I am designing a Lean Premixed swirl stabilized Combustor which has a premixer tube where fuel and air are mixed prior to combustion in the combustion chamber.
What is the typical maximum flow velocity range in the premixer tube so that a strong vortex breakdown region is formed inside the combustion chamber that would result in stable flame?
We've published a conference paper at IAC 2019 exactly about this topic, with the literature review and hundreds of our experiments. The title is Flame Initiation Inside the Gas Torch Ignition System for a Hybrid Rocket Motor.
Dear Olexiy, Thanks for the response, but I am unable to access your article. Kindly send it to me through the mail if it is convenient for you
I do not see the relevance of Mr. Shynkarenko's answer to your question. Your question concerns lean burning gas turbine engine and shynkerenko's answer is for hybrid rocker that uses exotic fuels/oxidizer.
Typically, the velocities are in the range of 20 to 50 m/s.
Hanasoge Mukunda Thank You for your response. Can you share any relevant article describing typical velocity ranges in the premixer of combustors?
Dear Mr. Huda,
The kind of information you are seeking needs to be deduced from actual work. You might want to see
https://ntrs.nasa.gov/search.jsp?R=20150007508 2019-08-21T03:51:50+00:00Z
The above article contains information that helps you in the direction of the answer. If you let me know your e-mail id, I will send you the related article.
My e-mail id is [email protected]
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