Engine airflow passage structure and fanjet

Abstract

The invention discloses an engine airflow passage structure and a fanjet and relates to the technical field of aircraft engines, solving the technical problem of low erodynamic efficiency of engines due to high internal flow losses of transitional sections in the prior art. The engine airflow passage structure comprises a hub, a cartridge, turbine blades, a supporting plate and a fairing device. The turbine blades are fixedly connected with the hub, and tip clearances are reserved between tips of the turbine blades and the inner wall of the cartridge. The supporting plate is disposed between the hub and the cartridge. The fairing device is fixedly arranged on the cartridge between the turbine blades and the supporting plate, and is used for fairing airflow flowing from the tip clearances to the supporting plate and preventing the airflow from flow separation around the supporting plate. The fanjet comprises a low-pressure turbine, a high-pressure turbine and the engine airflow passage structure. With the engine airflow passage structure and the fanjet, the internal flow looses of the transitional sections can be reduced and the erodynamic efficiency of aircraft engines can be improved.

Description

technical field [0001] The invention relates to the technical field of aeroengines, in particular to an engine air flow channel structure and a turbofan engine provided with the engine air flow channel structure. Background technique [0002] For a long time to come, turbofan engines with high bypass ratios will still be the best choice for powering large airliners. The thrust generated by the fan of a turbofan engine with a large bypass ratio accounts for 60% to 80% of the total thrust of the engine. Therefore, keeping the low-pressure turbine driving the fan working at a high efficiency state is of great importance for a civil engine with a large bypass ratio. Critical. [0003] At present, the bypass ratio of civilian engines has been developed to 9~10, and the diameter of the fan exceeds 3 meters. Under such conditions, on the one hand, the high-pressure components of the engine still work at a relatively high speed (10000r / min~15000r / min), which requires the diameter ...

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Problems solved by technology

[0007] The purpose of the present invention is to propose an air flow passage structure of an engine and a turbofan engine provided with the air flow passage structure of the engine, which solves the technical problem of relatively low flow loss in the transition section in the prior art, resulting in low aerodynamic efficiency of the engine

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