چكيده به لاتين
Film cooling is used to protect the surface of the turbine blades against hot combustion gas. This method is an effective solution to protect the surface against hot gas by injecting cool air into the boundary layer to create a protective layer on the blade surface. Prevents direct contact of the vane surface with hot exhaust gas from the combustion chamber. Many parameters are involved in the cooling performance of the layers, the main purpose of cooling is to optimize the effect of these parameters and achieve maximum efficiency. Due to the difficulties in performing experimental, numerical methods have been used in this field. In turbomachines, due to the turbulence of the flow regime, suitable turbulence equations are used to model the turbulence of the flow. In this dissertation, the interaction effects of coolant injection angle and rotation were studied. Geometric models and mesh were created with Gambit software and Fluent software was used to solve the governing equations and flow analysis. The perturbation models used are the two equations k-ɛ standard and k-ɛ RNG. The results showed that in the case of secondary currents, which caused the flow path to be disturbed on the blade surface and the angle of cooling fluid outlet caused changes in the injection layer. Also, with increasing the rotational speed of the blade, the cooling efficiency decreased. Changing the injection angle also led to a change in efficiency, which for the 90-degree angle was the highest efficiency relative to the size of the angles. Increased cooling efficiency noted that it can be used for better cooling.
