BLADED COOLING BY HELICAL RAMP, CASCADE IMPACT AND BY BRIDGE SYSTEM IN A DOUBLE SKIN

摘要

The turbine blade consists of a hollow aerodynamic surface extending radially between its foot and tip, having leading and trailing edges (5,6) and concave (7) and convex (8) lateral surfaces. The interior of the blade is fed with cooling air through its foot. The blade has two radial partitions (9,10) which connect its lateral walls and divide its interior cavity into forward (11), intermediate (12) and rear sections. The forward and intermediate sections are fed with air through an inlet at the foot of the blade, the air being discharged through outlets at its head. The rear section is fed with air through a separator inlet at the foot of the blade, the air passing out through slits (19) in the blade's trailing edge. In addition, the forward section of the blade cavity has a spiral channel for the air flow, and the intermediate section has a liner (40) with perforated sides set at a distance from the blade side walls to provide impact cooling. The rear section has an additional partition, dividing it into two linked chambers (15,16).