CN113090393B - Device capable of igniting for multiple times based on solid energetic material - Google Patents

Abstract

The invention discloses a device capable of multiple ignitions based on solid energetic materials, which can be used for multiple ignitions of various aerospace engines such as detonation engines and ramjet engines. The solid charge is filled in the ignition tube, and the ignition charge is controlled to be ignited. The high-temperature and high-pressure flame after ignition is quickly introduced into the combustion chamber of the engine through the flame transfer tube to achieve ignition, and the ignition energy is much greater than the energy generated by spark discharge, which can meet some requirements. Ignition requirements under extreme conditions, such as direct initiation of detonation waves in rotary detonation engines. At the same time, in order to achieve multiple ignitions, multiple ignition tubes are connected in parallel, and a rotary valve-like mechanism is used to rotate the ignition tube box to a preset angle, and switch the unfired ignition tube to the position that communicates with the flame transfer tube, so as to realize the following One ignition, the number of ignitions depends on the number of parallel ignition tubes.

Description

A device with multiple ignitions based on solid energetic materials

technical field

The invention belongs to the field of ignition devices for aerospace engines, in particular to a device capable of multiple ignitions based on solid energetic materials.

Background technique

For aerospace engines such as detonation engines, a great amount of ignition energy is required to achieve normal combustion, such as the direct detonation of detonation waves, but the ignition energy provided by electric spark plugs is far from enough, so engineering applications are traditionally used. Very long detonation tube to achieve DDT (detonation to detonation process). For a rotary detonation engine whose combustion chamber is annular, the general traditional solution is to use a pre-detonation tube, and a slender pre-detonation tube is installed on the side of the combustion chamber, which is filled with a premixed gas of hydrogen and oxygen. The hydrogen-oxygen mixture is easy to form a detonation wave, which is ignited by an electric spark plug, and the detonation wave is generated by DDT in the pre-detonation tube. Detonate. However, there are many problems with this method. The first is that the general length of the pre-detonation tube is more than 0.5 meters. If it is too short, it may not be possible to complete the DDT to form a detonation wave, which increases the overall size of the engine. If a hydrogen-oxygen mixture is used as a fuel, an additional set of hydrogen-oxygen storage and delivery system is required, which greatly increases the mass, size and complexity of the system. The more complex the system, the greater the probability of problems. Second, the process of filling the pre-detonation tube with premixed gas can be automated through electronically controlled valves, but it is difficult to replace the sealing cover between the detonation tube orifice and the combustion chamber without manual operation, because simple mechanical rotation replacement is very difficult. It is difficult to ensure the tightness of the interface, and it is easy for the detonation wave to leak from the interface, and the combustion chamber cannot be ignited. That means the method is one-off, making it difficult to reignite the spacecraft if it stalls in flight. Therefore, an ignition device with simple structure, small size, high reliability and reusability has become a necessary condition for various new aerospace engines to move from laboratory to engineering application.

SUMMARY OF THE INVENTION

The purpose of the present invention is to provide a device that can be ignited multiple times based on solid energetic materials, so as to realize the multiple ignition function of some aerospace engines

The technical solution that realizes the object of the present invention is:

A device that can be ignited multiple times based on solid energetic materials, comprising a combustion chamber, a flame transfer tube, an ignition tube, an ignition tube box, a rear cover, a central shaft, a charge, and a front cover;

The ignition tube box is arranged between the rear cover plate and the front cover plate, and can rotate relative to the two cover plates; one end of the central shaft passes through the rear cover plate and is fixedly connected with the ignition tube box, and the other end of the central shaft is connected with a rotary drive The device is used to drive the ignition tube box to rotate; a plurality of ignition tubes are arranged in the ignition tube box, and the plurality of ignition tubes are arranged in parallel at equal intervals in a ring shape. The axial direction of the ignition tube is parallel to the axial direction of the flame transfer tube. A heat insulating material is arranged between the ignition pipes; a fire transmission hole is arranged on the front cover plate, one end of the flame transmission pipe is connected with the fire transmission hole, and the other end is connected with the combustion chamber; the outer side of the front cover plate is provided with a partition Hot material, a sealing cover is arranged on the outside of the ignition tube; a sealed charge is arranged in the ignition tube, and a detonating device is arranged at the end of each ignition tube to ignite the charge; during operation, the ignition tube box rotates to ignite the charge. One of the ignition tubes is aligned with the fire transmission hole, and the detonating device ignites the charge to complete the ignition of the fuel in the combustion chamber.

Compared with the prior art, the present invention has the following significant advantages:

The detonation engine can be repeatedly ignited, and even under the flying condition of the aircraft, the engine can still be re-ignited after the engine is turned off; the length of the original detonation engine igniter can reach 50-100cm, and the present invention can be reduced to about 10cm.

The ignition energy generated by the explosion of the solid charge is sufficient to realize the direct detonation of the detonation wave, and the present invention does not require the long tube of the DDT process to reduce the overall size of the engine, so that the engine is reduced by one long tube of 50 to 100 cm and becomes a standard Cylindrical, in addition, the simple mechanical rotary valve is used to achieve multiple ignitions, which is safe and reliable. In addition to rotary detonation engines, other engines requiring high ignition energy may also use the present invention.

Description of drawings

FIG. 1 is a plan view of a solid energetic material-based multiple-ignition device.

2 is a three-dimensional cross-sectional view of a solid energetic material-based multiple-ignition device.

Figure 3 is a partial structural diagram of the ignition tube box, the ignition tube, the flame transfer tube and the central shaft.

Figure 4 is a partial structural diagram of the flame transfer tube and the front cover.

Figure 5 is a partial structural diagram of the rear cover.

Detailed ways

The present invention will be further introduced below with reference to the accompanying drawings and specific embodiments.

1 is a plan view of the device of the present invention that can be ignited multiple times based on solid energetic materials, and FIG. 2 is a three-dimensional cross-sectional view, which is composed of a combustion chamber 1, a flame transfer tube 2, an ignition tube 3, an ignition tube box 4, Rear cover 5, central shaft 6, charge 7, front cover 8.

1-5, the ignition cartridge 4 is arranged between the rear cover plate 5 and the front cover plate 8, and can be rotated relative to the two cover plates, and the three constitute a rotary valve; one end of the central shaft 6 passes through the rear cover The plate 5 is fixedly connected with the ignition tube box 4, and the other end of the central shaft 6 is connected with a rotary drive device for driving the ignition tube box 4 to rotate; 3 are arranged in parallel at equal intervals in a ring shape, the axial direction of the ignition pipe 3 is parallel to the axial direction of the flame transfer pipe 2, and heat insulating material is provided between the ignition pipes 3; the front cover plate 8 is provided with a fire transfer hole 81 , one end of the flame transfer pipe is connected with the fire transfer hole 81, and the other end is connected with the combustion chamber 1; the outer side of the front cover plate 8 is provided with a heat insulating material; the ignition pipe 3 is provided with a sealed charge 7 for ignition A plastic sealing cover 31 is provided outside the mouth of the tube 3, and the end of each ignition tube 3 is provided with a detonating device for igniting the charge 7; during operation, the ignition tube box 4 is rotated, and one of the ignition tubes 3 is aligned with the transmission. In the fire hole 81 , the detonating device ignites the charge 7 to complete the ignition of the fuel in the combustion chamber 1 .

In order to solve the above problems brought by the traditional method, the present invention proposes a solution of using solid fuel to ignite. Put black powder or other similar solid fuel into the ignition tube 3 , the ignition tube 3 to be ignited is aligned with the flame transfer tube 2 , and the flame transfer tube 2 communicates with the combustion chamber 1 of the engine. The shortest length of the entire ignition tube 3 is only a few centimeters, which is much shorter than the length of the pre-detonation tube, which greatly reduces the overall size and weight of the aerospace engine. In addition, the control of the ignition energy requirement can be realized by the ignition tubes 3 of different diameters or the different charges. The charge 7 in the ignition tube 3 is ignited by the impact of an electric spark plug or a striker. The high temperature and high pressure flame and shock wave generated by the explosion of the charge 7 can easily break through the plastic sealing cover 31 and enter the combustion chamber 1 of the engine, and the energy released is far greater. For the detonation engine, the ignition energy generated by this igniter is sufficient to support the direct detonation of the detonation wave, compared to the energy that can be directly released by the general electric spark plug.

In order to achieve multiple ignitions, a plurality of ignition tubes 3 can be connected in parallel in a ring shape to form an ignition tube box 4. After the first firing, the position of the ignition tubes 3 remains unchanged, and the ignition tubes 3 that have been ignited are facing each other. The engine combustion chamber 1, and other ignition tubes are not communicated with the engine combustion chamber 1, and are blocked by the front cover plate 8, so there is no need to worry about the high temperature and high pressure gas entering the unignited ignition tube 3, and the detonation tube is charged. When it is necessary to re-ignite, the ignition tube box 4 is driven by the power unit to rotate as a whole by a predetermined angle, and the ignition tube 3 of the unignited charge 7 is rotated to be aligned with the flame transfer tube 2, so that the to-be-ignited tube 3, The flame transfer tube 2 and the combustion chamber 1 are connected to each other, enter the mode of preparing to ignite and wait for ignition, and detonate the charge 7 again, and the engine can be ignited to work again. Generally, six to eight ignition tubes 3 can be connected in parallel, so as not to make the overall size too large and to ensure sufficient ignition times.

But the problem is that because the charge itself is a mixture of combustibles and oxidants, it is easy to be accidentally ignited. Once high temperature, high pressure or physical impact occurs, the charge is prone to spontaneous combustion and self-explosion, resulting in danger.

The ignition box 4 is integrally formed into a cylinder, which is also a rotary valve. There is a front cover plate 8 on the top which is closely attached to the top surface of the ignition box 4. The cover plate has a through hole with the same diameter as the ignition tube. The pipes are connected to the combustion chamber of the engine. Before ignition, the ignition tube to be ignited needs to be accurately aligned with the fire-passing hole 81 on the front cover plate 8, so that the explosion capability of the ignition tube can be smoothly transmitted to the engine combustion chamber 1 without energy loss. In addition, the front cover 8 must be closely fitted with the ignition box 4. If there is a gap, it may cause high temperature and high pressure gas leakage, whether it is generated when the ignition pipe is ignited or the combustion chamber of the engine is in operation. . During ignition, the high temperature and high pressure gas generated by the ignition pipe 3 may cause a part of the ignition energy to be lost if it leaks. More seriously, if the high temperature and high pressure gas in the combustion chamber of the engine is transmitted from the gap of the cover plate to the unignited ignition during ignition In the tube 3, it will cause serious harm, and the engine will continue to work for several hours in practical applications, unlike the explosion of only a moment when the ignition explodes, the high temperature and high pressure combustion generated by the engine operation is a continuous test of the front cover. The tightness of the plate 8 and the ignition box 4 .

There is not only mass transfer but also heat transfer from the combustion chamber 1 of the engine. The engine releases a lot of heat. The surface temperature of the combustion chamber of the engine is extremely high, generally reaching about 1000K. The igniter is installed on the wall of the combustion chamber of the engine. On the other hand, during the long-term operation of the engine, it has also been subjected to the high temperature roasting. Once the charge reaches the minimum temperature required for combustion, it is very likely that self-explosion will occur. Therefore, the heat insulation measures of the igniter must be done well. First of all, the igniter needs to have a certain safety distance from the wall of the combustion chamber of the engine, because a large amount of heat will be transferred through the metal wall with good thermal conductivity because it directly contacts the metal wall of the combustion chamber of the engine. To the ignition tube 3, a flame transfer tube 2 of suitable length is required to extend the distance between the igniter and the wall surface of the combustion chamber 1. But it should not be too long, otherwise it may cause energy loss in the process of ignition energy transfer and increase the overall size. In addition, it is necessary to use a large amount of thermal insulation material to wrap the igniter as a whole, especially the front end of the igniter, which is facing the combustion chamber of the engine, which means that it receives the maximum heat. Since the ignited ignition tube 3 is directly connected to the combustion chamber during operation, the ignition tube 3 is also filled with high-temperature and high-pressure gas during operation, so the heat will also flow from the ignition tube to the adjacent ignition tube 3 transfer, resulting in self-ignition and self-explosion, so it is also necessary to fill with insulating material between the ignition tubes in the ignition box.

For the filling method of the charge, the simple and traditional method is that the ignition tube box 4 is a whole, and a circle of ignition tubes 3 is excavated on the ignition tube box 4 in a ring shape. The end of the ignition tube 3 is sealed and has an electric spark plug. The charge 7 is loaded at the end, and the electric spark plug releases energy to ignite the charge 7 during ignition, and the explosion wave breaks through the plastic sealing cover 31 . This method has a simple structure, but it is also time-consuming to fill a new charge 7 each time. Since most of the solid charge is injected into the pipeline when it is mushy and waits for it to solidify, if the aircraft has just landed, it has already been used. All of the ignition charges are completely filled, but there is a sudden and temporary flight mission, so it is too late to load a new charge.

There is also a new filling method, which is to put the charge into the independent ignition tube 3 in advance for storage. When it is needed, the ignition tube 3 can be loaded into the ignition tube box 4 to meet the needs of fast maneuvering response. In addition to the use of spark plugs for ignition, this charging method can also be used to detonate the charge by hitting the bomb tail with a striker. In addition, due to the protection of the ignition tube 3 tube shell, the impact of the explosion on the igniter itself can be reduced during detonation.

Claims (1)

1. A device that can be ignited multiple times based on solid energetic materials, characterized in that it comprises a combustion chamber, a flame transfer tube, an ignition tube, an ignition tube box, a rear cover, a central shaft, a charge, and a front cover; The ignition tube box is arranged between the rear cover plate and the front cover plate, and can rotate relative to the two cover plates; one end of the central shaft passes through the rear cover plate and is fixedly connected with the ignition tube box, and the other end of the central shaft is connected with a rotary drive The device is used to drive the ignition tube box to rotate; a plurality of ignition tubes are arranged in the ignition tube box, and the plurality of ignition tubes are arranged in parallel at equal intervals in a ring shape. The axial direction of the ignition tube is parallel to the axial direction of the flame transfer tube. A heat insulating material is arranged between the ignition pipes; a fire transmission hole is arranged on the front cover plate, one end of the flame transmission pipe is connected with the fire transmission hole, and the other end is connected with the combustion chamber; the outer side of the front cover plate is provided with a partition Hot material, a sealing cover is arranged on the outside of the ignition tube; a sealed charge is arranged in the ignition tube, and a detonating device is arranged at the end of each ignition tube to ignite the charge; during operation, the ignition tube box rotates to ignite the charge. One of the ignition tubes is aligned with the fire-passing hole, and the detonating device ignites the charge to complete the ignition of the fuel in the combustion chamber; The detonating device is an electric spark plug or a striker, the electric spark plug is arranged in the ignition tube, and the striker is arranged in the ignition tube box, facing the end of the ignition tube; The ignition tube and the ignition tube box have an integrated structure or a split structure. In the integrated structure, a plurality of ignition tubes are processed in the ignition tube box; in the split structure, a plurality of ignition tubes are installed in the installation of the ignition tube box. inside the hole.

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