0
TECHNICAL PAPERS

Mainstream Aerodynamic Effects Due to Wheelspace Coolant Injection in a High-Pressure Turbine Stage: Part II—Aerodynamic Measurements in the Rotational Frame

[+] Author and Article Information
Christopher McLean, Cengiz Camci

Turbomachinery Heat Transfer Laboratory, The Pennsylvania State University, University Park, PA 16802e-mail: cxc11@psu.edu

Boris Glezer

Optimized Turbine Solutions, 4140 Calle Isabelino, San Diego, CA 92130e-mail: bglezer@san.rr.com

J. Turbomach 123(4), 697-703 (Feb 01, 2001) (7 pages) doi:10.1115/1.1397303 History: Received February 01, 2001
Copyright © 2001 by ASME
Your Session has timed out. Please sign back in to continue.

References

Eckert,  E., 1984, “Analysis of Film Cooling and Full Coverage Film Cooling of Gas Turbine Blades,” ASME J. Eng. Gas Turbines Power, 106.
Friedrichs,  S., Hodson,  H., and Dawes,  W., 1997, “Aerodynamic Aspects of Endwall Film-Cooling,” ASME J. Turbomach., 119, pp. 786–793.
Jabbari,  M., and Goldstein,  R., 1993, “Film Cooling, Mass Transfer, and Flow at the Base of a Turbine Blade,” J. Eng. Phys. Thermophys., 65, No. 3.
Jabbari,  M., Marston,  K., Eckert,  E., and Goldstein,  R., 1996, “Film Cooling of the Gas Turbine Endwall by Discrete-Hole Injection,” ASME J. Turbomach., 118, pp. 278–284.
Goldstein,  R., and Chen,  H., 1985, “Film Cooling on a Gas Turbine Blade Near the End Wall,” ASME J. Eng. Gas Turbines Power, 107.
Gaugler,  R., and Russell,  L., 1984, “Comparison of Visualized Turbine Secondary Flows and Measured Heat Transfer Patterns,” ASME J. Eng. Gas Turbines Power, 106.
Graziani,  R., Blair,  M., Taylor,  J., and Mayle,  R., 1980, “An Experimental Study of Endwall and Airfoil Surface Heat Transfer in a Large Scale Turbine Blade Cascade,” ASME J. Eng. Power, 102, pp. 257–267.
Abhari,  R., 1996, “Impact or Rotor-Stator Interaction on Turbine Blade Film Cooling,” ASME J. Turbomach., 118.
Lakshminarayana, B., Camci, C., Halliwell, I., and Zaccaria, M., 1992, “Investigation of Three Dimensional Flow Field in a Turbine Including Rotor/Stator Interaction,” presented at the AIAA/SAE/ASME/ASEE 28th Joint Propulsion Conference and Exhibit, July 6–8, Nashville, TN.
Lakshminarayana,  B., Camci,  C., Halliwell,  I., and Zaccaria,  M., 1996, “Design and Development of a Turbine Research Facility to Study Rotor-Stator Interaction,” Int. J. Turbo and Jet Engines, 13, pp. 155–172.
Zaccaria, M. A., 1994, “Investigation of Three Dimensional Flow Field in a Turbine Including Rotor/Stator Interaction,” Ph.D. Thesis in Aerospace Engineering, The Pennsylvania State University.
Wiedner, G., 1994, “Passage Flow Structure and its Influence on Endwall Heat Transfer in a 90° Turning Duct,” Ph.D. Thesis in Aerospace Engineering, The Pennsylvania State University.
Brophy, M., Treaster, A., Stinebring, D., and Welz, J., 1984, “Optimization of a Five-Hole Probe Wake Measurement System,” Applied Research Laboratory, The Pennsylvania State University.
Friedrichs, S., Hodson, H. P., and Dawes, W. N., 1995, “Distribution of Film-Cooling Effectiveness on a Turbine Endwall Measured Using the Ammonia and Diazo Technique,” ASME Paper No. 95-GT-1.

Figures

Grahic Jump Location
Rotating instrument and traversing package contained within the rotor drum
Grahic Jump Location
Schematic diagram showing the placement of the five-hole probes for rotational frame data
Grahic Jump Location
Legend for data presentation of coolant flow measurements
Grahic Jump Location
Total pressure loss coefficient in rotational frame at H of 0.15 (a), 0.50 (b), and 0.90 (c). Probe 1.5 chords downstream of the rotor exit.
Grahic Jump Location
Axial velocity in the rotational frame at H of 0.15 (a), 0.50 (b), and 0.90 (c). Probe 1.5 chords downstream of the rotor exit.
Grahic Jump Location
Radial velocity in the rotational frame at H of 0.15 (a), 0.50 (b), and 0.90 (c). Probe 1.5 chords downstream of the rotor exit.
Grahic Jump Location
Tangential velocity in the rotational frame at H of 0.15 (a), 0.50 (b), and 0.90 (c). Probe 1.5 chords downstream of the rotor exit.
Grahic Jump Location
Exit angle in the rotational axial-tangential plane (β) at H of 0.15 (a), 0.50 (b), and 0.90 (c). Probe 1.5 chords downstream of the rotor exit.
Grahic Jump Location
Exit angle in the rotational axial-radial plane (α) at H of 0.15 (a), 0.50 (b), and 0.90 (c). Probe 1.5 chords downstream of the rotor exit.
Grahic Jump Location
Pressure measurements on the rotor leading edge for root injection blowing ratios of 1.00 percent (a), 1.25 percent (b), and 1.50 percent (c)
Grahic Jump Location
Kulite data from the rotor platform. The root injection (jagged line) shows noticeable wake reduction from the noncooled case. Four vane passages are shown.
Grahic Jump Location
Frequency domain processing of leading edge Kulite run data with fast Fourier transform

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 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