COOLED MULTISTAGE TURBINE OF TURBOJET ENGINE Russian patent published in 1999 - IPC

FIELD: turbojet engines. SUBSTANCE: cooled multistage turbine of turbojet engine includes wheel rotor of last stage with cooled rotor blades whose radial cooling passages are connected with gas duct of turbine by their end outlets; their inlets are hydraulically connected with supply main running through inner cavities of radial struts located after turbine with cooling air source. Outer loop of engine is used as cooling air source for cooling passages of rotor blades. Inlet of supply main of cooling passages is made in form of air intakes. Air intakes of cooling air supply main, radial passages of disk and rotor blades are made for probable compression of cooling air flow. Inlets of dynamic air intakes are directed to engine inlet. Cooling air supply main of rotor wheel of turbine last stage is provided with inlet guide apparatus. EFFECT: enhanced operational efficiency of turbine. 3 cl, 2 dwg