Aero-engine power testing device

The invention relates to the field of power testing, and provides an aero-engine power testing device, which comprises a speed reduction device comprising an input shaft, an output shaft, a first transmission wheel, a second transmission wheel and a one-way clutch, the input shaft is used for being connected with a main shaft of an engine, the input shaft is sleeved with the first transmission wheel, and the second transmission wheel is connected with the output shaft through the one-way clutch; the one-way clutch is arranged to be in a joint state when the second transmission wheel rotates in the first direction and in a separation state when the second transmission wheel rotates in the second direction, and the first transmission wheel and the second transmission wheel are in speed reduction transmission connection. And a rotor of the eddy current damper is connected with the output shaft. In the rotating process of the eddy current damper, the output shaft is driven to continue to rotate in the first direc