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 Roshanlal August 7, 2010 10:13

Supersonic combustion

Hi friends

I'm trying to model a supersonic reacting flow with crosswise injection of hydrogen gas at mach 1 into mach 2.5 main air stream. I'm using finite rate combustion model with the fluent 6.3 solver

I want to find the combustion efficieny. And in the papers its given as

ηc = 1 – [ ∫αρu dA / ∑m fuel in ] ; α = mass fraction of fuel

How to evaluate this formula with fluent reports. Should I find the term ∫αρu dA by surface integral and flow rate with α as the variable. Is there any other means to get efficiency of combustion

Roshan

 hello2ap August 28, 2010 21:13

Quote:
 Originally Posted by Roshanlal (Post 270659) Hi friends I'm trying to model a supersonic reacting flow with crosswise injection of hydrogen gas at mach 1 into mach 2.5 main air stream. I'm using finite rate combustion model with the fluent 6.3 solver I want to find the combustion efficieny. And in the papers its given as ηc = 1 – [ ∫αρu dA / ∑m fuel in ] ; α = mass fraction of fuel How to evaluate this formula with fluent reports. Should I find the term ∫αρu dA by surface integral and flow rate with α as the variable. Is there any other means to get efficiency of combustion Roshan
can u tell me which method u r using for combustion

 Roshanlal August 29, 2010 00:41

I ve mentioned it - FINITE RATE MODEL is being used for the supersonic combustion

 hello2ap August 29, 2010 19:59

Quote:
 Originally Posted by Roshanlal (Post 273219) I ve mentioned it - FINITE RATE MODEL is being used for the supersonic combustion
thanks friend but which one premixed or non pre mixed model

 hello2ap August 29, 2010 20:10

Quote:
 Originally Posted by hello2ap (Post 273277) thanks friend but which one premixed or non pre mixed model
can u give me any supersonic combustion releted paper or case data file of combustion i highly appreciated you. thanks.
hello2apsingh@gmail.com
actually i have tried many time but till now i am not success in supersonic combustion plz help me thanks

 Roshanlal August 31, 2010 11:45

Yar I'm also trying to get the solution but not succeeded yet. But i think as far as supersonic simulation is concerned, U need to use density based solver. The models u mentioned is applicable for pressure based one, ie not supersonic

 hello2ap September 2, 2010 01:45

if we are using density based and taking air as ideal gas and if we using finite rate /eaddy dissipation model it shows only mixing and not burning of the fuel. and after some changes it show turbulence viscosity limited or absolute pressure critical.
have u done on any supersonic combustion kilnly help me
thanks

 Roshanlal September 3, 2010 05:55

hi how do u know that it gives mixing only? i think when reaction is enabled there is the possibility of starting combustion, provided it has enough temperature to start reactions. i want to know how should i ascertain that burning had occured??

i'm doing work on cavity. Using this way i got enough mass fration of pdt of combustion, H2O. but it is not happening in the regions as seen in the literature. I have also the same doubt wheather combustion modelling is not the proper one. Yar if this is not the way then what can be ?? Help plz

 hello2ap March 16, 2011 06:52

hello If any one need help regarding any combustion model supersonic or hypersonic or subsonic,2d les modeling or 3d. write to me at hello2apsingh@gmail.com

Thanks

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