HP Turbine Flow simulation Solver settings
Hello All
I am trying to study aerodynamics of first stage of NASA GE E3 engine. However even after much effort the the residuals are not converging below the single degree. Can anybody help me by telling as to what knid of solver settings I need to get an appreciable solution. Right now I am using Coupled implicit, Viscous KE RNG model. The flow is compressible (Ideal gas) . As of now I have am simulating the flow thro the stationary passage but further on I worlf like to have the rotor to have a around 2000 rpm. Any help will be a great favor 
Re: HP Turbine Flow simulation Solver settings
You need to baby the solution. The initial conditions could be the problem, and patching some values may help. Or you may want to start with very small underrelaxation factors, and a smaller Courant number. Then you can gradually increase the values. If that doesn't work you can start with an inviscid solution, get it to converge, move to a laminar solution and get it to converge, and then run the ke rng model. Or you may want to start with 0 rpm, and then gradually increase the rpm.

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