Variable cycle high bypass ratio turbofan engine

Abstract

The present invention provides a turbofan engine with variable cycle and high bypass ratio, which comprises a plurality of turbine guide vanes, the turbine guide vanes include blade parts of a fixed structure, and a plurality of movable blade segments, and the plurality of movable blades The segment is connected by a hinge and forms a hollow area with the blade part of the fixed structure; by changing the movable blade segment to rotate to the inside or outside of the turbine guide vane, the distance between the two turbine guide vanes can be adjusted. Throat area. Under the condition of high bypass ratio, the invention reduces the flow area of ​​the guide vane of the turbine and changes the installation angle of the guide vane of the supercharging stage, which can achieve the effect of anti-breathing of the supercharging stage; avoids the energy loss caused by the deflation after the supercharging stage, Realize the all-envelope supercharging stage without blow-off; the connotation can pass through more air, which can provide a greater margin for the development of engine thrust.

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. Such as 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 propulsio...

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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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