The invention discloses an integrated liquid propellant rocket engine high speed turbo-pump rotor dynamic characteristic testing device. The integrated liquid propellant rocket engine high speed turbo-pump rotor dynamic characteristic testing device comprises a device upper pad (1), a device lower pad (2), a lubricating oil return cavity (3), a bearing intermediate lubricating oil path (4), a lubricating oil inlet(5), a device external axial positioning surface (6), a device external radial positioning surface (7), a lubricating oil return hole (8), bearing two-side lubricating oil injecting pipes (9), a rotor supporting axial positioning surface (10), a rotor supporting radial positioning surface (11), sensor observation points (12), positioning pin holes (13), and bearing intermediate oil injecting pipe (14). Supporting points of two ends of a test piece are connected and supported by an integral tool. The dynamic characteristic testing device provided by the invention is mainly suitable for a turbo-pump rotor system having a small span and a high rotating speed, and at the same time, has a bearing lubricating function, a function of acquiring the arrangement of the observation points, and other functions, and therefore the accuracy and the stability of the dynamic characteristic test of the high speed turbo-pump rotor system are guaranteed.