[okumush]

Hello foamers,

I am currently working on NASA Rotor 37 on OF8 & OF9.The simulation results seems to be weird. No matter what I do the compressor stays choked state.

Briefly, i am going to list what i have done.

At the first, i created my mesh by using Turbogrid and i used Fluent to get .msh file and then i used FluentMeshToFoam to get my mesh into the foam directory.

My simulation type is RAS and model is k-epsilon and the solver that i used is rhoSimplefoam.

My 0/p, 0/T and 0/U files are,

0/p

/*--------------------------------*- C++ -*----------------------------------*\
========= |
\\ / F ield | OpenFOAM: The Open Source CFD Toolbox
\\ / O peration | Website: https://openfoam.org
\\ / A nd | Version: 8
\\/ M anipulation |
\*---------------------------------------------------------------------------*/
FoamFile
{
version 2.0;
format ascii;
class volScalarField;
object p; // pressure (N/m2),(kg/(m.s2)).
}
// ************************************************** *********************** //

dimensions [1 -1 -2 0 0 0 0];

internalField uniform 101325;

boundaryField
{
inlet
{
type totalPressure;
gamma 1;
p0 uniform 101325;
}
outlet
{
type fixedValue;
value uniform 120000;
}
hub
{
type zeroGradient; // This boundary condition applies a zero-gradient condition from the patch internal field onto the patch faces.
}
shroud
{
type zeroGradient; // This boundary condition applies a zero-gradient condition from the patch internal field onto the patch faces.
}
blade
{
type zeroGradient; // This boundary condition applies a zero-gradient condition from the patch internal field onto the patch faces.
}
"(cyclic1_n|cyclic2_n)"
{
type cyclicAMI;
//value $internalField;
}
}

// ************************************************** *********************** //

0/T

/*--------------------------------*- C++ -*----------------------------------*\
========= |
\\ / F ield | OpenFOAM: The Open Source CFD Toolbox
\\ / O peration | Website: https://openfoam.org
\\ / A nd | Version: 8
\\/ M anipulation |
\*---------------------------------------------------------------------------*/
FoamFile
{
version 2.0;
format ascii;
class volScalarField;
object T; // temperature (K).
}
// ************************************************** *********************** //

dimensions [0 0 0 1 0 0 0];

internalField uniform 288.15;

boundaryField
{
inlet
{
type totalTemperature;
gamma 1;
T0 uniform 288.15;
}
outlet
{
type zeroGradient;
}
hub
{
type zeroGradient;
}
shroud
{
type zeroGradient;
}
blade
{
type zeroGradient;
}
"(cyclic1_n|cyclic2_n)"
{
type cyclicAMI;
//value $internalField;
}
}

// ************************************************** *********************** //

0/U

/*--------------------------------*- C++ -*----------------------------------*\
========= |
\\ / F ield | OpenFOAM: The Open Source CFD Toolbox
\\ / O peration | Website: https://openfoam.org
\\ / A nd | Version: 8
\\/ M anipulation |
\*---------------------------------------------------------------------------*/
FoamFile
{
version 2.0;
format ascii;
class volVectorField;
object U; // velocity (m/s).
}
// ************************************************** *********************** //

dimensions [0 1 -1 0 0 0 0];

internalField uniform (0 0 149);

boundaryField
{
inlet
{
type pressureDirectedInletVelocity;
inletDirection uniform (0 0 1);
value $internalField;
}
outlet
{
type inletOutlet; // This boundary condition provides a generic outflow condition, with specified inflow for the case of return flow.
//phi phi;
inletValue uniform (0 0 0); // Inlet value for reverse flow
value $internalField;
}
hub
{
type fixedValue; // This boundary condition supplies a fixed value constraint, and is the base class for a number of other boundary conditions.
value uniform (0 0 0);
}
shroud
{
type fixedValue; // This boundary condition supplies a fixed value constraint, and is the base class for a number of other boundary conditions.
value uniform (0 0 0);
}
blade
{
type fixedValue; // This boundary condition supplies a fixed value constraint, and is the base class for a number of other boundary conditions.
value uniform (0 0 0);
}
"(cyclic1_n|cyclic2_n)"
{
type cyclicAMI; // Cyclic patch for Arbitrary Mesh Interface (AMI)
//value $internalField;
}
}

// ************************************************** *********************** //

And i attached my mach number representation at the meridional section of the r37. I also attached my case directory (Openfoam.org version 9).

Download case directory

At this point, I need your experience and comments on what could be wrong.

[okumush]

Mach presentation is



According to experimental results, shock waves occur at the leading edge section of the blades. I added mach contours from NASA paper.

[okumush]

Any idea? I need to true solution for my thesis.