GAS TURBINE ENGINE BLADE EQUIPPED WITH A COOLING SYSTEM AND METHOD OF MANUFACTURING SUCH BLADE BY CASTING USING SMELTED WAX MODELS Russian patent published in 2023 - IPC F01D5/18 B22C7/02 

FIELD: aircraft.

SUBSTANCE: invention relates to a blade (20) of a gas turbine engine comprising a feather (21) located along the radial axis, and the first cooling system (28) located inside the feather, whereas the first cooling system (28) comprises the first cavity (34) and the second cavity (35) located at the outlet of the first cavity in the direction of passage of the cooling fluid in the feather, whereas the first and second cavities are located radially inside the feather and are at least partially separated by the first radial partition (36), the radially inner free end (37) of which is at least partially defines the first passage (40) for the cooling fluid connecting the first and second cavities. According to the invention, the radially inner free end (37) is expanded and has an overall cross-section essentially in the form of a keyhole.

EFFECT: reduction in local mechanical stresses associated with the implementation of the cooling system is achieved, and at the same time the invention makes it possible to avoid large structural changes in the blade.

11 cl, 6 dwg