoils and Wings,” AIAA Paper No. 91-1596.
Michelassi, V., and Martelli, F., 1998, “Modeling of Unsteady-Heat Transfer in a Transonic Turbine Stage,” AIAA Paper No. 98-2555.
Durbin,  P. A., 1996, “On the k–ε Stagnation Point Anomaly,” Int. J. Heat Fluid Flow, 17, pp. 89–90.
Abu-Ghannam,  B. J., and Shaw,  R., 1980, “Natural Transition of Boundary Layers—The Effects of Turbulence, Pressure Gradient, and Flow History,” J. Mech. Eng. Sci., 22, No. 5, pp. 213–228.
Kapteijn,  C., Amecke,  J., and Michelassi,  V., 1996, “Aerodynamic Performance of a Transonic Turbine Guide Vane With Trailing Edge Coolant Ejection: Part 1—Experimental Approach,” ASME J. Turbomach., 118, pp. 519–528.
Sieverding,  C. H., Arts,  T., Dénos,  R., and Martelli,  F., 1996, “Investigation of the Flow Field Downstream of a Turbine Trailing Edge Cooled Nozzle Guide Vane,” ASME J. Turbomach., 118, pp. 291–300.
Dietz, A. J., and Ainsworth, R. W., 1992, “Unsteady Pressure Measurements on the Rotor of a Model Turbine Stage in a Transient Flow Facility,” ASME Paper No. 92-GT-156.
Hodson,  H. P., 1985, “Measurements of Wake-Generated Unsteadiness in the Rotor Passages of an Axial Flow Turbine,” ASME J. Eng. Gas Turbines Power, 107, pp. 467–476.
Hilditch, M. A., Smith, G. C., Anderson, J. S., and Chana, K. S., 1996, “Unsteady Measurements in an Axial Flow Turbine,” Proc. 85th Propulsion and Energetic Panel Symposium on Loss Mechanism and Unsteady Flows in Turbomachines, Derby, UK, AGARD CP No. 571.
Hodson,  H. P., 1985, “An Inviscid Blade-to-Blade Prediction of a Wake-Generated Unsteady Flow,” ASME J. Eng. Gas Turbines Power, 107, pp. 337–344.
Venable,  B. L., Delaney,  R. A., Busby,  J. A., Davis,  R. L., Dorney,  D. J., Dunn,  M. G., Haldeman,  C. W., and Abhari,  R. S., 1999, “Influence of Vane-Blade Spacing on Transonic Turbine Stage Aerodynamics, Part 1: Time-Averaged Data and Analysis,” ASME J. Turbomach., 121, pp. 663–672.

Figures

Grahic Jump Location
Rotor/stator position at phase 0; schematic of the vane shock and wake system for a stator–rotor spacing of 0.35 cs,ax
Grahic Jump Location
Phase-locked average and rms of the measured rotor relative inlet total pressure: influence of trailing edge coolant ejection
Grahic Jump Location
Computed isentropic Mach number distribution on the vane (6500 rpm, 0.35 cs,ax,mc=3 percent)
Grahic Jump Location
Computed rotor inlet flow angle
Grahic Jump Location
Influence of: (a) rotational speed (0.35 cs,ax,ṁc=3 percent), and (b) stator–rotor spacing (6500 rpm, mc=3 percent) on measured relative inlet total pressure fluctuations
Grahic Jump Location
Time-averaged values of measured and computed rotor blade pressure (0.35 cs,ax,ṁc=3 percent)
Grahic Jump Location
Pressure fluctuations from measurements and computations (6500 rpm, 0.35 cs,ax,ṁc=3 percent): (a) gages 5–13, (b) gages 15–4, (c) gages 24–16
Grahic Jump Location
Computed shock function in the stage with schematic of expansion waves (blue lines) and compression waves (red lines); the phases of rotor blades 2, 3, 4, and 5 are 0.17, 0.83, 0.49, and 0.17, respectively
Grahic Jump Location
Schematic showing the vane trailing edge shock as it sweeps the blade front suction side
Grahic Jump Location
(a) Minimum, maximum of mean period; (b) time-averaged rms; and (c) correlation coefficient of the experimental pressure traces for spacings 0.35 cs,ax and 0.50 cs,ax (6500 rpm, ṁc=3 percent)
Grahic Jump Location
The rms traces (6500 rpm, 0.35 cs,ax,ṁc=3 percent) in the blade nose region; propagation directions at v,v+a,v−a for a perturbation injected at point 14 at φ=0.15
Grahic Jump Location
Unsteady blade force modulus and angle (0.35 cs,ax,ṁc=3 percent) from experiments at 6000, 6500, and 6800 rpm and computations at 6500 rpm
Grahic Jump Location
Unsteady velocity and static pressure field in the rotor passage

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