摘要：Because of the problem of a high fuel temperature rise at shut-off, a conventional centrifugal pump could not be used as an aero-engine fuel pump for the afterburner fuel supply. In this study, a centrifugal pump with a cooling bypass was designed to address this problem. Experiments and numerical simulations were conducted to assess the design. The results showed that the circulation cooling achieved by a small amount of cooling fuel from a cooling bypass could effectively solve the problem. When the pump with a cooling bypass operated at shut-off, a large vapour core appeared at the centre of the impeller due to cavitation. This large vapour core reduced both the pump power consumption and the heat generated by friction, thereby greatly reducing the fuel temperature rise in the pump. Further research works showed that the radius of the vapour core was a function of the flow rate and the pump rotational speed. Moreover, the cooling fuel flow rate was regulated by the size of the nozzle hole. It is clear that a centrifugal pump with a cooling bypass overcomes the problem of the high fuel temperature rise in the pump at shut-off.
