Instability Suppression in a Swirl-Stabilized Combustor Using Microjet Air Injection

Handle URI:
http://hdl.handle.net/10754/598632
Title:
Instability Suppression in a Swirl-Stabilized Combustor Using Microjet Air Injection
Authors:
LaBry, Zachary; Shanbhogue, Santosh; Speth, Raymond; Ghoniem, Ahmed
Abstract:
In this study, we examine the effectiveness of microjet air injection as a means of suppressing thermoacoustic instabilities in a swirl-stabilized, lean-premixed propane/air combustor. High-speed stereo PIV measurements, taken to explore the mechanism of combustion instability, reveal that the inner recirculation zone plays a dominant role in the coupling of acoustics and heat release that leads to combustion instability. Six microjet injector configurations were designed to modify the inner and outer recirculation zones with the intent of decoupling the mechanism leading to instability. Microjets that injected air into the inner recirculation zone, swirling in the opposite sense to the primary swirl were effective in suppressing combustion instability, reducing the overall sound pressure level by up to 17 dB within a certain window of operating conditions. Stabilization was achieved near an equivalence ratio of 0.65, corresponding to the region where the combustor transitions from a 40 Hz instability mode to a 110 Hz instability mode. PIV measurements made of the stabilized flow revealed significant modification of the inner recirculation zone and substantial weakening of the outer recirculation zone.
Citation:
LaBry Z, Shanbhogue S, Speth R, Ghoniem A (2010) Instability Suppression in a Swirl-Stabilized Combustor Using Microjet Air Injection. 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition. Available: http://dx.doi.org/10.2514/6.2010-1524.
Publisher:
American Institute of Aeronautics and Astronautics (AIAA)
Journal:
48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition
KAUST Grant Number:
KUS-110-010-01
Issue Date:
4-Jan-2010
DOI:
10.2514/6.2010-1524
Type:
Conference Paper
Sponsors:
The authors would like to acknowledge the King Abdullah University of Science and Technology for their support of this research. This work was funded by the KAUST grant, number KUS-110-010-01.
Appears in Collections:
Publications Acknowledging KAUST Support

Full metadata record

DC FieldValue Language
dc.contributor.authorLaBry, Zacharyen
dc.contributor.authorShanbhogue, Santoshen
dc.contributor.authorSpeth, Raymonden
dc.contributor.authorGhoniem, Ahmeden
dc.date.accessioned2016-02-25T13:33:29Zen
dc.date.available2016-02-25T13:33:29Zen
dc.date.issued2010-01-04en
dc.identifier.citationLaBry Z, Shanbhogue S, Speth R, Ghoniem A (2010) Instability Suppression in a Swirl-Stabilized Combustor Using Microjet Air Injection. 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition. Available: http://dx.doi.org/10.2514/6.2010-1524.en
dc.identifier.doi10.2514/6.2010-1524en
dc.identifier.urihttp://hdl.handle.net/10754/598632en
dc.description.abstractIn this study, we examine the effectiveness of microjet air injection as a means of suppressing thermoacoustic instabilities in a swirl-stabilized, lean-premixed propane/air combustor. High-speed stereo PIV measurements, taken to explore the mechanism of combustion instability, reveal that the inner recirculation zone plays a dominant role in the coupling of acoustics and heat release that leads to combustion instability. Six microjet injector configurations were designed to modify the inner and outer recirculation zones with the intent of decoupling the mechanism leading to instability. Microjets that injected air into the inner recirculation zone, swirling in the opposite sense to the primary swirl were effective in suppressing combustion instability, reducing the overall sound pressure level by up to 17 dB within a certain window of operating conditions. Stabilization was achieved near an equivalence ratio of 0.65, corresponding to the region where the combustor transitions from a 40 Hz instability mode to a 110 Hz instability mode. PIV measurements made of the stabilized flow revealed significant modification of the inner recirculation zone and substantial weakening of the outer recirculation zone.en
dc.description.sponsorshipThe authors would like to acknowledge the King Abdullah University of Science and Technology for their support of this research. This work was funded by the KAUST grant, number KUS-110-010-01.en
dc.publisherAmerican Institute of Aeronautics and Astronautics (AIAA)en
dc.titleInstability Suppression in a Swirl-Stabilized Combustor Using Microjet Air Injectionen
dc.typeConference Paperen
dc.identifier.journal48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Expositionen
dc.contributor.institutionMassachusetts Institute of Technologyen
kaust.grant.numberKUS-110-010-01en
All Items in KAUST are protected by copyright, with all rights reserved, unless otherwise indicated.