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Research Papers

Effects of Double Wall Cooling Configuration and Conditions on Performance of Full-Coverage Effusion Cooling

[+] Author and Article Information
Nathan Rogers, Zhong Ren, Warren Buzzard, Brian Sweeney, Nathan Tinker

Propulsion Research Center,
University of Alabama in Huntsville,
5000 Technology Drive,
Olin B. King Technology Hall,
Huntsville, AL 35899;
Department of Mechanical and
Aerospace Engineering,
University of Alabama in Huntsville,
5000 Technology Drive,
Olin B. King Technology Hall,
Huntsville, AL 35899

Phil Ligrani

Professor
Eminent Scholar
Propulsion Research Center,
University of Alabama in Huntsville,
5000 Technology Drive,
Olin B. King Technology Hall S236,
Huntsville, AL 35899;
Department of Mechanical and
Aerospace Engineering,
University of Alabama in Huntsville,
5000 Technology Drive,
Olin B. King Technology Hall S236,
Huntsville, AL 35899
e-mail: pml0006@uah.edu

Keith Hollingsworth

Professor
Propulsion Research Center,
University of Alabama in Huntsville,
5000 Technology Drive,
Olin B. King Technology Hall S236,
Huntsville, AL 35899;
Department of Mechanical and
Aerospace Engineering,
University of Alabama in Huntsville,
5000 Technology Drive,
Olin B. King Technology Hall S236,
Huntsville, AL 35899

Fred Liberatore, Rajeshriben Patel, Shaun Ho

Combustion Engineering, Solar Turbines, Inc.,
2200 Pacific Highway,
Mail Zone E-4,
San Diego, CA 92186-5376

Hee-Koo Moon

Aero/Thermal and Heat Transfer,
Solar Turbines, Inc.,
2200 Pacific Highway,
Mail Zone C-9,
San Diego, CA 92186-5376

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received October 2, 2016; final manuscript received October 31, 2016; published online January 24, 2017. Editor: Kenneth Hall.

J. Turbomach 139(5), 051009 (Jan 24, 2017) (13 pages) Paper No: TURBO-16-1268; doi: 10.1115/1.4035277 History: Received October 02, 2016; Revised October 31, 2016

Experimental results are presented for a double wall cooling arrangement which simulates a portion of a combustor liner of a gas turbine engine. The results are collected using a new experimental facility designed to test full-coverage film cooling and impingement cooling effectiveness using either cross flow, impingement, or a combination of both to supply the film cooling flow. The present experiment primarily deals with cross flow supplied full-coverage film cooling for a sparse film cooling hole array that has not been previously tested. Data are provided for turbulent film cooling, contraction ratio of 1, blowing ratios ranging from 2.7 to 7.5, coolant Reynolds numbers based on film cooling hole diameter of about 5000–20,000, and mainstream temperature step during transient tests of 14 °C. The film cooling hole array consists of a film cooling hole diameter of 6.4 mm with nondimensional streamwise (X/de) and spanwise (Y/de) film cooling hole spacing of 15 and 4, respectively. The film cooling holes are streamwise inclined at an angle of 25 deg with respect to the test plate surface and have adjacent streamwise rows staggered with respect to each other. Data illustrating the effects of blowing ratio on adiabatic film cooling effectiveness and heat transfer coefficient are presented. For the arrangement and conditions considered, heat transfer coefficients generally increase with streamwise development and increase with increasing blowing ratio. The adiabatic film cooling effectiveness is determined from measurements of adiabatic wall temperature, coolant stagnation temperature, and mainstream recovery temperature. The adiabatic wall temperature and the adiabatic film cooling effectiveness generally decrease and increase, respectively, with streamwise position, and generally decrease and increase, respectively, as blowing ratio becomes larger.

Copyright © 2017 by ASME
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References

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Figures

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Fig. 1

Experimental test facility, with all components

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Fig. 2

Side, cross-sectional view of the test section, including optical instrumentation arrangements

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Fig. 3

Film cooling test plate. The dashed line indicates area of present spatially resolved measurements.

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Fig. 4

Impingement test plate

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Fig. 5

Film cooling and impingement test plates, with relative hole locations

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Fig. 6

Experimental test facility, with temperature and pressure measurement locations

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Fig. 7

Instrumentation for mainstream flow channel

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Fig. 8

Instrumentation for cross flow supply channel

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Fig. 9

Instrumentation for impingement supply passage

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Fig. 10

Instrumentation for impingement supply plenum

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Fig. 11

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. 12

Comparison of present data with results from Ref. [1] for BR = 5.0, for streamwise variation of line-averaged adiabatic film cooling effectiveness. Blowing ratios for present study are 2.8, 4.3, 5.3, 6.4, and 7.5.

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Fig. 13

Comparison of present data with results from Ref. [1] for BR = 5.0, for streamwise variation of line-averaged heat transfer coefficient. Blowing ratios for present study are 2.8, 4.3, 5.3, 6.4, and 7.5.

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Fig. 14

Local, spatially resolved surface adiabatic wall temperature distribution with main flow velocity of 7.6 m/s, main flow temperature of 301 K, and blowing ratio of 5.3

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Fig. 15

Local, spatially resolved surface adiabatic film cooling effectiveness distribution with main flow velocity of 7.6 m/s, main flow temperature of 301 K, and blowing ratio of 5.3

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Fig. 16

Local, spatially resolved surface heat transfer coefficient distribution with main flow velocity of 7.6 m/s, main flow temperature of 301 K, and blowing ratio of 5.3

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Fig. 17

Streamwise variation of local, spatially resolved adiabatic wall temperature at location y/de = 23 with main flow velocity of 7.6 m/s, main flow temperature of 301 K, and blowing ratios of 2.8, 4.3, 5.3, 6.4, and 7.5

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Fig. 18

Streamwise variation of local, spatially resolved adiabatic wall temperature at location y/de = 20 with main flow velocity of 7.6 m/s, main flow temperature of 301 K, and blowing ratios of 2.8, 4.3, 5.3, 6.4, and 7.5

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Fig. 19

Streamwise variation of local, spatially resolved adiabatic film cooling effectiveness at location y/de = 23 with main flow velocity of 7.6 m/s, main flow temperature of 301 K, and blowing ratios of 2.8, 4.3, 5.3, 6.4, and 7.5

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Fig. 20

Streamwise variation of local, spatially resolved adiabatic film cooling effectiveness at location y/de = 20 with main flow velocity of 7.6 m/s, main flow temperature of 301 K, and blowing ratios of 2.8, 4.3, 5.3, 6.4, and 7.5

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Fig. 21

Streamwise variation of local, spatially resolved heat transfer coefficient at location y/de = 23 with main flow velocity of 7.6 m/s, main flow temperature of 301 K, and blowing ratios of 2.8, 4.3, 5.3, 6.4, and 7.5

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Fig. 22

Streamwise variation of local, spatially resolved heat transfer coefficient at location y/de = 20 with main flow velocity of 7.6 m/s, main flow temperature of 301 K, and blowing ratios of 2.8, 4.3, 5.3, 6.4, and 7.5

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Fig. 23

Streamwise variation of line-averaged adiabatic wall temperature with main flow velocity of 7.6 m/s, main flow temperature of 301 K, and blowing ratios of 2.8, 4.3, 5.3, 6.4, and 7.5

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Fig. 24

Streamwise variation of line-averaged adiabatic film cooling effectiveness with main flow velocity of 7.6 m/s, main flow temperature of 301 K, and blowing ratios of 2.8, 4.3, 5.3, 6.4, and 7.5

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Fig. 25

Streamwise variation of line-averaged heat transfer coefficient with main flow velocity of 7.6 m/s, main flow temperature of 301 K, and blowing ratios of 2.8, 4.3, 5.3, 6.4, and 7.5

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