Engine and flexible casing with connecting rod adjustment mechanism and scale-type combined inner wall

Abstract

The invention provides an engine flexible casing adopting connecting rod adjusting mechanisms and scale type combined inner walls. The engine flexible casing comprises a mounting casing body, the multiple groups of connecting rod adjusting mechanisms and the multiple groups of scale type combined inner walls. The mounting casing body is a cylindrical thin-wall circular pipe. The multiple groups ofconnecting rod adjusting mechanisms are arranged on the inner surface of the mounting casing body and each comprise a position adjusting connecting rod, a position adjusting driving device, a shape adjusting connecting rod and a shape adjusting driving device. The multiple groups of scale type combined inner walls are arranged on the connecting rod adjusting mechanisms. The position adjusting driving devices are arranged between the position adjusting connecting rods and the mounting casing body. The position adjusting driving devices are used for driving the position adjusting connecting rods to adjust the radial positions of the scale type combined inner walls. The shape adjusting driving devices are arranged between the position adjusting connecting rods and the shape adjusting connecting rods and between the shape adjusting connecting rods and the scale type combined inner walls, and the shape adjusting driving devices are used for driving the shape adjusting connecting rods to adjust the curvature of the scale type combined inner walls. The invention further provides an engine including the flexible casing, a gas generator and a mixer.

Description

technical field [0001] The disclosure relates to an engine adopting a connecting rod adjustment mechanism and a scale-type combined inner wall and a flexible casing thereof. Background technique [0002] With the expansion of the flight envelope of the aircraft and the increase of the complexity of the task, the aero-engine needs to adjust its working state according to the task, taking into account the high-altitude, high-speed, high-thrust and low-altitude, low-speed, and low fuel consumption within the full flight envelope, while ensuring the maneuverability of the aircraft. At the same time, the combat radius of the aircraft is increased. Therefore, a variety of bypass ratio adjustment mechanisms have been proposed at home and abroad, so that the engine has the ability to adjust the bypass ratio according to different working conditions. [0003] Patent US3938328 is a kind of multi-cycle engine scheme proposed by Boeing Company in 1973. Based on the turbofan engine, th...

AI Technical Summary

Problems solved by technology

The setting of multiple sets of regulating valves and duct ejectors increases the complexity of the structure, and also affects the aerodynamic instability of the engine during the bypass ratio adjustment process

[0006] Patent CN105840549A proposes a corrugated casing, which can adjust the radial position of the corrugated casing through a stepping motor and a worm, but the radial position adjustment range of the casing structure is very limited and can only be applied to the adjustment of the blade tip clearance , unable to meet the requirements of the bypass ratio adjustment of the whole engine

[0007] It can be seen that the multiple bypass ratio adjustment mechanisms proposed at home and abroad are still difficult to meet the optimal thrust and fuel consumption requirements of different flight missions: first, the range of bypass ratio changes is very limited, and the comprehensive performance of the full envelope is limited; The channel ratio adjustment process is discontinuous, and the aerodynamic efficiency of the engine is low during the adjustment process; the third is that the internal adjustment structure of the duct is highly complex, and the aerodynamic stability of the engine is poor

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