HOLLOW BLADE OF TURBINE ROTOR FOR GAS TURBINE ENGINE Russian patent published in 2009 - IPC F01D5/18 F01D5/20 

FIELD: engines and pumps.

SUBSTANCE: hollow blade of rotor for turbine of gas turbine engine comprises internal cooling passage, open cavity, encircling flange and cooling channels that connect internal cooling passage to external surface of internal wall. Open cavity is installed on free end of blade and is limited with bottom wall that passes along the whole end of blade. Encircling flange passes between front edge and back edge of blade along external and internal walls of blade. Cooling channels are inclined relative to this internal wall of blade with the possibility of their opening on external surface of internal wall in direction of encircling flange top. Encircling flange creates thin wall. Material thickening is provided between encircling flange and bottom wall of cavity along at least part of blade internal wall. Surface of encircling flange that faces cavity side is mostly flat, as a result encircling flange expands in its basis in area of adjacency to bottom wall with the possibility of cooling channels opening in close proximity from encircling flange top without reduction of blade end mechanical strength.

EFFECT: increase of blade reliability without reduction of its aerodynamic characteristics.

6 cl, 5 dwg