METHOD OF MAKING GAS TURBINE ENGINE BLADE COMPRISING VERTEX WITH COMPLEX CAVITY Russian patent published in 2019 - IPC B22C9/10 

FIELD: machine building.

SUBSTANCE: invention relates to casting of gas turbine engine blade. Blade comprises a wall of the pressure trowel and a back wall separated from each other by the inner space of the blade, a vertex (S) with closing wall (29) connecting the trough and back walls in the area of the apex (S) with limiting the cavity shape. In wall (29) there are through holes (38, 39). When casting the blade, rod (28) defining the cavity shape is used, and alumina pins (31, 32) defining each through hole (38, 39). Then, stage of chemical etching of rod (28) and stage of chemical etching of aluminous pins (31, 32) for extraction of rod and pins after casting, and machining stage of closing wall (29) to produce raised shape or relief molds on bottom of cavity. Rod (18) is made with projections at the level of each through hole (38, 39) of the closing wall for (29) giving it after casting of nominal thickness D, which exceeds thickness of other walls of the blade, and thickness d, reduced at the level of each through hole (38, 39).

EFFECT: providing complex cavity of blade without complication of its casting process.

6 cl, 9 dwg