TURBINE COOLED ROTOR BLADE Russian patent published in 2011 - IPC F01D5/18 

FIELD: engines and pumps.

SUBSTANCE: cooled turbine rotor blade for stationary gas turbine with flow axial passing is performed with attachment area from which to blade tip there goes carrying surface profile formed by blade wall located at suction side and blade wall located at pressure side. Carrying surface profile contains one front edge and one rear edge with located inside carrying surface profile next to each other cooling channels that are, at least, partially separated from one another by rib that connects blade wall located at pressure side to blade wall connected to suction side and runs from attachment area to blade tip, and with head wall that limits cooling channels at blade tip. At least one of the ribs, at reviewing from attachment area towards tip area, has in fact unchangeable thickness with formation of sharp-angled area in longitudinal section of cooling channel. This rib is curved at blade tip area towards the front or rear edge. There provided is, at least, one hole located in distortion that connects two neighbouring cooling channels and through which part of the cooling agent flow of cooling channel neighbouring the angled area can overflow to cooling channel sharp-angled area.

EFFECT: increase of blade service life.

11 cl, 1 dwg