COOLING SYSTEM OF GAS TURBINE BLADES Russian patent published in 2008 - IPC F01D5/18 

FIELD: mechanical engineering: gas turbines.

SUBSTANCE: proposed cooling system of gas turbine blades contains assembly of channels formed by semiribs arranged on opposite walls of inner surface of blade-suction face of blade and its pressure surface-tilted to axis of feather from side of suction face and pressure surface in opposite directions and contacting by end faces in places of intersection. Semiribs are made curvilinear, they form intersecting channels with alternating diffuser-contraction sections and their arrangement is chosen to provided coincidence of diffuser of crossed channel with contraction of crossing channel. Inner surface of suction face and pressure surface of blade are made wavy. Cavity on wall of inner surface coincides with widening of channel, and projection on wall coincides with narrowing of channel, thus forming spatial diffuser-contraction sections and their arrangement is chosen to provide coincidence of diffuser section with contraction sections in places of intersection with curvilinear channels.

EFFECT: improved efficiency of cooling, increased service life of blade.

2 cl, 6 dwg