STABILITY OF THE CO- AND COUNTER-ROTATING SWIRLERS IN A LIQUID-FUELED CAN COMBUSTOR

Date

2023-01-01

Author

Kiyici, Firat
Topal, Ahmet
Hepkaya, Ender
Ozogul, Hamdullah
Zayim, Ahmet Kaan
Kaplan, Mustafa
Perçin, Mustafa

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This study experimentally investigates the effects of swirler channel orientation on combustion instability. For this purpose, the performance of the co- and counter-rotating radial-radial swirlers is assessed in terms of pressure fluctuations in a liquid-fueled can combustor operated with kerosene fuel. High-frequency pressure transducers are used to obtain pressure fluctuations in the combustor in non-reacting and reacting flow conditions. First, non-reacting experiments are conducted to observe the performance of the swirlers at mass flow rates of 10.5, 12, 14, and 15 g/s. Non-reacting experiments show that Precessing Vortex Core occurs at a Strouhal number of 1.9 and dominates the flow field for both swirlers. In the reacting conditions, the effect of the mass flow rate (10.5, 12, 14, and 15 g/s) at a constant fuel flow rate (0.7 g/s) and the impact of the fuel flow rate (0.7, 0.8, 0.9, and 1.0 g/s) at a constant mass flow rate (15 g/s) are investigated. The peak frequency decreases in the reacting conditions compared to non-reacting cases. In the constant fuel flow rate case, the Precessing Vortex Core is observed in the co-rotating swirler for all air flow rates, but it disappears in the counter-rotating swirler at higher mass flow rates. At the constant mass flow rate cases, combustion instability occurs in the co-rotating swirler, while the counter-rotating swirler operates without any sign of instability. In all reacting cases, the peak frequency amplitude is remarkably higher in the co-rotating swirler.

Subject Keywords

Combustion instability, Swirler channel orientation

URI

https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85177566653&origin=inward
https://hdl.handle.net/11511/106470

Collections

Department of Aerospace Engineering, Conference / Seminar