COOLED BLADE OF GAS TURBINE Russian patent published in 2020 - IPC F01D5/18 

FIELD: turbines or turbomachines.

SUBSTANCE: invention relates to turbine construction and can be used in high-temperature gas turbines, particularly in cooled blades. Cooled blade of the gas turbine includes a hollow feather consisting of a blade wall with holes and at least one inner cavity equipped with a distributing header and a deflector with holes. Deflector with holes forms with inner wall of blade body deflector cavity communicated with dispensing header by means of deflector holes, and with gas-air channel of engine by means of holes in wall of blade body. Deflector openings are diverging towards the inner wall of the blade body, the total input area of the deflector expanding holes is smaller than the total area of the holes in the blade wall. In places of expanding holes on inner surface of deflector there are made beads. Deflector cavity is divided by partitions into chambers. Ratio of total inlet area of deflector expanding holes with total area of holes on blade back is selected from condition of required drop for each of chambers.

EFFECT: invention allows increasing service life of turbine blade due to overall improvement of cooling efficiency.

3 cl, 3 dwg