阅读说明：本技术 一种喷气式发动机冲击波防护系统 (Jet engine shock wave protection system ) 是由 刘庭申 艾俊强 王家启 王利敏 杨成凤 卫永斌 张辉 王超 于 2019-12-24 设计创作，主要内容包括：本发明公开了一种喷气式发动机冲击波防护系统,包括机体,机体上开设有进气道,还包括高压气出气管、高压稳压腔、高压气进气管、激波管孔板、激波管阀门,机体内部设置有高压气出气管,高压气出气管出口与进气道前段管道连通,高压气出气管与设置在其后部的高压稳压腔连通,高压稳压腔与高压气进气管连通,激波管孔板后端与所述的高压气出气管出口下端铰接,激波管阀门后端与高压气出气管中段上壁面铰接,激波管孔板上设置有若干通气孔,本发明利用储存在高压稳定室中的高压气在进气道前段管道内形成向前运动的锤激波,在进气道进口前与外来的冲击波迎面碰撞,避免/消弱冲击波对进气道结构、发动机冲击。(The invention discloses a shock wave protection system of a jet engine, which comprises a machine body, wherein the machine body is provided with an air inlet channel, and further comprises a high-pressure air outlet pipe, a high-pressure stabilizing cavity, a high-pressure air inlet pipe, a shock tube pore plate and a shock tube valve, the machine body is internally provided with the high-pressure air outlet pipe, the outlet of the high-pressure air outlet pipe is communicated with a front section pipeline of the air inlet channel, the high-pressure air outlet pipe is communicated with the high-pressure stabilizing cavity arranged at the rear part of the high-pressure air outlet pipe, the high-pressure stabilizing cavity is communicated with the high-pressure air inlet pipe, the rear end of the shock tube pore plate is hinged with the lower end of the outlet of the high-pressure air outlet pipe, the rear end of the shock tube valve is hinged with the upper wall surface of the middle section of the high-pressure, the impact of the shock wave on the air inlet structure and the engine is avoided/weakened.)

1. The utility model provides a jet engine shock wave protection system, includes organism (1), organism (1) on seted up intake duct (2), its characterized in that: still include high-pressure gas outlet duct, high-pressure steady voltage chamber (11), shock tube orifice plate (7), shock tube valve (8), organism (1) inside be provided with the high-pressure gas outlet duct, high-pressure gas outlet duct export and intake duct front segment pipe (3) way intercommunication, high-pressure gas outlet duct with set up at its rear portion high-pressure steady voltage chamber (11) intercommunication, high-pressure steady voltage chamber (11) and high-pressure gas intake pipe (10) intercommunication, shock tube orifice plate (7) rear end with high-pressure gas outlet duct export lower extreme articulated, shock tube valve (8) rear end with wall is articulated on the high-pressure gas outlet duct middle section, shock tube orifice plate (7) on be provided with a plurality of air vents.

2. The jet engine blast protection system according to claim 1, wherein: the high-pressure air inlet pipe (10) is provided with a high-pressure air inlet cover (9).

3. The jet engine blast protection system according to claim 1, wherein: the shock tube pore plate (7) size and the intake duct front section pipe (3) size phase-match, make the shock tube pore plate (7) can cover intake duct front section pipe (3) completely.

4. The jet engine blast protection system according to claim 1, wherein: the size of the shock tube valve (8) is matched with that of the high-pressure gas outlet pipe, so that the shock tube valve (8) can completely close the high-pressure stabilizing cavity (11).

5. The jet engine blast protection system according to claim 1, wherein: and a jet engine (5) is arranged at the outlet (6) of the air inlet channel.

6. The jet engine blast protection system according to claim 1, wherein: the rear end of the shock tube pore plate (7) is hinged with the lower end of the outlet of the high-pressure gas outlet pipe through a rotating shaft.

7. The jet engine blast protection system according to claim 1, wherein: the rear end of the shock tube valve (8) is hinged with the upper wall surface of the middle section of the high-pressure gas outlet pipe through a rotating shaft.

8. The jet engine blast protection system according to claim 1, wherein: the high-pressure gas outlet pipe, the high-pressure stabilizing cavity (11) and the high-pressure gas inlet pipe (10) are all located above the gas inlet channel (2).

Technical Field

The invention belongs to the technical field of aircraft design, and particularly relates to a jet engine shock wave protection system.

Background

When the aircraft encounters strong explosion in a long distance in the flying process, shock waves generated by explosion can impact the structure of the aircraft body, and particularly if the engine structure is damaged by strong shock wave airflow, the flight safety of the aircraft can be seriously affected. The safety problem of the airplane engine when facing shock waves is less considered in the current airplane design process, and the related design for protecting the engine and the air inlet channel from being damaged by the shock waves is not seen yet. Therefore, a jet engine shock wave protection system is needed to be provided, so that the shock load applied to the jet engine when the jet engine meets shock waves transmitted from a remote place is reduced, and the structural safety of the jet engine is guaranteed.

Disclosure of Invention

The purpose of the invention is as follows: a jet engine shock wave protection system is provided, which can reduce the structural damage of the jet engine when encountering external shock waves.

The technical scheme of the invention is as follows:

the utility model provides a jet engine shock wave protection system, includes the organism, the organism on seted up the intake duct, still include high-pressure gas outlet duct, high-pressure steady voltage chamber, shock tube orifice plate, shock tube valve, the inside high-pressure gas outlet duct that is provided with of organism, high-pressure gas outlet duct export with intake duct anterior segment pipeline intercommunication, high-pressure gas outlet duct and the high-pressure steady voltage chamber intercommunication of setting at its rear portion, high-pressure steady voltage chamber and high-pressure gas intake pipe intercommunication, shock tube orifice plate rear end with high-pressure gas outlet duct export lower extreme articulated, shock tube valve rear end with the wall is articulated on the high-pressure gas outlet duct middle section, the shock tube orifice plate on be provided with a plurality of air vents.

The high-pressure air inlet pipe is provided with a high-pressure air inlet cover.

The shock tube pore plate size with intake duct anterior segment pipe size phase-match makes the shock tube pore plate can cover intake duct anterior segment pipe completely.

The size of the shock tube valve is matched with that of the high-pressure gas outlet pipe, so that the shock tube valve can completely close the high-pressure stabilizing cavity.

And a jet engine is arranged at the outlet of the air inlet channel.

The rear end of the shock tube pore plate is hinged with the lower end of the outlet of the high-pressure gas outlet pipe through a rotating shaft.

The rear end of the shock tube valve is hinged with the upper wall surface of the middle section of the high-pressure gas outlet pipe through a rotating shaft.

The high-pressure gas outlet pipe, the high-pressure stabilizing cavity and the high-pressure gas inlet pipe are all located above the gas inlet channel.

The invention has the beneficial effects that: the invention provides a jet engine shock wave protection system, which reduces the structural damage of a jet engine caused by external shock waves, provides required air flow and air flow meeting intake distortion quality for the engine in a short time, ensures the stable operation of the engine, forms a forward-moving hammer shock wave in a front-section pipeline of an air inlet channel through high-pressure air stored in a high-pressure stabilizing chamber, and reduces the impact of the shock wave on the air inlet channel structure and the engine structure by colliding with the shock wave on the front side of an inlet; meanwhile, the damping of the shock wave orifice plate and the effect of reducing intake distortion are utilized, air meeting the quality and flow rate of a flow field can be provided for the engine in a very short time, and the safe work of the engine is guaranteed.

Drawings

FIG. 1 is a schematic structural view of the present invention;

the high-pressure gas inlet comprises a body 1, a body 2, an inlet channel 3, an inlet channel front section pipeline 4, an inlet channel inlet 5, a jet engine 6, an inlet channel outlet 7, a shock tube pore plate 8, a shock tube valve 9, a high-pressure gas inlet cover 10, a high-pressure gas inlet pipe 11 and a high-pressure stabilizing cavity.

Detailed Description

The invention will be further described with reference to the accompanying drawings, in which fig. 1 shows a jet engine blast protection system according to the invention, comprising a body 1, the machine body 1 is provided with an air inlet channel 2, and also comprises a high-pressure air outlet pipe, a high-pressure stabilizing cavity 11, a high-pressure air inlet pipe 10, a shock tube pore plate 7 and a shock tube valve 8, the machine body 1 is internally provided with a high-pressure gas outlet pipe, the outlet of the high-pressure gas outlet pipe is communicated with the front section pipe 3 of the air inlet channel, the high-pressure gas outlet pipe is communicated with a high-pressure stabilizing cavity 11 arranged at the rear part of the high-pressure gas outlet pipe, the high-pressure stabilizing cavity 11 is communicated with a high-pressure gas inlet pipe 10, the rear end of the shock tube pore plate 7 is hinged with the lower end of the outlet of the high-pressure gas outlet pipe, the rear end of the shock tube valve 8 is hinged with the upper wall surface of the middle section of the high-pressure gas outlet pipe, and the shock tube pore plate 7 is provided with a plurality of vent holes.

The high-pressure air inlet pipe 10 is provided with a high-pressure air inlet cover 9, and the size of the shock tube pore plate 7 is matched with the size of the air inlet channel front section pipe 3, so that the shock tube pore plate 7 can completely cover the front section pipe of the air inlet channel.

The size of the shock tube valve 8 is matched with that of the high-pressure gas outlet pipe, so that the shock tube valve 8 can completely close the high-pressure stabilizing cavity 11.

And a jet engine 5 is arranged at the outlet 6 of the air inlet channel.

The rear end of the shock tube pore plate 7 is hinged with the lower end of the outlet of the high-pressure gas outlet pipe through a rotating shaft.

The rear end of the shock tube valve 8 is hinged with the upper wall surface of the middle section of the high-pressure gas outlet pipe through a rotating shaft.

The high-pressure gas outlet pipe, the high-pressure stabilizing cavity 11 and the high-pressure gas inlet pipe 10 are all positioned above the gas inlet channel 2.

Before flying, the high-pressure air inlet cover 9 arranged on the machine body 1 is opened and added through the high-pressure air inlet pipe 10High pressure compressed gas is introduced, and then the high pressure gas inlet cover 9 is closed. When the aircraft encounters shock waves, firstly, the shock tube pore plate 7 on the front section wall surface of the air inlet channel 3 is opened by utilizing the onboard control system, and the shock tube pore plate 7 is arranged from A-A₀Position to A-A₁A location; then, the shock tube control valve 8 is opened by utilizing the onboard control system, and the shock tube control valve 8 is controlled from B to B₀Position to B-B₁A location; at the moment, high-pressure gas stored in a high-pressure stabilizing chamber 11 moves towards a pipeline 3 at the front section of the air inlet channel through a high-pressure gas outlet pipe, and because the backward moving air flow in the air inlet channel 2 meets the high-pressure air flow from the pressure stabilizing chamber, a hammer shock wave is formed in the high-pressure gas outlet pipe and moves forwards along the air inlet channel 2, then the shock wave rushes out of the air inlet channel 2 through an air inlet channel inlet 4 and meets with a shock wave from the front of an aircraft in front of the air inlet channel inlet 4, and the shock wave on an air inlet channel structure and an engine can be avoided/weakened; meanwhile, the jet engine 5 can suck the airflow near the wall of the front pipeline through the shock tube pore plate 7, when the airflow passes through the shock tube pore plate 7, the shock tube pore plate 7 plays a role in damping and reducing intake distortion, the air demand and impact load of the jet engine 5 in a very short time can be ensured, and engine parts are protected from being damaged and work is stable.

The invention utilizes the high-pressure air stored in the high-pressure stable cavity 11 to form a hammer shock wave moving forwards in the front-section pipeline 3 of the air inlet channel, and the hammer shock wave collides with an external shock wave in front of the inlet 4 of the air inlet channel, so that the impact of the shock wave on the air inlet channel structure and an engine is avoided/weakened; during the period, the jet engine 4 can suck the airflow near the shock tube pore plate 7 of the front pipeline, and when the airflow passes through the shock tube pore plate 7, the shock tube pore plate 7 plays a role in damping and reducing intake distortion, so that the air demand, impact load and stable operation of the jet engine 5 in a very short time are ensured.