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Research Papers

The Effect of Internal Crossflow on the Adiabatic Effectiveness of Compound Angle Film Cooling Holes

[+] Author and Article Information
John W. McClintic

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

Sean R. Klavetter

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

James R. Winka

The University of Texas at Austin,
204 E. Dean Keeton Street,
Austin, TX 78712
e-mail: james.winka@ge.com

Joshua B. Anderson

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

David G. Bogard

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

Jason E. Dees

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

Gregory M. Laskowski

GE Aviation,
1000 Western Avenue,
Lynn, MA 01905
e-mail: laskowsk@ge.com

Robert Briggs

GE Aviation,
1 Neumann Way,
Cincinnati, OH 45215
e-mail: robert1.briggs@ge.com

1Present address: GE Global Research.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received October 10, 2014; final manuscript received October 20, 2014; published online December 29, 2014. Editor: Ronald S. Bunker.

J. Turbomach 137(7), 071006 (Jul 01, 2015) (10 pages) Paper No: TURBO-14-1266; doi: 10.1115/1.4029157 History: Received October 10, 2014; Revised October 20, 2014; Online December 29, 2014

In gas turbine engines, film cooling holes are often fed by an internal crossflow, with flow normal to the direction of the external flow around the airfoil. Many experimental studies have used a quiescent plenum to feed model film cooling holes and thus do not account for the effects of internal crossflow. In this study, an experimental flat plate facility was constructed to study the effects of internal crossflow on a row of cylindrical compound angle film cooling holes. There are relatively few studies available in literature that focus on the effects of crossflow on film cooling performance, with no studies examining the effects of internal crossflow on film cooling with round, compound angled holes. A crossflow channel allowed for coolant to flow alternately in either direction perpendicular to the mainstream flow. Experimental conditions were scaled to match realistic turbine engine conditions at low speeds. Cylindrical compound angle film cooling holes were operated at blowing ratios ranging from 0.5 to 2.0 and at a density ratio (DR) of 1.5. The results from the crossflow experiments were compared to a baseline plenum-fed configuration. This study showed that significantly greater adiabatic effectiveness was achieved for crossflow counter to the direction of coolant injection.

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References

Figures

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Fig. 1

Schematic of wind tunnel test section

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Fig. 2

Profile of the approach boundary layer without film cooling

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Fig. 3

Schematic of main and coolant flow loops

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Fig. 4

Schematic of coolant supply channel

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Fig. 5

Velocity profile along the channel centerline

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Fig. 6

Schematic of coolant supply plenum

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Fig. 7

IR calibration curves for both cameras

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Fig. 8

Lateral profiles for in-line crossflow, M = 1.0, x/d = 7 show good jet-to jet uniformity

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Fig. 9

Difference between using one and 3D analyses to correct for conduction

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Fig. 10

Laterally averaged heat transfer augmentation data from Sen et al. [12]

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Fig. 11

Effect of using Eq. (5) to correct for conduction and thermal boundary layer effects for the counter crossflow configuration, M = 1.0

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Fig. 12

Terminology used for the two different crossflow directions in this study

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Fig. 13

Comparing laterally averaged effectiveness of plenum-fed holes to Schmidt et al. [1]

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Fig. 14

Spatially averaged adiabatic effectiveness over the range x/d = 4–30 for all configurations

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Fig. 15

Laterally averaged adiabatic effectiveness for all blowing ratios for each configuration

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Fig. 16

Contour plots for all configurations tested

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Fig. 17

Comparing lateral profiles of adiabatic effectiveness at x/d = 4 and 10 at M = 0.50 and 0.75

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