The main reason for limiting the working flow range of the compressor is the unstable flow phenomenon of the compressor working at a small flow rate, including stall, surge, and rotational instability. Among them, the rotating stall phenomenon is particularly prone to occur during the operation of centrifugal compressors. In this paper, a three-stage nitrogen centrifugal compressor is taken as the research object, and the dynamic development process of rotating stall in the diffuser is captured by full-channel numerical calculation. After research, the leading-edge vortex at the diffuser inlet is the cause of rotating stall. In the throttling process, the backflow in the diffuser causes the channel blockage and the stall phenomenon triggered by the leading-edge overflow. There are six stall channels in the first-stage diffuser and nine stall channels in the second-stage diffuser. The propagation direction is the same as the rotation direction of the blade, and the propagation speeds are 4.348% and 5.26%, respectively.
Centrifugal pumps account for a significant share of global industrial energy consumption. Optimizing the shape of all components is the main goal in the design process to improve operating efficiency and reduce environmental impact. However, centrifugal pumps often operate under off-design conditions, where the flow i...
A. Fracassi, A. Ghidoni, M. Ghisalberti et al.· The Physics of Fluids· 0 citations
Research has shown that rotating detonation turbine engines have the potential to enhance aero-engine performance. However, the rotating back-propagation pressure wave (RBPW) generated by the detonation-based combustor can adversely affect the upstream compressor. In this study, this unsteady backpressure was simulat...
Y. Qi, Cha Xiong, Yining Zhang et al.· Journal of Engineering For G...· 0 citations
High-speed rotating cooling passages in aero-engine turbine blades experience significant centrifugal compression, leading to strong coupling between thermodynamic states and flow structures, which challenges the validity of incompressible assumptions. In this study, large eddy simulations are performed to investigate...
Yujie Liu, Ru-Quan You, Run-Zhou Liu et al.· The Physics of Fluids· 0 citations
Future jet engine compressors are expected to feature overall pressure ratios (OPR) that approach 70:1. The core of the compressor will downsize with higher OPR, increasing the importance of managing blade-tip clearance. This clearance is influenced by compressor rotor expansion, which is dictated by the flow structu...
Sebastian Syncerz, Dominic W. A. Lafone-Ward, Mai Mohamed et al.· Journal of turbomachinery· 0 citations
Non-periodic leading-edge wear near the impeller tip is investigated with respect to the aerodynamic performance, steady flow organization, and near-stall unsteady evolution of a centrifugal compressor. A full-annulus three-dimensional impeller–vaned-diffuser model is established for a baseline configuration (O-M) and...
Hong Xie, Zhi-Biao Cai, Bo Yang et al.· Aerospace· 0 citations
To suppress the flow-induced vibration of a single-stage single-suction centrifugal pump (rated head 5 m, flow rate 30 m
3
/h, rotational speed 1000 r/min), the key impeller parameters were taken as design variables and screened via the parameter sensitivity analysis method in this study. The internal flow field wa...
Jia-Fu Guo, Xinxiang He, Abdul Mutalib bin Leman et al.· Proceedings of the Instituti...· 0 citations
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