BLADE COOLING FOR GAS TURBINE ENGINE

摘要

A hollow blade for a turbine in a gas turbine engine comprising passageways in the hollow blade for passing a coolant therethrough and pairs of ridges having a chevron shape and being segmented form a channel therebetween with corresponding pairs on opposed side walls of the passageway such that each corresponding opposed pair has the chevron angle open in opposite directions relative to the longitudinal direction of the passageway.