Turbine blade suitable for aero-engine

The invention discloses a turbine blade suitable for an aero-engine. The turbine blade is provided with a blade leading edge, a blade suction surface, a blade pressure surface and a blade trailing edge. At least two vertically disposed vortex generators are mounted on the blade suction surface; the vortex generators are of a quarter oval plate-like structure, the length of the long axis sides andthe short axis sides are separately 7% and 5% of the chord length of the turbine blade, the thickness is 0.5% of the chord length of the turbine blade, and the long axis sides are fixed to the blade suction surface. The turbine blade suitable for the aero-engine is provided with the vortex generators with specific number and specific angles on the basis of an original turbine blade, thereby controlling the intensity of leakage vortex, the vortex generators induce and form vortex which is opposite to the direction of the leakage vortex to weaken the intensity of the leakage vortex, the mixing loss caused by the leakage