Intelligent engine adopting self-adaptive machine case and self-adaptive fan

Abstract

The invention provides an engine adopting a self-adaptive machine case and a self-adaptive fan. The engine comprises the self-adaptive machine case, the self-adaptive fan and a fuel gas generator; theself-adaptive machine case comprises a self-adaptive machine case driving execution part, an inlet section self-adaptive machine case, a fan section self-adaptive machine case, an engine middle section self-adaptive machine case and an outlet section self-adaptive machine case, wherein the inlet section self-adaptive machine case, the fan section self-adaptive machine case, the engine middle section self-adaptive machine case and the outlet section self-adaptive machine case are sequentially connected; the self-adaptive fan comprises self-adaptive fan blades and a fan driving execution part;a self-adaptive external duct is formed between the engine middle section self-adaptive machine case and an internal duct machine case of the fuel gas generator; an internal duct is formed in the internal duct machine case; the self-adaptive machine case driving execution part drives the self-adaptive machine case to move to control the cross section area of the external duct; and the fan drivingexecution part drives the self-adaptive fan blades to move in the axial direction to enable the self-adaptive fan blades to be matched with the fan section self-adaptive machine case.

Description

technical field [0001] The present disclosure relates to an engine, in particular to an intelligent engine adopting an adaptive casing and an adaptive fan. Background technique [0002] With the expansion of the flight envelope of aircraft and the increase of mission complexity, aero-engines need to take into account high-altitude, high-speed, high-thrust and low-altitude, low-speed, and low fuel consumption within the full flight envelope. As we all know, turbojet engine has greater unit thrust at high speed, while turbofan engine has better economic performance at low speed flight; therefore, the concept of variable cycle engine combining turbojet and turbofan engine came into being. [0003] Patent US3938328 is a kind of multi-cycle engine scheme proposed by Boeing Company in 1973. Based on the turbofan engine, this scheme adds an outer ring passage at the rear end of the first-stage fan, and sets adjustment mechanisms for changing the airflow of the inner and outer ring...

AI Technical Summary

Problems solved by technology

However, due to the large number of flow adjustment mechanisms, the length of the transition section is increased, resulting in a longer axial dimension of the engine; the redistribution of gas flow increases the aerodynamic mixing loss; the engine has strong aerodynamic instability during the adjustment process, which is the cause of the duct. The continuous adjustment of the ratio increases the design difficulty

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