TURBOJET ENGINE TURBINE COOLING SYSTEM Russian patent published in 2003 - IPC

FIELD: turbojet engines. SUBSTANCE: proposed cooling system of turbojet engine has the following units installed in series: manifold with controlled valves at outlet communicating by inlet with air space of combustion chamber, multichannel air duct passing through inner spaces of nozzle blades, swirling nozzle assembly and working wheel cooling channels. Cooling system of double flow turbojet engine incorporates air-to-air heat exchanger located in air duct of outer loop. Manifold communicates with air space of combustion chamber through cooled channels of heat exchanger. Additional manifold is placed between manifold outlet and multichannel air duct. Each channel of air duct is formed by deflector installed in nozzle blade along its inner surface. Outlet channel of swirling nozzle assembly is turned in direction of rotation of working wheel, middle line of said wheel forming angle of 60^°-85^° with longitudinal axis of engine. EFFECT: reduced temperature of turbine working wheel with resulting decrease of radial clearance between stator and working wheel. 3 cl, 5 dwg