Algorithm• Artificial compressibility

• Symmetric Coupled Gauss Seidel Parallel Pressure (SCGS-PP)

• 1st, 3rd and 5th order convective schemes

• 2nd, 4rd and 6th order representations for the diffusive, pressure gradient and divergence terms

• Collocated and staggered grids

• Nth order fully implicit time integration

• Explicit time integration possible (convection & diffusion)

• Multigrid (collocated grid code)

• Parallelized using Message Passing Interface (MPI) and domain

decomposition. • Immersed boundary method for complicated geometry's

Compressible N-S equations

• The artificial compressibility method for the incompressible N-S equations is essentially equivalent to low Mach number preconditioning for the compressible N-S equations.

• Since we are interested in subsonic flows the differencing schemes should not have to change.

• The current capability of N scalars will be replaced with N ideal gases. This will ease the addition of reactions in possible future work.

Results

• Normal injection, blowing ratio of .5

• 2.14 million grid points with heat transfer , Re 2000

• 3.5 million grid points with a plenum, Re 4700

• 5.2 million grid points with heat transfer , Re 2000

• No perturbations in flow field

Top view

4 D D 10 D

3 D Z

X

Side view

4 D D 10 Djet

crossflow

5 D

Y

Z

Budgets

• Term by term analysis of RANS models

• Determine validity of various turbulence model assumptions for this class of flows.

• Bottom Line: Improvements in turbulence models for film cooling.

GOALS• Use DNS data to improve RANS models for film cooling.

• DNS provides a wealth of information on all aspects of a flow

• Use this information to do term by term analysis of RANS models

• Determine validity of various turbulence model assumptions for this class of flows.

• Bottom Line: Improvements in turbulence models for film cooling.

2.14 million grid points

3.5 million grid points with plenum

-3 -2 -1 0 1 2 3 4 5 6 7 8 9 10

x

X

Y

Z

s1: -0.04 0.04 0.11 0.18 0.26 0.33 0.41 0.48 0.56 0.63 0.70 0.78 0.85 0.93 1.00

A snapshot in timeView is of a slice down the center of the jetThe contours are of temperature

Frame 001 4 Mar 2001 time= 25.9950000000000010 Re= 2000.00000000000000 | time= 25.9950000000000010 Re= 2000.00000000000000 |Frame 001 4 Mar 2001 time= 25.9950000000000010 Re= 2000.00000000000000 | time= 25.9950000000000010 Re= 2000.00000000000000 |

-2 -1 0 1 2 3 4 5 6 7 8 9 10

x

Y X

Z

s1: 0.41 0.46 0.50 0.54 0.58 0.63 0.67 0.71 0.76 0.80 0.84 0.88 0.93 0.97 1.01

A snapshot in timeView is of the blade surfaceThe contours are of temperature (adiabatic wall boundary condition is used)

Frame 001 4 Mar 2001 time= 25.9950000000000010 Re= 2000.00000000000000 | time= 25.9950000000000010 Re= 2000.00000000000000 |Frame 001 4 Mar 2001 time= 25.9950000000000010 Re= 2000.00000000000000 | time= 25.9950000000000010 Re= 2000.00000000000000 |

X

Y

Zs1: 0.41 0.46 0.50 0.54 0.58 0.63 0.67 0.71 0.76 0.80 0.84 0.88 0.93 0.97 1.01

A snapshot in timeView is looking upstream 5 jet diametersdownstream of the center of the jetThe velocity vectors are colored by temperature

Frame 001 4 Mar 2001 time= 25.9950000000000010 Re= 2000.00000000000000 | time= 25.9950000000000010 Re= 2000.00000000000000 |Frame 001 4 Mar 2001 time= 25.9950000000000010 Re= 2000.00000000000000 | time= 25.9950000000000010 Re= 2000.00000000000000 |