The disks of combined rotor of the rotating machines

such as aero-engine

heavy-duty gas turbine

are often joined by discontinuous interface

both structural analysis and thermal-structural coupling analysis were carried out for cold preloading and speedup stages as well as steady-state temperature field by establishing a two-wheel contact finite element model. The evolution of fretting parameters

including contact stress

the shear stress and fretting wear depth of the annular contact interface

was investigated. Results showed that the contact stress decreased gradually from the inner diameter to the outer diameter under the action of preloading force. The contact stress and shear stress were the largest at the inner diameter

and the fretting wear was the most serious. The maximum contact stress at the annular contact interface increased and the minimum contact stress decreased with the increase of the rotational speed and the centrifugal force

which caused the non-uniformity contact stress distribution and intensified the wear. The steady-state temperature field caused a large increase of the average contact stress

and it would seriously aggravate wear. Judging from the uniformity of the contact stress distribution and fretting wear condition

the thermal load is the main factor causing fretting wear on the discontinuous interface of combined rotor.