ROTOR OF HIGH-TEMPERATURE GAS TURBINE Russian patent published in 2003 - IPC

FIELD: mechanical engineering; turbines. SUBSTANCE: proposed rotor of high-temperature gas turbine contains disks with cooled working blades installed at disk projections. Cooling channels are made at inlet of roots of cooled working blades. Rotor contains also deflector of first stage disk made with ring peripheral rib and installed on disk by means of bayonet joint. Radial channels are made in bayonet joint. Radial channels are made in bayonet joint, and tangential channels are made in rim from side of blade leading edge. Said tangential channels connect inner space of blade with cooling air supply space. Summary area of passage section of radial and tangential channels exceeds summary area of passage section of blade root cooling channels. Inner space of blades is divided by rib into two spaces. Leading edge of blades is perforated. EFFECT: improved reliability of rotor owing to minimization of hydraulic losses of cooling air and increase of efficiency of working blade cooling system. 3 dwg