FIELD: double-flow turbojet engines.
SUBSTANCE: proposed cooling system of gas turbine of double-flow turbojet engine with additional compression of air in small-size fan contains space to take off secondary air flow from main combustion chamber, power diaphragm, set of vanes of nozzle assembly and disk deflectors. Inlet sections of central channels of nozzle assembly vanes are connected by air manifold with lips to take off air from outer loop. Outlet sections of said channels are connected with space to deliver air to central fan installed on shaft of high-pressure turbine.
EFFECT: improved specific parameters of double-flow turbojet engine.
1 dwg
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