Document Type : Original Article
Author
APU
Abstract
Aircraft engine designers have been trying to reduce weight and increase engine efficiency for a long time. One of the passive methods to prevent flow separation, control the boundary layer, increase the pressure ratio, and reduce the weight of the turbine and compressor, is the use of tandem. Tandem improves the performance of the compressor by increasing the rotation angle of the flow and increasing the pressure ratio of the compressor. In this study, the tandem compressor geometry was extracted from the model designed at the NASA Lewis Research Center and a high-quality network was applied to it. In the present study, both rotor and stator have tandem. The software used in this study is CFX 2021, which has been analyzed with the κ-ω SST turbulence model. In this study, the difference between normal and tandem compressors was investigated and finally it was observed that the efficiency of the floor and rotor of the normal compressor is better than that of the tandem compressor. It has also been observed that the compressor stage has increased the pressure ratio by 3% at the nominal speed of the tandem, and this value is 1.5% in the rotor. Further, it was concluded that in the compressor floor, the tandem has increased the pressure ratio by 3%. Then it was concluded that the parameter of attack angle of tandem blade is higher than that of normal blade...
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