COOLED BLADE OF ROTOR FOR INDUSTRIAL GAS-TURBINE PLANT (VERSIONS) Russian patent published in 2006 - IPC F01D5/18 

FIELD: mechanical engineering; gas-turbine plants.

SUBSTANCE: proposed cooled blade of rotor for industrial gas-turbine plant has front and rear cooling air loops. Feather of blade has back and pressure surface connected in area of leading edge and in area of trailing edge to form space through which at least part of cooling air loops pass and which accommodates first, front loop channel and second, rear loop channel. Each channel is provided with section in which flow is directed upwards and section in which flow is directed downwards. Each loop channel has three-connected sections displaced relatively in longitudinal direction so that cooling air flow getting into corresponding channel passes successively through indicated sections starting from middle area of feather with discharge of cooling air from third section. Rotor blade contains number of band projections on side walls of back and feather pressure surface. Band projections of each set are displaced relatively in longitudinal direction at preset pitch and are spatially separated and are mainly parallel to adjacent band projections of the same set on other wall. Each band projection is located inside one of sections of corresponding channel and is characterized by height of projection measured relative to adjacent part of side wall and ratio of height of projection to pitch of projections for said section. According to one design version, band projections have constant height and constant pitch over entire section of corresponding channels for majority of channel sections, except for sections close to areas of leading and trailing edges of blade feather.

EFFECT: reduced cost of manufacture of blade.

18 cl, 10 dwg