U-bend internal cooling channel¶
NOTE: Before running this case, please read the instructions in NACA0012 airfoil incompressible to get an overall idea of the DAFoam optimization setup.
This is an aerothermal optimization case for a U-bend internal cooling channel. The summary of the case is as follows:
Case: Aerothermal optimization for U bend cooling channels with radiation and buoyancyGeometry: von Karman U bend ductObjective function: Weighted pressure loss and Nusselt numberDesign variables: 114 FFD points moving in the x, y, and z directionsConstraints: Symmetry and curvature constraints (total number: 41)Mach number: 0.02Reynolds number: 4.2e4Mesh cells: 4.8KAdjoint solver: buoyantBoussinesqSimpleDAFoam
The optimization progress will then be written in the log.opt file.
For this case, the optimization converges in 8 steps, see the following figure. The baseline design has CPL=1.152, Nu=76.82 and the optimized design has CPL=0.7764, Nu=78.73.
We use buoyantBoussinesqSimpleDAFoam, which contains heat transfer, buoyancy, and radiation.