TURBOJET ENGINE WITH HIGH BYPASS RATIO Russian patent published in 2010 - IPC F02K3/04 

FIELD: engines and pump.

SUBSTANCE: proposed turbojet engine comprises at least one compressor, combustion chamber and fan arranged upstream of the compressor and driven by turbine, and device arranged downstream of the fan to make circular chambers for bypass stream that flows around housings of compressor, combustion chamber and turbine. Said devices comprise, in fact, fixed cylindrical case surrounding housings of compressor, combustion chamber and turbine to make cylindrical inner surface directing bypass stream. Said case is made as a single rigid element and has its front edge jointed to structural casing, for example to intermediate casing, and its rear edge jointed to exhaust nozzle casing, thus, performing load distribution between intermediate and exhaust nozzle casings. Casing part, downstream of jet flow, comprises pivoted shutters and shutters drives to move them between the position of rest whereat they are located on one lined with the casing and operating position whereat they extend from the casing to obstruct bypass flow.

EFFECT: reduced deformation of housing caused by bending strain and lower secondary flow thrust force in landing.

5 cl, 4 dwg