| This paper focuses on the development of a high pressure ratio and high rotating speed centrifugal compressor, a key part of 100kW micro gas turbine system.Fine/Turbo is examined, which is used to investigate the centrifugal compressor. Its ability to predict the flow field and performance of high ratio centrifugal compressor is analyzed. Fine/Turbo satisfied the basic requirement.Numerical investigation shows that vaneless diffuser between impeller and vane diffuser affects the performance of compressor. A centrifugal compressor with an airfoil vane diffuser is simulated with the software. The internal flow of vane diffuser is researched. A diffuser with splitter blades is designed and analyzed. The result shows that its aerodynamics performance is superior to the diffuser without blades.The article shows the influence of tip clearance on performance at different rotate speed and investigates the flow field of high pressure ratio and high rotate speed centrifugal impeller. The development of vortices and secondary flow, the transportation of low energy fluid are discussed. The complex tip leakage flow-affects the loss mechanism near shroud.There are many numerical investigations into the centrifugal compressor in this article. The influence of blade number, blade thickness, location of splitter blades and tip clearance on mass flow, pressure ratio and efficiency is showed.
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