FIELD: mechanical engineering; gas-turbine engines. SUBSTANCE: rotor of turbine of gas-turbine engine contains disks with central holes coupled to each other. First disk is connected with hollow shaft installed on bearings placed in oil space. Oil space communicates with air-and-oil separator made in form of tube secured on shaft and passing with clearance through central holes. Tube has conical section narrowing in direction of flow of air-oil mixture. Cover disk connected to outer surface of wall of last disk forms space communicating with turbine setting. Space accommodates radial blades made over periphery of cover disk or disk. Central hole of last disk has widening sectional at outlet. Outlet cut of tube is located in zone of widening section without projecting beyond disk surface. Tube is secured on shaft by means of intermediate bushing, and widening section of central hole of last disk is made to radius. EFFECT: enhanced operation. 3 cl, 1 dwg
