Based on a typical aircraft engine

the calculation model was built by studying model simplification methods and analyzing main loads and loading procedures in maneuver flight. By grasping the change rule of radial tip clearance subjected to different kinds of maneuvering loads by finite element simulation

it can provide significant reference for studying the effects of tip clearance variation on aero-engine performance. Discovered by rational analysis on the distortion of cases and rotors in consequence of gyroscopic moment and normal overload

it can be concluded that two kinds of loads can cause distinct deformation in the core engine. The mean of the relative variation of radial tip clearance subjected to gyro moment was up to -2.174

while the value subjected to normal overload was up to -1.572 owing to the weaker influence of normal overload. Consequently

the impacts of maneuvering loads on engines cannot be ignored when studying the radial tip clearance variation.