The invention discloses a micro
turbine for an aero-engine. The micro
turbine comprises a
turbine disc, and turbine blades sequentially distributed on the turbine disc along the circumferential direction of the turbine disc, wherein the turbine disc further comprises locking pipes used for locking the turbine blades in corresponding mortises on the turbine disc; the locking
pipe is arranged at theconnecting position of the small end of a tenon and the mortise of the
turbine blade; and the locking
pipe deforms under the action of external force
punching and riveting so as to be squeezed in thetenon and the mortise at the same time to lock the
turbine blade, and then the
turbine blade is prevented from moving backwards towards the exhaust end of the turbine. According to the micro turbinefor the aero-engine, due to the fact that deformation of the locking pipes under the action of
punching and riveting force is spatial multi-dimensional deformation, the positioning locking tightness of the locking pipes to the turbine blades is larger than the locking tightness of locking pieces, and therefore the turbine blade can be effectively prevented from moving backwards towards the exhaustend of the turbine, and then the breaking fault of the turbine blade occurring after the turbine blade scrapes a rear
stator is reduced; and the turbine blades are high in positioning tightness, so that the
fretting wear of the tenon contact surface is small, and the vibration stress of the tenon contact surface is small.