Variable-cycle large-bypass-ratio turbofan engine

Abstract

The invention provides a variable-cycle large-bypass-ratio turbofan engine. The variable-cycle large-bypass-ratio turbofan engine comprises a plurality of turbine guide vanes. The turbine guide vanescomprise blade parts with fixed structures and a plurality of movable blade segments, wherein the movable blade segments are connected through hinges, and a hollow area is formed by the movable bladesegments and the blade parts with the fixed structures. The movable blade segments are changed to rotate towards the interiors or exteriors of the turbine guide vanes, so that the throat area betweentwo turbine guide vanes is adjusted. Under the condition of the high bypass ratio, the flow areas of the turbine guide vanes are reduced, the booster stage guide vane installing angle is changed, andthe booster stage anti-surge effect can be achieved; the energy loss caused by gas discharge after the booster stage is avoided, and non-gas discharge of the full-envelope booster stage is realized; more air can pass through an inner bypass so as to provide larger margin for the development of the thrust of the engine.

Description

technical field [0001] The invention relates to the field of aero-engines, in particular to a variable-cycle turbofan engine with a large bypass ratio. Background technique [0002] figure 1 It is a structural schematic diagram of a dual-shaft direct-drive turbofan engine with a large bypass ratio in the prior art. like figure 1 As shown, a general dual-shaft direct-drive high bypass ratio turbofan engine will sequentially pass through the fan that initially compresses the airflow, the booster stage that further compresses the internal airflow, and the high-pressure compressor in order to heat the airflow according to the axial flow direction of the airflow. The combustion chamber, the high-pressure turbine and the low-pressure turbine that respectively drive the high-pressure compressor and the fan (including the booster stage), and the nozzle that allows the high-temperature and high-pressure air to be ejected at high speed. [0003] In order to improve the propulsion e...

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Problems solved by technology

[0008] The technical problem to be solved by the present invention is to overcome the high temperature of the outlet of the combustion chamber, the limited development of the thrust margin and the limited life of the engine under the ground take-off and climb state of the turbofan engine in the prior art, and the variable bypass ratio also brings In order to overcome defects such as the working mismatch of the supercharging stage, a variable cycle turbofan engine with a large bypass ratio is provided, which combines the variable turbine guide vane and the adjustable guide vane of the supercharging stage to coordinate operation, and changes the bypass ratio of the aeroengine in real time

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