Gas turbine ring for turbo machine, has segments with lower cooling circuit that is independent of upper cooling circuit and shifted radially relative to upper circuit, where respective circuits cool segments outer and inner surfaces

摘要

The ring has ring segments (16) with an internal upper cooling circuit (A) and an internal lower cooling circuit (B). The lower cooling circuit is independent of the upper cooling circuit and shifted radially with respect to the upper cooling circuit. The respective cooling circuits cool an outer annular surface (20) and an inner annular surface (18) of the segments exposed to the flow of hot gas of a gas turbine.