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Effect of Impeller Geometry and Tongue Shape on the Flow Field of Cross Flow Fans

Journal of Thermal Science 2003年第2期12卷 118-125页

作者： M.Govardhan G.Venkateswarlu Department of Mechanical Engineering Indian Institute of Technology MadrasChennai 600 036IndiaDepartment of Mechanical EngineeringIndian Institute of Technology MadrasChennai 600 036India

Experiments were conducted to investigate the effect of impeller geometry and tongue shape on the flow field of cross flow *** impellers(Ⅰ，Ⅱ，Ⅲ）having same outer diameter,but different radius ratio and blade angles were employed for the *** impeller was tested with two tongue *** survey was carried out for each impeller and tongue shape at two flow *** for each flow coefficient at different circumferential *** flow is two-dimensional along the blade span except near the *** total pressure developed by the impellers in each case is found to be maximum at a circumferential position of around 270°.The total and static pressures at the inlet of impellers are more or less same regardless of impeller and tongue geometry,but they vary considerably at exit of the *** Ⅲ with tongue T2 develops higher total pressure and efficiency where as impeller Ⅱ with tongue T2 develops minimum total *** diffusion and smaller vortex size are the reasons for better performance of impeller Ⅲwith tongue T2。

关键词： Impeller tongue circumferential position flow coefficient eccentric vortex total pressure coefficient static pressure coefficient.

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Numerical Analysis and Experimental Validation of a Submerged Inlet on the Plane Surface

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Chinese Journal of Aeronautics 2005年第3期18卷 199-205页

作者：孙姝郭荣伟 Internal Flow Research Center Nanjing University of Aeronautics and Astronautics Nanjing 210016 China

In order to get a deep insight of a submerged inlet on the plane surface, the integrated flow field of the inlet and fuselage has been numerically studied. The investigation is mainly focused on the formation of the total pressure distribution at the exit of the inlet, the structure of the inner flow and the effects of the boundary layer along the fuselage on the performance of the inlet. Moreover, in comparison with the experimental data at different angles of attack, yaws and mass flow ratios, the reliabilities of the computational fluid dynamics（CFD） studied are verified. Results indicate：（1） the CFD results agree well with the experiment results and the relative errors of the total pressure coefficient is less than 1% ; （2） at the inlet＇s exit, the contour of total pressure obtained by CFD is similar to the experiment result except the contour in the low total pressure zone in CFD is slightly larger; （3） the secondary flow at the cross section behave as two counter-rotating vortices. Along the flow direction, the fields influenced by the vortex pair transport downstream and expand to the whole section at the exit; （4） the total pressure loss at the exit of the submerged inlet can be divided into external loss and internal loss. Usually, the external loss is greater than the internal loss, and both decrease with the augment of the Mach number at the exit. In addition, when the angle of attack ranges from -2° to 8°, the total pressure coefficient ascends gradually, due to the reduction of the external loss caused by the less boundary layer flow captured and the invisible change of the internal loss.

关键词： submerged inlet on the plane surface CFD boundary layer counter-rotating vortices total pressure coefficient

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