Large-bypass-ratio turbofan engine of vane tip jet driven fan

Abstract

The invention provides a large-bypass-ratio turbofan engine of a vane tip jet driven fan and a designing method. A large-bypass-ratio fan rotor driven by vane tip jet is arranged on an external duct portion and comprises an additional ducted fan rotor, a vane tip driving portion and a rotary additional duct rotor hub; an additional duct stator is arranged on a downstream portion of the additional ducted fan rotor and a downstream portion of a vane tip driving portion; and air is led to vane tips of the additional ducted fan rotor from an external duct of the original double-rotor turbofan engine by an air leading channel. The large-bypass-ratio turbofan engine of the vane tip jet driven fan has the advantages that the bypass ratio is increased, torque transmission is implemented by an aerodynamic force, and the problem that the rotation speed of the fan is not matched with that of the driving component; the peripheral speed is greatly improved, and the improvement potential of the bypass ratio is high; compared with the prior art, the large-bypass-ratio turbofan engine is simple in structure; and the large-bypass-ratio turbofan engine is improved on the basis of the existing double-rotor turbofan engine, development risk and the development cost of the large-bypass-ratio turbofan engine of the vane tip jet driven fan are reduced, and the development cycle is shortened.

Description

technical field [0001] The invention relates to a turbofan engine with a large bypass ratio that drives a fan with blade tip jet, and belongs to the technical field of the new concept turbofan engine. Background technique [0002] Higher thrust-to-weight ratio and lower fuel consumption have always been the unremitting pursuit of aero-engines, and turbofan engines, with their high thrust-to-weight ratio and low fuel consumption, have gradually become the mainstream of aero-engine design and are the core of aero-engine fields in various countries. technology. Bypass ratio is one of the core parameters of turbofan engine design. Turbofan engines with small bypass ratios have high maneuverability and are usually used in the military field; turbofan engines with large bypass ratios have low fuel consumption and are usually used in civilian applications. field. The civilian models of major aero-engine companies all take continuous improvement of the bypass ratio of turbofan eng...

AI Technical Summary

Problems solved by technology

But its shortcomings are also very obvious: the fan and turbine work at a high temperature, and it is difficult to realize integrated processing and manufacturing, and a complex sealing structure is required to avoid gas leakage; secondly, in the conventional front fan scheme, part of the gas is used internally, which can increase the core machine pressure ratio , to improve the economy of the core machine, but for the rear fan scheme, the pressurized gas is directly discharged, which cannot be used by the core machine

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