To design a radial compressor there are many geometry parameters that must be considered. Leading edge shape, trailing edge shape and of course the shape of the unit blade itself. Geometry parameters of the impeller defined by its operation condition. Radial compressor with high rotational velocity (high rpm) will have more looked down leading edge than radial compressor that works in the lower rpm regime. The radial compressor with high pressure ratio usually has more radial trailing edge than radial compressor with low pressure rise. In the designing radial compressor rotor, or its commonly known as impeller, we can define the blade leading edge by using relative velocity and tangential velocity. Defining blade leading edge usually more easier than defining traling edge section. There are several consideration before we can define trailing edge shape of the impeller. Number of blade, flow angle out from the impeller and radius outer impeller are some things that need to included in the calculation. In this study will be assessed the effect of trailing edge shape (based on the beta angle) to the radial compressor performance especially on isentropic efficiency and the pressure rise, CPR. By using CFD, Computational Fluid Dynamic, will be predicted and compare the trend line in every single model of impeller trailing edge. With this study, hopefully. could make a kind of margin how far we can tolerate deviation in at the trailing edge when we do the manufacturing process.
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