Heat transfer performance of RP-3 aviation kerosene at supercritical pressure within a rotating U-shaped channel

Abstract

The combined cycle engine based on turbine is typical in the field of cycle engines. However, the problem of high temperature heat load of turbine blades is serious. In order to solve this kind of problem, the method of using hydrocarbon fuel as cooling medium to improve the cooling efficiency of turbine blades are proposed. In this paper, the flow and heat transfer characteristics of RP-3 aviation kerosene in a rotating U-shaped channel under supercritical pressure were studied by numerical simulation. The flow and heat transfer characteristics of RP-3 aviation kerosene under supercritical pressure at different rotational speeds were numerically simulated by SST k-ω model. The results show that the centrifugal section and the horizontal section show obvious fluid stratification, and the mainstream distribution in the centripetal section is relatively uniform due to the bending effect and rotational buoyancy. Compared with the heat transfer capacity in the static state of the centrifugal section, the heat transfer of the fluid in the rotating state deteriorates, recovers and strengthens with the increase in the rotational speed. Moreover, compared with the centripetal section, the rotational speed has a particularly significant effect on the heat transfer performance in the centrifugal section and the horizontal section. When the rotational speed exceeds 300 rpm, the deterioration trend of heat transfer is weakened and the overall heat transfer performance is greatly improved.