Abstract: An insert inserting structure and a method for enabling a stationary blade of a gas turbine to withstand high temperatures of even 1500 C. in order to realize a 150.degree. C. class gas turbine is provided. In a stationary blade of a gas turbine including a hollow opening (2, 3, 4) into which an insert (5, 6, 7) having a plurality of cooling-air ejecting apertures (8) formed in a side wall thereof is inserted to thereby cool wall surfaces of said hollow opening (2, 3, 4) with cooling air ejected from said cooling-air ejecting apertures (8), a structure for inserting an insert in a stationary blade of a gas turbine, comprising a pair of seal plates (9a, . . . , 9f) disposed on side walls of said insert (5, 6, 7) and two grooves (11a, . . . , 11f) disposed on said wall surfaces of said hollow opening (2, 3, 4) so as to receive fittingly said seal plates (9a, . . . , 9f), respectively, wherein at least one (11b, 11c, 11d, 11e) of said two grooves (11a, . . .

Abstract: In a cooling air passage in a gas turbine stationary blade shroud a groove at a shroud end face is formed to extend along the shroud end face. An open portion of the groove is covered by a plug so as to form a cooling air passage. A cooling air passage in which the work accuracy is remarkably enhanced can thus be very easily worked. Preferably the cooling air passage is formed by electric discharge machining (EDM). The same process can be used to form an open portion of the groove, as well as any desired turbulators. The open portion of the groove is closed by a plug which is brazed or welded in place.