The invention discloses a high-low cycle composite fatigue test piece design method for a
turbine disc cold
extrusion reinforced hole structure, and the method comprises the steps: obtaining a geometric model of a perforated
turbine disc, and simplifying a non-key region; obtaining working conditions of the
turbine disc and material performance parameters under all the working conditions; and establishing a finite
element analysis model of the perforated wheel disc, and conducting calculating to obtain a hole edge
equivalent stress maximum point and a
stress gradient. A flat test piece with acenter hole is used as a basic shape, uniaxial tensile loading is used as a basic load form, an examination section of a turbine disc hole structure test piece is designed, and the maximum stress value and distribution of the
stress concentration position of the hole edge of the test piece accord with the condition of a
real structure by adjusting the width of the test piece, finely adjusting thetensile load and the like. By the
modes of adjusting the thickness of the test piece, the frequency and magnitude of the exciting force and the like, the maximum vibration stress value of the hole edge is equal to the maximum vibration stress value of a real wheel disc hole structure, and it is ensured that the loads are all within the optimal
working range of the high-low cycle composite fatiguetest
system; and a test piece double-wedge-shaped clamping end is designed, and thus the
low stress level of the clamping end and the
low stress concentration degree of a transition section are guaranteed.