Turbofan engine with automatic bypass ratio regulating capacity

Abstract

The invention relates to the technical field of aerospace power, in particular to a turbofan engine with automatic bypass ratio regulating capacity. The technical scheme is that the turbofan engine with the automatic bypass ratio regulating capacity comprises a first valve, a fan, a speed reducer, a second valve, an air compressor, a combustion chamber, a high pressure turbine, a low pressure turbine, a third valve, a fourth valve and a fifth valve; the fan is connected with the low pressure turbine to form a low pressure rotor system through the speed reducer; the low pressure rotor system issupported on a first bearing, a second bearing, a third bearing and a sixth bearing; the air compressor is connected with the high pressure turbine to form a high pressure rotor system; the high pressure rotor system is supported on a fourth bearing and a fifth bearing; the first valve is mounted at the front end of a second bypass case; the second valve is mounted on an intermediate case; the third valve is mounted on a rear case; the fourth valve is mounted at the rear end of a first bypass case; and the fifth valve is mounted at the rear end of the second bypass case. The turbofan engine with the automatic bypass ratio regulating capacity is high in adaptive capacity, high in specific thrust, high in propulsive efficiency and low in oil consumption rate.

Description

technical field [0001] The invention relates to the technical field of aerodynamics, in particular to a turbofan engine with bypass ratio self-adjusting capability. Background technique [0002] Aeroengines are the "heart" of aircraft and the core components of large aircraft systems. With the continuous expansion of human beings in the fields of national defense, scientific research, and civil use, aircrafts, especially aeroengines, are required to perform multiple tasks, long range, high altitude, high speed, etc. All aspects have put forward new and higher requirements. Traditional conventional cycle engines mainly include turbojet engines and turbofan engines. Turbojet engines rely entirely on the high-temperature gas flow in the duct to generate thrust and are usually used as power for high-speed flight. However, turbojet engines have high fuel consumption and The propulsion efficiency is low; the turbofan engine generates thrust jointly by the external fan airflow and...

AI Technical Summary

Problems solved by technology

Traditional conventional cycle engines mainly include turbojet engines and turbofan engines. Turbojet engines rely entirely on the high-temperature gas flow in the duct to generate thrust and are usually used as power for high-speed flight. However, turbojet engines have high fuel consumption and The propulsion efficiency is low; the turbofan engine generates thrust jointly by the external fan airflow and the internal high-temperature gas flow, which has the advantages of high propulsion efficiency, low fuel consumption, good balance between thermal efficiency and propulsion efficiency, etc., but the large-diameter fan increases the The windward area makes the turbofan engine with a relatively large duct unsuitable for supersonic cruise flight

It can be seen that the current two conventional fixed-cycle engines have certain shortcomings and deficiencies to varying degrees, and it is difficult to adapt to the development requirements of future aircraft.

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