[Roshanlal]

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]

Originally Posted by Roshanlal

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]

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

[hello2ap]

Originally Posted by Roshanlal

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]

Originally Posted by hello2ap

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]

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]

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]

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]

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