CN117846819A - Pre-detonation tube device of continuous detonation engine and control method thereof - Google Patents

Abstract

The invention discloses a control method of a pre-detonation tube device of a continuous detonation engine, which belongs to the technical field of continuous detonation engines, wherein one end of the pre-detonation tube is tangentially connected with a continuous detonation annular combustion chamber, the other end of the pre-detonation tube is provided with an ignition device, the ignition device is a spark plug or a gunpowder bag connected with a control device, and the control device can control the gunpowder bag to explode; the pre-detonation tube is also provided with a feed port, and the feed port is used for introducing fuel and gaseous oxidant into the pre-detonation tube; the spark plug and the gunpowder bag are used for detonating the fuel and the gaseous oxidant in the mixed state in the pre-detonation tube in a dynamic injection mode. The device can control the explosive package explosion by adopting a wired or wireless control device, so that the oxidant/fuel mixture in the pre-detonation tube is detonated by utilizing the instantaneous high-energy working medium generated by the explosive package explosion, the ignition energy density of the explosive package is high, and compared with the ignition device of the spark plug, the device is more beneficial to improving the detonation success rate of the pre-detonation tube.

Description

Pre-detonation tube device of continuous detonation engine and control method thereof

Technical Field

The invention belongs to the technical field of continuous detonation engines, and particularly relates to a pre-detonation tube device of a continuous detonation engine and a control method thereof.

Background

Detonation is a manner of approximately isovolumetric combustion, unlike isobaric combustion in conventional engines. Because the gas volume is hardly expanded in the detonation combustion process, the chemical energy is almost completely converted into the internal energy, so that the entropy is reduced and the thermal efficiency is high. Detonation is the only combustion mode that can raise the total pressure, thereby improving the functioning power. The propagation speed of detonation waves is typically in the order of kilometers per second. Currently, among various detonation engines, the continuous detonation engine is most expected to realize engineering application. Which itself has a primary detonation of the gas, the combustion speed is high, the control is easy, the self-compression and self-maintenance are realized, the structure is simple, the volume is small, the efficiency is high, the specific impulse is large, the thrust is greatly adjustable, the ignition can be realized for many times, and the like. Is expected to bring about technical innovation in the aerospace propulsion field, and has good engineering application prospect.

The detonation modes of the combustion chamber of the continuous detonation engine are roughly divided into two types: direct detonation and indirect detonation. The direct detonation mode is to directly detonate an ignition source such as a spark plug and an electric explosion wire in an annular combustion chamber to ignite unburned premixed gas to generate spherical detonation waves, but the spherical detonation waves generated in the way are not easy to transfer under the influence of the special configuration of the annular combustion chamber, specifically, the direct detonation mode directly ignites a fuel/oxidant mixture through the spark plug, but after the spark plug is ignited, two detonation waves which are generated to circumferentially propagate along two opposite directions of the annular combustion chamber collide at the other side of the combustion chamber, so that the detonation waves can be annihilated, and therefore, the ignition source is required to provide higher detonation energy to realize successful detonation, and the actual ignition success rate is only about 40%.

In order to solve the problem of low detonation success rate, the indirect detonation utilizes the initial detonation wave formed by the flame in the pre-detonation tube device during the process of rapidly undergoing deflagration to detonation to ignite the unburned mixed gas after entering the annular combustion chamber, thereby forming the self-sustained propagating rotary detonation wave. The indirect detonation has the advantages of small required detonation energy and strong repeatability. However, the conventional indirect detonation method is to ignite a fuel/oxidizer mixture diffused from an annular combustion chamber into a pre-detonation tube by a spark plug, cause combustion to undergo detonation-to-detonation in the pre-detonation tube to form a detonation wave, and detonate the rotating detonation wave by the initial detonation wave. Because in the traditional indirect detonation mode, reactants in the pre-detonation tube come from an annular combustion chamber connected with the pre-detonation tube, when the air is supplied to the annular combustion chamber, the initial speed direction of air inlet injection is mainly directed to the downstream guide tube and the vacuum detonation discharging tank direction, one end of the pre-detonation tube is tangentially connected with the combustion chamber, and the ignition position of a spark plug in the pre-detonation tube is positioned at the end of the pre-detonation tube away from the annular combustion chamber, so that the reactants supplied to the annular combustion chamber are difficult to accumulate to a sufficient ignition detonation concentration in the ignition position in the pre-detonation tube, and the ignition success rate of indirect detonation is reduced.

Disclosure of Invention

In view of the above, the present invention provides a pre-detonation tube device of a continuous detonation engine and a control method thereof, which improves the success rate of ignition by actively injecting fuel and oxidant into the pre-detonation tube and igniting by a powder pack.

The invention discloses a pre-detonation tube device of a continuous detonation engine, which adopts the following technical scheme:

the pre-detonation tube device of the continuous detonation engine comprises a pre-detonation tube, wherein one end of the pre-detonation tube is tangentially connected with a continuous detonation annular combustion chamber, the other end of the pre-detonation tube is provided with an ignition device, the ignition device is a spark plug or a gunpowder bag connected with a control device, and the control device can control the gunpowder bag to explode;

the pre-detonation tube is also provided with a feed port, and the feed port is used for injecting fuel and gaseous oxidant into the pre-detonation tube;

the spark plug and the gunpowder bag are used for detonating the fuel and the gaseous oxidant in the pre-detonation tube under the state of dynamic injection and mixing.

Further, the feed ports include a gaseous oxidant feed port and a fuel feed port.

Further, the gaseous oxidant feed port and the fuel feed port are arranged in a hedging manner;

the fuel feed port is a solid fuel powder injection hole or a liquid fuel injection hole or a gas fuel injection port.

Further, the gaseous oxidant feed port and the fuel feed port are located on the outer peripheral side of the spark plug or the cartridge.

Further, the pre-detonation tube is also provided with a pressure relief port and a pressure monitoring port;

the pressure relief opening is used for installing a pressure relief device;

the pressure monitoring port is used for installing a pressure sensor.

Further, the pressure relief port, the pressure monitoring port, the gaseous oxidant feed port and the fuel feed port are uniformly distributed along the circumference of the pre-detonation tube.

Further, the inner wall of the pre-detonation tube is provided with a plurality of protrusions.

Further, the protrusions are spherical or square.

Further, the pre-detonation tube is curved.

The control method of the pre-detonation tube device of the continuous detonation engine adopts the following technical scheme:

and introducing fuel and gaseous oxidant from the gaseous oxidant feed port and the fuel feed port, so that the gaseous oxidant and the fuel are mixed inside the pre-detonation tube to form an explosive mixture, and controlling the gunpowder package to explode through the control device.

The beneficial effects are that:

1. one end of the pre-detonation tube is tangentially connected with the continuous detonation annular combustion chamber, the other end of the pre-detonation tube is provided with an ignition device, the ignition device is a spark plug or a gunpowder bag connected with a control device, and the control device can control the gunpowder bag to explode; the pre-detonation tube is also provided with a feed port, and the feed port is used for introducing fuel and gaseous oxidant into the pre-detonation tube; the spark plug and the gunpowder bag are used for detonating the fuel and the gaseous oxidant in the mixed state in the pre-detonation tube in a dynamic injection mode.

Therefore, the fuel and the gaseous oxidant can be actively introduced into the pre-detonation tube through the feed inlet, so that the fuel and the gaseous oxidant are easy to ensure that the ignition position of the fuel and the gaseous oxidant in the pre-detonation tube is accumulated to a sufficient ignition initiation concentration, and the initiation success rate is improved. After the engine is stopped, nitrogen (discharged from the tail of the continuous detonation annular combustion chamber) can be introduced into the pre-detonation tube through a feed port on the pre-detonation tube to blow off the pipeline, so that residual fuel, gaseous oxidant or high-temperature products and the like in the pre-detonation tube are blown off. Moreover, a wired or wireless control device can be adopted to control the explosive package explosion, so that the instantaneous high-energy working medium generated by the explosive package explosion is utilized to detonate the oxidant/fuel mixture in the pre-detonation tube, the ignition energy density of the explosive package is high, and compared with a spark plug ignition device, the ignition device is more beneficial to improving the detonation success rate of the pre-detonation tube.

2. The feed ports include a gaseous oxidant feed port and a fuel feed port. In this way, the fuel and the gaseous oxidant are supplied to the pre-detonation tube separately in a non-premixed feed mode, the fuel and the gaseous oxidant are separated before entering the pre-detonation tube in the non-premixed feed mode, and only the pre-detonation tube is mixed to form a premixed explosive mixture. In addition, the flow rates of the fuel and the gaseous oxidant can be respectively and independently adjusted by the non-premixed feed, so that the equivalent ratio can be adjusted, and the detonation success rate is improved.

3. The gaseous oxidant feed inlet and the fuel feed inlet are arranged in a hedging manner, so that the gaseous oxidant and the fuel can be fully mixed in the pre-detonation tube to form an explosive mixture, the mixing effect is improved, and the detonation success rate is further improved. The fuel feed port can be a solid fuel powder injection hole or a liquid fuel injection hole or a gas fuel injection port, when the fuel feed port is a solid fuel powder (such as aluminum powder) injection hole, the solid fuel powder can be blown into the pre-detonation tube by high-pressure gas, after the solid fuel powder is fully mixed with a gas oxidant, an ignition source is initiated to form gas/solid two-phase detonation, when the fuel feed port is a liquid fuel (such as aviation kerosene and gasoline) injection hole, the liquid fuel can be pressed into the pre-detonation tube by high-pressure liquid/gas, and meanwhile, the liquid fuel is rapidly atomized after being sprayed out due to the high-pressure effect to form tiny liquid drops with the particle size of tens of micrometers, and after the fuel liquid drops are fully mixed with the gas oxidant, the ignition source is initiated to form gas/liquid two-phase detonation. When the fuel feed port is a gas fuel (such as methane, hydrogen and the like) injection hole, the gas fuel can be injected into the pre-detonation tube, and the ignition source is initiated after the gas fuel and the gas oxidant are fully mixed. The solid powder fuel has high energy density and good stability, and the solid powder and the liquid fuel are convenient to store and transport, so that the gas fuel, the liquid fuel and the solid fuel can be used, and the application range of the pre-detonation tube fuel of the continuous detonation engine is widened.

4. The gaseous oxidant feed inlet and the fuel feed inlet are arranged on the outer peripheral side of the spark plug or the gunpowder pack, so that the spark plug or the gunpowder pack is arranged at the middle position of the opposite-impact gaseous oxidant and fuel, and an explosive mixture meeting the ignition initiation concentration is easily formed at the explosion position of the gunpowder pack, thereby improving the initiation success rate.

5. The pre-detonation tube is also provided with a pressure relief opening for installing a pressure relief device. Therefore, when special conditions such as pipeline blockage and the like which need to exhaust and release pressure due to ablation or pollution exist in the pre-detonation tube, the pressure can be released through the pressure release opening, and the pre-detonation tube is safer and more reliable.

6. The pre-detonation tube is also provided with a pressure monitoring port for installing a pressure sensor. Therefore, the pressure in the pre-detonation tube can be monitored in real time through the pressure sensor, the safety and reliability are improved, and the influence of the pressure on the detonation success rate is more convenient to study.

7. The pressure relief opening, the pressure monitoring opening, the gaseous oxidant feed opening and the fuel feed opening are uniformly distributed along the circumference of the pre-detonation tube, so that the pressure monitoring is performed near the detonation center, the maximum pressure in the pre-detonation tube can be reflected, in addition, the pressure relief is performed near the detonation center, the pressure relief effect can be improved, and the safety and the reliability are further improved.

Drawings

FIG. 1 is a schematic illustration of a straight tubular pre-detonation tube connected to a continuous detonation annular combustor (spark plug not shown);

FIG. 2 is a view in the direction A-A of FIG. 1;

FIG. 3 is a schematic illustration of a straight tubular pre-detonation tube connected to a continuous detonation annular combustor (showing a spark plug) according to the present invention;

FIG. 4 is a schematic cross-sectional view of a connection of a pre-detonation tube in the shape of a bent tube with a continuous detonation annular combustor;

FIG. 5 is a schematic view of a straight tubular pre-detonation tube provided with protrusions on the inner wall;

FIG. 6 is a schematic view of a pre-detonation tube with a curved inner wall provided with protrusions according to the present invention;

FIG. 7 is a schematic diagram of a fuel supply line according to the present invention;

wherein 1-pre-detonation tube, 101-pre-detonation tube outlet, 102-bulge, 2-continuous detonation annular combustion chamber, 3-feed port, 301-gaseous oxidant feed port, 302-fuel feed port, 4-spark plug mounting hole, 5-pressure monitoring port, 6-relief port, 7-spark plug, 26-first purge gas source B, 27-second check valve B, 28-gaseous fuel supply source B, 29-first flow regulating valve B, 30-first relief valve B, 31-first pressure sensor B, 32-second flow regulating valve B, 33-third flow regulating valve B, 34-first flow meter B, 35-second pressure sensor B, 36-first temperature sensor B, 37-fourth flow regulating valve B, 38-first check valve B, 39-third pressure sensor B, 40-fifth flow regulating valve B, 41-second purge gas source B, 42-third check valve B, 43-sixth flow regulating valve B, 44-first relief valve B, 45-high pressure gas source C, 46-first flow regulating valve C, 47-first pressure reducing valve C, 48-first pressure sensor C, 49-liquid fuel reservoir C, 50-first flow meter C, 51-second pressure sensor C, 52-second flow regulating valve C, 53-first check valve C, 54-third flow regulating valve C, 55-first purge gas source C, 56-second check valve C, 57-second purge gas source C, 58-third check valve C, 59-fourth flow regulating valve C, 60-first safety valve C, 61-high-pressure gas supply D, 62-first flow regulating valve D, 63-first pressure reducing valve D, 64-first pressure sensor D, 65-first flow meter D, 66-first check valve D, 67-solid powder fluidizing device, 68-second flow meter D, 69-second pressure sensor D, 70-second flow regulating valve D, 71-second check valve D, 72-third flow regulating valve D, 73-first blowing gas source D, 74-third check valve D, 75-second blowing gas source D, 76-fourth check valve D, 77-fourth flow regulating valve D, 78-first safety valve D.

Detailed Description

The invention will now be described in detail by way of example with reference to the accompanying drawings.

Embodiment one:

referring to fig. 1-7, a pre-detonation tube device of a continuous detonation engine comprises a pre-detonation tube 1, wherein one end of the pre-detonation tube 1 is tangentially connected with a continuous detonation annular combustion chamber 2 and is communicated with the continuous detonation annular combustion chamber 2 through a pre-detonation tube outlet 101, a spark plug 7 is arranged at the other end of the pre-detonation tube 1, a feed inlet 3 is further arranged on the pre-detonation tube 1, and the feed inlet 3 is used for introducing gaseous oxidant and fuel into the pre-detonation tube 1.

In this way, the fuel and the oxidant can be actively introduced into the pre-detonation tube 1 through the feed port 3, so that the fuel and the oxidant can be easily ensured to accumulate to a sufficient ignition initiation concentration at the ignition position in the pre-detonation tube 1, and the initiation success rate is improved. After the engine is stopped, nitrogen gas (discharged from the tail of the continuous detonation annular combustion chamber 2) can be introduced into the pre-detonation tube 1 through a feed port 3 on the pre-detonation tube 1 to blow off the pipeline, so that residual fuel, gaseous oxidant, high-temperature products and the like in the pre-detonation tube 1 are blown off.

Specifically, in the present embodiment, the feed port 3 includes the gaseous oxidant feed port 301 and the fuel feed port 302, which is equivalent to separately feeding the fuel and the oxidant to the pre-detonation tube 1 through the non-premixed feed mode, the non-premixed feed mode makes the fuel and the gaseous oxidant separate before entering the pre-detonation tube 1, and only mixes in the pre-detonation tube 1 to form a premixed explosive mixture, and compared with the premixed feed, the non-premixed feed can avoid the damage to the upstream of the feed pipeline caused by tempering, and is safer and more reliable. In addition, the flow rates of the fuel and the gaseous oxidant can be respectively and independently adjusted by the non-premixed feed, so that the equivalent ratio can be adjusted, and the detonation success rate is improved. In addition, in the present embodiment, the ignition plug 7 is mounted on the ignition plug mounting hole 4 of the pre-detonation tube 1.

More specifically, the gaseous oxidant feed inlet 301 and the fuel feed inlet 302 are arranged in a hedging manner, so that the gaseous oxidant and the fuel can be fully mixed in the pre-detonation tube 1 to form an explosive mixture, the mixing effect is improved, and the detonation success rate is further improved.

In the present embodiment, the gaseous oxidizing agent supply port 301 and the fuel supply port 302 are located on the outer peripheral side of the ignition plug 7, and thus, the ignition plug 7 is positioned at the intermediate position between the opposed gaseous oxidizing agent and the fuel, so that an explosive mixture satisfying the ignition initiation concentration is easily formed at the ignition position of the ignition plug 7, and the initiation success rate is improved.

Also, in the present embodiment, the fuel supply port 302 may be a solid fuel powder injection hole or a liquid fuel injection hole or a gas fuel injection port. When the fuel feed inlet 302 is a solid fuel powder (such as aluminum powder) injection hole, the solid fuel powder can be blown into the pre-detonation tube 1 by high-pressure (in the invention, the high-pressure refers to 5-30 MPa) gas, after the solid fuel powder is fully mixed with a gas oxidant, an ignition source is initiated to form gas/solid two-phase detonation, when the fuel feed inlet 302 is a liquid fuel (such as aviation kerosene and gasoline) injection hole, the liquid fuel can be pressed into the pre-detonation tube 1 by the high-pressure liquid/gas, meanwhile, the liquid fuel is quickly atomized after being sprayed out due to the high-pressure effect to form tiny liquid drops with the particle size of tens of micrometers, and after the fuel liquid drops are fully mixed with the gas oxidant, the ignition source is initiated to form gas/liquid two-phase detonation. When the fuel feed inlet 302 is a gas fuel (e.g., methane, hydrogen, etc.) injection orifice, the gas fuel may be injected into the pre-detonation tube 1, and after the gas fuel is fully mixed with the gas oxidizer, the ignition source is initiated. The solid powder fuel has high energy density and good stability, and the solid powder and the liquid fuel are convenient to store and transport, so that the gas fuel, the liquid fuel and the solid fuel can be used, and the fuel application range of the pre-detonation tube 1 of the continuous detonation engine is widened.

More specifically, the present embodiment provides a fuel supply line structure, referring to fig. 7, the fuel supply line is a multiphase fuel supply line, including a gaseous fuel supply sub-line, a liquid fuel supply sub-line, and a solid powder fuel supply sub-line, in which:

the gaseous fuel supply sub-line is provided with a gaseous fuel supply source B28, a first flow rate adjustment valve B29, a first pressure reducing valve B30, a first pressure sensor B31, a second flow rate adjustment valve B32, a third flow rate adjustment valve B33, a first flow meter B34, a second pressure sensor B35, a fourth flow rate adjustment valve B37, a first check valve B38, a third pressure sensor B39, and a fifth flow rate adjustment valve B40 in this order from upstream to downstream (downstream at the end connected to the fuel supply port 302); a first blowing branch B is formed by branching at the inlet end of the first flow regulating valve B29, the first blowing branch B is connected with a first blowing air source B26, and a second one-way valve B27 is arranged on the first blowing branch B; a first pressure relief branch B is formed by branching between the first pressure relief valve B30 and the second flow regulating valve B32, the first pressure relief branch B is communicated with outdoor atmosphere, and a sixth flow regulating valve B43 and a first safety valve B44 are connected in parallel on the first pressure relief branch B; a first temperature sensor B36 is further arranged between the first flowmeter B34 and the fourth flow regulating valve B37, a second blowing branch B is formed by branching between the first check valve B38 and the third pressure sensor B39, the second blowing branch B is connected with a second blowing air source B41, and a third check valve B42 is arranged on the second blowing branch B;

the liquid fuel supply sub-pipeline is provided with a high-pressure air source C45, a first flow regulating valve C46, a first pressure reducing valve C47, a first pressure sensor C48, a liquid fuel storage tank C49, a first flow meter C50, a second pressure sensor C51, a second flow regulating valve C52, a first check valve C53 and a third flow regulating valve C54 in sequence from upstream to downstream; a first blowing branch C is formed by branching between the liquid fuel storage tank C49 and the first flowmeter C50, the first blowing branch C is connected with a first blowing air source C55, and a second one-way valve C56 is arranged on the first blowing branch C; a second blowing branch C is formed by branching between the first check valve C53 and the third flow regulating valve C54, the second blowing branch C is connected with a second blowing air source C57, and a third check valve C58 is arranged on the second blowing branch C; a first pressure relief branch C is formed by branching between the first pressure relief valve C47 and the liquid fuel storage tank C49, the first pressure relief branch C is communicated with the outdoor atmosphere, and a fourth flow regulating valve C59 and a first safety valve C60 are connected in parallel on the pressure relief branch C;

the solid powder fuel supply sub-pipeline is provided with a high-pressure air source D61, a first flow rate regulating valve D62, a first pressure reducing valve D63, a first pressure sensor D64, a first flow meter D65, a first one-way valve D66, a solid powder fluidization device 67, a second flow meter D68, a second pressure sensor D69, a second flow rate regulating valve D70, a second one-way valve D71 and a third flow rate regulating valve D72 in sequence from upstream to downstream; a first blowing branch D is formed by branching between the solid powder fluidization device 67 and the second flowmeter D68, the first blowing branch D is connected with a first blowing air source D73, and a third one-way valve D74 is arranged on the first blowing branch D; a second blowing branch D is formed by branching between the second check valve D71 and the third flow regulating valve D72, the second blowing branch D is connected with a second blowing air source D75, and a fourth check valve D76 is arranged on the second blowing branch D; a first pressure relief branch D is formed by branching between the first pressure relief valve D63 and the first flowmeter D65, and a fourth flow regulating valve D77 and a first safety valve D78 are connected in parallel on the first pressure relief branch D; the outlet ends of the fifth flow rate regulating valve B40, the third flow rate regulating valve C54, and the third flow rate regulating valve D72 are joined to a single main line and then communicate with the fuel inlet of the pre-detonation tube 1.

The second blowing branch B, the second blowing branch C and the second blowing branch D in the fuel supply pipeline can blow out the fire source in the combustion chamber when the continuous detonation annular combustion chamber 2 catches fire, and the blowing branches can not blow off the fuel in the corresponding sub-pipelines when working, so that the fuel is saved. In addition, it should be noted that the fuel supply line may be designed in a similar manner to the gaseous fuel supply sub-line, in which case the fuel is limited to gaseous fuel, but it is preferred to design the fuel supply line as a multi-phase fuel supply line in the present embodiment. Furthermore, the oxidant supply line may be configured as in the gaseous fuel supply sub-line of the present embodiment, in which case the gas source would need to be replaced with gaseous oxidant. In addition, it should be noted that the blow-off line in the prior art is generally directly connected to the continuous detonation annular combustor 2, which is difficult to remove the residual oxidant, fuel and high-temperature reactants in the oxidant supply line, the fuel supply line and the lumen of the pre-detonation tube 1 of the continuous detonation engine, which is disadvantageous for system safety and maintenance.

Specifically, the fuel supply line has the following functions: function one: providing the pre-detonation tube 1 with a gaseous fuel (gaseous fuel including, but not limited to, methane, hydrogen, etc.); and the function II: providing the pre-detonation tube 1 with a liquid fuel (liquid fuel includes but is not limited to aviation kerosene, gasoline, etc.); and the third function: providing the pre-detonation tube 1 with a solid fuel (solid fuel including, but not limited to, aluminum powder, etc.); function IV: monitoring the pressure, flow rate and temperature of the fuel supply pipeline; function five: safety pressure relief of the fuel supply line; function six: purging the fuel supply line; function seven: preventing backflow of fuel in the fuel supply line. The method for realizing the functions specifically comprises the following steps:

the implementation of the first function, namely, when the gaseous fuel is provided for the pre-detonation tube 1, closing the sixth flow regulating valve B43, the third flow regulating valve C54 and the third flow regulating valve D72, opening the first flow regulating valve B29, the second flow regulating valve B32 and the third flow regulating valve B33, regulating the opening degree of the first pressure reducing valve B30, and controlling the pressure and the flow rate of the gaseous fuel entering the pre-detonation tube 1;

the realization of the second function, namely, when the liquid fuel is provided for the pre-detonation tube 1, the fifth flow regulating valve B40, the fourth flow regulating valve C59 and the third flow regulating valve D72 are closed, the third flow regulating valve C54, the first flow regulating valve C46 and the second flow regulating valve C52 are opened, the opening degree of the first reducing valve C47 is regulated, and the pressure and the flow of the liquid fuel entering the pre-detonation tube 1 are controlled;

the realization of the third function, namely, when solid fuel is provided for the pre-detonation tube 1, the fifth flow regulating valve B40, the third flow regulating valve C54 and the fourth flow regulating valve D77 are closed, the third flow regulating valve D72, the first flow regulating valve D62 and the second flow regulating valve D70 are opened, the opening degree of the first pressure reducing valve D63 is regulated, and the flow of the solid fuel entering the pre-detonation tube 1 is controlled;

realization of the fourth function, i.e., monitoring the pressure, flow rate, temperature of the fuel supply line, specifically, the first pressure sensor B31 is used to monitor the pressure of the gaseous fuel after passing through the first pressure reducing valve B30, the second pressure sensor B35 is used to monitor the pressure of the gaseous fuel after passing through the first flow meter B34, and the third pressure sensor B39 is used to monitor the pressure of the gaseous fuel flowing into the fifth flow regulating valve B40; the first pressure sensor C48 is used for monitoring the pressure of the liquid fuel after passing through the first pressure reducing valve C47, and the pressure of a blowing-off gas source such as nitrogen; the first pressure sensor D64 is used for monitoring the pressure of a blowing air source such as nitrogen after passing through the first pressure reducing valve D63, and the second pressure sensor D69 is used for monitoring the pressure of a blowing air source such as nitrogen after passing through the second flowmeter D68; the first temperature sensor B36 is for monitoring the temperature downstream of the first flow meter B34;

the realization of the function five, namely the safe pressure relief of the fuel supply pipeline, when the abnormal high pressure occurs in the pipeline and exceeds the threshold values of the first safety valve B44, the first safety valve C60 and the first safety valve D78, the corresponding safety valve starts to work, and the high-pressure gas in the corresponding pipeline is discharged to avoid danger. When the safety valve cannot work due to certain factors, the flow regulating valve connected in parallel with the safety valve is used as a standby valve to be opened, and high-pressure gas in the pipeline is discharged;

the implementation of the sixth function, namely, when the fuel supply pipeline is blown off, specifically, when the gaseous fuel supply sub-pipeline is blown off, the sixth flow regulating valve B43 is closed, the first flow regulating valve B29, the second flow regulating valve B32, the third flow regulating valve B33, the fourth flow regulating valve B37 and the fifth flow regulating valve B40 are opened, nitrogen is injected through the first blowing air source B26 and the second blowing air source B41, and nitrogen blowing is provided for the gaseous fuel supply sub-pipeline so as to remove residual gaseous fuel in the gaseous fuel supply sub-pipeline; when the liquid fuel supply sub-pipeline is blown off, the fourth flow regulating valve C59 is closed, the first flow regulating valve C46, the second flow regulating valve C52 and the third flow regulating valve C54 are opened, nitrogen is injected through the first blowing-off air source C55 and the second blowing-off air source C57, and nitrogen blowing is provided for the liquid fuel supply sub-pipeline so as to remove the residual liquid fuel in the liquid fuel supply sub-pipeline; when nitrogen purging is provided for the solid powder fuel supply sub-pipeline, the fourth flow regulating valve D77 is closed, the first flow regulating valve D62, the second flow regulating valve D70 and the third flow regulating valve D72 are opened, nitrogen is injected through the first purging air source D73 and the second purging air source D75, nitrogen purging is provided for the solid powder fuel supply sub-pipeline, and residual solid powder fuel in the solid powder fuel supply sub-pipeline is removed;

the realization of the function seven, namely, the backflow of fuel in the fuel supply pipeline is prevented, and the backflow of high-temperature high-pressure air flow in the pre-detonation tube 1 is prevented by installing the first check valve B38, the first check valve C53 and the second check valve D71, so that the safety of the system is ensured.

Embodiment two:

unlike the first embodiment, in this embodiment, the ignition device is a cartridge connected to a control device capable of controlling the explosion of the cartridge for initiating the injection of the fuel and the gaseous oxidizer mixed into the pre-detonation tube 1. It will be appreciated that the cartridge is now mountable into the pre-detonation tube 1 by means of a corresponding mounting arrangement. Accordingly, the gaseous oxidizer supply port 301 and the fuel supply port 302 are located on the outer peripheral side of the cartridge and are disposed in a hedging manner. In the embodiment, a wired or wireless control device can be adopted to control the explosive package explosion, so that the instantaneous high-energy working medium generated by the explosive package explosion is utilized to detonate the oxidant/fuel mixture in the pre-detonation tube 1, the ignition energy density of the explosive package is high, and compared with the ignition of the spark plug 7, the ignition success rate of the pre-detonation tube 1 is more beneficial to improvement.

It should be noted in particular that, unlike the traditional powder pack ignition process (which is the ignition of static combustibles by powder packs), in this implementation, after the powder pack is ignited and exploded, the resulting high-energy working medium is contacted with the gaseous oxidant and the gaseous/liquid/solid fuel in the pre-detonation tube 1 lumen in a dynamically injected and blended state and detonates the oxidant/fuel mixture, thereby forming detonation waves and propagating towards the combustion chamber. That is, in this embodiment, the dynamic flowing combustible material is ignited by the cartridge, and in the conventional scheme, the dynamic flowing combustible material is ignited by the spark plug 7, and in the conventional scheme, the static combustible material is ignited by the cartridge.

In the embodiment, detonation waves formed by the pre-detonation tube 1 are transmitted into the continuous detonation annular combustor 2 to serve as a detonation source of the continuous detonation annular combustor 2, so that the ignition energy is improved, and the detonation waves in the continuous detonation annular combustor 2 are effectively detonated.

Embodiment III:

as an improvement, on the basis of implementing the first and second embodiments, the pre-detonation tube 1 is further provided with a pressure relief port 6 for installing a pressure relief device, which may be a pressure relief valve. Thus, when special conditions such as pipeline blockage and the like which need to discharge and release pressure due to ablation or pollution exist in the pre-detonation tube 1, the pressure can be released through the pressure release opening 6, and the pressure release device is safer and more reliable. And still be provided with pressure monitoring mouth 5 on the pre-detonation tube 1 for install pressure sensor, so, can monitor the pressure in the pre-detonation tube 1 through pressure sensor real-time, safe and reliable more, the influence of research pressure to the detonation success rate of also being convenient for more.

As a further improvement, in this embodiment, the pressure relief port 6, the pressure monitoring port 5, the gaseous oxidant feed port 301 and the fuel feed port 302 are circumferentially and uniformly distributed, so that the pressure monitoring is equivalent to the pressure monitoring near the detonation center of the pre-detonation tube 1, the maximum pressure in the pre-detonation tube 1 can be reflected, and the pressure relief near the detonation center can be achieved, so that the pressure relief effect can be improved, and the safety and reliability can be further improved.

Referring to fig. 1 and 3, the pre-detonation tube 1 may be straight tube, more preferably, as shown in fig. 4, the pre-detonation tube 1 is curved, the specific shape after bending may be designed according to the actual requirement, at this time, the material of the pre-detonation tube 1 may be soft copper or copper alloy, so, because the pre-detonation tube 1 of the conventional continuous detonation engine adopts steel material with very hard material as the basic material, and is a straight tube which cannot be bent, the detonation-to-detonation occurs in the straight tube channel, and the DDT (detonation-to-detonation) process needs a certain distance, so that the straight pre-detonation tube 1 is generally longer, which is very unfavorable for volume reduction, and the design of the continuous detonation engine pre-detonation tube 1 into the curved shape is favorable for volume reduction, and meanwhile, can provide a longer distance for the DDT process, improve the detonation success rate, and can better adapt to the complex pipeline structure and the line structure environment of the experimental test and the actual engine, and greatly avoid the problem of structural interference.

As a further improvement, referring to fig. 5 and 6, the inner wall of the pre-detonation tube 1 is provided with a plurality of protrusions 102, so, because the inner wall surface of the pre-detonation tube 1 of the conventional continuous detonation engine is a smooth surface without protrusions 102, the DDT process occurs through interaction between the combustion flow field and the smooth wall surface, and the DDT process needs a certain distance, the conventional pre-detonation tube 1 is generally relatively long, which results in that in a limited volume space, a sufficient distance can not be obtained to complete DDT, so that the airflow emitted from the outlet 101 of the pre-detonation tube after ignition is easily caused to be not detonation wave, which is very unfavorable for ignition, while the inner wall of the pre-detonation tube 1 is provided with protrusions 102, the flame produced by the embodiment has a beneficial effect on accelerating the flame, the detonation flame passing through the protrusions 102 has a tensile, curling and thermal efficiency increase, the propagation speed increases, and the detonation wave propagation speed increases the shock wave front section to produce shock wave, and the interaction between shock wave and the detonation wave and the flame to trigger the detonation wave, thereby increase the success rate of the flame, and the detonation flame. Specifically, the protrusions 102 may be spherical or square-shaped structures, etc.

Embodiment four:

on the basis of any one of the above embodiments, the present embodiment provides a method for controlling a pre-detonation tube device of a continuous detonation engine, including:

the gaseous oxidant and fuel are fed from the gaseous oxidant feed 301 and the fuel feed 302, so that the gaseous oxidant and fuel are mixed inside the pre-detonation tube 1 to form an explosive mixture, and the spark plug 7 is energized or the gunpowder pack is controlled to explode by a control device. After the operation, the temperature and pressure non-uniformity caused by the exothermic reaction in the pre-detonation tube 1 can be propagated and accumulated and enhanced in the pre-detonation, and finally the detonation-to-detonation process is completed, so that detonation wave is formed to spray out of the channel of the pre-detonation tube 1 and enter the continuous detonation annular combustion chamber 2 filled with combustible reactants, thereby achieving the purpose of detonation.

In summary, the above embodiments are only preferred embodiments of the present invention, and are not intended to limit the scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (10)

1. The pre-detonation tube device of the continuous detonation engine comprises a pre-detonation tube, one end of the pre-detonation tube is tangentially connected with a continuous detonation annular combustion chamber, and the other end of the pre-detonation tube is provided with an ignition device, and the device is characterized in that the ignition device is a spark plug or a gunpowder bag connected with a control device, and the control device can control the gunpowder bag to explode;

the pre-detonation tube is also provided with a feed port, and the feed port is used for injecting fuel and gaseous oxidant into the pre-detonation tube;

the spark plug and the gunpowder bag are used for detonating the fuel and the gaseous oxidant in the pre-detonation tube under the state of dynamic injection and mixing.

2. The pre-detonation tube device of a continuous detonation engine of claim 1, wherein the feed port includes a gaseous oxidant feed port and a fuel feed port.

3. The pre-detonation tube device of a continuous detonation engine of claim 2, wherein the gaseous oxidant feed port and the fuel feed port are disposed in a counter-flushing relationship;

the fuel feed port is a solid fuel powder injection hole or a liquid fuel injection hole or a gas fuel injection port.

4. A pre-detonation tube device of a continuous detonation engine according to claim 3, wherein the gaseous oxidant feed port and the fuel feed port are located on the outer peripheral side of the spark plug or the cartridge.

5. The pre-detonation tube device of the continuous detonation engine according to claim 3 or 4, wherein the pre-detonation tube is further provided with a pressure relief port and a pressure monitoring port;

the pressure relief opening is used for installing a pressure relief device;

the pressure monitoring port is used for installing a pressure sensor.

6. The pre-detonation tube device of a continuous detonation engine of claim 5, wherein the pressure relief port, the pressure monitoring port, the gaseous oxidant feed port, and the fuel feed port are uniformly distributed along a circumference of the pre-detonation tube.

7. The pre-detonation tube device of a continuous detonation engine of claim 6, wherein an inner wall of the pre-detonation tube is provided with a plurality of protrusions.

8. The pre-detonation tube device of a continuous detonation engine of claim 7, wherein the protuberance is spherical or square.

9. The pre-detonation tube device of the continuous detonation engine according to any one of claims 2 to 8, wherein the pre-detonation tube is curved.

10. A control method of a pre-detonation tube device of a continuous detonation engine, characterized by using the pre-detonation tube device of a continuous detonation engine according to any one of claims 2 to 9, comprising:

and introducing fuel and gaseous oxidant from the gaseous oxidant feed port and the fuel feed port, mixing the gaseous oxidant and the fuel in the pre-detonation tube to form an explosive mixture, and enabling the spark plug to be electrified or controlling the gunpowder bag to explode through a control device.