The influence of nozzle parameters on the atomization performance of aviation kerosene is not clear. To solve this problem, the kerosene atomization characteristics under different nozzle hole diameters (d), nozzle hole numbers (N), nozzle hole cone angle (φ), as well as nozzle hole tilt angle (α) were investigated by numerical simulation. The results showed that when the nozzle hole diameter increased from 0.16 mm to 0.2 mm, the liquid penetration length and spray cone angle increased from 36 mm and 13° to 41 mm and 15°, respectively. Due to the influence of cross interference, the liquid penetration length of aviation kerosene presented a non-linear relationship with the nozzle hole number. In addition, for multi-hole nozzles, the cross-interference phenomenon reduced significantly as the spray hole cone angle decreased. The decrease in nozzle hole tilt angle facilitated the increase of turbulent kinetic energy, thus increasing the fuel evaporation rate. On this basis, the simulation analysis of the atomization and combustion process in aviation kerosene rotary engine was carried out. The findings indicated that the liquid penetration length and particle distribution of kerosene were more suitable for a small-scaled kerosene rotary engine with a narrow combustion chamber when the d of the two-hole nozzle is 0.18 mm, and φ and a are 12° and 15°, respectively. Compared to the original nozzle parameters, the average pressure at the optimized nozzle parameters increased from 1.83 MPa to 4.16 MPa, showing an increase of 127%, and the total heat release rate increased by 107%.