| 摘要 |
FIELD: engines.SUBSTANCE: technical result is achieved due to that turbofan aircraft engine with external fan module comprises a fan, a gas generator with turbine driving fan, power fan drive turbine selection unit connected to shaft. Remote fan modules are connected by drives to power take-off unit, motor and remote fan units with adjustable nozzles integrated with aircraft. Fan motor further comprises inlet guide vanes, which is designed as a stationary blade row outer and inner rotary driven blade row. Between fan motor and gas generator has an annular air supply window with a shutter. Adjustable engine nozzle is in form of an adjustable jet nozzle outdoor kennel and nozzle tapered inner loop. Method of operating engine is input to motor that is supplied air compressed by fan and fan when air flow is separated between inner and outer contours of engine. Airflow internal circuit and fuel is supplied to combustion chamber and inner contour of gasifier is burned fuel. Combustion products of gas generator after inner loop and outer loop air flow is directed to nozzle, and worked out on the fan turbine power is used to drive motor fan and fan extension modules. Engine and remote fan units create reactive thrust. In cruising mode, adjust area of annular window between outer and inner contours of engine and position of rotary blades of inner rim of fan inlet guide apparatus and forming an inner annular air flow to input of gasifier inner contour with a smaller air flow through gasifier. Outer annular stream of air fed at a greater rate in outer contour of motor, which increases degree of engine bypass. Gaseous combustion products are fed to a jet nozzle tapering inner contour, and air from outer contour of engine is directed to an adjustable nozzle, thus reducing fuel supply in accordance with increasing degree of engine bypass ratio.EFFECT: invention can improve coordination of take-off and cruise modes of engine operation and improve fuel efficiency of civil and transport aircraft engines.2 cl, 4 dwg |
