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

Investigation on the Effect of a Realistic Flow Field on the Adiabatic Effectiveness of an Effusion-Cooled Combustor

[+] Author and Article Information
Luca Andrei

DIEF—Department of Industrial
Engineering Florence,
University of Florence,
via di Santa Marta 3,
Firenze 50139, Italy
e-mail: luca.andrei@htc.de.unifi.it

Antonio Andreini

DIEF—Department of Industrial
Engineering Florence,
University of Florence,
via di Santa Marta 3,
Firenze 50139, Italy
e-mail: antonio.andreini@htc.de.unifi.it

Cosimo Bianchini

DIEF—Department of Industrial
Engineering Florence,
University of Florence,
via di Santa Marta 3,
Firenze 50139, Italy
e-mail: cosimo.bianchini@htc.de.unifi.it

Bruno Facchini

DIEF—Department of Industrial
Engineering Florence,
University of Florence,
via di Santa Marta 3,
Firenze 50139, Italy
e-mail: bruno.facchini@htc.de.unifi.it

Lorenzo Mazzei

DIEF—Department of Industrial
Engineering Florence,
University of Florence,
via di Santa Marta 3,
Firenze 50139, Italy
e-mail: lorenzo.mazzei@htc.de.unifi.it

Fabio Turrini

Combustors Product Engineering,
Avio Aero,
via Primo Maggio 56,
Rivalta di Torino 10040, Italy
e-mail: fabio.turrini@avioaero.com

1Corresponding author.

Contributed by the Combustion and Fuels Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 16, 2014; final manuscript received August 27, 2014; published online November 18, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 137(5), 051501 (May 01, 2015) (9 pages) Paper No: GTP-14-1402; doi: 10.1115/1.4028676 History: Received July 16, 2014; Revised August 27, 2014; Online November 18, 2014

Effusion cooling represents the state of the art of liner cooling technology for modern combustors. This technique consists of an array of closely spaced discrete film cooling holes and contributes to lower the metal temperature by the combined protective effect of coolant film and heat removal through forced convection inside each hole. Despite many efforts reported in literature to characterize the cooling performance of these devices, detailed analyses of the mixing process between coolant and hot gas are difficult to perform, especially when superposition and density ratio effects as well as the interaction with complex gas side flow field become significant. Furthermore, recent investigations on the acoustic properties of these perforations pointed out the challenge to maintain optimal cooling performance also with orthogonal holes, which showed higher sound absorption. The objective of this paper is to investigate the impact of a realistic flow field on the adiabatic effectiveness performance of effusion cooling liners to verify the findings available in literature, which are mostly based on effusion flat plates with aligned cross flow, in case of swirled hot gas flow. The geometry consists of a tubular combustion chamber, equipped with a double swirler injection system and characterized by 22 rows of cooling holes on the liner. The liner cooling system employs slot cooling as well: its interactions with the cold gas injected through the effusion plate are investigated too. Taking advantage of the rotational periodicity of the effusion geometry and assuming axisymmetric conditions at the combustor inlet, steady state RANS calculations have been performed with the commercial code Ansys® CFX simulating a single circumferential pitch. Obtained results show how the effusion perforation angle deeply affects the flow-field around the corner of the combustor, in particular, with a strong reduction of slot effectiveness in case of 90 deg angle value.

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References

ICAO, 2010, “Environmental Report, Aviation and Climate Change,” International Civil Aviation Organization, Montreal, Canada, available at: http://www.icao.int/environmental-protection/Documents/Publications/ENV_Report_2010.pdf
Lazik, W., Doerr, T., Bake, S., Bank, R. V. D., and Rackwitz, L., 2008, “Development of Lean-Burn Low-NOx Combustion Technology at Rolls-Royce Deutschland,” ASME Paper No. GT2008-51115. [CrossRef]
Lefebvre, A. H., and Ballal, D. R., 2010, Gas Turbine Combustion, CRC Press-Taylor & Francis Group, Boca Raton, FL.
Behrendt, T., Hassa, C., and Gerendas, M., 2008, “Characterisation of Advanced Combustor Cooling Concepts Under Realistic Operating Conditions,” ASME Paper No. GT2008-51191. [CrossRef]
Wurm, B., Schulz, A., Bauer, H. J., and Gerendas, M., 2012, “Impact of Swirl Flow on the Cooling Performance of an Effusion Cooled Combustor Liner,” ASME J. Gas Turbines Power, 134(12), p. 121503. [CrossRef]
Andrei, L., Andreini, A., Bianchini, C., Facchini, B., and Mazzei, L., 2013, “Numerical Analysis of Effusion Plates for Combustor Liners Cooling With Varying Density Ratio,” ASME Paper No. GT2013-95039. [CrossRef]
Marinov, S., Kern, M., Merkle, K., Zarzalis, N., Peschiulli, A., Turrini, F., and Sara, O. N., 2010, “On Swirl Stabilized Flame Characteristics Near the Weak Extinction Limit,” ASME Paper No. GT2010-22335. [CrossRef]
Bianchini, C., Andrei, L., Andreini, A., and Facchini, B., 2013, “Numerical Benchmark of Non-Conventional RANS Turbulence Models for Film and Effusion Cooling,” ASME J. Turbomach., 135(4), p. 041026. [CrossRef]
Andreini, A., Facchini, B., Picchi, A., Tarchi, L., and Turrini, F., 2014, “Experimental and Theoretical Investigation of Thermal Effectiveness in Multi-Perforated Plates for Combustor Liner Effusion Cooling,” ASME J. Turbomach., 136(9), p. 091003. [CrossRef]
Wurm, B., Schulz, A., Bauer, H. J., and Gerendas, M., 2013, “Cooling Efficiency for Assessing the Cooling Performance of an Effusion Cooled Combustor Liner,” ASME Paper No. GT2013-94304. [CrossRef]
Patil, S., Abraham, S., Taft, D., Ekkad, S., Kim, Y., Dutta, P., Moon, H.-K., and Srinivasan, R., 2010, “Experimental and Numerical Investigation of Convective Heat Transfer in a Gas Turbine Can Combustor,” ASME J. Turbomach., 133(1), p. 011028. [CrossRef]
Martiny, M., Schulz, A., and Wittig, S., 2000, “Effusion Cooled Combustor Liners of Gas Turbines—An Assessment of the Contributions of Convective, Impingement, and Film Cooling,” Symposium on Energy Engineering in the 21st Century (SEE2000), Hong Kong, Jan. 9–13.
Behrendt, T., and Gerendas, M., 2012, “Characterization of the Influence of Moderate Pressure Fluctuations on the Cooling Performance of Advanced Combustor Cooling Concepts in a Reacting Flow,” ASME Paper No. GT2012-68845. [CrossRef]
Ceccherini, A., Facchini, B., Tarchi, L., and Toni, L., 2009, “Combined Effect of Slot Injection, Effusion Array and Dilution Hole on the Cooling Performance of a Real Combustor Liner,” ASME Paper No. GT2009-60047. [CrossRef]
Scrittore, J. J., Thole, K. A., and Burd, S. W., 2007, “Investigations of Velocity Profiles for Effusion Cooling of a Combustor Liner,” ASME J. Turbomach., 129(3), pp. 518–526. [CrossRef]
Martiny, M., Schulz, A., and Wittig, S., 1995, “Full-Coverage Film Cooling Investigations: Adiabatic Wall Temperature and Flow Visualization,” ASME Paper No. 95-WA/HT-4.
Facchini, B., Tarchi, L., and Toni, L., 2009, “Investigation of Circular and Shaped Effusion Cooling Arrays for Combustor Liner Application—Part 1: Experimental Analysis,” ASME Paper No. GT2009-60037. [CrossRef]
Andreini, A., Bianchini, C., Ceccherini, A., Facchini, B., Mangani, L., Cinque, G., and Colantuoni, S., 2009, “Investigation of Circular and Shaped Effusion Cooling Arrays for Combustor Liner Application—Part 2: Numerical Analysis,” ASME Paper No. GT2009-60038. [CrossRef]
Hoda, A., and Acharya, S., 2000, “Predictions of a Film Coolant Jet in Crossflow With Different Turbulence Models,” ASME J Turbomach., 122(3), pp. 558–569. [CrossRef]
Harrison, K. L., and Bogard, D. G., 2008, “Comparison of RANS Turbulence Models for Prediction of Film Cooling Performance,” ASME Paper No. GT2008-51423. [CrossRef]
Cottin, G., Laroche, E., Savary, N., and Millan, P., 2011, “Modeling of the Heat Flux for Multi-Hole Cooling Applications,” ASME Paper No. GT2011-46330. [CrossRef]
Bergeles, G., Gosman, A. D., and Launder, B. E., 1978, “The Turbulent Jet in a Cross Stream at Low Injection Rates: A Three-Dimensional Numerical Treatment,” J. Numer. Heat Transfer, 1(2), pp. 217–242. [CrossRef]
Azzi, A., and Lakehal, D., 2002, “Perspectives in Modeling Film Cooling of Turbine Blades by Transcending Conventional Two-Equation Turbulence Models,” ASME J. Turbomach., 124(3), pp. 472–484. [CrossRef]
Holloway, D. S., Walters, D. K., and Leylek, J. H., 2005, “Computational Study of Jet-in-Crossflow and Film Cooling Using a New Unsteady-Based Turbulence Model,” ASME Paper No. GT2005-68155. [CrossRef]
Azzi, A., and Jubran, B. A., 2003, “Numerical Modeling of Film Cooling From Short Length Stream-Wise Injection Holes,” J. Heat Mass Transfer, 39(4), pp. 345–353. [CrossRef]
Lakehal, D., Theodoris, G. S., and Rodi, W., 1998, “Computation of Film Cooling of a Flat Plate by Lateral Injection From Arrow of Holes,” Int. J. Heat Fluid Flow, 19(5), pp. 418–430. [CrossRef]
Lakehal, D., 2002, “Near-Wall Modeling of Turbulent Convective Heat Transport in Film Cooling of Turbine Blades With the Aid of Direct Numerical Simulation Data,” ASME J. Turbomach., 124(3), pp. 485–498. [CrossRef]
Kim, J., Moin, P., and Moser, R., 1987, “Turbulence Statistics in Fully Developed Channel Flow at Low Reynolds Number,” J. Fluid Mech., 177, pp. 133–166. [CrossRef]
Kern, M., Marinov, S., Habisreuther, P., Zarzalis, N., Peschiulli, A., and Turrini, F., 2011, “Characteristics of an Ultra-Lean Swirl Combustor Flow by LES and Comparison to Measurements,” ASME Paper No. GT2011-45300. [CrossRef]
Schulz, A., 2001, “Combustor Liner Cooling Technology in Scope of Reduced Pollutant Formation and Rising Thermal Efficiencies,” Heat Transfer Gas Turbine Syst., 934, pp. 135–146. [CrossRef]
Andrei, L., Andreini, A., Bianchini, C., Caciolli, G., Facchini, B., Mazzei, L., Picchi, A., and Turrini, F., 2014, “Effusion Cooling Plates for Combustor Liners: Experimental and Numerical Investigations on the Effect of Density Ratio,” Energy Procedia, 45, pp. 1402–1411. [CrossRef]

Figures

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Fig. 1

Test case geometries and computational grid: (a) no slot geometry, (b) slot geometry, and (c) computational grid

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Fig. 2

Influence of perforation angle (DR = 1). (a) V = Vref distribution on meridional plane and (b) EffCool distribution on meridional plane.

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Fig. 3

Laterally averaged adiabatic effectiveness profile on liner wall: perforation angle influence (DR = 1)

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Fig. 4

Density ratio effect on adiabatic effectiveness distribution on liner wall

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Fig. 5

Laterally averaged adiabatic effectiveness profile on liner wall: DR influence. (a) G2 geometry and (b) G7 geometry.

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Fig. 6

Local blowing ratio along the liner: influence of DR and perforation

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Fig. 7

Laterally averaged adiabatic effectiveness profile on liner wall: comparison between flat plate and tubular combustor (DR = 1, BR = 2)

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Fig. 8

Slot coolant effect on adiabatic effectiveness distribution on liner wall

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Fig. 9

Slot coolant distribution on meridional plane

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Fig. 10

Laterally averaged adiabatic effectiveness profile on liner wall: slot cooling injection influence. (a) G2 geometry and (b) G7 geometry.

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Fig. 11

Laterally averaged adiabatic effectiveness profile on liner wall: slot cooling mass flow rate influence

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