GAS TURBINE ENGINE BLADE EQUIPPED WITH OPTIMIZED COOLING SYSTEM Russian patent published in 2024 - IPC F01D5/18 F02C7/12 

FIELD: machine building.

SUBSTANCE: blade (20) of a gas turbine engine, comprising: pen (21) with a wall of a pressure trough and a back wall, connected at the inlet by front edge (26) and at the outlet by trailing edge (27), cooling system (28) which contains an internal cavity located inside the pen, and a plurality of outlet holes, each substantially along a longitudinal axis X, wherein each outlet communicates with the cavity and is located nearby the rear edge, and calibration device (33) located in the cavity and having calibration channels (34) arranged substantially opposite the outlet holes. According to the invention, each calibration channel (34) has a cross-section substantially perpendicular to the longitudinal axis and having an oval shape.

EFFECT: reduction of mechanical stresses acting, in particular, on passages of the cooling air calibration device, and at the same time it should allow avoiding large structural changes of the device itself and the blade.

10 cl, 6 dwg