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Research Papers: Gas Turbines: Combustion, Fuels, and Emissions

Impact of Swirl Flow on the Cooling Performance of an Effusion Cooled Combustor Liner

[+] Author and Article Information
B. Wurm

e-mail: benno.wurm@kit.edu

H.-J. Bauer

Institut fuer Thermische Stroemungsmaschinen,
Karlsruher Institut fuer Technologie (KIT),
Kaiserstrae 12,
76131 Karlsruhe, Germany

M. Gerendas

Combustor Aerothermal and Cooling,
Rolls-Royce Deutschland Ltd & Co KG,
Eschenweg 11,
Dahlewitz 15827 Blankenfelde-Mahlow,
Germany

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received June 21, 2012; final manuscript received June 29, 2012; published online October 11, 2012. Editor: Dilip R. Ballal.

J. Eng. Gas Turbines Power 134(12), 121503 (Oct 11, 2012) (9 pages) doi:10.1115/1.4007332 History: Received June 21, 2012; Revised June 29, 2012

An experimental study on combustor liner cooling of modern direct lean injection combustion chambers using coolant ejection from both effusion cooling holes and a starter film has been conducted. The experimental setup consists of a generic scaled three sector planar rig in an open loop hot gas wind tunnel, which has been described earlier in Wurm et al. (2009, “A New Test Facility for Investigating the Interactions Between Swirl Flow and Wall Cooling Films in Combustors, Investigating the Interactions Between Swirl Flow and Wall Cooling Films in Combustors,” ASME Paper No. GT2009-59961). Experiments are performed without combustion. Realistic engine conditions are achieved by applying engine-realistic Reynolds numbers, Mach numbers, and density ratios. A particle image velocimetry (PIV) measurement technique is employed, which has been adjusted to allow for high resolution near wall velocity measurements with and without coolant ejection. As the main focus of the present study is a deeper understanding of the interaction of swirl flows and near wall cooling flows, wall pressure measurements are performed for the definition of local blowing ratios and to identify the impact on the local cooling performance. For thermal investigations an infrared thermography measurement technique is employed that allows high resolution thermal studies on the effusion cooled liner surface. The effects of different heat shield geometry on the flow field and performance of the cooling films are investigated in terms of near wall velocity distributions and film cooling effectiveness. Two different heat shield configurations are investigated which differ in shape and inclination angle of the so called heat shield lip. Operating conditions for the hot gas main flow are kept constant. The pressure drop across the effusion cooled liner is varied between 1% and 3% of the total pressure. Results show the impact of the swirled main flow on the stability of the starter film and on the effusion cooling performance. Stagnation areas which could be identified by wall pressure measurements are confirmed by PIV measurements. Thermal investigations reveal reduced cooling performance in the respective stagnation areas.

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Figures

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Fig. 2

Averaged axial velocity distribution without effusion and starter film cooling

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Fig. 3

Local blowing ratio test case C3: dp 1% (top); test case C4: dp 3% (bottom)

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Fig. 4

Axial velocity distribution 30 deg straight edge heat shield; profiles of axial velocity at x/P = 5 (profile 1) and x/P = 20 (profile 2)

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Fig. 5

Velocity distribution 30 deg straight edge heat shield

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Fig. 6

Temperature and local blowing ratio 30 deg straight edge heat shield: test case C3

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Fig. 7

Cooling effectiveness (contour) and local blowing ratios (isolines) for 30 deg straight edge heat shield: test case C3 (top) and C4 (bottom)

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Fig. 8

Effectiveness profiles for 30 deg straight edge heat shield for test cases C3 (dashed line) and C4 (solid line) at x/P = 4.5 (top, profile 1) and x/P = 7.5 (bottom, profile 2)

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Fig. 9

Cooling effectiveness for 30 deg straight edge heat shield for test cases C1 (top) and C2 (bottom)

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Fig. 10

Effectiveness profiles for 30 deg straight edge heat shield for test cases C1 (dashed line) and C2 (solid line) at x/P = 4.5 (top, profile 1) and x/P = 7.5 (bottom, profile 2)

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Fig. 11

Effectiveness profiles for 45 deg straight edge heat shield for test cases C1 (dashed line) and C2 (solid line) at x/P = 7 (top, profile 1) and x/P = 10 (bottom, profile 2)

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Fig. 12

Cooling effectiveness (top) and local velocity contours (bottom) for 45 deg straight edge heat shield for test case C2

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