Aerospace Knowledge and Technology Journal

Aerospace Knowledge and Technology Journal

The effect of loss parameters using tandem blade in axial compressor

Document Type : Research Paper

Authors
Alireza Sekhavat Benis 1
Reza Aghaei Togh 1
hamze eshraghi 2
1 Department of Aerospace Engineering, Technical and Engineering Faculty, Islamic Azad University, Science and Research Branch, Tehran, Iran
2 Faculty of Aerospace Engineering, Amirkabir University of Technology, Tehran, Iran
Abstract
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. 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 was analyzed with the κ-ω SST turbulence model. Finally, it was observed that the tandem causes a 2.5-degree increase in the flow deviation angle and also a 16% increase in the drop coefficient in the compressor rotor. In addition to the mentioned cases, it was observed that the tandem increases the diffusion coefficient in the compressor rotor by 9.8%. It has also been observed that at the distance of 80% of the rotor opening, the tandem increases the drop parameter in the compressor rotor by 9.3%. Finally, the result was obtained that the tandem, by increasing the drop parameters, increases the pressure ratio of the compressor stage, reduces the number of stages, reduces the weight and volume of the engine, and finally reduces the drag force created in the airship.
Keywords
axial compressor
tandem
drop parameter
pressure ratio
Subjects
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