Turbine blades, manufacturing methods of turbine blades, and gas turbines and processes

1. The present invention relates to a method for manufacturing turbine blades such as rotor blades and stationary blades of a gas turbine, a turbine blade, and a gas turbine equipped with the turbine blades.

Background technique:

2. The gas turbine has a compressor, a combustor, and a turbine. The compressor compresses the air taken in from the air intake to obtain high-temperature and high-pressure compressed air. The combustor supplies and burns compressed air with fuel to obtain high-temperature and high-pressure combustion gas. The turbine is driven by the combustion gas to drive a coaxially connected generator.

3. It is known that in turbine blades such as rotor blades and stator blades in a gas turbine, cooling passages are provided inside the turbine blades, and a cooling fluid flows in the cooling passages, thereby cooling the turbine blades exposed to high-temperature airflow . For example, the following patent document 1 describes a technique in which a plurality of cooling holes for the cooling medium to flow are penetratingly provided along the longitudinal direction of the blade portion, and the cooling holes are divided into large-diameter portions, intermediate-diameter portions, and small-diameter portions with different diameters. It is configured so that it is possible to sufficiently cool the tip end portion of the blade. In addition, Patent Document 2 below describes a technique in which a plurality of cooling passages through which cooling air flows are penetratingly provided along the longitudinal direction of the blade portion, and the diameter of the cooling passage is changed in the front-rear direction of the blade portion.

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