COOLING TURBINE BLADE (VERSIONS) AND METHOD OF TURBINE BLADE COOLING Russian patent published in 2017 - IPC F01D5/22 F01D5/18 

FIELD: machine engineering.

SUBSTANCE: cooling turbine blade contains the shank end for attaching the cooled blade to the turbine rotor, the aerodynamic profile, the end band and one or more central cooling channels, limited by the aerodynamic profile. The aerodynamic profile extends along the radial axis from the shank and limits one rear cooling channel, that extends radially through the aerodynamic profile proximally to the rear edge part of the aerodynamic profile. The rear channel is located within the distance from the rear edge part, which is less than 25% of the aerodynamic profile chord length. The end band is located radially on the outer end of the aerodynamic profile passes in the radial direction from the aerodynamic profile and limits inside itself the over-pressure central cavity and the over-pressure peripheral cavity. The aerodynamic profile limits one rear cooling inlet port, designed for passing one rear cooling fluid flow to the specified one rear cooling channel of the aerodynamic profile, as well as limits one rear exhaust outlet, designed to release one rear cooling fluid flow from the rear cooling channel to the over-pressure peripheral cavity. The end band limits at least one peripheral cavity hole, designed for one rear cooling fluid flow release from the peripheral cavity. Each of the central cooling channels passes radially through the central part of the aerodynamic profile. The aerodynamic profile limits the central cooling inlet port, designed for the central cooling fluid flow supply to one or more central cooling channels, and at least one central cooling outlet designed for the central cooling fluid flow release from one or several central cooling channels to the central cavity. The rear cooling channel and one or more central cooling channels provide the rear flow direction and the central flow of the cooling fluid to different cavities. At that the specified one or several central cooling channels are located within the distance from the aerodynamic profile center, which is less than 25% of the aerodynamic profile chord length.

EFFECT: improvement of the aerodynamic profile rear edge cooling and the end band.

16 cl, 6 dwg