FIELD: engines.
SUBSTANCE: combustion chamber for turbojet three-circuit engine with two high-pressure turbines includes a combustion combustion chamber and a heating chamber. In heating chamber there is heating element, high-temperature heat insulator and channel connecting heating chamber with combustion chamber. High-temperature insulator and guide vane are located inside said channel, and horizontal and vertical nozzles with electrodes for fuel ignition are arranged outside. Combustion chamber also has an air intake chamber accommodating a fairing and a channel having a stiffness rib outside, connecting the air intake chamber to the heating chamber, wherein a damper is located inside the above channel. In the heating chamber there is a screen which distributes air flow inside the heating chamber.
EFFECT: invention is aimed at increasing turbojet engine power and reducing fuel consumption during its operation, as well as enabling engine operation at high altitudes, where there is a lack of oxygen.
7 cl, 5 dwg
