This paper presents a low-order model applying the immersed boundary method on smeared geometry. It is thus able to represent the effect of turbomachinery within a complex system. Assessment of this model on the NASA rotor 67 has been made under clean flow conditions. Good agreement has been achieved between the immersed boundary method on smeared geometry model, experiments, and a high-fidelity computational fluids dynamics model. For high-speed conditions, about within 0.5, 1, and 1% agreements are achieved on the pressure ratio, efficiency, and choking flow, respectively, between immersed the boundary method on smeared geometry model and the experiment. The capability of the model capturing the fan’s behavior under inlet distortion has also been assessed under the flow with a level of 10% distortion of the total pressure, which covers a 120 deg sector. The nonuniform work input of the fan, which is one of the key features of the fan–distortion interaction, has been captured by the immersed boundary method on smeared geometry model. Finally, the model also helps to shed light on the physical understanding of fan–distortion interaction. It provides evidence suggesting that the tangential pressure gradient is one of the mechanisms causing the induced nonuniform work input of the fan subjected to the inlet distortion.
Hierarchical Immersed Boundary Method with Smeared Geometry
Journal of Propulsion and Power ; 33 , 5 ; 1151-1163
2017-04-10
13 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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