| In order to study the impact of aircraft maneuvering flight on the radial support reactions of the main shaft bearings of an
engine, the aircraft coordinate system and the engine rotor coordinate system were established, and Timoshenko beam elements and disk
elements with eccentric mass were used to model the rotor system, and differential equations of rotor system based on flight parameters and
the whole aeroengine model were derived. Parameters such as the speed ratio and acceleration of rolling flight parameters were given. Flight
parameters were input into the whole aeroengine model. In this model, main shaft bearing support reactions were calculated using the
Newmark-β method. The results show that the additional damping, stiffness, and excitation force generated by maneuvering flight on the
rotor will cause the main shaft bearing to produce asymmetrical radial reactions along the circumference of the bearing. The dynamic
eccentricity caused by maneuvering flight leads to the increases of support reactions of the main shaft bearings, and the maximum bearing
support reaction in the x-direction of each main shaft bearing increases to 70.4, 48.4, 58.9, 77.2, and 125.9 times that in non-maneuvering
flight, while the maximum bearing reaction in the y-direction increases by 4.2, 1.3, 3.1, 2.1, and 2.9 times that in non-maneuvering flight.
These conclusions have reference value for the structural design of aeroengine main shaft bearings. |