Axial-flow turbine blade, especially axial-flow turbine rotor blade for gas turbine engines

Claim 1

An axial flow turbine blade having a leading edge, comprising a first cooling fluid flow channel (1) extending substantially radially in the blade for supplying a cooling fluid into the blade, a second cooling fluid flow channel (2) also extending substantially radially in the blade between said first channel (1) and said leading edge for cooling especially said leading edge, a plurality of impingement ducts (3), each duct having a first longitudinal axis and interconnecting said first channel (1) with said second channel (2) for supplying cooling fluid from said first channel (1) into said second channel (2) through said ducts (3), whereby cooling fluid is projected into said second channel, a plurality of elongated cooling pins (4) of heat conducting material extending through the blade substantially from said leading edge and into said second chamber (2), each of said cooling pins (4) having a second longitudinal axis extending in axial alignment with the respective first longitudinal axis, each of said cooling pins (4) further having a free end reaching into said second channel (2) in the direction of said first and second longitudinal axes so that cooling fluid from said ducts (3) is aimed to axially impinge on said free ends of said cooling pins (4) for causing a symmetrical spacial dispersion of the cooling fluid enabling the cooling fluid to contact all surface areas of said cooling pins and of said second channel for an improved cooling action, at least said second channel (2) having wall surfaces positioned for deflecting the spacially dispersed cooling fluid, and further duct means (6) extending out of said second channel (2) for discharging cooling fluid out of said blade.