FIELD: engines and pumps.
SUBSTANCE: hollow blade of gas-turbine engine has inner cooling passage, open cavity located on free edge of blade and restricted with the bottom wall and side wall at least of one protrusion passing between the front edge and rear edge of blade and at least one cooling channel. The latter connects inner cooling passage to open cavity and is led out to the bottom of the above side wall of the protrusion. Side wall forms blunt angle exceeding 90° with the above bottom wall. In side wall there is groove in the place of outlet of the above cooling channel, which ends to upper edge of protrusion.
EFFECT: easy-to-manufacture blade with well-cooled protrusions provided on its end is designed.
11 cl, 4 dwg
