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

Adiabatic Effectiveness and Flow Field Measurements in a Realistic Effusion Cooled Lean Burn Combustor

[+] Author and Article Information
Antonio Andreini

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

Riccardo Becchi

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

Bruno Facchini

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

Lorenzo Mazzei

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

Alessio Picchi

Department of Industrial Engineering,
University of Florence,
via S.Marta 3,
Firenze 50139, Italy
e-mail: alessio.picchi@unifi.it

Fabio Turrini

GE Avio S.r.l.,
Combustion Systems Office,
Rivalta di Torino (TO) 10040, Italy
e-mail: fabio.turrini@avioaero.it

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 27, 2015; final manuscript received July 31, 2015; published online September 22, 2015. Editor: David Wisler.

J. Eng. Gas Turbines Power 138(3), 031506 (Sep 22, 2015) (11 pages) Paper No: GTP-15-1375; doi: 10.1115/1.4031309 History: Received July 27, 2015; Revised July 31, 2015

Over the last ten years, there have been significant technological advances toward the reduction of NOx emissions from civil aircraft engines, strongly aimed at meeting stricter and stricter legislation requirements. Nowadays, the most prominent way to meet the target of reducing NOx emissions in modern combustors is represented by lean burn swirl stabilized technology. The high amount of air admitted through a lean burn injection system is characterized by very complex flow structures such as recirculations, vortex breakdown, and precessing vortex core (PVC) that may deeply interact in the near wall region of the combustor liner. This interaction makes challenging the estimation of film cooling distribution, commonly generated by slot and effusion systems. The main purpose of the present work is the characterization of the flow field and the adiabatic effectiveness due to the interaction of swirling flow, generated by real geometry injectors, and a liner cooling scheme made up of a slot injection and an effusion array. The experimental apparatus has been developed within EU project LEMCOTEC (low emissions core-engine technologies) and consists of a nonreactive three-sectors planar rig; the test model is characterized by a complete cooling system and three swirlers, replicating the geometry of a GE Avio PERM (partially evaporated and rapid mixing) injector technology. Flow field measurements have been performed by means of a standard 2D PIV (particle image velocimetry) technique, while adiabatic effectiveness maps have been obtained using PSP (pressure sensitive paint) technique. PIV results show the effect of coolant injection in the corner vortex region, while the PSP measurements highlight the impact of swirled flow on the liner film protection separating the contribution of slot and effusion flows. Furthermore, an additional analysis, exploiting experimental results in terms of heat transfer coefficient, has been performed to estimate the net heat flux reduction (NHFR) on the cooled test plate.

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Schulz, A. , 2001, “ Combustor Liner Cooling Technology in Scope of Reduced Pollutant Formation and Rising Thermal Efficiencies,” Ann. N. Y. Acad. Sci., 934, pp. 135–146. [CrossRef] [PubMed]
Lefebvre, A. H. , 1998, Gas Turbine Combustion, Taylor & Francis, Philadelphia.
Lilley, D. G. , 1977, “ Swirl Flows in Combustion: A Review,” AIAA J., 15(8), pp. 1063–1078. [CrossRef]
Rhode, D. L. , Lilley, D. G. , and McLaughlin, D. K. , 1983, “ Mean Flowfields in Axisymmetric Combustor Geometries With Swirl,” AIAA J., 21(4), pp. 593–600. [CrossRef]
Brum, R. D. , and Samuelsen, G. S. , 1987, “ Two-Component Laser Anemometry Measurements of Non-Reacting and Reacting Complex Flows in a Swirl-Stabilized Model Combustor,” Exp. Fluids, 5(2), pp. 95–102. [CrossRef]
Spencer, A. , Hollis, D. , and Gashi, S. , 2008, “ Investigation of the Unsteady Aerodynamics of an Annular Combustor Using PIV and LES,” ASME Paper No. GT2008-50277.
Gnirss, M. , and Tropea, C. , 2008, “ Simultaneous PIV and Concentration Measurements in a Gas-Turbine Model,” Exp Fluids, 45(4), pp. 643–656. [CrossRef]
Patil, S. , Sedalor, T. , Tafti, D. , Ekkad, S. , Kim, Y. , Dutta, P. , Moon, H. K. , and Srinivasan, R. , 2011, “ Study of Flow and Convective Heat Transfer in a Simulated Scaled up Low Emission Annular Combustor,” ASME J. Therm. Sci. Eng. Appl., 3(3), p. 031010. [CrossRef]
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(3), p. 031012. [CrossRef]
Andreini, A. , Facchini, B. , Mazzei, L. , and Turrini, F. , 2015, “ Impact of Swirl Flow on Combustor Liner Heat Transfer and Cooling—A Numerical Investigation With Hybrid RANS–LES Models,” ASME Paper No. GT2015-42403.
Sasaki, M. , Takahara, K. , Kumagai, T. , and Hamano, M. , 1979, “ Film Cooling Effectiveness for Injection From Multirow Holes,” ASME J. Eng. Power, 101(1), pp. 101–108. [CrossRef]
Andrews, G. E. , Asere, A. A. , Gupta, M. L. , and Mkpadi, M. C. , 1990, “ Effusion Cooling: The Influence of Number of Hole,” Proc. Inst. Mech. Eng., Part A, 204(3), pp. 175–182. [CrossRef]
Andrews, G. E. , Bazdidi-Tehrani, F. , Hussain, C. I. , and Pearson, J. P. , 1991, “ Small Diameter Film Cooling Hole Heat Transfer: The Influence of Hole Length,” ASME Paper No. 91-GT-344.
Wurm, B. , Schulz, A. , and Bauer, H. J. , 2009, “ A New Test Facility for Investigating the Interaction Between Swirl Flow and Wall Cooling Films in Combustors,” ASME Paper No. GT2009-59961.
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]
Marinov, S. , Kern, M. , Merkle, K. , Zarzalis, N. , Peschiulli, A. , and Turrini, F. , 2010, “ On Swirl Stabilized Flame Characteristics Near the Weak Extinction Limit,” ASME Paper No. GT2010-22335.
Andrews, G. E. , Ahmed, N. T. , Phylaktou, R. , and King, P. , 2009, “ Weak Extinction in Low NOx Gas Turbine Combustion,” ASME Paper No. GT2009-59830.
Raffel, M. , Willert, C. E. , and Kompenhans, J. , 2007, Particle Image Velocimetry—A Practical Guide, 2nd ed., Springer, Berlin.
Charonko, J. J. , and Vlachos, P. P. , 2013, “ Estimation of Uncertainty Bounds for Individual Particle Image Velocimetry Measurements From Cross-Correlation Peak Ratio,” Meas. Sci. Technol., 24(6), p. 065301. [CrossRef]
Han, J. , Dutta, S. , and Ekkad, S. , 2012, Gas Turbine Heat Transfer and Cooling Technology, 2nd ed., Taylor & Francis, New York.
Wright, L. M. , Gao, Z. , Varvel, T. A. , and Han, J.-C. , 2005, “ Assessment of Steady State PSP, TSP, and IR Measurement Techniques for Flat Plate Film Cooling,” ASME Paper No. HT2005-72363.
Caciolli, G. , Facchini, B. , Picchi, A. , and Tarchi, L. , 2013, “ Comparison Between PSP and TLC Steady State Techniques for Adiabatic Effectiveness Measurement on a Multiperforated Plate,” Exp. Therm. Fluid Sci., 48, pp. 122–133. [CrossRef]
Jones, T. V. , 1999, “ Theory for the Use of Foreign Gas in Simulating Film Cooling,” Int. J. Heat Fluid Flow, 20(3), pp. 349–354. [CrossRef]
Kline, S. J. , and McClintock, F. A. , 1953, “ Describing Uncertainties in Single Sample Experiments,” Mech. Eng., 75, pp. 3–8.
Andreini, A. , Facchini, B. , Mazzei, L. , Bellocci, L. , and Turrini, F. , 2014, “ Assessment of Aero-Thermal Design Methodology for Effusion Cooled Lean Burn Annular Combustors,” ASME Paper No. GT2014-26764.
Andreini, A. , Da Soghe, R. , Facchini, B. , Mazzei, L. , Colantuoni, S. , and Turrini, F. , 2013, “ Local Source Based CFD Modeling of Effusion Cooling Holes: Validation and Application to an Actual Combustor Test Case,” ASME Paper No. GT2013-94874.
Andreini, A. , Caciolli, G. , Facchini, B. , and Tarchi, L. , 2013, “ Experimental Evaluation of the Density Ratio Effects on the Cooling Performance of a Combined Slot/Effusion Combustor Cooling System,” ISRN Aerosp. Eng., 2013, pp. 1–14. [CrossRef]
Sen, B. , Schmidt, D. L. , and Bogard, D. G. , 1996, “ Film Cooling With Compound Angle Holes: Heat Transfer,” ASME J. Turbomach., 118(4), pp. 800–806. [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 Paper No. GT2015-42587.


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Fig. 1

Cross-sectional view of the test rig with a detailed section of the PERM swirler

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Fig. 2

Position of the PIV measurement plane

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Fig. 3

Effusion test plate sprayed with PSP

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Fig. 4

Flow field on measurements plane (ΔP/P = 3.5%)

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Fig. 5

Adiabatic effectiveness distribution: effect of effusion system pressure drop (ΔP/P = 3.5%)

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Fig. 6

Detailed views of adiabatic effectiveness distribution ((ΔP/P)eff = 1%; no slot cooling)

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Fig. 7

Laterally averaged adiabatic effectiveness distribution: effect of effusion pressure drop

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Fig. 8

Adiabatic effectiveness distribution: effect of slot injection (ΔP/P = 3.5%)

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Fig. 9

Laterally averaged adiabatic effectiveness distribution: effect of slot injection (ΔP/Peff = 3%)

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Fig. 10

Adiabatic effectiveness profiles (ΔP/Peff=3%)

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Fig. 11

Laterally averaged NHFR distribution



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