AIR-COOLED TYPE PROFILE STRUCTURE OF GAS-TURBINE ENGINE

摘要

PURPOSE: To improve the cooling efficiency at its front edge without damaging the mechanical strength of the front edge, in a front edge cooling structure combined the film cooling of the blade type front edge of the turbine of a gas turbine engine with an impingement cooling. CONSTITUTION: In the air cooling type blade structure of the turbine blade of a gas turbine engine, the thing with a helical shape and rectangular cross-section is used as the cooling hole 40 of a blade front edge 18 and the cooled air blown off from the cooled air blow outlet of the helical cooling hole 40, while forming a blowout direction by a small elevation angle for the outer surface of the front edge 18, is streamed along the surface. These plural helical cooling holes 40 are separated mutually and arranged in parallel in the longitudinal direction of the blade 12 from the root 14 of the turbine blade 10 across the tip 16.