AIR COOLING PATH OF BLADE OF NOZZLE APPARATUS OF HIGH PRESSURE TURBINE OF A GAS TURBINE ENGINE (VERSIONS) Russian patent published in 2019 - IPC F01D5/18 

FIELD: machine building.

SUBSTANCE: air cooling path of the nozzle blade is made three-channel. Nozzle blade is made hollow, with aerodynamic profile and is equipped with radial partition separating internal volume of feather on front and rear cavities equipped with deflectors. Inlet section of first channel of the path includes cavity of large shelf interconnected with front cavity and inlet edge of every blade of unit for removal of excessive heat of blade feather. Inlet section of the second channel of the path is interconnected through the external ring with the back cavity of the blade with the outlet of heated by heat removal of air into flowing part of the high pressure turbine. Inlet section of the third channel of the cooling path of the blade is made in form of a common slit in the wall of the small flange of the unit communicated with the front cavity of each blade of the unit for removal of excess heat from the front part of the walls of the back and trough of blade feather. Deflector of front cavity is made in form of plate open to input edge, equipped with seven rows of holes with axes, different-inclined to working medium flow, and diagonally divides the back cavity with the front cavity for opposite cooling of walls of the diagonal parts of the cavity by air from the first and third channels of the path. Back and trough in front cavity are equipped with two and four rows of holes. Rear cavity of blade is equipped with deflector provided with perforated holes to vortex matrix and intended for cooling with smaller part of flow of rear part of blade and larger part of cooling flow of rotor of high pressure turbine.

EFFECT: invention is aimed at improvement of cooling efficiency of blades and resource of a nozzle mechanism of a high pressure turbine.

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