COOLED DOWN BLADE OF THE GAS TURBINE Russian patent published in 2018 - IPC F01D5/18 

FIELD: engines and pumps.

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 output edge a slotted channel is located. At that, the first and third radial channels are diverting, the second and fourth radial channels are supply channels. Second and fourth radial channels are made tapering with a minimum area in the blade peripheral section. First channel expansion is directly proportional to the second channel narrowing, and the third channel expansion is directly proportional to the fourth channel narrowing in each cross-section by the height of the hollow feather. In the hollow feather directing and shading fins, and fins-intensifiers are also installed. In the output edge slotted channel behind the jumpers a coplanar channels matrix is installed. At the end of the blade lock a jet nozzle is installed.

EFFECT: invention is aimed at increasing the life of working blades and, accordingly, the gas turbine as a whole.

4 cl, 4 dwg