To facilitate the manufacture and assembly of a gas turbine, in which stationary blades are arranged between the combustion chamber and the turbine rotor, by constituting both the stationary blade and the attached combustion chamber wall as a unit, and inserting this unit into a supporting structure.

In a gas turbine in which stationary blades 1.1 are arranged between the respective combustion chambers 1.2 and the turbine rotor, the stationary blade 1.1 is integrated in the combustion chamber wall 1.2.1 to form as a part of the combustion chamber wall so as to be a combustion chamber- stationary blade unit 1. The above unit 1 is inserted into a low-temperature supporting structure 3.1 of the gas turbine equipment, and is supported with this supporting structure 3.1. A cooling air passage 4 is defined between the respective supporting structures 3.1 and the attached segment 1.A or 1.B, and the passage 4 is partially extended to the inside of the stationary blade 1.1. The inflow opening 4.1 of the cooling air passage 4 is arranged in the area of the stationary blade 1.1 inside the low-temperature supporting structure 3.1 for performing the counterflow cooling of the combustion chamber wall.