Method for rotor blade tip clearance control and rotor blade manufactured by the method

A method for controlling rotor blade tip clearances in an aeroengine, comprising:

• setting a center of gravity of a rotor blade to be overlapped with a center of gravity of a rotor disk in an axial direction of the aeroengine;
• rotating the rotor disk;
• measuring a leading edge deformation amount of a leading edge of the rotor blade;
• measuring a trailing edge deformation amount of a trailing edge of the rotor blade;
• comparing the leading edge deformation amount and the trailing edge deformation amount when a difference between the leading edge deformation amount and the trailing edge deformation amount is larger than a specified range;
• and
• adjusting the center of gravity of the rotor disk based on the comparison of the leading edge deformation amount and the trailing edge deformation amount, until the leading edge deformation amount and the trailing edge deformation amount tends to be approximately the same,
• wherein adjusting the center of gravity of the rotor disk comprises offsetting the center of gravity of the rotor disk towards one of the leading edge and the trailing edge which has a smaller deformation amount by a predetermined offset amount.