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Old   August 7, 2010, 10:13
Default Supersonic combustion
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Roshan S Lal
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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
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Old   August 28, 2010, 21:13
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Quote:
Originally Posted by Roshanlal View Post
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
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Old   August 29, 2010, 00:41
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I ve mentioned it - FINITE RATE MODEL is being used for the supersonic combustion
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Old   August 29, 2010, 19:59
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Originally Posted by Roshanlal View Post
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
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Old   August 29, 2010, 20:10
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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
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Old   August 31, 2010, 11:45
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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
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Old   September 2, 2010, 01:45
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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
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Old   September 3, 2010, 05:55
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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
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Old   March 16, 2011, 06:52
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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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