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UID:0-314@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20191230T163000

DTEND;TZID=Asia/Jerusalem:20191230T173000

DTSTAMP:20230527T131926Z

URL:https://aerospace.technion.ac.il/events/mitigation-of-combustion-insta
 bilities-by-local-diluent-gas-in-a-lean-premixed-swirl-stabilized-combusti
 on-systems/

SUMMARY:Mitigation of Combustion Instabilities by Local Diluent Gas in a Le
 an Premixed Swirl-Stabilized Combustion Systems
DESCRIPTION:Lecturer:Nikhil Balasubramanian\n Faculty:Department of Aerospa
 ce Engineering\n Institute:Technion – Israel Institute of Technology\n L
 ocation:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n
  Abstract: \n Details: \n A major motivation for research in combustion sc
 ience and technology is to reduce emissions from power plants\, large scal
 e industrial furnaces\, automobiles\, aircrafts\, etc. Development of low 
 emission gas turbines has placed a great demand for novel methodologies fo
 r emission control\, without compromising power production.\nLean premixed
  combustion systems emerged as a viable solution to the problem\, and has 
 been successfully implemented in stationery gas turbine based energy produ
 ction units\, meeting the same energy demands and reducing  emissions to 
 single digit ppm levels. Premixed combustion systems offer better control 
 over the flame temperature\, which is directly linked to and CO emissions.
 \nHowever\, premixed combustion systems are susceptible to combustion inst
 abilities\, which is the coupling between heat release\, pressure and flow
  acoustics\, which can lead to high amplitude pressure oscillations. These
  oscillations can cause severe damage to the combustor hardware and flame 
 flashback.\nSuccessful prediction of thermo-acoustic instabilities is chal
 lenging due to the complex flow phenomena\, unsteady heat release and unde
 fined acoustic boundaries.\nWe built a fully premixed experimental swirl s
 tabilized combustion system at the Fine rocket propulsion center to analyz
 e the effect of injecting dilution gases in specific regions of the combus
 tor as a way to reduce combustion instabilities.
CATEGORIES:Seminars
LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng.

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DTSTART:20191027T010000

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