TURBOJET ENGINE WITH CONTROLLABLE BY-PASS RATIO Russian patent published in 2003 - IPC

FIELD: mechanical engineering; turbojet engines. SUBSTANCE: proposed turbojet engine with controllable by-pass ratio contains high-and low-pressure compressors, combustion chamber, high-and low-pressure turbines, and behindthe-turbine fairing. Behind-the- turbine fairing has outer and inner walls, with truncated cone ring channel in between. Each wall in upper part of cone has bottom step with central hole coaxial with longitudinal axis of engine. Space of bypass air channel of second circuit is connected with space of ring channel through hollow streamlined radial ribs installed over circumference behind lowpressure turbine. Central holes in bottom steps come in contact with by inner surfaces with outer surface of air bypass valve of the same diameter. Said valve is made in form of cylindrical shutter. Cylindrical shutter is provided with front and rear shells and is connected by said shells with piston rod of drive pneumatic cylinder coaxial with longitudinal axis of engine and movable along said axis. Inner wall of behind-the-turbine fairing is provided with bottom coupled by one side with inner surface of inner wall of behind-the-turbine fairing, and by other side, with flange of drive pneumatic cylinder. Other flange of pneumatic cylinder is connected with housing of turbine rear support. EFFECT: provision of high performance at higher power and maximum duties at high economy of fuel at subsonic cruise conditions. 2 cl, 3 dwg