Abstract: In order to obtain a print area from a printing start position to a printing end position in the longitudinal direction of printing paper without leaving any margin in the lateral direction of the paper, the width of a heater line of a thermal head (1a), corresponding to the lateral direction of the printing paper, is set to be not less than the width of the printing paper. Considering a shift length to be made by a cutter (6) in cutting, a CPU (10A) determines a first cutting position that is on the side of the print area with respect to the printing start position of the print area, and a final cutting position that is on the side of the print area with respect to the printing end position of the print area. Then, the CPU (10A) gives a cutting command which indicates the first and final cutting positions to the cutter (6) which will cut the printing paper at those positions. This allows an image printing apparatus to obtain cut printing paper which is entirely an effective print area without any margin.

Abstract: A heavy-duty gas turbine includes a compressor; a combustion liner; a turbine blade in a single stage or multi-stages; and a turbine nozzle provided in correspondence to the turbine blade. The turbine blade has a dovetail secured to a turbine disk and has an overall length of not less than 180 mm, and it is made of a single-crystal Ni-base alloy whose .gamma. phase is a single crystal. Operating gas temperature is not less than 1400.degree. C., and metal temperature of a first blade is not less than 1000.degree. C. under working stress.

Abstract: A gas-turbine moving blade made of a Ni-base superalloy containing less grain boundary strengthening elements, in which a blade portion is formed of a single crystal and the rest is formed of columnar crystals, and a gas turbine including the moving blade. A thermal efficiency of the gas turbine can be improved to 35% or more, and a thermal efficiency of complex power generation with a steam turbine can be improved to 45% or more.

Abstract: A heavy-duty gas turbine includes a compressor; a combustion liner; a turbine blade in a single stage or multi-stages; and a turbine nozzle provided in correspondence to the turbine blade. The turbine blade has a dovetail secured to a turbine disk and has an overall length of not less than 180 mm, and it is made of a single-crystal Ni-base alloy whose .gamma. phase is a single crystal. Operating gas temperature is not less than 1400.degree. C., and metal temperature of a first blade is not less than 1000.degree. C. under working stress.