Hollow turbine blade i.e. hollow guide vane, film cooling method, involves passive-controlling flow separation at blade, and bending nozzles under angle in transverse direction to mainstream direction of gas and under another angle

摘要

The method involves forming a cooling film on a surface of a hollow turbine blade (12) i.e. hollow guide vane, at a convex suction side. An incineration gas flow separation at the blade is passive-controlled by eddies produced by cooling air currents, where small quantities of coolants are discharged into the area of a high mach number of the blade from cooling air nozzles (13) with small diameter. The nozzles are bent under an angle in a transverse direction to a mainstream direction (16) of the incineration gas and under another angle diagonal to the surface of the blade. An independent claim is also included for an arrangement for cooling a film of a turbine blade.