COOLED BLADE OF GAS TURBINE Russian patent published in 2019 - IPC F01D5/18 

FIELD: machine building.

SUBSTANCE: cooled gas turbine blade contains a hollow feather with an inlet and an outlet edges, a lock part and an end wall. In the hollow feather a partition is installed. Between the input edge wall and the partition there is an input edge cooling channel, and between the end wall and the partition an axial channel is located. In the peripheral part of the output edge slit channel is located. In the middle part of the hollow feather the first, the second and the third radial partitions are installed, by which the first, the second and the third radial channels are formed accordingly. Distributing holes are made in the third radial partition. Behind the third radial partition wall in the output edge slot channel the matrix of coplanar channels is installed. In the lock part the nozzle is installed. Ribs-intensifiers are installed on walls of cooling channel of inlet edge, axial, first, second and third radial channels. In the cooling channel of the inlet edge a wavy partition with holes is installed. Holes in wavy partition are made directly at inner surface of inlet edge wall. Pitch of the holes is equal to the step of the wave of the wavy partition and is (1.5–2.2) h, where h is the height of the wave of the wavy partition wall at the section of its connection with the partition. Holes are located in the sections of minimum narrowing of the first and the second adjacent channels formed by the wavy partition.

EFFECT: invention is aimed at improvement of cooling efficiency of the inlet edge.

1 cl, 4 dwg