Super-high-hypersonic-speed two-dimensional inlet channel starting assisted vortex control adjustable valve device

Abstract

The invention discloses a super-high-hypersonic-speed two-dimensional inlet channel starting assisted vortex control adjustable valve device. The device comprises a main rotary valve. The bottom of the main rotary valve is hinged to the bottom wall of an air inlet channel external pressure section through a rotary shaft. The rotating angle of the main rotary valve on the bottom wall of the air inlet channel external pressure section is adjusted through a back angle adjusting support, and then the internal shrinkage ratio of an air inlet channel is adjusted. The lower portion of the main rotaryvalve is provided with a polygonal opening. A secondary sliding valve is slidably connected to the front portion of the main rotary valve. The opening degree of the polygonal opening of the main rotary valve is adjusted by sliding the secondary sliding valve. The super-high-hypersonic-speed two-dimensional inlet channel starting assisted vortex control adjustable valve device can implement adjustment on the internal shrinkage ratio of the air inlet channel through flexible rotation of the main valve and meanwhile can effectively control large-scale separation vortexes of the air inlet channelby controlling the opening degree of the secondary sliding valve, so that the starting performance of the air inlet channel is greatly improved. The super-high-hypersonic-speed two-dimensional inletchannel starting assisted vortex control adjustable valve device is suitable for adjustment and control over the open type air inlet channel in the starting process and also suitable for adjustment and control over the non-started air inlet channel during the restarting process.

Description

technical field [0001] The invention relates to a vortex-controlled adjustable valve device for assisting the start-up of a supersonic / hypersonic binary inlet, and belongs to the technical field of hypersonic air intake and exhaust. Background technique [0002] The intake port is an important part of the air-breathing scramjet engine to capture and compress air for combustion in the combustion chamber. For the engine to work normally, the intake port must work in the starting state. Therefore, inlet start is the basic prerequisite for the normal operation of hypersonic propulsion vehicles powered by scramjet engines. [0003] The hypersonic inlet will not start due to various disturbances such as angle of attack, side slip angle, combustion chamber back pressure, boundary layer or vortex engulfment. Once the air inlet is not activated, the engine cannot produce enough thrust, the resistance of the aircraft increases sharply, the combustion chamber stalls, and even the air...

AI Technical Summary

Problems solved by technology

[0005] (1) Suction control is currently the most widely used flow control method in ground tests and flight tests. It can indeed effectively improve the start-up performance of the intake port, but in the harsh working environment with long-term high heat flow and the integration of the airframe propulsion system Under the design concept, how to exclude the high temperature and low energy boundary layer is still full of difficulties and challenges;

[0006] (2) The biggest advantage of blow-off control is that it can control the jet intensity according to the working conditions, which has strong controllability, but it needs to provide additional air source and compression device;

[0007] (3) Acceleration start. Generally, for the combined power plant, rocket or turbojet engine can be used to accelerate after the intake port of the ramjet engine does not start. However, for the hypersonic intake port with relatively large internal contraction ratio, the acceleration start must Accelerate to a very high Mach number to restart, and for the internal contraction inlet with an internal contraction ratio exceeding 1.67, it is theoretically impossible to achieve self-starting by accelerating;

These methods all face a common problem: during the non-starting process and the starting process of the intake port, there is a large-scale separation vortex phenomenon in the intake port, and the existence of a large-scale separation area aggravates the difficulty of starting the intake port.

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