Filmgekühlte Brennkammerwand für Gasturbine und Verfahren zu ihrer Herstellung

摘要

Provided are a gas turbine multi-hole film-cooled combustor liner, which can be manufactured with improved accuracy in shape and position of cooling holes (3) in a very short time, ensuring desirable buckling strength and satisfactory cooling performance. A planar flat member is curved to form a liner shell (1) of a cylindrical shape, the cylindrical member is welded in the longitudinal direction thereof to form a cylindrical shell. Then a wavy configuration (11) and a corrugated configuration (12) are formed on the cylindrical shell by a hydro-bulging method, cooling holes (3) are formed through the liner shell (1) by laser drilling at or near wave crest portions of the wavy configuration of the liner shell (1), and inner rings are attached to the liner shell (1) by resistance spot welding or vacuum brazing.