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• W2247885405 abstract "In the present study, a reduced scale model of a low-pressure stage of a two-stage pump turbine was investigated when it operates in pump mode, which is as a centrifugal pump with vaned diffuser. An instability region was found in its Q-H curve. This instability region, centered into the flow rate interval between 0.45 to 0.7 QDes, restricts the stable operating range of the test pump. The object of this study was to analyze the origins and development of the unsteadiness inner pump during this saddle instability region, and to find the causes of this saddle, which could guide the design, and optimization of the test pump.Experimental and numerical approaches have been adopted to contribute the understanding on the highly complex flow interactions inside the test pump. The analyses pointed out that the instability of Q-H curve during this flow rate interval was mainly affected by the flow field unsteadiness into the diffuser. Severe flow separation occurred into the diffuser, affecting and/or affected by the unsteadiness from the impeller and return channel remarkably.Both at full and part load, due to the U shape stay vanes in the return system, a 3-dimentional complex flow was found on the suction side of stay vane near the U turn corner. This flow caused a periodic unforced pressure disturbance with frequency St=0.6625 in the diffuser. A rotating stall with 5 cells into the diffuser was also highlighted by the experimental analyses and the numerical results validated that this disturbance was mainly due to the unsteady flow patterns in the return channel.With the reduction of flow rate, the location of this unsteadiness in return channel move closer to the outlet of diffuser, and the unsteadiness made the flow separation near the stay vane leading edge on the suction side more severe and it impacted the flow in diffuser flow field in a more severe way.At the same time, two types of unsteadiness were detected in the impeller in the saddle instability region. They were the flow separation with the frequency St=0.6625 at the impeller blade suction side and the wake-jet near the trailing edge of impeller blade with the frequency St=0.335, respectively. The wake-jet caused a periodic disturbance with a frequency of St=0.335 in diffuser as well. The experimental results indicated that it propagate circumferentially with 2 cells.At the beginning of this saddle instability, in diffuser, the intensity of the fluctuations at St=0.335 and St=0.6625 both increase with the falling flow rate. With the development of these unsteady patterns, they mixed and caused a blockage in the gap between impeller and diffuser. This blockage caused the increase of the amplitude at BPF, which has been detected both by experimental and numerical results. At the same time, the further development of the blockage weakened the intensity of the two disturbances with frequency of St=0.335 and St=0.6625 in the blockage region. The blockage fully developed near the critical flow rate of 0.6 QDes. At this condition, the intensity of rotor and stator interaction increased and energy loss also increased which caused the drop of head and mean pressure at the exit of impeller. Furthermore, the disturbance in diffuser which caused by wake-jet of impeller lost the periodic character with frequency of St=0.335 at this condition. This is the reason why the non-linear component St=0.335 disappeared in diffuser around 0.6 QDes." @default.
• W2247885405 created "2016-06-24" @default.
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• W2247885405 date "2015-02-28" @default.
• W2247885405 modified "2023-09-24" @default.
• W2247885405 title "Flow Patterns Causing Saddle Instability in the Performance Curve of a Centrifugal Pump with Vaned Diffuser" @default.
• W2247885405 hasPublicationYear "2015" @default.
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