TURBOFAN GAS TURBINE ENGINE WITH ADJUSTABLE FAN OUTLET GUIDE VANES (VERSIONS) Russian patent published in 2011 - IPC F02K3/06 

FIELD: engines and pumps.

SUBSTANCE: turbofan gas turbine engine includes section of the front fan, which contains at least one row of fan rotor vanes located in circumferential direction and being the front ones in longitudinal direction; engine of the main circuit, which is located behind and downstream of section of the front fan; bypass channel of fans and exhaust channel. Engine of the main circuit includes in-series downstream located driven fan, compressor, combustion chamber and high pressure turbine connected with possibility of actuator to compressor by means of shaft of engine of the main circuit. Bypass channel of fans is located downstream of section of the front fan and is located radially on the outer side of engine of the main circuit. Radially, external inlet of bypass channel of fans is located in longitudinal direction between section of front fan and driven fan of the main circuit. Exhaust channel is located downstream of engine of the main circuit and is interconnected with it via fluid medium. Outlet of bypass channel of fans is located in longitudinal direction behind and downstream of radial external inlet. Section of front fan has single stage of adjustable fan guide vanes. Fan guide vanes are adjustable fan outlet guide vanes and are located downstream of the front rotor blades of fan and near them.

EFFECT: enlarging operating ranges of engine without flow choking, reducing the weight and front surface at the engine fan inlet.

9 cl, 6 dwg