CN112555051B - Scramjet engine based on lightning arc discharge ignition technology - Google Patents
Scramjet engine based on lightning arc discharge ignition technology Download PDFInfo
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- CN112555051B CN112555051B CN202011413710.9A CN202011413710A CN112555051B CN 112555051 B CN112555051 B CN 112555051B CN 202011413710 A CN202011413710 A CN 202011413710A CN 112555051 B CN112555051 B CN 112555051B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
- F02C7/266—Electric
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
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- Combustion & Propulsion (AREA)
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- Fuel-Injection Apparatus (AREA)
Abstract
The invention discloses a scramjet engine based on a lightning arc discharge ignition technology, which belongs to the technical field of scramjet engines and comprises an engine shell, an air inlet channel nose cone, a supersonic combustion chamber, a spray pipe and an oil supply mechanism; the inlet channel nose cone and the inner wall of the engine shell form two inlet channels which are symmetrical along the axis; the supersonic combustion chamber and the spray pipe are sequentially arranged on the shell of the engine; a plurality of transverse fuel jet ports are arranged at equal intervals along the circumferential direction of the engine shell; the oil supply mechanism is connected with the transverse fuel jet orifice through an oil delivery pipe. The invention adopts a transverse jet flow intensified mixing technology and applies high voltage to the fuel atomizing nozzle, so that atomized fuel respectively provided with positive charge and negative charge is rapidly mixed with air incoming flow of the scramjet engine under the condition of certain penetration depth, and ignition is carried out based on the principle that high-pressure fuel atomized cloud cluster collides to generate thunder arc discharge, thereby realizing the stable ignition and full combustion enhancement effects of the scramjet engine.
Description
Technical Field
The invention belongs to the technical field of scramjet engines, and particularly relates to a scramjet engine based on a lightning arc discharge ignition technology.
Background
As a novel engine, the scramjet engine has the advantages of simple structure, light weight, low cost, high unit thrust and high speed, is one of key technologies of hypersonic aircrafts and rocket engines in the future, and receives more and more attention from countries. However, because the scramjet engine runs in a supersonic speed environment, the residence time of fuel in the combustion chamber is only millimeter magnitude, the mixing and ignition of the fuel and incoming flow, the formation of diffusion flame and the spread of the diffusion flame to the whole combustion chamber are completed in such a short time, the stable and efficient combustion is realized, the difficulty is very high, and the key restriction factors of the combustion efficiency of the combustion chamber and the performance of the engine are also the key restriction factors.
In order to make the ignition of the scramjet engine smooth, in the prior art, a cavity structure is usually arranged in an ignition area, a low-speed ignition area is created by utilizing backflow formed in the cavity, and meanwhile, a spark plug is arranged in the area to ignite combustible mixed gas and serve as an ignition source to continuously ignite atomized fuel conveyed upstream, such as supersonic combustion chamber ignition technologies disclosed in patent applications CN110822480A, CN104359125A and CN 104764045A. In order to ensure smooth ignition of the technologies, combustible mixed gas with proper fuel and air mixing ratio is required to be formed in the cavity, the combustible mixed gas is just distributed in an electric spark action area of the spark plug, two key factors are absent, and the ignition success rate of the supersonic combustion chamber is undoubtedly influenced. In addition, because the cavity structure is generally not known in a downstream mode, the area of the cavity ignition source which has beneficial effects in the supersonic flow field is limited, the supersonic combustion chamber with a larger caliber is not beneficial to the propagation of combustion flame to the whole combustion chamber, and the combustion efficiency is low.
In view of the above, how to provide a method for improving the ignition success rate and enabling the combustion flame to penetrate through the whole scramjet combustion chamber becomes a problem to be solved by those skilled in the art.
Disclosure of Invention
Aiming at the defects or improvement requirements of the prior art, the invention provides the scramjet based on the lightning arc discharge ignition technology, so that the technical problem of ignition failure caused by complicated flow field structure in the concave cavity and enrichment of fuel at the ignition point in the concave cavity ignition mode of the scramjet in the prior art is solved.
To achieve the above object, according to one aspect of the present invention, there is provided a scramjet engine based on a lightning arc discharge ignition technique, comprising: the engine comprises an engine shell, an air inlet nose cone, a supersonic combustion chamber, a spray pipe and an oil supply mechanism;
the air inlet nose cone is arranged at the front end of the engine shell and forms two air inlet channels which are symmetrical along the axis with the inner wall of the engine shell; the supersonic combustion chamber and the spray pipe are sequentially arranged on the engine shell and are coaxially arranged with the air inlet nose cone;
a plurality of transverse fuel jet ports are arranged at equal intervals along the circumferential direction of the engine shell, and the transverse fuel jet ports are communicated with the supersonic combustion chamber;
the oil supply mechanism is connected with the transverse fuel jet orifice through an oil delivery pipe;
the oil supply mechanism is used for providing atomized fuel droplets carrying positive and negative charges into the supersonic combustion chamber through the transverse fuel jet port, the atomized fuel droplets carrying the same charges are repelled and dispersed and are mixed with the atomized fuel droplets carrying different charges and supersonic incoming flow air passing through the air inlet channel, the atomized fuel droplets carrying different charges are attracted to form atomized fuel clouds, and thunder arc discharge is generated among the atomized fuel clouds to ignite atomized fuel so as to realize ignition of the scramjet engine; the spray pipe is used for spraying out flame after ignition is finished and providing power for the scramjet engine.
Preferably, the oil supply mechanism comprises an insulating fuel oil storage tank, an ultra-high voltage direct current power supply, a fuel storage tank and a plurality of electromagnetic valve groups;
the insulating fuel oil storage tank is provided with a plurality of transverse fuel jet ports, the number of the transverse fuel jet ports is the same as that of the insulating fuel oil storage tank, and the insulating fuel oil storage tank is communicated with the transverse fuel jet ports in a one-to-one correspondence mode; the fuel storage tank is communicated with the insulating fuel oil storage tank through an oil delivery pipe and controls the opening and closing of the oil delivery pipe through a plurality of electromagnetic valve groups so as to realize the oil supplement of the insulating fuel oil storage tank; the high-voltage direct-current power supply is used for electrifying the positive electrode and the negative electrode so that fuel in the insulating fuel oil storage tank carries positive charges and negative charges.
Preferably, the insulating fuel reservoirs carrying positively charged fuel and the insulating fuel reservoirs carrying negatively charged fuel are arranged symmetrically or staggered such that the incoming positively and negatively charged fuel is arranged symmetrically or staggered within the transverse fuel jet openings.
Preferably, the potential difference between the positive electrode and the negative electrode is +/-30 kv to +/-100 kv.
Preferably, the oil supply mechanism further comprises a fuel control system, and the fuel control system is used for controlling the electromagnetic valve group to realize repeated switching of different oil ways, so that the scramjet engine can continuously work.
Preferably, at least two pairs of the transverse fuel jet ports are provided.
Preferably, the horizontal fuel injection hole distributes in the perpendicular on the coplanar of scramjet axis, just horizontal fuel injection hole set up in supersonic combustion chamber is close to the position of intake duct.
Preferably, the included angle between the axis of the transverse fuel jet orifice and the axis of the supersonic combustion chamber is 60-90 degrees.
Preferably, the transverse fuel jet port injects fuel into the supersonic combustion chamber, and the fuel injection distance is 1/2-1 of the diameter of the supersonic combustion chamber.
Preferably, the nozzle is of a divergent structure, and the diameter of the nozzle is gradually increased from the ignition end to the flame ejection end.
In general, compared with the prior art, the above technical solution contemplated by the present invention can achieve the following beneficial effects:
1. the invention changes the traditional ignition mode of a single ignition source, can realize multi-point ignition in atomized fuel cloud clusters by utilizing lightning arc discharge, can greatly increase the ignition success rate of the scramjet engine, and improves the working reliability of the scramjet engine.
2. Under the action of the oil supply mechanism, the atomized fuel cloud cluster sprayed into the supersonic combustion chamber through the transverse fuel jet port at high speed is provided with positive potential or negative potential, and the transverse fuel jet atomization process is further strengthened by utilizing the principle that like charges repel each other, so that the aim of quickly and uniformly mixing the atomized fuel in the supersonic combustion chamber is fulfilled.
3. The invention utilizes the principle of opposite attraction, atomized fuel clouds with positive potential or negative potential can attract each other when transversely penetrating through the supersonic combustion chamber, the atomized fuel is guided to approach to the central part of the supersonic combustion chamber, the penetration length of the transverse fuel jet atomization process is further increased, and the effect that the atomized fuel is uniformly mixed on the cross section of the whole supersonic combustion chamber is achieved.
4. The invention utilizes the fact that atomized fuel clouds with positive potential or negative potential can collide with each other when transversely penetrating through the supersonic combustion chamber, and an electric field with extremely high potential difference can be formed in the atomized fuel clouds, so that lightning arc discharge can occur, and the energy generated by the electric field can ignite the clouds with proper mixing of fuel and air.
Drawings
FIG. 1 is a schematic structural diagram of a scramjet engine based on a lightning arc discharge ignition technology according to an embodiment of the invention;
FIG. 2 is a schematic diagram of the transverse fuel jet orifice and positive and negative electrode arrangement of an embodiment of the invention;
FIG. 3 is a schematic diagram of a transverse fuel jet port and positive and negative electrode arrangement according to another embodiment of the present invention;
fig. 4 is a schematic structural diagram of a transverse fuel jet port external oil supply mechanism, which is exemplified by two pairs of transverse fuel jet ports in the embodiment of the present invention.
The same reference numbers will be used throughout the drawings to refer to the same or like elements or structures, wherein: an air inlet nose cone 1; an air inlet channel 2; a lateral fuel jet port 3; a nozzle 4; a supersonic combustion chamber 5; an engine case 6; an insulating fuel storage tank 7; a positive electrode 8; a power supply 9; a fuel storage tank 10; and a negative electrode 11.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
In the description of the present invention, it is to be understood that the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention; in addition, in the description of the present invention, "a plurality" means two or more unless otherwise specified. The terms first, second, third and the like in the description and in the claims of the present invention are used for distinguishing between different objects and not necessarily for describing a particular sequential order.
The invention provides a scramjet engine based on a lightning arc discharge ignition technology, which has a structure shown in figures 1 and 3 and comprises an engine shell 6, an air inlet nose cone 1, a transverse fuel jet opening and an oil supply mechanism, wherein the engine shell is provided with a plurality of air inlet nose cones, and the transverse fuel jet opening is connected with the oil supply mechanism through a connecting rod
As shown in fig. 1, the engine housing 6 is divided into a head section, a middle section and a tail end, the air inlet nose cone 1 is arranged at the head section of the engine housing 6 and is divided into two air inlet channels 2 by the cavity of the head section of the engine housing together with the inner wall of the engine housing 6, the middle section of the engine housing is provided with a supersonic combustion chamber 5, and the tail section of the engine housing 6 is provided with a nozzle 4 with a gradually expanding structure. The air inlet nose cone 1, the supersonic combustion chamber 5 and the spray pipe 4 are coaxially arranged.
Specifically, a plurality of transverse fuel jet ports 3 are equidistantly arranged along the circumferential direction of the middle section of the engine housing 6. It should be noted that the transverse fuel injection ports 3 are arranged in pairs, and in the present invention, in order to ensure that the scramjet engine can continuously work, at least two pairs of transverse fuel injection ports 3 are provided.
In a further description, the transverse fuel jet ports 3 are symmetrically arranged at the upstream position of the supersonic combustion chamber 5 and are communicated with the supersonic combustion chamber 5, so that the fuel and the air have sufficient mixing distance and an ignition space, and the ignition success rate is improved. The transverse fuel jet ports are arranged according to a certain rule, so that the positive potential cloud cluster generated by atomization collides with the negative potential cloud cluster.
Preferably, the included angle between the axis of the transverse fuel jet port 3 and the axis of the supersonic combustion chamber 5 is 60-90 degrees, so as to improve the mixing efficiency of fuel and air and improve the ignition success rate.
Preferably, the transverse fuel jet opening 3 injects fuel into the supersonic combustion chamber at supersonic speed, and the penetrating distance is 1/2-1 of the diameter of the supersonic combustion chamber.
Further, the fuel supply mechanism is composed of an insulating fuel reserve tank 7, a power supply 9, a fuel storage tank 10, a fuel control system, and a plurality of solenoid valves.
The insulating fuel oil storage tanks 7 are provided with a plurality of horizontal fuel jet orifices 3, and each insulating fuel oil storage tank is connected by an oil delivery pipe for each corresponding horizontal fuel jet orifice. The fuel storage tank 10 is communicated with each insulating fuel oil storage tank 7 in sequence, and the fuel control system controls the opening or closing of the oil delivery pipes to provide fuel for each insulating fuel oil storage tank, so that repeated switching of different oil ways is realized, and the scramjet engine can work continuously.
In a further description, the insulating fuel oil tank 7 is provided as an insulating tank, and the power supply 9 is an ultra-high voltage dc power supply. And a positive electrode 8 or a negative electrode 11 is arranged in each insulating fuel oil storage tank, and the positive electrode or the negative electrode in each insulating fuel oil storage tank is electrified through a high-voltage direct-current power supply, so that the fuel in each insulating fuel oil storage tank carries positive charges or negative charges.
Specifically, the potential difference between the positive electrode and the negative electrode is +/-30 kv to +/-100 kv.
As shown in fig. 1, when the scramjet engine of the present invention works, supersonic incoming flow passes through the air inlet nose cone 1 arranged at the nose section of the scramjet engine, so that supersonic incoming flow passes through the oblique shock wave generated by the air inlet nose cone 1 and the shock wave string generated in the air inlet 2, and enters the supersonic combustion chamber 5 after being decelerated and pressurized, and the air in the supersonic combustion chamber 5 can still reach above sonic velocity.
Atomized fuel ejected by the transverse fuel jet ports 3 distributed on the circumferential direction of the wall surface of the supersonic combustion chamber 5 has opposite electric potentials, so that atomized fuel clouds with positive electric potentials or negative electric potentials can be effectively collided in the supersonic combustion chamber 5. Atomized fuel is rapidly mixed with air after entering the supersonic combustion chamber 5, and atomized fuel droplets with the same charges can be rapidly dispersed and fully mixed with fuel droplets with opposite charges and supersonic incoming air based on the principle that like charges repel each other. A strong electric field is formed among atomized fuel clouds with different electric potentials, arc discharge occurs, and the high temperature generated by the arc discharge ignites the cloud clouds meeting the appropriate oil-gas ratio, so that ignition of the scramjet engine is realized. Because the atomized fuel clouds with different electric potentials in the supersonic combustion chamber 5 are fully mixed, a plurality of micro-arc discharge points are formed in the supersonic combustion chamber 5, and a plurality of ignition points are formed, so that the ignition success rate is greatly improved. After ignition is completed, the flame propagates downstream in the supersonic combustion chamber 5 and is ejected from the nozzle 4 to power the engine. This completes a workflow.
In one embodiment of the present invention, three pairs of transverse fuel jet ports 3 are circumferentially arranged on the wall surface of the supersonic combustion chamber 5, for example, as shown in fig. 2 and fig. 3, two arrangements of positive electrodes 8 and negative electrodes 11 in the insulating fuel oil storage tank 7 are respectively given, the former is that the positive electrodes 8 and the negative electrodes 11 are symmetrically arranged, and the latter is that the positive electrodes 8 and the negative electrodes 11 are arranged at intervals. In practical application, the arrangement mode of the positive electrode 8 and the negative electrode 11 in the insulating fuel oil storage tank 7 is not limited, and the atomized fuel clouds with positive potential or negative potential can be effectively in collision contact with each other.
To be further explained, in order to prevent the damage of the fuel system of the scramjet engine caused by the short circuit of the power supply or the electrostatic spark discharge, an insulating fuel oil storage tank 7 is adopted between the fuel storage tank 10 and the transverse fuel injection port 3 for transition, and the continuous operation of the scramjet engine is ensured according to the following working mode. A schematic diagram of the fuel supply mechanism is given as shown in fig. 4, taking as an example the arrangement of two pairs of transverse fuel jet orifices 3, and numbered as a transverse fuel jet orifice group a and a transverse fuel jet orifice group B. When the scramjet engine based on the lightning arc discharge ignition technology starts to work, the electrodes are not electrified. The liquid fuel enters the insulating fuel storage tank 7 through the fuel delivery pipe and the solenoid valve group V2. When the liquid fuel in the insulating fuel reserve tank 7 reaches a proper amount, the solenoid valve group V2 is closed. Then, the ultra-high voltage direct current power supply in the external oil way corresponding to the group A of jet orifices is electrified, under the action of the electrified ultra-high voltage direct current power supply, the potential of the liquid fuel belt in the insulating fuel oil storage tank 7 relative to the reference potential is +/-30 kv to +/-100 kv, the external oil way electromagnetic valve group V1 corresponding to the group A of jet orifices receives an opening signal, the liquid fuel with the opposite potential in the insulating fuel oil storage tank 7 in the external oil way corresponding to the group A of jet orifices passes through the electromagnetic valve group V1 and is injected into the supersonic combustion chamber 5 from the transverse fuel jet orifice 3 at a high speed, and the atomized liquid fuel is transmitted along with the direction of the supersonic airflow transmission in the supersonic combustion chamber 5. At the moment, the group A jet ports work to provide power for the engine. When the liquid fuel liquid allowance in the insulating fuel oil storage tank 7 in the external oil circuit of the group A of jet ports is low, the electromagnetic valve group V1 is closed, the electrodes are uncharged, the electromagnetic valve group V2 is opened to supplement fuel, and meanwhile, the group B of jet ports start to work by the same flow to provide power for the engine and go on and go back, so that the whole fuel conveying pipe is prevented from being electrified while the continuous work of the scramjet engine is ensured, and the potential safety hazard caused by the electrification of the fuel storage tank 10 is avoided.
In the embodiment, in order to further enhance the success rate of ignition, the potential difference between the positive electrode and the negative electrode is between +/-30 kv and +/-100 kv, so that the ignition energy is ensured when arc discharge occurs between atomized fuel clouds with different potentials.
The invention absorbs the advantages of the traditional transverse jet fuel mixing ignition, namely, the wall surface transverse jet can provide good fuel penetration capability and faster near-field mixing effect, the reflux area generated by the jet can play a role in flame stabilization, and meanwhile, the wall surface jet does not extend into the physical structure of a flow field, does not need additional cooling and does not generate additional resistance. Also overcome some of the disadvantages of the cavity ignition approach: due to the complex structure of the flow field in the concave cavity, fuel at the ignition point can be enriched, and ignition failure can be caused. Is a potential ignition form of the scramjet engine.
It will be understood by those skilled in the art that the foregoing is only a preferred embodiment of the present invention, and is not intended to limit the invention, and that any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (9)
1. A scramjet engine based on lightning arc discharge ignition technology, comprising: the engine comprises an engine shell (6), an air inlet nose cone (1), a supersonic combustion chamber (5), a spray pipe (4) and an oil supply mechanism;
the air inlet nose cone (1) is arranged at the front end of the engine shell (6), and forms two air inlet channels (2) which are symmetrical along the axis with the inner wall of the engine shell (6); the supersonic combustion chamber (5) and the spray pipe (4) are sequentially arranged on the engine shell (6) and are coaxially arranged with the air inlet nose cone (1);
a plurality of transverse fuel jet ports (3) are arranged at equal intervals along the circumferential direction of the engine shell (6), and the transverse fuel jet ports (3) are communicated with the supersonic combustion chamber (5);
the oil supply mechanism is connected with the transverse fuel jet orifice (3) through an oil delivery pipe;
the oil supply mechanism comprises an insulating fuel oil storage tank (7), a power supply (9), a fuel storage tank (10) and a plurality of electromagnetic valve groups;
the number of the insulating fuel oil storage tanks (7) is the same as that of the transverse fuel jet orifices (3), and the insulating fuel oil storage tanks (7) are communicated with the transverse fuel jet orifices (3) in a one-to-one correspondence manner; the fuel storage tank (10) is communicated with the insulating fuel oil storage tank (7) through an oil delivery pipe and controls the opening and closing of the oil delivery pipe through a plurality of electromagnetic valve groups so as to realize the oil supplement of the insulating fuel oil storage tank (7); a positive electrode (8) or a negative electrode (11) is arranged in the insulating fuel oil storage tank (7), and the power supply (9) is used for electrifying the positive electrode and the negative electrode so as to enable the fuel in the insulating fuel oil storage tank (7) to carry positive charges and negative charges;
the oil supply mechanism is used for providing atomized fuel droplets carrying positive charges and negative charges into the supersonic combustion chamber (5) through the transverse fuel jet port (3), the atomized fuel droplets carrying the same charges are repelled and dispersed and are mixed with the atomized fuel droplets carrying different charges and supersonic incoming air flowing through the air inlet channel (2), the atomized fuel droplets carrying different charges are attracted to form atomized fuel clouds, and thunder and lightning arc discharge is generated among the atomized fuel clouds to ignite atomized fuel so as to realize ignition of the scramjet engine; the spray pipe (4) is used for spraying out flame after ignition is finished and providing power for the scramjet engine.
2. A scramjet engine based on lightning arc discharge ignition technology, according to claim 1, characterized in that the insulating fuel reservoirs carrying positively charged fuel and the insulating fuel reservoirs carrying negatively charged fuel are arranged symmetrically or staggered, so that the incoming positively and negatively charged fuel is arranged symmetrically or staggered inside the lateral fuel jet ports (3).
3. The scramjet engine based on the lightning arc discharge ignition technology is characterized in that the potential difference between the positive electrode and the negative electrode is +/-30 kv- +/-100 kv.
4. The scramjet engine based on the lightning arc discharge ignition technology as claimed in claim 3, wherein the oil supply mechanism further comprises a fuel control system, and the fuel control system is used for controlling the solenoid valve set to achieve repeated switching of different oil paths, so that the scramjet engine can continuously work.
5. A scramjet engine based on lightning arc discharge ignition technology according to any of claims 1-4, characterized in that there are at least two pairs of transverse fuel injection ports (3).
6. A scramjet engine based on lightning arc discharge ignition technology according to claim 5, characterized in that the transverse fuel injection ports (3) are distributed on the same plane perpendicular to the axis of the scramjet engine, and the transverse fuel injection ports (3) are arranged at the position of the supersonic combustion chamber (5) close to the air inlet channel (2).
7. A scramjet engine based on lightning arc discharge ignition technology according to claim 6, characterized in that the included angle between the axis of the transverse fuel jet orifice (3) and the axis of the supersonic combustor (5) is 60-90 °.
8. A scramjet engine based on lightning arc discharge ignition technology according to claim 7, characterized in that the transverse fuel jet port (3) injects fuel into the supersonic combustion chamber (5) at a distance of 1/2-1 of the diameter of the supersonic combustion chamber (5).
9. A scramjet engine based on lightning arc discharge ignition technology according to claim 5, characterized in that the jet pipe (4) is of a divergent structure, and the diameter of the jet pipe (4) is gradually increased from the ignition end to the flame ejection end.
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| CN202011413710.9A CN112555051B (en) | 2020-12-04 | 2020-12-04 | Scramjet engine based on lightning arc discharge ignition technology |
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