Abstract:  Aiming at the problem that it was difficult to obtain the flow characteristics of the aviation fuel gear pump through theoretical analysis and experimental research, numerical simulation on the flow mechanism of the aviation fuel gear pump was carried out. The Reynolds average equation and the k-ε turbulence model were used as the mathematical model, and the dynamic grid method based on spring deformation and local redrawing technology was adopted to realize the grid deformation. The internal flow field was numerically solved under different rotational speeds in Fluent, the pressure and velocity distributions were obtained, and the influence of rotational speed on the flow field was analyzed. The results show that the area where the gears enter into and exit meshing is respectively a local high-pressure and low-pressure zone. The highest pressure can reach 4.3MPa ~20MPa, the lowest pressure can reach -10MPa~-40MPa. With the increase of rotational speed, their pressure difference increases, the flow velocity reaches the local maximum at the gear meshing point, the maximum speed can reach 105m/s ~269m/s, and this value is positively correlated with the rotational speed. The research results provide a theoretical basis for the operating maintenance and optimal design of aviation fuel gear pumps.

Key words:  gear pump; aviation fuel pump; numerical simulation; dynamic grid; turbulence model

TANG Qing, SHAN Jin-guang, ZHOU Long, et al. Numerical simulation of the flow mechanism for aviation fuel gear pump［J］.Journal of Mechanical & Electrical Engineering, 2021,38(9):1185-1190.