GAS-TURBINE DISK COOLING SYSTEM Russian patent published in 2006 - IPC F01D5/08 

FIELD: mechanical engineering; gas turbines.

SUBSTANCE: in proposed cooling system of gas-turbine disk containing fixed guide vane assembly for preliminary swirling of cooling air, screen with centripetal blades on inner surface secured on disk and forming ring space together with disk surface communicating by input holes with guide vane assembly, and by output holes with through holes in disk at output of which centrifugal bladed device is arranged whose blades are installed at angle of 20-35° opposite to direction of disk rotation heat insulating screen arranged from side of disk opposite to centripetal blades and forming with the latter a channel to pass cooling air. Design peculiarity is than diaphragm with swirl pipe is provided which forms, owing to power division of air flow, a cold space communicating through air distributing chamber formed by wall of fixed guide vane assembly, and diaphragm, with fixed guide vane assembly and hot space connected with gas duct of turbine.

EFFECT: provision of effective and uniform cooling of gas-turbine disk, reduced temperature differentials in disk and fatigue stresses.

2 dwg