GAS TURBINE GUIDE VANE COOLED BLADE Russian patent published in 2018 - IPC F01D5/18 F01D9/02 

FIELD: motors and pumps.

SUBSTANCE: gas turbine guide vane cooled blade comprises hollow airfoil 1 made in the form of front cavity 2 and rear cavity 3 separated by the radial partition 4. In the front cavity 2 the front deflector 5 is installed, fixed by the first transverse ribs 6 on the hollow airfoil 1 walls on the backrest and trough side. In the rear cavity 3 the rear deflector 7 is installed fixed by the second transverse ribs 8 on the hollow airfoil 1 walls on the backrest and trough side. In the front deflector 5 the front cavity 9 leading edge and walls jet cooling holes are made. In the rear deflector 7 the rear cavity 10 walls jet cooling holes are made. In the front cavity 2, in the hollow airfoil 1 walls, the film cooling holes 11 are made. Second transverse ribs 8 are made shortened and behind them, on the hollow airfoil 1 walls, on the backrest and the trough side, the shading fins 12 are mounted so, that the rear deflector 7 is fixed by their ends. At that, the shading fins 12 mounting portion length is selected from 0.6b to 0.7b, where b is the hollow airfoil 1 cross section chord. Each shading fin 12 is located in front of the rear cavity 10 walls corresponding jet cooling hole from the radial partition 4 side and is formed as the ring sector, which center coincides with the of the rear cavity 10 walls jet cooling holes center, and the closest to them shading fin 12 wall radius R is selected from 1.0d to 1.5d, where d is the rear cavity 10 walls jet cooling hole diameter. At that, the shading fins 12 width h in the radial direction is selected in the range of 1.05d to 1.10d. In the output edge 13 slot channel, the turbulizer pins 14 are installed.

EFFECT: invention is aimed at increase in the gas turbine guide vanes cooling efficiency.

1 cl, 6 dwg