Aero-engine compressor designers have a challenging task of developing compressors that have a higher-pressure ratio and better efficiency with a lower number of stages. Such designs would require blades with high diffusion factor and hence the inherent risk of flow separation. Tandem blade is an interesting concept, which possibly addresses this problem. In tandem blading, the forward blade and the aft blades are arranged in such a manner that a converging nozzle flow path is created between the two blades. The flow accelerates through this nozzle, energizes the suction surface flow, and thereby prevents the early onset of flow separation. This paper presents the steady computational analysis of a tandem rotor stage and baseline stage in low-speed axial flow compressor at design and off-design condition using ANSYS CFX. The study is further extended to analyze the effect of radial distortion on the performance of tandem rotor and the single rotor.
Effects of Radial Distortion on Low-Speed Tandem Stage Axial Compressor
Lect.Notes Mechanical Engineering
2022-07-24
23 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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