| Summary: | 碩士 === 國立交通大學 === 機械工程系所 === 104 === Turbine blades in a gas turbine engine must withstand high temperature and pressure that easily causes the blade broken. In order to protect turbine blades from the situation, a film cooling method has been always employed on the turbine blade. This study simulates the complex configuration of turbine blades with the 2-D compressible flow, and applies the immersed boundary method to the simulation. Because of the immersed boundary method, a complex configuration with structured grid can be simulated, and it is better than unstructured grids used to simulate the complex configuration.
Cooling fluids are issued from high pressure chamber inside the turbine to the outside surface of the blades. Because the pressure difference on each point on the turbine blade is not the same, each film cooling hole has different coolant mass flow rate that leads different kinds of vorticities when the cooling fluids mix with the hot gas. As a result, different heat transfer mechanisms are observed on the pressure and suction side.
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