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

Experimental Study of Thermo-Acoustic Instability Triggering in a Staged Liquid Fuel Combustor Using High-Speed OH-PLIF

[+] Author and Article Information
Antoine Renaud

Aeronautical Technology Directorate,
Japan Aerospace Exploration Agency (JAXA),
Tokyo 182-8522, Japan;
Faculty of Science and Technology,
Keio University,
Tokyo 223-8522, Japan
e-mail: antoine.renaud@centralesupelec.fr

Shigeru Tachibana

Aeronautical Technology Directorate,
Japan Aerospace Exploration Agency (JAXA),
Tokyo 182-8522, Japan
e-mail: tachibana.shigeru@jaxa.jp

Shuta Arase

Faculty of Science and Technology,
Keio University,
Tokyo 223-8522, Japan

Takeshi Yokomori

Faculty of Science and Technology,
Keio University,
Tokyo 223-8522, Japan
e-mail: yokomori@mech.keio.ac.jp

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 November 9, 2017; final manuscript received December 12, 2017; published online May 2, 2018. Editor: David Wisler.

J. Eng. Gas Turbines Power 140(8), 081505 (May 02, 2018) (9 pages) Paper No: GTP-17-1611; doi: 10.1115/1.4038915 History: Received November 09, 2017; Revised December 12, 2017

A staged injector developed by JAXA and fueled with kerosene is studied in a high-pressure combustion experiment. With a stable pilot fuel flow rate, the fuel flow rate in the main stage is progressively increased. A high-speed OH-planar laser-induced fluorescence (PLIF) system is used to record the flame motion at 10,000 fps. In the beginning of the recording, the flame behavior is dominated by relatively low-frequency rotation due to the swirling motion of the flow. These rotational motions then coexist with a thermo-acoustic instability around 475 Hz which increases the amplitude of the pressure fluctuations inside the chamber. Dynamic mode decomposition (DMD) analyses indicate that this instability is associated with a widening of the flame occurring when the pressure fluctuations are the highest, giving the instability a positive feedback. The instability frequency then abruptly switches to 500 Hz, while the mode shape remains the same. This frequency change is studied using time–frequency analysis to highlight a change in the feedback mechanism characterized by a modification of the time delay between pressure and heat release fluctuations.

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References

Correa, S. M. , 1998, “ Power Generation and Aeropropulsion Gas Turbines: From Combustion Science to Combustion Technology,” Symp. (Int.) Combust., 27(2), pp. 1793–1807. [CrossRef]
Candel, S. , 2002, “ Combustion Dynamics and Control: Progress and Challenges,” Proc. Combust. Inst., 29(1), pp. 1–28. [CrossRef]
Lieuwen, T. C. , and Yang, V. , 2005, Combustion Instabilities in Gas Turbine Engines: Operational Experience, Fundamental Mechanisms, and Modeling (Progress in Astronautics and Aeronautics, Vol. 210), American Institute of Aeronautics and Astronautics, Reston, VA.
Lefebvre, A. H. , 1995, “ The Role of Fuel Preparation in Low-Emission Combustion,” ASME J. Eng. Gas Turbines Power, 117(4), pp. 617–654. [CrossRef]
Kohse-Höinghaus, K. , Barlow, R. S. , Aldén, M. , and Wolfrum, J. , 2005, “ Combustion at the Focus: Laser Diagnostics and Control,” Proc. Combust. Inst., 30(1), pp. 89–123. [CrossRef]
Dhanuka, S. K. , Temme, J. E. , Driscoll, J. F. , and Mongia, H. C. , 2009, “ Vortex-Shedding and Mixing Layer Effects on Periodic Flashback in a Lean Premixed Prevaporized Gas Turbine Combustor,” Proc. Combust. Inst., 32(2), pp. 2901–2908. [CrossRef]
Dhanuka, S. K. , Temme, J. E. , and Driscoll, J. F. , 2011, “ Lean-Limit Combustion Instabilities of a Lean Premixed Prevaporized Gas Turbine Combustor,” Proc. Combust. Inst., 33(2), pp. 2961–2966. [CrossRef]
Stopper, U. , Meier, W. , Sadanandan, R. , Stöhr, M. , Aigner, M. , and Bulat, G. , 2013, “ Experimental Study of Industrial Gas Turbine Flames Including Quantification of Pressure Influence on Flow Field, Fuel/Air Premixing and Flame Shape,” Combust. Flame, 160(10), pp. 2103–2118. [CrossRef]
Temme, J. E. , Allison, P. M. , and Driscoll, J. F. , 2014, “ Combustion Instability of a Lean Premixed Prevaporized Gas Turbine Combustor Studied Using Phase-Averaged PIV,” Combust. Flame, 161(4), pp. 958–970. [CrossRef]
Boxx, I. , Slabaugh, C. , Kutne, P. , Lucht, R. P. , and Meier, W. , 2015, “ 3 kHz PIV/OH-PLIF Measurements in a Gas Turbine Combustor at Elevated Pressure,” Proc. Combust. Inst., 35(3), pp. 3793–3802. [CrossRef]
Tachibana, S. , Saito, K. , Yamamoto, T. , Makida, M. , Kitano, T. , and Kurose, R. , 2015, “ Experimental and Numerical Investigation of Thermo-Acoustic Instability in a Liquid-Fuel Aero-Engine Combustor at Elevated Pressure: Validity of Large-Eddy Simulation of Spray Combustion,” Combust. Flame, 162(6), pp. 2621–2637. [CrossRef]
Yamamoto, T. , Shimodaira, K. , Kurosawa, Y. , and Yoshida, S. , 2011, “ Combustion Characteristics of Fuel Staged Combustor for Aeroengines at LTO Cycle Conditions,” ASME Paper No. GT2011-46133.
Yamamoto, T. , Shimodaira, K. , Yoshida, S. , and Kurosawa, Y. , 2013, “ Emission Reduction of Fuel-Staged Aircraft Engine Combustor Using an Additional Premixed Fuel Nozzle,” ASME J. Eng. Gas Turbines Power, 135(3), p. 031502. [CrossRef]
Sadanandan, R. , Stöhr, M. , and Meier, W. , 2008, “ Simultaneous OH-PLIF and PIV Measurements a Gas Turbine Model Combustor,” Appl. Phys. B, 90(3–4), pp. 609–618. [CrossRef]
Schmid, P. J. , 2010, “ Dynamic Mode Decomposition of Numerical and Experimental Data,” J. Fluid Mech., 656, pp. 5–28. [CrossRef]
Schmid, P. J. , 2011, “ Application of the Dynamic Mode Decomposition to Experimental Data,” Exp. Fluids, 50(4), pp. 1123–1130. [CrossRef]
Rowley, C. W. , Mezić, I. , Bagheri, S. , Schlatter, P. , and Henningson, D. S. , 2009, “ Spectral Analysis of Nonlinear Flows,” J. Fluid Mech., 641, pp. 115–127.
Poinsot, T. J. , Trouve, A. C. , Veynante, D. P. , Candel, S. M. , and Esposito, E. J. , 1987, “ Vortex-Driven Acoustically Coupled Combustion Instabilities,” J. Fluid Mech., 177(1), pp. 265–292.
Palies, P. , Durox, D. , Schuller, T. , and Candel, S. , 2010, “ The Combined Dynamics of Swirler and Turbulent Premixed Swirling Flames,” Combust. Flame, 157(9), pp. 1698–1717. [CrossRef]
Samaniego, J. M. , Yip, B. , Poinsot, T. , and Candel, S. , 1993, “ Low-Frequency Combustion Instability Mechanisms in a Side-Dump Combustor,” Combust. Flame, 94(4), pp. 363–380. [CrossRef]
Richecoeur, F. , Hakim, L. , Renaud, A. , and Zimmer, L. , 2012, “ DMD Algorithms for Experimental Data Processing in Combustion,” Summer Program, Center for Turbulence Research, Stanford, CA, June 25–July 20, pp. 459–468.
Moeck, J. P. , Bourgouin, J.-F. , Durox, D. , Schuller, T. , and Candel, S. , 2012, “ Nonlinear Interaction Between a Precessing Vortex Core and Acoustic Oscillations in a Turbulent Swirling Flame,” Combust. Flame, 159(8), pp. 2650–2668. [CrossRef]
Alekseenko, S. V. , Dulin, V. M. , Kozorezov, Y. , and Markovich, D. M. , 2012, “ Effect of High-Amplitude Forcing on Turbulent Combustion Intensity and Vortex Core Precession in a Strongly Swirling Lifted Propane/Air Flame,” Combust. Sci. Technol., 184(10–11), pp. 1862–1890. [CrossRef]
Renaud, A. , Ducruix, S. , Scouflaire, P. , and Zimmer, L. , 2015, “ Experimental Study of the Interactions Between Air Flow Rate Modulations and PVC in a Swirl-Stabilised Liquid Fuel Burner,” ASME Paper No. GT2015-42775.
Dowling, A. P. , and Morgans, A. S. , 2005, “ Feedback Control of Combustion Oscillations,” Annu. Rev. Fluid Mech., 37(1), pp. 151–182. [CrossRef]
Ducruix, S. , Schuller, T. , Durox, D. , and Candel, S. , 2003, “ Combustion Dynamics and Instabilities: Elementary Coupling and Driving Mechanisms,” J. Propul. Power, 19(5), pp. 722–734. [CrossRef]
de la Cruz Garcia, M. , Mastorakos, E. , and Dowling, A. , 2009, “ Investigations on the Self-Excited Oscillations in a Kerosene Spray Flame,” Combust. Flame, 156(2), pp. 374–384. [CrossRef]
Noiray, N. , Durox, D. , Schuller, T. , and Candel, S. , 2008, “ A Unified Framework for Nonlinear Combustion Instability Analysis Based on the Flame Describing Function,” J. Fluid Mech., 615, pp. 139–167.
Matveev, K. I. , and Culick, F. E. C. , 2003, “ A Model for Combustion Instability Involving Vortex Shedding,” Combust. Sci. Technol., 175(6), pp. 1059–1083. [CrossRef]
Apeloig, J. M. , d'Herbigny, F.-X. , Simon, F. , Gajan, P. , Orain, M. , and Roux, S. , 2015, “ Liquid-Fuel Behavior in an Aeronautical Injector Submitted to Thermoacoustic Instabilities,” J. Propul. Power, 31(1), pp. 309–319. [CrossRef]
Silva, C. F. , Nicoud, F. , Schuller, T. , Durox, D. , and Candel, S. , 2013, “ Combining a Helmholtz Solver With the Flame Describing Function to Assess Combustion Instability in a Premixed Swirled Combustor,” Combust. Flame, 160(9), pp. 1743–1754. [CrossRef]

Figures

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Fig. 2

Instantaneous image from the OH-PLIF recordings

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Fig. 1

Schematics of a radial cut of the staged injector and the single sector combustion chamber. A mean OH-PLIF image is added to highlight the region of interest.

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Fig. 3

Colormap used for the representation of the DMD modes

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Fig. 4

Signal from the pressure transducer highlighting the three studied parts

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Fig. 10

Results of the dynamic mode decomposition of the OH-PLIF gradient between t = 1 s and t = 1.5 s

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Fig. 8

Rayleigh index between t = 0.5 s and t = 1 s

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Fig. 9

Power spectral density of the pressure transducer signal between t = 1 s and t = 1.5 s

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Fig. 5

Results of the dynamic mode decomposition of the OH-PLIF gradient between t = 0 s and t = 0.5 s

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Fig. 6

Power spectral density of the pressure transducer signal between t = 0.5 s and t = 1 s

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Fig. 7

Results of the dynamic mode decomposition of the OH-PLIF gradient between t = 0.5 s and t = 1 s

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Fig. 11

Rayleigh index between t = 1 s and t = 1.5 s

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Fig. 12

Instantaneous amplitude and frequency from the Hilbert transform of the pressure transducer signal between t = 0.5 s and t = 1.5 s

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Fig. 13

Phase portrait of the pressure and heat release fluctuations between t = 0.5 s and t = 1.5 s

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Fig. 14

Phase difference between the pressure fluctuations and the OH* fluctuations

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