METHOD FOR MANUFACTURE OF COOLED GAS TURBINE ENGINE BLADE AND COOLED BLADE OF GAS TURBINE ENGINE Russian patent published in 1997 - IPC

FIELD: foundry, in particular, casting of engine blades with monocrystallic structure from fireproof and intermetallic alloys. SUBSTANCE: method involves manufacturing rod fin from spatial netted material; positioning cylindrical ceramic pins onto fin; making blade model and then ceramic mold; pouring melt of fireproof alloy and performing directed crystallization; removing ceramics from inner cavity to obtain blade with spatial-netted structure fin. Cooled blade has lock with cavity for supplying cooled air and fin whose inner cavity or at least a portion of it is provided with passages defined by spatial-netted construction, with space between passages being at least equal to two diameters of passage cross section. Outlet openings on outer surface are adapted to connect inner part of fin with its outer part. Such construction allows gas temperature in front of turbine to be increased up to 1,800-1,850 C and cooling capacity to be equal to 0.6. EFFECT: increased efficiency in cooling blade, light weight combined with improved strength and enhanced reliability in operation. 4 cl, 2 dwg