0
Research Papers

Swirl Impinging Cooling on an Airfoil Leading Edge Model at Large Reynolds Number

[+] Author and Article Information
Nian Wang

Turbine Heat Transfer Laboratory,
Department of Mechanical Engineering,
Texas A&M University,
College Station, TX

Je-Chin Han

Turbine Heat Transfer Laboratory,
Department of Mechanical Engineering,
Texas A&M University,
College Station, TX
e-mail: jc-han@tamu.edu

1Corresponding author.

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF THERMAL SCIENCE AND ENGINEERING APPLICATIONS. Manuscript received November 7, 2017; final manuscript received November 30, 2018; published online January 29, 2019. Assoc. Editor: Steve Q. Cai.

J. Thermal Sci. Eng. Appl 11(3), 031006 (Jan 29, 2019) (8 pages) Paper No: TSEA-17-1431; doi: 10.1115/1.4042151 History: Received November 07, 2017; Revised November 30, 2018

Jet impingement cooling has been extensively investigated due to its significant applications on the airfoil leading edge region; however, most of which are about normal jet impingement. The systematic research on swirl jet impinging cooling on leading edge is relatively rare. This study comprehensively investigated the heat transfer distribution of swirl jet impingement with one row of tangential jets. The location of the cross-over jets is offset from the centerline toward either suction or pressure side. Five jet Reynolds numbers varying from 10,000 to 80,000 are tested to reach real engine cooling condition. Jet plates with jet-to-jet spacing (s/d = 2, 4, and 8) and the ratio of surface diameter-to-jet diameter (D/d = 4, 6.6, and 13.3) are tested. We conducted the experiments with a test matrix of 45 cases. The optimum geometric parameters of the jet plate are revealed. Results indicate that for a given Reynolds number, the jet plate configuration with D/d = 4 and s/d = 2 provides the highest Nusselt number profile than the other jet plate configurations, while the jet plate configuration with D/d = 13.3 and s/d = 8 provides the lowest Nusselt number profiles. The best heat transfer region shifts by varying the jet plate configuration depending on the strength of swirl flow. Additionally, correlation of tangential jet impingement has been developed to predict the area-averaged Nusselt number, which is useful for airfoil leading edge cooling design and heat transfer analysis.

FIGURES IN THIS ARTICLE
<>
Copyright © 2019 by ASME
Your Session has timed out. Please sign back in to continue.

References

Han, J. C. , Dutta, S. , and Ekkad, S. V. , 2000, Gas Turbine Heat Transfer and Cooling Technology, Taylor and Francis, New York.
Wright, L. M. , and Han, J. C. , 2014, “Heat Transfer Enhancement for Turbine Blade Internal Cooling,” J. Enhanced Heat Transfer, 21(2–3), pp. 111–140. [CrossRef]
Weigand, B. , and Spring, S. , 2011, “Multiple Jet Impingement–A Review,” Heat Transfer Res., 42(2), pp. 101–142. [CrossRef]
Chupp, R. E. , Helms, D. E. , McFadden, P. W. , and Brown, T. R. , 1969, “Evaluation of Internal Heat Transfer Coefficients for Impingement Cooled Turbine Airfoils,” AIAA J. Aircr., 6(3), pp. 203–208. https://arc.aiaa.org/doi/10.2514/3.44036
Kercher, D. M. , and Tabakoff, W. , 1970, “Heat Transfer by a Square Array of Round Air Jets Impinging Perpendicular to a Flat Surface Including the Effect of Spent Air,” J. Eng. Power, 92(1), pp. 73–82. [CrossRef]
Metzger, D. E. , Florschuetz, L. W. , Takeuchi, D. I. , Behee, R. D. , and Berry, R. A. , 1979, “Heat Transfer Characteristics for Inline and Staggered Arrays of Circular Jets With Crossflow of Spent Air,” ASME J. Heat Transfer, 101(3), pp. 526–531. [CrossRef]
Florschuetz, L. W. , Truman, C. R. , and Metzger, D. E. , 1981, “Streamwise Flow and Heat Transfer Distributions for Jet Array Impingement With Crossflow,” ASME J. Heat Transfer, 103(2), pp. 337–342. [CrossRef]
Florschuetz, L. W. , Berry, R. A. , and Metzger, D. E. , 1980, “Periodic Streamwise Variations of Heat Transfer Coefficients for Inline and Staggered Arrays of Circular Jets With Crossflow of Spent Air,” ASME J. Heat Transfer, 102(1), pp. 132–137. [CrossRef]
Huang, Y. , Ekkad, S. V. , and Han, J. C. , 1998, “Detailed Heat Transfer Distributions Under an Array of Orthogonal Jets,” AIAA J. Thermophys. Heat Transfer, 12(1), pp. 73–79. [CrossRef]
Taslim, M. E. , and Bethka, D. , 2009, “Experimental and Numerical Impingement Heat Transfer in an Airfoil Leading-Edge Cooling Channel With Cross-Flow,” ASME J. Turbomach., 131(1), p. 011021. [CrossRef]
Taslim, M. E. , and Khanicheh, A. , 2005, “Experimental and Numerical Study of Impingement on an Airfoil Leading-Edge With and Without Showerhead and Gill Film Holes,” ASME J. Turbomach., 128(2), pp. 310–320. [CrossRef]
Taslim, M. E. , and Setayeshgar, L. , 2001, “Experimental Leading-Edge Impingement Cooling Through Racetrack Crossover Holes,” ASME Paper No. 001-GT-0153.
Jordan, C. N. , Wright, L. M. , and Crites, D. C. , 2016, “Impingement Heat Transfer on a Cylindrical, Concave Surface With Varying Jet Geometries,” ASME J. Heat Transfer, 138(12), p. 122202. [CrossRef]
Jordan, C. N. , Wright, L. M. , and Crites, D. C. , 2012, “Effect of Impingement Supply Condition on Leading Edge Heat Transfer With Rounded Impinging Jets,” ASME Paper No. HT2012-58410.
Jordan, C. N. , Elston, C. A. , Wright, L. M. , and Crites, D. C. , 2013, “Leading Edge Impingement With Racetrack-Shaped Jets and Varying Inlet Supply Conditions,” ASME Paper No. GT2013-94611.
Liu, Z. , and Feng, Z. P. , 2011, “Numerical Simulation on the Effect of Jet Nozzle Position on Impingement Cooling of Gas Turbine Blade Leading Edge,” Int. J. Heat Mass Transfer, 54(23–24), pp. 4949–4959. [CrossRef]
Ekkad, S. V. , Huang, Y. , and Han, J. C. , 2000, “Impingement Heat Transfer Measurements Under an Array of Inclined Jets,” J. Thermophys. Heat Transfer, 14(2), pp. 286–288.
Gau, C. , and Chung, C. M. , 1991, “Surface Curvature Effect on Slot-Air-Jet Impingement Cooling Flow and Heat Transfer Process,” ASME J. Heat Transfer, 113(4), pp. 858–864. [CrossRef]
Metzger, D. E. , and Bunker, R. S. , 1990, “Local Heat Transfer in Internally Cooled Turbine Airfoil Leading Edge Regions—Part I: Impingement Cooling Without Film Coolant Extraction,” ASME J. Turbomach., 112(3), pp. 451–458. [CrossRef]
Bunker, R. S. , and Metzger, D. E. , 1990, “Local Heat Transfer in Internally Cooled Turbine Airfoil Leading Edge Regions—Part II: Impingement Cooling With Film Coolant Extraction,” ASME J. Turbomach., 112(3), pp. 459–466. [CrossRef]
Azad, G. M. , Huang, Y. , and Han, J. C. , 2000, “Jet Impingement Heat Transfer on Pinned Surfaces Using a Transient Liquid Crystal Technique,” Int. J. Rotating Mach., 8(3), pp. 164–173.
Azad, G. M. , Huang, Y. , and Han, J. C. , 2000, “Jet Impingement Heat Transfer on Dimpled Surfaces Using a Transient Liquid Crystal Technique,” AIAA J. Thermophys. Heat Transfer, 14(2), pp. 186–193. [CrossRef]
Kanokjaruvijit, K. , and Martinez-Botas, R. , 2005, “Parametric Effects on Heat Transfer of Impingement on Dimpled Surface,” ASME J. Turbomach., 127(2), pp. 287–296. [CrossRef]
Taslim, M. E. , Bakhtari, K. , and Liu, H. , 2003, “Experimental and Numerical Investigation of Impingement on a Rib-Roughened Leading-Edge Wall,” ASME J. Turbomach., 125(4), pp. 682–691. [CrossRef]
Mhetras, S. , Han, J.-C. , and Huh, M. , 2014, “Impingement Heat Transfer From Jet Arrays on Turbulent Target Walls at Large Reynolds Numbers,” ASME Trans. J. Therm. Sci. Eng. Appl., 6(2), p. 021003. [CrossRef]
Parbat, S. N. , Siw, S. C. , and Chyu, M. , 2016, “Impingement Cooling in Narrow Rectangular Channel With Novel Surface Features,” ASME Paper No. GT2016-58084.
Buzzard, W. , Ren, Z. , Ligrani, P. , Nakamata, C. , and Ueguchi, S. , 2016, “Influences of Target Surface Roughness on Impingement Jet Array Heat Transfer—Part 1: Effects of Roughness Pattern, Roughness Height, and Reynolds Number,” ASME Paper No. GT2016-56354.
Buzzard, W. , Ren, Z. , Ligrani, P. M. , Nakamata, C. , and Ueguchi, S. , 2016, “Influences of Target Surface Roughness on Impingement Jet Array Heat Transfer—Part 2: Effects of Roughness Shape, and Reynolds Number,” ASME Paper No. GT2016-56355.
Hay, N. , and West, P. D. , 1975, “Heat Transfer in Free Swirling Flow in a Pipe,” ASME J. Heat Transfer, 97(3), pp. 411–416. [CrossRef]
Glezer, B. , Moon, H. K. , and O'Connell, T. , 1996, “A Novel Technique for the Internal Blade Cooling,” ASME Paper No. 96-GT-181.
Moon, H. K. , O'Connell, T. , and Glezer, B. , 1998, “Heat Transfer Enhancement in a Circular Channel Using Lenghtwise Continuous Tangential Injection,” ASME J. Heat Transfer, 6, pp. 559–564.
Ligrani, P. M. , Hedlund, C. R. , Babinchak, B. T. , Thambu, R. , Moon, H. K. , and Glezer, B. , 1998, “Flow Phenomena in Swirl Chambers,” Exp. Fluids, 24(3), pp. 254–264. [CrossRef]
Thambu, R. , Babinchak, B. T. , Ligrani, P. M. , Hedlund, C. R. , Moon, H. K. , and Glezer, B. , 1999, “Flow in a Simple Swirl Chamber With and Without Controlled Inlet Forcing,” Exp. Fluids, 26(4), pp. 347–357. [CrossRef]
Rao, Y. , Biegger, C. , and Weigand, B. , 2016, “Heat Transfer and Pressure Loss in Swirl Tubes With One and Multiple Tangential Jets Pertinent to Gas Turbine Internal Cooling,” Int. J. Heat Mass Transfer, 106, pp. 1356–1367. [CrossRef]
Kline, S. J. , and McClintock, F. A. , 1953, “Describing Uncertainties in a Single Sample Experiment,” Mech. Eng., 75, pp. 3–8.
Wang, N. , Chen, A. F. , Zhang, M. J. , and Han, J. C. , 2017, “Turbine Blade Leading Edge Cooling With One Row of Normal or Tangential Impinging Jets,” ASME J. Heat Transfer, 140(6), p. 062201. [CrossRef]

Figures

Grahic Jump Location
Fig. 1

Schematic of the turbine airfoil leading-edge region cooling design

Grahic Jump Location
Fig. 2

Schematic of experiment setup

Grahic Jump Location
Fig. 3

Schematic of the test section for regionally averaged heat transfer measurement

Grahic Jump Location
Fig. 4

Schematic of copper plate target wall assembly

Grahic Jump Location
Fig. 5

Schematic of jet plates configuration

Grahic Jump Location
Fig. 6

Variation of regional average heat transfer with arc distance for all cases

Grahic Jump Location
Fig. 7

CFD velocity contour for tangential jet, D/d = 6.6, s/d = 4, Re = 20K [36]

Grahic Jump Location
Fig. 8

Regional Nusselt number variation with Reynolds number for all cases

Grahic Jump Location
Fig. 9

Nuavg variation with jet Reynold number for all cases

Grahic Jump Location
Fig. 10

Data distribution along the proposed correlation

Grahic Jump Location
Fig. 11

Pressure loss coefficients for all cases: (a) D/d = 4, (b) D/d = 6.6, and (c) D/d = 13.3

Tables

Errata

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.

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