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Research Papers

Effect of Internal Crossflow Velocity on Film Cooling Effectiveness—Part II: Compound Angle Shaped Holes

[+] Author and Article Information
John W. McClintic

Department of Mechanical Engineering,
The University of Texas at Austin,
204 E. Dean Keeton Street,
Austin, TX 78712
e-mail: johnwmcclintic@gmail.com

Joshua B. Anderson

Department of Mechanical Engineering,
The University of Texas at Austin,
204 E. Dean Keeton Street,
Austin, TX 78712
e-mail: mranderson@utexas.edu

David G. Bogard

Department of Mechanical Engineering,
The University of Texas at Austin,
204 E. Dean Keeton Street,
Austin, TX 78712
e-mail: dbogard@mail.utexas.edu

Thomas E. Dyson

GE Global Research Center,
1 Research Circle,
Schenectady, NY 12309
e-mail: dyson@ge.com

Zachary D. Webster

GE Aviation,
1 Neumann Way,
Cincinnati, OH 45125
e-mail: Zachary.Webster@ge.com

1Corresponding author.

2Present address: Williams International, Commerce Charter Township, MI 48390.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received August 21, 2017; final manuscript received September 5, 2017; published online October 25, 2017. Editor: Kenneth Hall.

J. Turbomach 140(1), 011004 (Oct 25, 2017) (10 pages) Paper No: TURBO-17-1128; doi: 10.1115/1.4037998 History: Received August 21, 2017; Revised September 05, 2017

In gas turbine engines, film cooling holes are commonly fed with an internal crossflow, the magnitude of which has been shown to have a notable effect on film cooling effectiveness. In Part I of this study, as well as in a few previous studies, the magnitude of internal crossflow velocity was shown to have a substantial effect on film cooling effectiveness of axial shaped holes. There is, however, almost no data available in the literature that shows how internal crossflow affects compound angle shaped film cooling holes. In Part II, film cooling effectiveness, heat transfer coefficient augmentation, and discharge coefficients were measured for a single row of compound angle shaped film cooling holes fed by internal crossflow flowing both in-line and counter to the spanwise direction of coolant injection. The crossflow-to-mainstream velocity ratio was varied from 0.2 to 0.6 and the injection velocity ratio was varied from 0.2 to 1.7. It was found that increasing the magnitude of the crossflow velocity generally caused degradation of the film cooling effectiveness, especially for in-line crossflow. An analysis of jet characteristic parameters demonstrated the importance of crossflow effects relative to the effect of varying the film cooling injection rate. Heat transfer coefficient augmentation was found to be primarily dependent on injection rate, although for in-line crossflow, increasing crossflow velocity significantly increased augmentation for certain conditions.

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References

Bunker, R. S. , 2005, “ A Review of Shaped Hole Turbine Film-Cooling Technology,” ASME J. Heat Transfer, 127(4), pp. 441–453. [CrossRef]
Taslim, M. E. , and Khanicheh, A. , 2005, “ Film Effectiveness Downstream of an Row of Compound Angle Holes,” ASME J. Heat Transfer, 127(4), pp. 434–440. [CrossRef]
Bell, C. M. , Hamakawa, H. , and Ligrani, P. M. , 2000, “ Film Cooling from Shaped Holes,” ASME J. Heat Transfer, 122(2), pp. 224–232. [CrossRef]
Ganzert, W. , Hildebrandt, T. , and Fottner, L. , 2000, “ Systematic Experimental and Numerical Investigations on the Aerothermodynamics of a Film Cooled Turbine Cascade With Variation of the Cooling Hole Shape—Part I: Experimental Approach,” ASME Paper No. 2000-GT-0295.
Gritsch, M. , Schulz, A. , and Wittig, S. , 2003, “ Effect of Internal Coolant Crossflow on the Effectiveness of Shaped Film-Cooling Holes,” ASME J. Turbomach., 125(3), pp. 547–554. [CrossRef]
Saumweber, C. , and Schulz, A. , 2012, “ Effect of Geometry Variations on the Cooling Performance of Fan-Shaped Cooling Holes,” ASME J. Turbomach., 134(6), p. 061008. [CrossRef]
Wilkes, E. K. , Anderson, J. B. , McClintic, J. W. , and Bogard, D. G. , 2016, “ An Investigation of Turbine Film Cooling Effectiveness With Shaped Holes and Internal Cross-Flow with Varying Operational Parameters,” ASME Paper No. GT2016-56162.
McClintic, J. W. , Anderson, J. B. , Bogard, D. G. , Dyson, T. E. , and Webster, Z. , 2017, “ Effect of Internal Crossflow Velocity on Film Cooling Effectiveness—Part I: Axial Shaped Holes,” ASME Paper No. GT2017-64624.
McClintic, J. W. , Klavetter, S. R. , Winka, J. R. , Anderson, J. B. , Bogard, D. G. , Dees, J. E. , Laskowski, G. M. , and Briggs, R. , 2015, “ The Effect of Internal Crossflow on the Adiabatic Effectiveness of Compound Angle Film Cooling Holes,” ASME J. Turbomach., 137(7), p. 071006. [CrossRef]
Stratton, Z. T. , Shih, T. I. , Laskowski, G. M. , Barr, B. , and Briggs, R. , 2015, “ Effects of Crossflow in an Internal-Cooling Channel on Film Cooling of a Flat Plate Through Compound-Angle Holes,” ASME Paper No. GT2015-42771.
Dittmar, J. , Schulz, A. , and Wittig, S. , 2002, “ Assessment of Various Film Cooling Configurations Including Shaped and Compound Angle Holes Based on Large Scale Experiments,” ASME Paper No. GT2002-30176.
Anderson, J. B. , Wilkes, E. K. , McClintic, J. W. , and Bogard, D. G. , 2016, “ Effects of Freestream Mach Number, Reynolds Number, and Boundary Layer Thickness on Film Cooling Effectiveness of Shaped Holes,” ASME Paper No. GT2016-56152.
Schroeder, R. P. , and Thole, K. A. , 2014, “ Adiabatic Effectiveness Measurements for a Baseline Shaped Film Cooling Hole,” ASME Paper No. GT2014-25992.
Gritsch, M. , Saumweber, C. , Schulz, A. , Wittig, S. , and Sharp, E. , 2000, “ Effect of Internal Coolant Crossflow Orientation on the Discharge Coefficient of Shaped Film-Cooling Holes,” ASME J. Turbomach., 122(1), pp. 146–152. [CrossRef]
Klavetter, S. R. , McClintic, J. W. , Bogard, D. G. , Dees, J. E. , Laskowski, G. M. , and Briggs, R. , 2016, “ The Effect of Rib Turbulators on Film Cooling Effectiveness of Round Compound Angle Holes Fed by an Internal Cross-Flow,” ASME J. Turbomach., 138(12), p. 121006. [CrossRef]
Dyson, T. E. , McClintic, J. W. , Bogard, D. G. , and Bradshaw, S. D. , 2013, “ Adiabatic and Overall Effectiveness for a Fully Cooled Turbine Vane,” ASME Paper No. GT2013-94928.
Moffat, R. J. , 1985, “ Using Uncertainty Analysis in the Planning of an Experiment,” ASME J. Fluids Eng., 107(2), pp. 173–178. [CrossRef]
Anderson, J. B. , McClintic, J. W. , Bogard, D. G. , Dyson, T. E. , and Webster, Z. , 2017, “ Freestream Flow Effects on Film Effectiveness and Heat Transfer Coefficeint Augmentation for Compound Angle Shaped Holes,” ASME Paper No. GT2017-64853.

Figures

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Fig. 2

Compound angle 7-7-7 film cooling hole geometry

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Fig. 1

Schematic of test section and coolant channel

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Fig. 3

Jet characteristic parameters—sample η profile at x/d = 10

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Fig. 4

Discharge coefficients for all conditions scaled with (a) PR and (b) Uj/Uc

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Fig. 5

Spatially averaged effectiveness from x/d = 5–20 for: (a) all conditions (plenum data from Ref. [18]), (b) counter crossflow and (c) in-line crossflow

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Fig. 6

Contours of uncorrected η for VRc = 0.5

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Fig. 7

Contours of uncorrected η for VR = 1.11

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Fig. 13

(a) Locations of peak hf/h0 for in-line crossflow and (b) compared with (z/d)CL at VRc = 0.4

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Fig. 8

ηCL averaged from x/d = 5–20 scaled with VRi (a) in-line crossflow, (b) in-line crossflow and axial holes, and (c) counter crossflow

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Fig. 10

(z/d)CL averaged from x/d = 5–20: (a) counter crossflow (b) compared to in-line crossflow

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Fig. 11

W/d averaged from x/d = 5–20: (a) counter crossflow (b) compared to in-line crossflow

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Fig. 12

Lateral profiles of hf,norm and η/ηCL for VRc = 0.6, x/d = 5 for (a) counter and (b) in-line crossflow

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Fig. 14

Laterally averaged hf,norm for (a) counter and (b) in-line crossflow. (c) Spatially averaged hf,norm for x/d = 5–14. Plenum data are from Ref. [18].

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Fig. 15

Predicted φp and measured η for VR = 1.11, spatially averaged over x/d = 5–14

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Fig. 9

ηCL averaged from x/d = 5–20 scaled with different scaling parameters (a) VR (b) and (c) VR, and VRc0.15

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