Experimental study of equivalence ratio and fuel flow rate effects on nonlinear thermoacoustic instability in a swirl combustor

Simple item page
dc.contributor.authorZhao H
dc.contributor.authorLi G
dc.contributor.authorZhao D
dc.contributor.authorZhang Z
dc.contributor.authorSun D
dc.contributor.authorYang W
dc.contributor.authorLi S
dc.contributor.authorLu Z
dc.contributor.authorZheng Y
dc.date.accessioned2018-05-21T01:00:51Z
dc.date.available2018-05-21T01:00:51Z
dc.date.issued2017en
dc.date.updated2017-11-09T23:18:10Z
dc.description.abstractIndustrial combustion systems such as power generation gas turbines, rocket motors, furnaces and boilers often face the problem of large-amplitude self-excited pressure oscillations that occur due to the onset of thermoacoustic instability. To prevent the onset of such instability, understanding the effects of fuel–air equivalence ratio ϕ, fuel flow rate Vf on self-excited nonlinear thermoacoustic oscillations is of fundamental and practical importance. Experimental investigation of the roles of these parameters on triggering thermoacoustic instability in a swirl combustor has received very little attention. In this work, we design a swirling thermocoustic combustor and conduct a series of experimental tests. Autocorrelation and recurrence analysis of phase space trajectories reconstructed from the acoustic pressure time trace are performed. These experimental tests allow us to study the effect of fuel–air equivalence ratio ϕ on the onset of thermoacoustic instability by varying the fuel volume flow rate Vf. We demonstrate that the fuel volume flow rate and the equivalence ratio play different but critical roles on generating thermoacoustic instability at different frequencies and amplitudes. Maximum sound pressure level can be as high as 135dB. In addition, mode switching, (i.e. frequency swap) is found to occur between approximately ω3 ≈ 510Hz and ω1 ≈ 170Hz, depending on the equivalence ratio ϕ. Furthermore, the dominant frequency corresponding to the maximum amplitude is shown to be shifted by approximately 20%, as the fuel flow rate Vf is increased and the combustion condition is changed from lean to rich. These findings are quite useful for designing a feedback control strategy to stabilize an unstable combustor. The present work opens up an applicable means to design a stable swirling combustor.en
dc.identifier.doihttps://doi.org/10.1016/j.apenergy.2017.10.061
dc.identifier.issn0306-2619
dc.identifier.urihttp://hdl.handle.net/10092/15396
dc.language.isoen
dc.subjectThermoacousticsen
dc.subjectMode switchingen
dc.subjectSwirl combustoren
dc.subjectCombustion instabilityen
dc.subjectRecurrence analysisen
dc.subjectEnergy conversionen
dc.subject.anzsrcFields of Research::40 - Engineering::4017 - Mechanical engineering::401703 - Energy generation, conversion and storage (excl. chemical and electrical)en
dc.subject.anzsrcFields of Research::40 - Engineering::4017 - Mechanical engineering::401701 - Acoustics and noise control (excl. architectural acoustics)en
dc.subject.anzsrcField of Research::09 - Engineering::0913 - Mechanical Engineering::091302 - Automation and Control Engineeringen
dc.subject.anzsrcFields of Research::51 - Physical sciences::5103 - Classical physics::510304 - Thermodynamics and statistical physicsen
dc.titleExperimental study of equivalence ratio and fuel flow rate effects on nonlinear thermoacoustic instability in a swirl combustoren
dc.typeJournal Articleen
Files
Original bundle
Now showing 1 - 1 of 1
Thumbnail Image
Name:
pagination_APEN_10428.pdf
Size:
3.41 MB
Format:
Adobe Portable Document Format
Description:
Accepted version
Download
Collections
Engineering: Journal Articles