TURBINE NOZZLE BLADE, TURBINE AND AERODYNAMIC PORTION OF TURBINE NOZZLE BLADE Russian patent published in 2017 - IPC F01D5/14 F01D9/02 

FIELD: machine engineering.

SUBSTANCE: nozzle blade of the last turbine stage comprises an aerodynamic portion extending from the platform to the end portion of the blade and including front and rear edges, a side of reduced and increased pressure, as well as a flow restriction partition. The flow restriction partition extends along the aerodynamic portion extending outward from the leading edge to the trailing edge of said aerodynamic portion and is closer to the end portion, from the platform, along the side of reduced pressure. The partition projects outward from the leading edge and has substantially a V-shaped or U-shaped configuration. The partition smoothly transitions into the front edge and the rear edge and extends outward towards the middle thereof to form a fillet in the middle. Another invention of the group relates to a turbine comprising working blades and said nozzle blades.

EFFECT: reduction of loss on the blade aerodynamic portion by reducing the migration of the flow in the radial direction and reducing its turbulence.

9 cl, 10 dwg