AIRCRAFT GAS-TURBINE ENGINE BEARING SUPPORT COOLING SYSTEM Russian patent published in 2003 - IPC

FIELD: aviation industry; aircraft engines. SUBSTANCE: proposed system is designed for cooling bearing supports of aircraft gas-turbine engine. System contains screen installed under combustion chamber and consisting of three coaxially arranged shells forming inner and outer channels to pass cooling air. Outer channel communicates with outlet of axial-flow multistage compressor, and inner channel is connected to intermediate stage of compressor. Outer and inner shells forming outer channel are provided with zigzags in outlet part arranged opposite to each other, with projection towards combustion chamber. In central parts, shells are interconnected by partition with holes to pass cooling air. EFFECT: provision of effective cooling of bearing supports owing to high temperature of cooling air. 2 cl, 1 dwg