Impingement cooled gas turbine combustor with internal film cooling.

摘要

A gas turbine combustor, having a side wall formed of side wall members (12, 14, 16, 18, etc.,) in telescopic relation to form annular air admission gaps 24 to obtain film cooling, a cylindrical jacket 36 encompasses at least the upstream stages of the combustor and is provided with impingement ports (38-45) located in an axial direction to provide impingement cooling upon the relatively hotter portions of the side wall members before the air in the jacket performs its film-cooling effect by entering the combustor through the annular air admission gas.