| 摘要 |
PURPOSE:To increase temperature and efficiency by a method wherein a compressor integrally coupled with the turbine of a gas turbine is formed such that blades in the specified number of stages with which an integral type rotor shaft is filled are provided and air is compressed at a given temperature or more. CONSTITUTION:A gas turbine is formed such that a compressor is integrally coupled with a turbine driven by means of combustion gas generated by a combustor 5. In this case, the compressor is formed such that an integral type rotor shaft 6 filled with blades 7 in twelve stages or more is provided. The rotary shaft 6 is formed of a specified Ni-Cr-Mo-V light low alloy steel having 50% fracture appearance transition temperature and 475 deg.C, and a 10<5> time creep rupture strength and a ratio D/L between a maximum diameter D and the length L, ranging from the first stage of the blades 7 to the final stage thereof, is set to 0.40-0.55. The blades 7 are arranged in 15 stages or more, the blades ranging from the first stage to a fifth stage are made of a Ti alloy and other blades are made of a martensite stainless steel. |
