Novel butterfly wing type rotating channel supercritical pressure hydrocarbon fuel heat transfer performance investigation.

In this paper, a novel butterfly wing type hydrocarbon fuel cooling channel structure is proposed and applied for the first time in the cooling of rotating power generation turbine blades of hypersonic vehicles. The effects of rotating butterfly wing-type channel root height and cross-critical temperature on the friction factor and heat transfer performance of hydrocarbon fuel are investigated in depth. Numerical results show that the thermal performance of the butterfly wing type channel corresponding to the root height of 0.8 D is the highest. Compared to the 1 D channel, the thermal performance of the butterfly wing type channel corresponding to the root height of 0.8 D is increased by a maximum of 1.8 times. Compared to the 1 D channel, the Nusselt number of the wing type channel corresponding to the root height 0.2 D is increased by a maximum of 1.03 times. Compared to the inlet temperature greater than critical temperature, the thermal performance of the wing type channel at inlet temperature less than critical temperature is increased by a maximum of 2.1 times. Compared to the 1 D channel, the wing type channel reduces the first channel backflow and vortex area by almost 50%. • A novel butterfly wing type hydrocarbon fuel cooling channel is proposed and firstly used in hypersonic vehicles. • Thermal performance of the channel with a root height of 0.8 D is increased by maximum 1.8 times. • The butterfly wing type channel can improve the thermal performance of the fuel at high rotation speed. • The wing type channel can reduce the backflow and vortex area by almost 50%. • Fuel "upward convexity" and "downward concavity" cause the wing channel heat transfer level to increase. [ABSTRACT FROM AUTHOR]