I am currently working on Gas Turbine Blade Cooling design where inside a turbine blade a cooling channel is incorporated. The cooling channel is made of a single pipe system which is recirculated inside the turbine blade. Both inlet and outlet of the cooling channel is present at the base of the blade profile. The blade is of dimension around 120mm span and 160mm tall. Material- blade: N155 coolant: air Simulation is being done in ansys fluent 18.2
General solver type set at pressure based, velocity formulation absolute and time steady. For the initial run viscosity model taken as laminar and energy model ON. Boundary condition imposed inlet air of gas turbine section: Temp- 1100K Velocity- 265m/s Pressure-101325Pa(Gauge Pressure- 0) coolant inlet: Temp-500K Velocity- 30m/s Pressure-101325Pa(Gauge Pressure- 0) With the initiation of calculation only, divergence is occuring in the AMG solver. Any suggestion or help would be highly appriciated.
Try to start the calculation with small temperatures and speeds. When you receive a sustainable solution, you can increase the value of the parameters. So step by step to reach its initial parameters.
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