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Research Papers: Jets, Wakes, and Impingment Cooling

Full-Coverage Film Cooling: Heat Transfer Coefficients and Film Effectiveness for a Sparse Hole Array at Different Blowing Ratios and Contraction Ratios

[+] Author and Article Information
Phil Ligrani

Department of Engineering Science,
University of Oxford,
Oxford, UK
e-mail: pml0006@uah.edu

Matt Goodro

Department of Engineering Science,
University of Oxford,
Oxford, UK

Michael D. Fox, Hee-Koo Moon

Solar Turbines Inc.,
San Diego, CA

1Corresponding author.

2Present address: Eminent Scholar in Propulsion, Professor of Mechanical and Aerospace Engineering, College of Engineering, Department of Mechanical and Aerospace Engineering, Propulsion Research Center, Olin B. King Technology Hall S236, University of Alabama in Huntsville, Huntsville, AL 35899.

3Present address: Mechanical Engineer, Hill Air Force Base, USAF, 6030 Gum Lane, Bldg. 1217, Hill AFB, UT 84056.

4Present address: Solar Turbines Inc., Heat Transfer Research, 2200 Pacific Highway, P. O. Box 85376, Mail Zone C-9, San Diego, CA 92186-5376.

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF HEAT TRANSFER. Manuscript received April 9, 2013; final manuscript received November 14, 2014; published online December 17, 2014. Assoc. Editor: Terry Simon.

J. Heat Transfer 137(3), 032201 (Mar 01, 2015) (12 pages) Paper No: HT-13-1194; doi: 10.1115/1.4029168 History: Received April 09, 2013; Revised November 14, 2014; Online December 17, 2014

The present experimental investigation considers a full coverage film cooling arrangement with different streamwise static pressure gradients. The film cooling holes in adjacent streamwise rows are staggered with respect to each other, with sharp edges and streamwise inclination angles of 20 deg with respect to the liner surface. Data are provided for turbulent film cooling, contraction ratios of 1 and 4, blowing ratios (BRs) (at the test section entrance) of 2.0, 5.0, and 10.0, a coolant Reynolds number of 12,000, freestream temperatures from 75 °C to 115 °C, a film hole diameter of 7 mm, and density ratios from 1.15 to 1.25. Nondimensional streamwise and spanwise film cooling hole spacings, X/D and Y/D, are 18 and 5, respectively. Data illustrating the effects of contraction ratio, BR, and streamwise location on local, line-averaged, and spatially averaged adiabatic film effectiveness data; and on local, line-averaged and spatially averaged heat transfer coefficient data are presented. Varying BR values are present along the length of the contraction passage, which contains the cooling hole arrangement, when contraction ratio is 4. Dependence on BR indicates important influences of coolant concentration and distribution. For example, line-averaged and spatially averaged adiabatic effectiveness data show vastly different changes with BR for the configurations with contraction ratios of 1 and 4. In addition, much larger effectiveness alterations are present as BR changes from 2.0 to 10.0, when significant acceleration is present and Cr = 4 (in comparison with the Cr = 1 data).

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References

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Figures

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Fig. 1

Film cooling wind tunnel test facility

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Fig. 2

Film cooling test section. + denotes measurement location for mainstream static pressure.

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Fig. 3

Film cooling test plate for X/D = 18, Y/D = 5 and hole angle 20 deg. (a) Test section dimensions and layout, where all dimensions are given in millimeters. (b) Test section coordinate system.

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Fig. 4

Example of variation of local surface heat flux with surface temperature for one test surface location during a typical transient test

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Fig. 5

BR variation with x/D for different contraction ratios, calculated on the basis of static pressure ratios

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Fig. 6

(a) Variation of acceleration parameter through the test section for contraction ratios Cr of 1 and 4. (b) Variation of ratio of coolant mass flow rate to mainstream mass flow rate for X/D = 18, Y/D = 5, and a BR of 5.0 for contraction ratios Cr of 1 and 4.

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Fig. 7

Spatially resolved surface adiabatic effectiveness for hole spacing X/D = 18, Y/D = 5, contraction ratio Cr = 4, and hole inclination angle α = 20 deg, for BR of (a) 2.0, (b) 5.0, and (c) 10.0

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Fig. 8

Spatially resolved surface heat transfer coefficients for hole spacing X/D = 18, Y/D = 5, contraction ratio Cr = 4, and hole inclination angle α = 20 deg, for BR of (a) 2.0, (b) 5.0, and (c) 10.0

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Fig. 9

Line-averaged adiabatic film effectiveness for hole spacings X/D = 18 and Y/D = 5, streamwise hole inclination angle of 20 deg, and contraction ratios Cr of 1, with line-averaging over y/D. Data given for BR values of 2.0, 5.0, and 10.0.

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Fig. 10

Line-averaged adiabatic film effectiveness for hole spacings X/D = 18 and Y/D = 5, streamwise hole inclination angle of 20 deg, and contraction ratios Cr of 4, with line-averaging over y/D. Data given for BR values of 2.0, 5.0, and 10.0.

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Fig. 11

Area-averaged adiabatic film effectiveness for hole spacings X/D = 18 and Y/D = 5, streamwise hole inclination angle of 20 deg, and contraction ratios Cr of 1. Data given for BR values of 2.0, 5.0, and 10.0.

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Fig. 12

Area-averaged adiabatic film effectiveness for hole spacings X/D = 18 and Y/D = 5, streamwise hole inclination angle of 20 deg, and contraction ratios Cr of 4. Data given for BR values of 2.0, 5.0, and 10.0.

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Fig. 13

Line-averaged surface heat transfer coefficients for hole spacings X/D = 18 and Y/D = 5, streamwise hole inclination angle of 20 deg, and contraction ratios Cr of 1, with line-averaging over y/D. Data given for BR values of 2.0, 5.0, and 10.0.

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Fig. 14

Line-averaged surface heat transfer coefficients for hole spacings X/D = 18 and Y/D = 5, streamwise hole inclination angle of 20 deg, and contraction ratios Cr of 4, with line-averaging over y/D. Data given for BR values of 2.0, 5.0, and 10.0.

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Fig. 15

Area-averaged surface heat transfer coefficients for hole spacings X/D = 18 and Y/D = 5, streamwise hole inclination angle of 20 deg, and contraction ratios Cr of 1. Data given for BR values of 2.0, 5.0, and 10.0.

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Fig. 16

Area-averaged surface heat transfer coefficients for hole spacings X/D = 18 and Y/D = 5, streamwise hole inclination angle of 20 deg, and contraction ratios Cr of 4. Data given for BR values of 2.0, 5.0, and 10.0.

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Fig. 17

Variations of line-averaged adiabatic film effectiveness at contraction ratios Cr of 1 and 4 for BR of 2.0, streamwise hole inclination angle of 20 deg, streamwise hole spacing X/D of 18, and spanwise hole spacing Y/D of 5

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Fig. 18

Variations of line-averaged adiabatic film effectiveness at contraction ratios Cr of 1 and 4 for BR of 5.0, streamwise hole inclination angle of 20 deg, streamwise hole spacing X/D of 18, and spanwise hole spacing Y/D of 5

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Fig. 19

Variations of line-averaged adiabatic film effectiveness at contraction ratios Cr of 1 and 4 for BR of 10.0, streamwise hole inclination angle of 20 deg, streamwise hole spacing X/D of 18, and spanwise hole spacing Y/D of 5

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Fig. 20

Line-averaged surface heat transfer coefficient variations at contraction ratios Cr of 1 and 4 for BR of 2.0, streamwise hole inclination angle of 20 deg, streamwise hole spacing X/D of 18, and spanwise hole spacing Y/D of 5

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Fig. 21

Line-averaged surface heat transfer coefficient variations at contraction ratios Cr of 1 and 4 for BR of 5.0, streamwise hole inclination angle of 20 deg, streamwise hole spacing X/D of 18, and spanwise hole spacing Y/D of 5

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Fig. 22

Line-averaged surface heat transfer coefficient variations at contraction ratios Cr of 1 and 4 for BR of 10, streamwise hole inclination angle of 20 deg, streamwise hole spacing X/D of 18, and spanwise hole spacing Y/D of 5

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