Research Papers

Heat Transfer for the Film-Cooled Vane of a 1-1/2 Stage High-Pressure Transonic Turbine—Part I: Experimental Configuration and Data Review With Inlet Temperature Profile Effects

[+] Author and Article Information
Harika S. Kahveci

e-mail: harika.kahveci@ge.com

Charles W. Haldeman

e-mail: haldeman.5@osu.edu

Randall M. Mathison

e-mail: mathison.4@osu.edu

Michael G. Dunn

e-mail: dunn.129@osu.edu
Gas Turbine Laboratory,
The Ohio State University,
2300 West Case Road,
Columbus, OH 43235

1Present address: GE Energy, Greenville, SC.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 18, 2011; final manuscript received March 25, 2012; published online November 1, 2012. Editor: David Wisler.

J. Turbomach 135(2), 021027 (Nov 01, 2012) (12 pages) Paper No: TURBO-11-1144; doi: 10.1115/1.4006775 History: Received July 18, 2011; Revised March 25, 2012

This paper investigates the vane airfoil and inner endwall heat transfer for a full-scale turbine stage operating at design corrected conditions under the influence of different vane inlet temperature profiles and vane cooling flow rates. The turbine stage is a modern 3D design consisting of a cooled high-pressure vane, an un-cooled high-pressure rotor, and a low-pressure vane. Inlet temperature profiles (uniform, radial, and hot streaks) are created by a passive heat exchanger and can be made circumferentially uniform to within ±5% of the bulk average inlet temperature when desired. The high-pressure vane has full cooling coverage on both the airfoil surface and the inner and outer endwalls. Two circuits supply coolant to the vane, and a third circuit supplies coolant to the rotor purge cavity. All of the cooling circuits are independently controlled. Measurements are performed using double-sided heat-flux gauges located at four spans of the vane airfoil surface and throughout the inner endwall region. Analysis of the heat transfer measured for the uncooled downstream blade row has been reported previously. Part I of this paper describes the operating conditions and data reduction techniques utilized in this analysis, including a novel application of a traditional statistical method to assign confidence limits to measurements in the absence of repeat runs. The impact of Stanton number definition is discussed while analyzing inlet temperature profile shape effects. Comparison of the present data (Build 2) to the data obtained for an uncooled vane (Build 1) clearly illustrates the impact of the cooling flow and its relative effects on both the endwall and airfoils. Measurements obtained for the cooled hardware without cooling applied agree well with the solid airfoil for the airfoil pressure surface but not for the suction surface. Differences on the suction surface are due to flow being ingested on the pressure surface and reinjected on the suction surface when coolant is not supplied for Build 2. Part II of the paper continues this discussion by describing the influence of overall cooling level variation and the influence of the vane trailing edge cooling on the vane heat transfer measurements.

Copyright © 2013 by ASME
Your Session has timed out. Please sign back in to continue.


Goldstein, R. J., 1971, Film Cooling. Advances in Heat Transfer, Vol. 7, T. F.Irvine and J. P.Hartnett, eds., Academic Press, New York, pp. 321–379.
Kercher, D. M., 1998, “A Film-Cooling CFD Bibliography: 1971–1996,” Int. J. Rotating Mach., 4(1), pp. 66–72. [CrossRef]
Kercher, D. M., 2000, “Turbine Airfoil Leading Edge Film Cooling Bibliography,” Int. J. Rotating Mach., 6(5), pp. 313–319. [CrossRef]
Elovic, E., and Koffel, W. K., 1983, “Some Considerations in the Thermal Design of Turbine Airfoil Cooling Systems,” Int. J. Turbo Jet Engines, 1, pp. 45–66. Available at http://www.degruyter.com/view/j/tjj
Simoneau, R. J., and Simon, F. F., 1993, “Progress Towards Understanding and Predicting Heat Transfer in the Turbine Gas Path,” Int. J. Heat Fluid Flow, 14(2), pp. 106–128. [CrossRef]
Bunker, R., 2000, “A Review of Turbine Blade Tip Heat Transfer,” International Symposium on Heat Transfer in Gas Turbine Systems, Izmir, Turkey.
Dunn, M., 2001, “Convective Heat Transfer and Aerodynamics in Axial Flow Turbines,” J. Turbomach., 123, pp. 637–686. [CrossRef]
Dring, R. P., Blair, M. F., and Joslyn, H. D., 1980, “An Experimental Investigation of Film Cooling on a Turbine Rotor Blade,” J. Eng. Power, 102, pp. 81–87. [CrossRef]
Dunn, M., 1985, “Turbine Heat-Flux Measurements: Influence of Slot Injection on Vane Trailing Edge Heat Transfer and Influence of Rotor on Vane Heat Transfer,” ASME J. Eng. Power, 107, pp. 76–83. [CrossRef]
Dunn, M., 1985, “Heat-Flux Measurements and Analysis for a Rotating Turbine Stage,” AGARD-CPP-390, Paper No. 16.
Metzger, D., Dunn, M., and Hah, C., 1991, “Turbine Tip and Shroud Heat Transfer,” ASME J Turbomach., 113, pp. 502–507. [CrossRef]
Dunn, M. G., and Chupp, R. E., 1989, “Influence of Vane/Blade Spacing and Cold-Gas Injection on Vane and Blade Heat-Flux Distributions for the Teledyne 702 HP Turbine Stage,” AIAA J. Propul. Power, 5(2), pp. 212–220. [CrossRef]
Takeishi, K., Aoki, S., Sato, T., and Tsukagoshi, K., 1992, “Film Cooling on a Gas Turbine Rotor Blade,” J. Turbomach., 114(4), pp. 828–834. [CrossRef]
Abhari, R. S., and Epstein, A. H., 1992, “An Experimental Study of Film Cooling in a Rotating Transonic Turbine,” IGTI-Turbo Expo, Cologne, Germany, Paper No. 92-GT-201.
Haldeman, C. W., Dunn, M. G., and Mathison, R. M., 2010, “Fully-Cooled Single Stage HP Transonic Turbine–Part II: Influence of Cooling Mass Flow Changes and Inlet Temperature Profiles on Blade and Shroud Heat-Transfer,” J. Turbomach., 134, p. 031011. [CrossRef]
Haldeman, C. W., Dunn, M. G., and Mathison, R. M., 2010, “Fully-Cooled Single Stage HP Transonic Turbine–Part I: Influence of Cooling Mass Flow Variations and Inlet Temperature Profiles on Blade Internal and External Aerodynamics,” J. Turbomach., 134(3), p. 031010. [CrossRef]
Ong, J., and Miller, R. J., 2008, “Hot Streak and Vane Coolant Migration in a Downstream Rotor,” ASME Turbo Expo 2008, Berlin, Germany, Paper No. GT2008-50971.
Povey, T., Chana, K. S., Jones, T. V., and Hurrion, J., 2007, “The Effect of Hot-Streaks on HP Vane Surface and Endwall Heat Transfer: An Experimental and Numerical Study,” J. Turbomach., 129(1), pp. 32–43. [CrossRef]
Povey, T., and Qureshi, I., 2009, “Developments in Hot-Streak Simulators for Turbine Testing,” J. Turbomach., 131(3), p. 031009. [CrossRef]
Pau, M., Paniagua, G., Delhaye, D., and de La Loma, A., 2008, “Aerothermal Impact of Stator-Rim Flow and Rotor Platform Film Cooling on a Transonic Turbine Stage,” ASME Turbo Expo 2008, Berlin, Germany, Paper No. GT2008-51295.
Mathison, R. M., Haldeman, C. W., and Dunn, M. G., 2010, “Heat Transfer for the Blade of a Cooled Stage and One-Half High-Pressure Turbine–Part I: Influence of Vane Cooling and Disk Cavity Purge Flow,” J. Turbomach., 134(3), p. 031014. [CrossRef]
Mathison, R. M., Haldeman, C. W., and Dunn, M. G., 2010, “Aerodynamics and Heat Transfer for a Cooled One and One-Half Stage High-Pressure Turbine–Part I: Vane Inlet Temperature Profile Generation and Migration,” J. Turbomach., 134(1), p. 011006. [CrossRef]
Mathison, R. M., 2009, “Experimental and Computational Investigation of Inlet Temperature Profile and Cooling Effects on a One and One-Half Stage High Pressure Turbine Operating at Design Corrected Conditions,” Ph.D. thesis, The Ohio State University, Columbus, Ohio.
Haldeman, C. W., Mathison, R. M., and Dunn, M. G., 2004, “Design, Construction and Operation of a Combustor Emulator for Short-Duration High-Pressure Turbine Experiments,” AIAA Joint Propulsion Conference, Ft. Lauderdale, FL, Paper No. AIAA-2004-3829.
Hodak, M. P., 2010, “Qualification of Fourth Generation Kapton Heat-flux Gauge Calibration Performance,” M.S. thesis, The Ohio State University, Columbus, Ohio.
Cohen, B., 2005, “Numerical and Experimental Investigation of Unsteady Heat-Transfer Data Reduction Algorithms,” Department of Mechanical Engineering, Ohio State University, p. 112.
Kahveci, H. S., 2010, “The Influence of Film Cooling and Inlet Temperature Profile on Heat Transfer for the Vane Row of a 1-1/2 Stage Transonic High-Pressure Turbine,” Ph.D. thesis, The Ohio State University, Columbus, Ohio.
Mathison, R. M., Wishart, M. B., Haldeman, C. W., and Dunn, M. G., 2010, “Temperature Predictions and Comparison With Measurements for the Blade Leading Edge and Platform of a 1-1/2 Stage Transonic HP Turbine,” J. Turbomach., 134(1), p. 011016. [CrossRef]
Sen, B., Schmidt, D. L., and Bogard, D. G., 1996, “Film Cooling With Compound Angle Holes: Heat Transfer,” ASME J. Turbomach., 118, pp. 800–806. [CrossRef]


Grahic Jump Location
Fig. 1

Turbine stage and housing schematic

Grahic Jump Location
Fig. 2

Typical heat-flux sensor response

Grahic Jump Location
Fig. 3

Vane heat-flux gauge locations on the (a) airfoil and (b) inner endwall (schematic not to scale)

Grahic Jump Location
Fig. 4

Cooling hole geometry on vane airfoil surface (not to scale)

Grahic Jump Location
Fig. 5

Inlet profiles for nominal cooling levels in terms of (a) normalized and (b) scaled temperatures

Grahic Jump Location
Fig. 6

Comparison of Stanton number definitions for suction surface at 90% span

Grahic Jump Location
Fig. 7

Uncertainty in Stanton number calculation

Grahic Jump Location
Fig. 14

Inner endwall (a) heat flux and (b) Stanton number

Grahic Jump Location
Fig. 13

Stanton number based on local temperature (various profile shapes) for nominal cooling

Grahic Jump Location
Fig. 12

Comparison of uncooled data at endwall

Grahic Jump Location
Fig. 11

Impact of cooling on vane airfoil

Grahic Jump Location
Fig. 10

Comparison of inlet temperature profiles for Builds 1 and 2

Grahic Jump Location
Fig. 9

Comparison of statistics with experimental data

Grahic Jump Location
Fig. 8

Temperature profiles as (a) measured experimentally and (b) statistically modeled



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