COOLABLE GAS TURBINE BLADE Russian patent published in 2021 - IPC F01D5/18 

FIELD: power plant engineering.

SUBSTANCE: coolable gas turbine blade is comprised of a blade airfoil with a through cooling channel made in the gas turbine blade. An emission layer is applied onto the inner surface of the blade airfoil, wherein an element - anode - is located at a distance from the emission layer, consisting of an electron sensing layer facing the emission layer and a heat-resistant anode substrate. The distance between any point of the emission layer and any point of the electron sensing layer is greater than zero for any combination of mechanical and thermal loads applied to the blade airfoil during operation. A cooling channel is formed within the heat-resistant anode substrate, and the cavity formed by the emission layer and the electron sensing layer is vacuumized and sealed. Distancing elements made of heat-resistant electrically non-conductive material are located in this cavity, the heat-resistant anode substrate is in electrical contact with the blade airfoil. An easily ionizable chemical element is located within the cavity formed by the emission layer and the electron sensing layer, wherein the amount of the element is determined by the vapor pressure rate in the cavity formed by the emission layer and the electron sensing layer providing a defined density of emission current and thermal emission cooling at given operating temperatures of the emission layer.

EFFECT: provided is thermal emission cooling of the blade.

5 cl, 1 dwg