HIGH PRESSURE NOZZLE VANE BLADE COMPRISING INSERT WITH VARIABLE GEOMETRY Russian patent published in 2019 - IPC F01D9/04 F01D5/18 

FIELD: machine building.

SUBSTANCE: blade (10) of gas turbine engine (1) nozzle assembly (8) comprises feather (12) comprising trough wall (16) and back wall (14), and insert (20) located between trough wall (16) and wall (14) of the backrest. Insert (20) comprises closed wall (22) having outer surface (24) located opposite wall (16) of trough and back wall (14), and inner surface (26) opposite to outer surface (24). Outer surface (24) of closed wall (22) and opposite wall of blade (12) are separated by air gap (30). In closed wall (22) there is a row of through holes (28) passing between outer surface (24) and inner surface (26). In closed wall (22) there is a row of recesses (25) extending to outer surface (24). Through holes (28) are made in recesses (25). Heights (h) of exposure between said through holes (28) and wall (16) of back pressure or wall (14) of the back exceed the value of air gap (30). Recesses (25) are mainly hemispherical, ovoid or drop-shaped.

EFFECT: invention is aimed at optimization of cooling, to reduce amount of cooling air, limitation of thermomechanical damages.

9 cl, 5 dwg