Electricity leading device cooling device for aero-engine dynamic stress measurement test

The invention relates to a cooling device for an electric conduction device for an aero-engine dynamic stress measurement test. The cooling device comprises an electric conduction device mounting disc; the air inlet pipe assembly is mounted on the electricity leading device mounting disc; the air inlet pipe is of a double-layer structure composed of an air inlet pipe outer cylinder and an air inlet pipe inner cylinder. A through hole of the air inlet pipe inner barrel forms a main air inlet channel; an auxiliary air inlet channel is formed between the air inlet pipe outer cylinder and the air inlet pipe inner cylinder; the electricity guiding device protection cover assembly is installed on the electricity guiding device installation disc and is of a double-layer structure composed of a protection cover outer cylinder and a protection cover inner cylinder; an inner cavity of the protection cover inner cylinder forms a first cavity; a second cavity is formed between the protective cover outer cylinder and the