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Research Papers

Heat Transfer in Reacting Cooling Films: Influence and Validation of Combustion Modeling in Numerical Simulations

[+] Author and Article Information
Stephanie Pohl

Institut für Thermodynamik,
Fakultät für Luft- und Raumfahrttechnik,
Universität der Bundeswehr München,
Werner-Heisenberg-Weg 39,
Neubiberg 85577, Germany
e-mail: stephanie.pohl@unibw.de

Gabriele Frank

Institut für Thermodynamik,
Fakultät für Luft- und Raumfahrttechnik,
Universität der Bundeswehr München,
Werner-Heisenberg-Weg 39,
Neubiberg 85577, Germany
e-mail: gabriele.frank@unibw.de

Michael Pfitzner

Institut für Thermodynamik,
Fakultät für Luft- und Raumfahrttechnik,
Universität der Bundeswehr München,
Werner-Heisenberg-Weg 39,
Neubiberg 85577, Germany
e-mail: michael.pfitzner@unibw.de

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received November 2, 2014; final manuscript received November 18, 2014; published online January 28, 2015. Editor: Kenneth C. Hall.

J. Turbomach 137(8), 081003 (Aug 01, 2015) (10 pages) Paper No: TURBO-14-1284; doi: 10.1115/1.4029350 History: Received November 02, 2014; Revised November 18, 2014; Online January 28, 2015

The demand for increased performance and lower weight of gas turbines gives rise to higher fuel-to-air ratios and a more compact design of the combustion chamber, thereby increasing the potential of fuel escaping unburnt from the combustor. Chemical reactions are likely to occur when the coolant air, used to protect the turbine blades, interacts with the unreacted fuel. Within this work, Reynolds-averaged Navier–Stokes (RANS) simulations of reacting cooling films exposed to high temperature fuel-rich exhaust gases are performed using the commercial computational fluid dynamics (CFD) code ansys fluent and validated against experimental results obtained at the Air Force Research Laboratory in Ohio. The results underline that the choice of the turbulence model has a significant impact on the evolution of the flow field and the mixing effectiveness. The flamelet as well as the equilibrium combustion model is able to predict an adequate distance of the reaction zone normal to the wall. Its thickness, however, is still much smaller and its onset too far upstream as compared to the experimental results. According to the present analysis, the flamelet combustion model applied along with k–ω shear stress transport (SST) or k–ε turbulence model turned out to be an appropriate choice in order to model near wall reacting flows with reasonable prospect of success.

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References

Lukachko, S., Kirk, D., and Waitz, I., 2002, “Gas Turbine Engine Durability Impacts of High Fuel-Air Combustors: Part 1—Potential for Secondary Combustion of Partially Reacted Fuel,” ASME Paper No. GT2002-30077. [CrossRef]
Kirk, D., Guenette, G., Lukachko, S., and Waitz, I., 2002, “Gas Turbine Engine Durability Impacts of High Fuel-Air Combustors: Part 2—Near Wall Reaction Effects on Film-Cooled Heat Transfer,” ASME Paper No. GT2002-30182. [CrossRef]
Milanes, D., Kirk, D., Fidkowski, K., and Waitz, I., 2004, “Gas Turbine Durability Impacts of High Fuel-Air Ratio Combustors: Near Wall Reaction Effects on Film-Cooled Backward-Facing Step Heat Transfer,” ASME Paper No. GT2004-53259. [CrossRef]
Anderson, W., Polanka, M., Zelina, J., Evans, D., Stouffer, S., and Justinger, G., 2009, “Effects of a Reacting Cross-Stream on Turbine Film Cooling,” ASME Paper No. GT2009-59242. [CrossRef]
Polanka, M., Zelina, J., Anderson, W., Sekar, B., Evans, D., King, P., Thornburg, H., Lin, C., and Stouffer, S., 2011, “Heat Release in Turbine Film Cooling I: Experimental and Computational Comparison of Three Geometries,” J. Propul. Power, 27(2), pp. 257–268. [CrossRef]
Lin, C., Holder, R., Polanka, M., Zelina, J., Sekar, B., Thornburg, H., and Briones, A., 2011, “Heat Release in Turbine Film Cooling II: Numerical Details of Secondary Combustion Surrounding Shaped Holes,” J. Propul. Power, 27(2), pp. 269–281. [CrossRef]
Bohan, B., Blunck, D., Polanka, M., Kostka, S., Jiang, N., Roy, S., and Stouffer, S., 2012, “Impact of an Upstream Film-Cooling Row on Mitigation of Secondary Combustion in a High Fuel-Air Environment,” ASME Paper No. GT2012-68310. [CrossRef]
Zelina, J., Greenwood, R., and Shouse, D., 2006, “Operability and Efficiency Performance of Ultra-Compact, High Gravity (g) Combustor Concepts,” ASME Paper No. GT2006-90119. [CrossRef]
Harrison, K., and Bogard, D., 2008, “Comparison of RANS Turbulence Models for Prediction of Film Cooling Performance,” ASME Paper No. GT2008-51423. [CrossRef]
Walters, D., and Leylek, J., 2000, “A Detailed Analysis of Film-Cooling Physics: Part I—Streamwise Injection With Cylindrical Holes,” ASME J. Turbomach., 122(1), pp. 102–112. [CrossRef]
DeLallo, M., Polanka, M., and Blunck, D., 2012, “Impact of Trench and Ramp Film Cooling Designs to Reduce Heat Release Effects in a Reacting Flow,” ASME Paper No. GT2012-68311. [CrossRef]
Evans, D., 2008, “The Impact of Heat Release in Turbine Film Cooling,” MS thesis, Air Force Institute of Technology, WPAFB, OH, Paper No. AFIT/GAE/ENY08-J02.
Chan, W., Kolla, H., Ihme, M., and Chen, J., 2012, “Analysis of a Jet in Cross Flow Using an Unsteady Flamelet Model,” Spring Technical Meeting of the Central States Section of the Combustion Institute, Dayton, OH, Apr. 22–24, pp. 1156–1167.
Wang, L., Pitsch, H., Yamamoto, K., and Orii, A., 2011, “An Efficient Approach of Unsteady Flamelet Modeling of a Cross-Flow-Jet Combustion System Using LES,” Combust. Theory Model., 15(6), pp. 849–862. [CrossRef]
Grout, R., Gruber, A., Yoo, C., and Chen, J., 2011, “Direct Numerical Simulation of Flame Stabilization Downstream of a Transverse Fuel Jet in Cross-Flow,” Proc. Combust. Inst., 33(1), pp. 1629–1637. [CrossRef]
Kolla, H., Grout, R., Gruber, A., and Chen, J., 2011, “Effect of Injection Angle on Stabilization of a Reacting Turbulent Hydrogen Jet in Cross-Flow,” 7th U.S. National Technical Meeting of the Combustion Institute, Atlanta, GA, Mar. 20–23.
Frank, G., Ferraro, F., and Pfitzner, M., 2013, “RANS Simulations of Chemical Reactions in Cooling Films,” 5th European Conference for Aeronautics and Space Sciences (EUCASS), Munich, July 1–5.
Rotexo, 2012, cosilab, Rotexo GmbH & Co. KG, Bochum, Germany.
Smith, G. P., Golden, D. M., Frenklach, M., Moriarty, N. W., Eiteneer, B., Goldenberg, M., Bowman, C. T., Hanson, R. K., Song, S., Gardiner, Jr., W. C., Lissianski, V. V., and Qin, Z., 2012, GRI Mech 3.0, Gas Research Institute, Chicago, IL, http://combustion.berkeley.edu/gri-mech/version30/text30.html
ANSYS, 2011, ANSYSFluent, Release 14.0, Theory Guide, ANSYS Inc., Canonsburg, PA.
Peters, N., 1984, “Laminar Diffusion Flamelet Models in Non-Premixed Turbulent Combustion,” Prog. Energy Combust. Sci., 10(3), pp. 319–339. [CrossRef]
Frank, G., Pohl, S., and Pfitzner, M., 2014, “Heat Transfer in Reacting Cooling Films, Part II: Modelling Near-Wall Effects in Non-Premixed Combustion With OpenFOAM,” ASME Paper No. GT2014-25215. [CrossRef]
Fiala, T., and Sattelmayer, T., 2013, “A Posteriori Computation of OH* Radiation From Numerical Simulations in Rocket Combustion Chambers,” 5th European Conference for Aeronautics and Space Sciences (EUCASS), Munich, July 1–5.
Kathrotia, T., Fikri, M., Bozkurt, M., Hartmann, M., Riedel, U., and Schulz, C., 2010, “Study of the H + O + M Reaction Forming OH*: Kinetics of OH* Chemiluminescence in Hydrogen Combustion Systems,” Combust. Flame, 157(7), pp. 1261–1273. [CrossRef]
O’ Conaire, M., Curran, H., Simmie, J., Pitz, W., and Westbrook, C., 2004, “A Comprehensive Modeling Study of Hydrogen Oxidation,” Int. J. Chem. Kinet., 36(11), pp. 603–622. [CrossRef]
Burcat, A., and Ruscic, B., 2005, “Third Millennium Ideal Gas and Condensed Phase Thermochemical Database for Combustion with Updates from Active Thermochemical Tables,” joint report, Argonne National Laboratory, Argonne, IL, Report No. ANL-05/20, and Technion-Israel Institute of Technology, Haifa, Report No. TAE 960.

Figures

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Fig. 1

Cooling hole geometry taken from Ref. [7]

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Fig. 2

Computational domain and boundary conditions

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Fig. 3

Comparison of midplane temperature profile for different meshes: (a) 1.1 million cells (baseline mesh) and (b) 3 million cells (refined mesh)

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Fig. 4

Comparison of temperature profile for different meshes and axial locations

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Fig. 5

Detail of the mesh used for the numerical simulations

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Fig. 6

Mean value of temperature as function of the mean mixture fraction variance: left χst˜ = 0.1 s-1 and right χst˜ = 181 s-1

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Fig. 7

Comparison of dimensionless temperature profile at the midplane for different turbulence models: (a) standard k-[ɛ], (b) realizable k-[ɛ], and (c) k-[ω] SST. Combustion: flamelet concept.

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Fig. 8

Lines of constant Z˜ colored by their variance Z"2˜. Top: kε and bottom: k–ω SST.

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Fig. 9

Comparison of dimensionless temperature profile at the midplane for different combustion models and k–ω SST turbulence model. Left: air injection, right: N2 injection. (a) and (b) equilibrium model, (c) and (d) FR/ED model, and (e) and (f) flamelet model.

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Fig. 10

Distribution of scalar dissipation rate for k–ω SST turbulence model and flamelet combustion concept

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Fig. 11

Mixing effectiveness η⋆ for the use of different turbulence and combustion models

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Fig. 12

Simulated OH ⋆ molar concentration at midplane for equilibrium assumption (left) and chemiluminescence reaction (right) compared to experimental data taken from Ref. [7]. (a) experimentally measured OH*, (b) and (c) equilibrium with k-ω SST turbulence model, (d) FR/EDM and thermal equilibrium assumption not evaluable due to abscence of OH in 2-step mechanism, (e) FR/EDM with k-ω SST turbulence model (chemiluminuescence reaction), (f) and (g) flamelet with k-ω SST turbulence model (h) and (i) flamelet with k-ɛ turbulence model.

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