Gas turbine rotor cold air conveying test piece and test parameter design method

The invention discloses a gas turbine rotor cold air conveying test piece, which comprises a wheel disc component A and a wheel disc component B, wherein the wheel disc component A and the wheel disccomponent B form a hollow cavity, a central hole B is formed in the wheel disc component B, and a through hole is formed in the wheel disc component A. The parameter design method comprises the following steps: obtaining a similarity criterion; determining a modeling ratio; and calculating a modeling test cold air conveying test piece diameter, a modeling test center hole diameter, a modeling testend face tooth meshing gap area, a modeling test end face tooth meshing gap number, a modeling test kidney-shaped hole total area, a modeling test kidney-shaped hole number, a modeling test compressed air mass flow rate, a modeling test inlet gas total pressure, a modeling test outlet gas static pressure and a modeling test rotor rotating speed. According to the invention, the flow characteristicparameters of the key stru