How to simulate the LOX/GH2 spray combustion
 

Hello,

Recently, I am trying to simulate a spray combustion using gaseous methane and liquid oxygen for the liquid rocket engine (Non-Premixed Model--> equilibrium approach).

To validate the numerical procedure (Non-Premixed Model--> pdf of Equilibrium approach), I have taken the Rocket Combustion Modeling (RCM-2 case)_10 bar as a chamber pressure in which the gaseous hydrogen and liquid oxygen as propellant. To simulate this, I have used the mass flow inlet boundary condition for gaseous hydrogen and discrete phase model (Lagrangian approach) for liquid oxygen as droplets so that it will evaporate. I have created the PDF table using chemical equilibrium from the Non-Premixed combustion model in which the boundary as (h2 = 1 (fuel), 0 (oxid)) and ((o2 =0 (fuel), 1 (oxid)). And I have given 1 for mean mixture fraction at the hydrogen mass flow rate boundary condition. it shows that the combustion does not happen.

When I created the same PDF table by using chemical equilibrium from the Non-Premixed combustion model in which the boundary as (h2 = "0" (fuel), "1" (oxid)) and ((o2 ="1" (fuel), "0" (oxid)). and I have given "0" for mean mixture fraction at the hydrogen mass flow rate boundary condition. I checked that the combustion has happened and I plotted the temperature along axial and radial at a different location as with the experimental data, which showed that the simulation result is agreed with the experiment. I want to know this way of approach is correct or wrong?.

Please kindly request you to give your suggestion or anything about this.

Thank you very much.