Improve the performance of a rotor blade by changing the distance between the tipping point and axial displacement of the blade

Improving the performance of gas turbines in today's world is an important and key issue, of course, in optimizing the performance of its core components. As an important part of the gas turbine, the compressor has always attracted particular attention. Many studies and experiments have been done to increase its efficiency. On the other hand, numerical analyzes and modeling are rapidly expanding due to the high cost of experimental tests and the rigidity of test conditions. The study of numerical methods and turbulence models continues to provide a more complete and better simulation of all aspects of fluid problems, and new aspects of this field are unveiled every day. The purpose of this study is to simulate the flow of a single stage of the NASA rotor 37, and then improve the geometry of the rotor based on the adjustment of the tip clearance and the axial displacement of the blade. First, the best turbulence model (k-ε RNG) was selected for simulation. Then, with regard to the two parameters of axial displacement and tip clearance, optimization of the rotor function was investigated. At first simulations were examined based on axial displacement for five states. In the following, four sizes for Blade No. 2 (best efficiency for axial displacement) were considered, which achieved the highest efficiency for the design level tip clearance (0.365 mm).