Spray Combustion Dynamics under Thermoacoustic Oscillations
Thermoacoustic instabilities in combustors have
remained a topic of investigation for over a few decades due to the
challenges it posses to the operation of low emission gas turbines.
For combustors burning liquid fuel, understanding the cause-andeffect
relationship between spray combustion dynamics and
thermoacoustic oscillations is imperative for the successful
development of any control methodology for its mitigation. The
paper presents some very unique operating characteristics of a
kerosene-fueled diffusion type combustor undergoing limit-cycle
oscillations. Combustor stability limits were mapped using three
different-sized injectors. The results show that combustor instability
depends on the characteristics of the fuel spray. A simple analytic
analysis is also reported in support of a plausible explanation for the
unique combustor behavior. The study indicates that high amplitude
acoustic pressure in the combustor may cause secondary breakdown
of fuel droplets resulting in premixed pre-vaporized type burning of
the diffusion type combustor.
[1] J. C. Solt, J. Tuzson, Proceedings of 1993 ASME IGTI Conference
Paper 93-GT-270, 1993.
[2] T. Lieuwen, B. T. Zinn, AIAA 36th Aerospace Sciences Meeting &
Exhibit Paper 98-0641, 1998.
[3] A. Y. Tong, W. A. Sirignano, Journal of Propulsion and Power 5(3)
(1989) 257-261.
[4] W. A. Chishty, Effects of Thermoacoustic Oscillations on Spray
Combustion Dynamics with Implications for Lean Direct Injection
Systems, PhD thesis, Virginia Polytechnic Institute and State University,
Blacksburg, VA, USA, 2005.
[5] A. M. Mellor, Design of Modern Turbine Combustors, Academic Press
Limited, 1990.
[6] C. Clanet, G. Searby, P. Clavin, Journal of Fluid Mechanics 385 (1999)
157-197.
[7] S. Dowson, J. Fitzpatrick, Journal of Sound and Vibration 230(3) (2000)
649-660.
[8] A. V. Anilkumar, C. P. Lee, T. G. Wang, NASA Conference Publication
3338, (1996) 559-564.
[9] R. Schmehl, G. Klose, G. Maier, S. Wittig, S., NATO RTO Gas Turbine
Engine Combustion, Emissions and Alternate Fuels, 1999.
[10] P. J. O-Rourke, A. A. Amsden, SAE Technical Report 872089, 1987.
[11] J.-H. Park, Y. Yoon, Atomization and Sprays 12 (2002) 387- 401.
[1] J. C. Solt, J. Tuzson, Proceedings of 1993 ASME IGTI Conference
Paper 93-GT-270, 1993.
[2] T. Lieuwen, B. T. Zinn, AIAA 36th Aerospace Sciences Meeting &
Exhibit Paper 98-0641, 1998.
[3] A. Y. Tong, W. A. Sirignano, Journal of Propulsion and Power 5(3)
(1989) 257-261.
[4] W. A. Chishty, Effects of Thermoacoustic Oscillations on Spray
Combustion Dynamics with Implications for Lean Direct Injection
Systems, PhD thesis, Virginia Polytechnic Institute and State University,
Blacksburg, VA, USA, 2005.
[5] A. M. Mellor, Design of Modern Turbine Combustors, Academic Press
Limited, 1990.
[6] C. Clanet, G. Searby, P. Clavin, Journal of Fluid Mechanics 385 (1999)
157-197.
[7] S. Dowson, J. Fitzpatrick, Journal of Sound and Vibration 230(3) (2000)
649-660.
[8] A. V. Anilkumar, C. P. Lee, T. G. Wang, NASA Conference Publication
3338, (1996) 559-564.
[9] R. Schmehl, G. Klose, G. Maier, S. Wittig, S., NATO RTO Gas Turbine
Engine Combustion, Emissions and Alternate Fuels, 1999.
[10] P. J. O-Rourke, A. A. Amsden, SAE Technical Report 872089, 1987.
[11] J.-H. Park, Y. Yoon, Atomization and Sprays 12 (2002) 387- 401.
@article{"International Journal of Mechanical, Industrial and Aerospace Sciences:60114", author = "Wajid A. Chishty and Stephen D. Lepera and Uri Vandsburger", title = "Spray Combustion Dynamics under Thermoacoustic Oscillations", abstract = "Thermoacoustic instabilities in combustors have
remained a topic of investigation for over a few decades due to the
challenges it posses to the operation of low emission gas turbines.
For combustors burning liquid fuel, understanding the cause-andeffect
relationship between spray combustion dynamics and
thermoacoustic oscillations is imperative for the successful
development of any control methodology for its mitigation. The
paper presents some very unique operating characteristics of a
kerosene-fueled diffusion type combustor undergoing limit-cycle
oscillations. Combustor stability limits were mapped using three
different-sized injectors. The results show that combustor instability
depends on the characteristics of the fuel spray. A simple analytic
analysis is also reported in support of a plausible explanation for the
unique combustor behavior. The study indicates that high amplitude
acoustic pressure in the combustor may cause secondary breakdown
of fuel droplets resulting in premixed pre-vaporized type burning of
the diffusion type combustor.", keywords = "Secondary droplet breakup, Spray dynamics, Taylor
Analogy Breakup Model, Thermoacoustic instabilities.", volume = "5", number = "1", pages = "211-6", }