TY - GEN
T1 - Numerical and experimental study of vortex structure and energy loss in a novel self-priming pump
AU - Chang, Hao
AU - Agarwal, Ramesh K.
AU - Li, Wei
AU - Zhou, Ling
AU - Shi, Weidong
N1 - Funding Information:
This work was sponsored by the National Natural Science Foundation of China (No.51679111, No.51409127 and No.51579118), National Key R&D Program Project (No.2017YFC0403703), PAPD, Six Talents Peak Project of Jiangsu Province (No.HYZB-002), Key R&D Program Project in Jiangsu Province (BE2015119, BE2015001-4, BE2016319, BE2017126), Natural Science Foundation of Jiangsu Province (No.BK20161472), Science and Technology Support Program of Changzhou (No.CE20162004) and Graduate Student Scientific Research Innovation Projects of Jiangsu Province (Grant No. SJKY19_2547), The first author would like to thank Chinese Scholarship Council (CSC) for the financial support and Washington University in St. Louis for providing the opportunity to spend a year as a visiting PhD student.
Publisher Copyright:
© 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2020
Y1 - 2020
N2 - Since the conventional numerical approaches cannot explicitly confirm the location and type of the vortex structure, therefore this paper employs the vorticity transport equation to systematically analyze the type, magnitude and location of vortices for different blade thickness distributions in a novel self-priming pump. Also, the entropy production theory is applied to investigate the energy loss in the pump. Based on the analysis, it is found that the entropy generated by the separation of turbulent boundary layer at the trailing edge of the blade is a major factor leading to hydraulic loss. The separation of the boundary layer can not only cause the energy loss, but also generates the trailing edge vortex to block the passage of the impeller and reduces the expelling coefficient of the blade. It is found that the hydraulic performance of the blades with increase in thickness distribution of the blade from leading edge to trailing edge is better than that of the blades with decrease in thickness distribution. The flow rate also has influence on the vortex structure and entropy production. Finally, the optimal blade shape is obtained, and experimental test of its hydraulic performance is performed to benchmark the simulation results. This research can provide guidelines for designing the optimal thickness distribution for the blades for design operating conditions.
AB - Since the conventional numerical approaches cannot explicitly confirm the location and type of the vortex structure, therefore this paper employs the vorticity transport equation to systematically analyze the type, magnitude and location of vortices for different blade thickness distributions in a novel self-priming pump. Also, the entropy production theory is applied to investigate the energy loss in the pump. Based on the analysis, it is found that the entropy generated by the separation of turbulent boundary layer at the trailing edge of the blade is a major factor leading to hydraulic loss. The separation of the boundary layer can not only cause the energy loss, but also generates the trailing edge vortex to block the passage of the impeller and reduces the expelling coefficient of the blade. It is found that the hydraulic performance of the blades with increase in thickness distribution of the blade from leading edge to trailing edge is better than that of the blades with decrease in thickness distribution. The flow rate also has influence on the vortex structure and entropy production. Finally, the optimal blade shape is obtained, and experimental test of its hydraulic performance is performed to benchmark the simulation results. This research can provide guidelines for designing the optimal thickness distribution for the blades for design operating conditions.
UR - http://www.scopus.com/inward/record.url?scp=85092370970&partnerID=8YFLogxK
U2 - 10.2514/6.2020-1801
DO - 10.2514/6.2020-1801
M3 - Conference contribution
AN - SCOPUS:85092370970
SN - 9781624105951
T3 - AIAA Scitech 2020 Forum
BT - AIAA Scitech 2020 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Scitech Forum, 2020
Y2 - 6 January 2020 through 10 January 2020
ER -