0
TECHNICAL PAPERS

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

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

Turbomachinery Heat Transfer Laboratory, The Pennsylvania State University, University Park, PA 16802

Boris Glezer

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

J. Turbomach 123(4), 687-696 (Feb 01, 2001) (10 pages) doi:10.1115/1.1401026 History: Received February 01, 2001
Copyright © 2001 by ASME
Your Session has timed out. Please sign back in to continue.

References

Karstensen, K., 1997, “The Solar Turbines Project—Developing the 21st Century Gas Turbine,” Department of Energy Office of Fossil Energy, Project Synopsis.
Alwang, A., 1981, “Measurement of Non-Steady Fluid Dynamic Quantitiés,” von Karman Institute for Fluid Dynamics Lecture Series—Measurement Techniques in Turbomachines.
Metzger, D., Kim, Y., and Yu, Y., 1993, “Turbine Cooling: An Overview of Some Focus Topics,” Proc. 1993 International Symposium on Transport Phenomena in Thermal Engineering.
Owen, J. M., and Rogers, R. H., 1989, “Flow and Heat Transfer in Rotating Disc Systems, Vol. 1: Rotor-Stator Systems,” Research Studies Press ltd. and John Wiley.
Bunker, R., Metzger, D., and Wittig, S., 1992, “Local Heat Transfer in Turbine Disk Cavities: Part I—Rotor and Stator Cooling With Hub Injection of Coolant,” ASME J. Turbomach., 114 .
Bunker, R., Metzger, D., and Wittig, S., 1992, “Local Heat Transfer in Turbine Disk Cavities: Part II—Rotor Cooling With Radial Location Injection of Coolant,” ASME J. Turbomach., 114 .
von Karman, T., 1921, “Über Llaminare und Turbulente Reibung,” Z. Angew. Math. Mech., 1 .
Cobb,  E., and Saunders,  O., 1956, “Heat Transfer From a Rotating Disk,” Proc. R. Soc. London, Ser. A, 26A, pp. 343–351.
Maroti, L., Deak, G., and Kreith, F., 1960, “Flow Phenomena of Partially Enclosed Rotating Disks,” ASME J. Basic Eng., 82 .
Daily,  J., and Nece,  R., 1960, “Chamber Dimensional Effects on Induced Flow and Frictional Resistance of Enclosed Rotating Disks,” ASME J. Basic Eng., 82, pp. 217–232.
Dorfman, L. A., 1963, Hydrodynamic Resistance and the Heat Loss of Rotating Solids, Oliver and Boyd, Edinburgh.
Metzger,  D., Mathis,  W., and Grochowsky,  L., 1979, “Jet Cooling at the Rim of a Rotating Disk,” ASME J. Eng. Power, 101, pp. 68–72.
Popiel,  C., and Boguslawski,  L., 1986, “Local Heat Transfer From a Rotating Disk in an Impinging Round Jet,” ASME J. Heat Transfer, 108, pp. 357–364.
Qureshi, G., Nguyen, M., Saad, N., and Tadros, R., 1989, “Heat Transfer Measurements for Rotating Turbine Disks,” ASME Paper No. 89-GT-26.
Pincombe, J., 1989, “Chapter 33, Gas Turbine Disk Cooling Flows,” Handbook of Flow Visualization, Wen-Jei Yang, ed., Hemisphere Publishing Corp.
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 Jet Engines, 13, pp. 155–172.
Laksminarayana, B., Camci, C., Halliwell, I., and Zaccaria, M., 1992, “Investigation of Three Dimensional Flow Field in a Turbine Including Rotor/Stator Interaction,” AIAA/SAE/ASME/ASEE 28th Joint Propulsion Conference and Exhibit, July 6–8, Nashville, TN.
Friedrichs,  S., Hodson,  H. P., and Dawes,  W. N., 1997, “Aerodynamic Aspects of Endwall Film-Cooling,” ASME J. Turbomach., 119, pp. 786–795.
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.
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.
McDonel, J. D., and Eiswerth, J. E., 1977, “Effects of Film Injection on Performance of a Cooled Turbine,” AGARD Conference Proceedings, CP-229.
Abernathy, R. B., Benedict, R. P., and Dowdell, R. B., 1985, “ASME Measurement Uncertainty,” ASME J. Fluids Eng., 107 .

Figures

Grahic Jump Location
Wheelspace coolant flow in a high-pressure turbine stage showing the complexity of the internal wheelspace and the mixing of the coolant flow with the mainstream flow, 4.
Grahic Jump Location
Axial flow Turbine Research Facility of the Pennsylvania State University
Grahic Jump Location
Cooling flow injection chambers for radial cooling, impingement cooling, and root injection
Grahic Jump Location
Velocity triangles for the rotor at the hub (r=0.3353 m), midspan (r=0.3998 m), and tip (r=0.4583 m)
Grahic Jump Location
Five-hole probe location in the stationary frame
Grahic Jump Location
Static pressure loss coefficient, 1.5 axial chords down-stream of the rotor exit looking upstream from location 5
Grahic Jump Location
Total pressure loss coefficient, 1.5 axial chords downstream of the rotor exit looking upstream from location 5
Grahic Jump Location
Change in normalized, passage averaged, velocity components (u,v,w) due to 1 percent radial cooling. Stationary frame, 1.5 chords downstream.
Grahic Jump Location
Change in normalized, passage averaged, velocity components (u,v,w) due to 1 percent impingement cooling. Stationary frame, 1.5 chords downstream.
Grahic Jump Location
Change in normalized, passage averaged, velocity components (u,v,w) due to 1 percent root injection. Stationary frame, 1.5 chords downstream.
Grahic Jump Location
Change in pitch (α) and yaw (β) angles due to 1 percent radial cooling. Stationary frame 1.5 chords downstream.
Grahic Jump Location
Change in pitch (α) and yaw (β) angles due to 1 percent impingement cooling. Stationary frame, 1.5 chords downstream.
Grahic Jump Location
Change in pitch (α) and yaw (β) angles due to 1 percent root injection. Stationary frame, 1.5 chords downstream.
Grahic Jump Location
Change in total-to-total efficiency (η) due to 1 percent radial cooling
Grahic Jump Location
Change in total pressure ratio (P05/P04) due to 1 percent radial cooling
Grahic Jump Location
Change in total temperature ratio (T05/T04) due to 1 percent radial cooling
Grahic Jump Location
Change in total-to-total efficiency (η) due to 1 percent impingement cooling
Grahic Jump Location
Change in total pressure ratio (P05/P04) due to 1 percent impingement cooling
Grahic Jump Location
Change in total temperature ratio (T05/T04) due to 1 percent impingement cooling
Grahic Jump Location
Change in total-to-total efficiency (η) due to 1 percent root injection
Grahic Jump Location
Change in total pressure ratio (P05/P04) due to 1 percent root injection
Grahic Jump Location
Change in total temperature ratio (T05/T04) due to 1 percent root injection

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