COOLED TURBINE Russian patent published in 2015 - IPC F02C7/12 F01D5/18 

FIELD: machine building.

SUBSTANCE: cooled turbine of aircraft gas turbine engine contains an impeller with working vanes, installed on it, two cooling loops, series connected with air channels in the impeller, with independent ring diffusion channels, nozzle vanes and a heat exchanger. Ring diffusion channels are formed on the impellor surface and connected with nozzle vortex devices and transit air ducts upstream. Every nozzle blade is composed of a structural element confined by top and bottom shrouds and space between them, confined by blade root convex and concave walls in the form of leading edge and distribution chamber arranged along blade root axis. Leading edge distribution manifold inlet is communicated with combustion chamber air chamber while its outlet communicates via perforations with turbine flow section. Heat exchanger inlet communicates with air chamber of combustion chamber and its outlet communicates with air manifold and distribution chamber. The cooled turbine incorporates distribution manifold for cooling air, cooling deflector and two transit deflectors arranged in said distribution chamber in its axis with clearance between each other and relative to blade root concave and convex wall to make cooling channels along said walls. Cooling deflector has perforated bores on its two opposite walls and arranged in distribution chamber at distribution manifold wall and gas its perforated wall directed to nozzle blades root concave and convex walls. Blade top and bottom shrouds have air ducts their inlets being communicated with turbine flow section. The distribution manifold for cooling air is connected with an air source, with the air duct inlet of the top shroud and the inlet of the cooling baffle plate. The air duct inlet in the bottom shroud is connected with the outlet of the cooling baffle plate. Air manifold is connected with inlet of transit deflectors, and distribution chamber communicates with the turbine flow section.

EFFECT: invention allows to improve efficiency of the turbine cooling, and also to increase its profitability.

7 cl, 5 dwg