Fan aerodynamic layout structure and method of a turbofan engine

Abstract

The invention discloses a fan aerodynamic layout structure and method of an inlet turbofan engine with a non-full-blade high-pressure rotor, which belongs to the technical field of aero-engine fans. The blades of the rotor are pressed to pressurize the airflow near the fan inlet disc. By rationally designing the non-full-blade high-pressure rotor at the fan inlet, the circulation capacity of the fan can be effectively improved, and the internal pressure ratio of the fan can be effectively improved at the same time. The invention can be directly applied to a high-performance turbofan engine, and can reduce the weight, fuel consumption rate and noise level of the turbofan engine without increasing the external dimension of the engine.

Description

technical field [0001] The present invention relates to a turbofan engine fan aerodynamic layout structure and method, in particular to a turbofan engine fan aerodynamic layout structure and method with a non-full blade high-pressure rotor at the inlet, which can maintain the fan efficiency and outer diameter basically unchanged It greatly improves the fan flow capacity and fan internal pressure ratio, especially suitable for high-performance aviation gas turbofan engines. Background technique [0002] The fan is one of the largest parts in size and weight in an aviation turbofan engine. Its performance not only directly determines the performance parameters such as the thrust-to-weight ratio and fuel consumption rate of the engine, but also affects the stability and reliability of the turbofan engine. Sex also plays a major role. On the premise that the size of the engine remains unchanged, increasing the upwind flow per unit area means that the work added by the fan incre...

AI Technical Summary

Problems solved by technology

However, the increase of the axial Mach number will further increase the relative Mach number of the blade tip inlet, forming a stronger shock wave in the blade channel, leading to the aggravation of the shock wave / boundary layer interaction, and in severe cases, large-scale Open separation, the loss increases sharply, which limits the efficiency of the compressor and the improvement of the stable working margin

Reducing the hub ratio of the fan inlet will reduce the reaction force of the fan, increase the load on the root of the fan stator blade, and increase the design difficulty; Imported wheel-to-hub ratio will make it difficult to arrange the blades on the small-sized wheel disc, which increases the difficulty of fan rotor processing

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