Linear stability analysis of acoustically driven pressure oscillations in a lean premixed gas turbine combustor

Content Provider	Semantic Scholar
Author	Santavicca, Domenic A.
Copyright Year	2009
Abstract	The dynamic response of a turbulent premixed flame to acoustic velocity perturbations was experimentally determined in a swirl-stabilized lean-premixed gas turbine combustor. CH* chemiluminescence intensity and the twomicrophone method were used to measure heat release rates and inlet velocity fluctuations, respectively. Using the n-τ formulation, gain and phase of flame transfer functions were incorporated into an analytic thermoacoustic model to predict instability frequencies and modal structures. Self-excited instability measurements were performed to verify eigenfrequencies predicted by the thermoacoustic model. Instability frequency predicted by the model is supported by experimental results. Results show that the self-excited instability frequency of ∼ 220 Hz results from the fact that the flames amplify flow perturbations with f = 150 ∼ 250 Hz. The other instability frequency of ∼ 350 Hz occurs because the whole combustion system has an eigenfrequency corresponding to the ¼-wave eigenmode of the mixing section.
Starting Page	3436
Ending Page	3447
Page Count	12
File Format	PDF HTM / HTML
DOI	10.1007/s12206-009-0924-0
Volume Number	23
Alternate Webpage(s)	http://www.j-mst.org/On_line/admin/files/32-05232_3436-3447_.pdf
Language	English
Access Restriction	Open
Content Type	Text
Resource Type	Article