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

Impact of Swirl Flow on Combustor Liner Heat Transfer and Cooling: A Numerical Investigation With Hybrid Reynolds-Averaged Navier–Stokes Large Eddy Simulation Models

[+] Author and Article Information
Lorenzo Mazzei

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

Antonio Andreini

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

Bruno Facchini

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

Fabio Turrini

Combustors Product Engineering,
GE Avio S.r.l.,
via Primo Maggio 56,
Rivalta di Torino, TO 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 13, 2015; final manuscript received August 17, 2015; published online November 3, 2015. Editor: David Wisler.

J. Eng. Gas Turbines Power 138(5), 051504 (Nov 03, 2015) (10 pages) Paper No: GTP-15-1261; doi: 10.1115/1.4031622 History: Received July 13, 2015; Revised August 17, 2015

This paper reports the main findings of a numerical investigation aimed at characterizing the flow field and the wall heat transfer resulting from the interaction of a swirling flow provided by lean-burn injectors and a slot cooling system, which generates film cooling in the first part of the combustor liner. In order to overcome some well-known limitations of Reynolds-averaged Navier–Stokes (RANS) approach, e.g., the underestimation of mixing, the simulations were performed with hybrid RANS–large eddy simulation (LES) models, namely, scale-adaptive simulation (SAS)–shear stress transport (SST) and detached eddy simulation (DES)–SST, which are proving to be a viable approach to resolve the main structures of the flow field. The numerical results were compared to experimental data obtained on a nonreactive three-sector planar rig developed in the context of the EU project LEMCOTEC. The analysis of the flow field has highlighted a generally good agreement against particle image velocimetry (PIV) measurements, especially for the SAS–SST model, whereas DES–SST returns some discrepancies in the opening angle of the swirling flow, altering the location of the corner vortex. Also the assessment in terms of Nu/Nu0 distribution confirms the overall accuracy of SAS–SST, where a constant overprediction in the magnitude of the heat transfer is shown by DES–SST, even though potential improvements with mesh refinement are pointed out.

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ICAO, 2010, “ Enviromental Report, Aviation and Climate Change,” International Civil Aviation Organization, Montreal, Canada, http://www.icao.int/environmental-protection/Documents/Publications/ENV_Report_2010.pdf
Lazik, W. , and Doerr, T. , 2008, “ Development of Lean-Burn Low-NOx Combustion Technology at Rolls-Royce Deutschland,” ASME Paper No. GT2008-51115.
Lefebvre, A. H. , and Ballal, D. R. , 2010, Gas Turbine Combustion, CRC Press—Taylor & Francis, New York.
Behrendt, T. , Hassa, C. , and Gerendas, M. , 2008, “ Characterisation of Advanced Combustor Cooling Concepts Under Realistic Operating Conditions,” ASME Paper No. GT2008-51191.
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. Eng. Gas Turbines Power, 134(12), p. 121503. [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.
Andreini, A. , Caciolli, G. , Facchini, B. , Picchi, A. , and Turrini, F. , 2014, “ Experimental Investigation of the Flow Field and the Heat Transfer on a Scaled Cooled Combustor Liner With Realistic Swirling Flow Generated by a Lean-Burn Injection System,” ASME J. Turbomach., 137(2), p. 031012. [CrossRef]
Patil, S. , Abraham, S. , and Ekkad, S. , 2009, “ Experimental and Numerical Investigation of Convective Heat Transfer in a Gas Turbine Can Combustor,” ASME Paper No. GT2009-59377.
Wurm, B. , Schulz, A. , Bauer, H.-J. , and Gerendas, M. , 2014, “ Impact of Swirl Flow on the Penetration Behaviour and Cooling Performance of a Starter Cooling Film in Modern Lean Operating Combustion Chambers,” ASME Paper No. GT2014-25520.
Strelets, M. , 2001, “ Detached Eddy Simulation of Massively Separated Flows,” AIAA Paper No. 2001-0879.
Menter, F. R. , and Egorov, Y. , 2004, “ Re-Visiting the Turbulent Scale Equation,” IUTAM Symposium One Hundred Years of Boundary Layer Research, Göttingen, Germany, Aug. 12–14, pp. 279–290.
Menter, F. R. , and Egorov, Y. , 2004, “ A Scale-Adaptive Simulation Model Using Two-Equation Models,” AIAA Paper No. 2005-1095.
Widenhorn, A. , Noll, B. , and Aigner, M. , 2009, “ Numerical Study of a Non-Reacting Turbulent Flow in a Gas Turbine Model Combustor,” AIAA Paper No. 2009-647.
Patil, S. , and Tafti, D. , 2011, “ Large Eddy Simulation of Flow and Convective Heat Transfer in a Gas Turbine Can Combustor With Synthetic Inlet Turbulence,” ASME Paper No. GT2011-46561.
Kao, Y.-H. , Tambe, S. B. , and Jeng, S.-M. , 2014, “ Aerodynamics Study of a Linearly-Arranged 5-Swirler Array,” ASME Paper No. GT2014-25094.
Syred, N. , 2006, “ Review of Oscillation Mechanisms and the Role of the Precessing Vortex Core (PVC) in Swirl Combustion Systems,” Prog. Energy Combust. Sci., 32(2), pp. 93–161. [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.
Kline, S. J. , and McClintock, F. A. , 1953, “ Describing Uncertainties in Single Sample Experiments,” Mech. Eng., 75(1), pp. 3–8.
Menter, F. R. , 2012, “ Best Practice: Scale-Resolving Simulations in ansys CFD,” ANSYS Germany GmbH, Darmstadt, Germany.
Spalart, P. R. , Jou, W.-H. , Strelets, M. , and Allmaras, S. R. , 1997, “ Comments on the Feasibility of LES for Wings, and on a Hybrid RANS/LES Approach,” 1st AFOSR International Conference on DNS/LES, Ruston, LA, Aug. 4–8, pp. 137–147.
Menter, F. R. , and Kuntz, M. , 2003, “ Development and Application of a Zonal DES Turbulence Model for cfx-5,” ANSYS CFX, Canonsburg, PA.
Egorov, Y. , and Menter, F. R. , 2007, “ Development and Application of SST-SAS Turbulence Model in the Desider Project,” Second Symposium on Hybrid RANS-LES Methods, Corfu, Greece, June 17–18, pp. 261–270.
Pope, S. B. , 2004, “ Ten Questions Concerning the Large-Eddy Simulation of Turbulent Flows,” New J. Phys., 6(1), p. 35.
Boudier, G. , Gicquel, L. Y. M. , and Poinsot, T. J. , 2008, “ Effects of Mesh Resolution on Large Eddy Simulation of Reacting Flows in Complex Geometry Combustors,” Combust. Flame, 155(1–2), pp. 196–214. [CrossRef]
Celik, I. B. , Cehreli, Z. N. , and Yavuz, I. , 2005, “ Index of Resolution Quality for Large Eddy Simulations,” ASME J. Fluids Eng., 127(5), pp. 949–958. [CrossRef]
Andreini, A. , Becchi, R. , Facchini, B. , Picchi, A. , and Turrini, F. , 2015, “ Effect of Slot Injection and Effusion Array on the Liner Heat Transfer Coefficient of a Scaled Lean Burn Combustor With Representative Swirling Flow,” ASME J. Eng. Gas Turbines Power (in press).
Andreini, A. , Becchi, R. , Facchini, B. , Mazzei, L. , Picchi, A. , and Turrini, F. , 2015, “ Adiabatic Effectiveness and Flow Field Measurements in a Realistic Effusion Cooled Lean Burn Combustor,” ASME Paper No. GT2015-42584.


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Fig. 4

Position of the PIV measurements planes

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Fig. 3

Experimental apparatus [7]

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Fig. 2

Classical flow pattern of an array of swirles (top) and dome-attached swirling flow (bottom) [15]

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Fig. 1

Measured and predicted flow field on the median plane

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Fig. 5

Sketch of the computational domain

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Fig. 6

Computational grids: mesh 1 (left, coarse) and 2 (right, fine)

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Fig. 7

Flow field on the center plane

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Fig. 8

Profiles of velocity component in streamwise direction (center plane)

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Fig. 9

Two-dimensional velocity on the median plane (PVC visualized by a constant pressure isosurface)

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Fig. 10

Effect of mesh refinement and turbulence modeling on the criterion proposed by Pope (center plane)

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Fig. 12

Nusselt number distributions on the central sector

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Fig. 13

Sketch of the main recirculation structures inside the test section

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Fig. 14

Laterally averaged Nusselt number augmentation

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Fig. 11

Effect of mesh refinement on the criterion proposed by Celik et al. [25] (center plane)



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