CN114320609B - Fuel injection device of hypersonic-speed and scramjet engine - Google Patents
Fuel injection device of hypersonic-speed and scramjet engine Download PDFInfo
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- CN114320609B CN114320609B CN202210201571.6A CN202210201571A CN114320609B CN 114320609 B CN114320609 B CN 114320609B CN 202210201571 A CN202210201571 A CN 202210201571A CN 114320609 B CN114320609 B CN 114320609B
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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Abstract
The invention provides a fuel injection device of a hypersonic speed scramjet engine, which comprises: a detonator device; an injection channel; a fuel-explosive pellet disposed in the injection passage; the detonation device is used for detonating the fuel-explosive pellets to enable the fuel to form fuel-air mixed aerosol in the air flow inside the super-combustion engine. The invention adopts micro explosion to realize that fuel is injected into supersonic airflow in the super-combustion engine to form fuel-air mixed aerosol with air, can realize rapid and efficient fuel-air mixing required by supersonic combustion within millisecond time scale, overcomes the difficulty of the prior art, and can meet the requirement of hypersonic combustion.
Description
Technical Field
The invention relates to the technical field of air-breathing hypersonic-speed and ultra-combustion engines, in particular to a fuel injection device of a hypersonic-speed and ultra-combustion engine.
Background
The air-breathing hypersonic engine can propel the aerospace vehicle at a flight speed far exceeding the local sound speed (the ratio of the flight speed to the local sound speed, namely the Mach number is more than 6), and is considered to be the most important high-speed flight power system in the near future.
Two forms of air-breathing supersonic engines are ramjets and scramjets. A feature of ramjet engines is that combustion of the fuel mixed with air occurs in the internal air stream which has been reduced to subsonic velocity. When the flying Mach number is 3-6, the ramjet is an efficient power system for air suction type propulsion application. When the flying Mach number exceeds 6, due to the fact that the kinetic energy of incoming flow is very large, the velocity of air flow inside the engine is reduced to subsonic velocity, so that a series of problems that the kinetic energy loss caused by shock waves is too large, the requirement on heat protection of a combustion chamber is too high, the chemical energy lost by air dissociation is too large and the like are caused, subsonic velocity combustion is not beneficial any more, and therefore when the flying Mach number exceeds 6, the air flow of the combustion chamber needs to be kept at supersonic velocity, namely supersonic velocity combustion is adopted. The scramjet engine refers to the scramjet engine with a combustion chamber adopting supersonic combustion.
Before supersonic combustion is carried out in a combustion chamber of the scramjet engine, fuel needs to be injected into supersonic airflow and sufficient mixing of the fuel and the air needs to be achieved. Because the air flow passes through the engine at supersonic speed, the whole process of fuel-air mixing-combustion-power-application-exhaust needs to be completed within millisecond order, so that the most important thing for realizing supersonic combustion is to quickly achieve sufficient fuel-air mixing, thereby effectively utilizing oxygen entering a combustion chamber of the engine to realize sufficient combustion of fuel.
The fuel-air mixing mode of the prior scramjet engine essentially utilizes the instability of shear flow to mix fuel and air. These methods include: the method adopts a turbulent flow or laminar shear layer tail flow vortex rolling process to realize mixing, fuel normal injection mixing and axial rotation mixing (comprising two schemes of a supersonic speed rotating nozzle and a fuel injector adopting a vortex generator on the inner wall surface of an engine). The common problems with these solutions are: (1) because the rolling speed of the vortex of the shear layer is far lower than that of the supersonic airflow of the main flow, the full mixing of fuel and air can not be realized in millisecond order; (2) shear layer vortices are characterized by concentrating the fuel in localized regions inside the vortex, and even if total mixing of fuel and air is achieved, it is difficult to achieve the molecular-scale mixing required for efficient combustion (combustion is the exchange of intermolecular atoms due to molecular collisions, so that the fuel and air mixture needs to reach a stoichiometric ratio at the molecular level before combustion occurs). At present, neither shear layer wake or swirl nor fuel side injection can achieve the uniform mixing of fuel and air required for adequate combustion with reasonable total pressure loss.
Disclosure of Invention
The invention aims to provide a fuel injection device of a hypersonic-speed super-combustion engine, which aims to solve the problem that in the existing shear layer mixing scheme, the vortex rotation speed depended on by mixing is one order of magnitude lower than the main flow speed of airflow in the engine, so that effective mixing cannot be realized before the airflow enters a combustion chamber; meanwhile, the inherent characteristic of the vortex that the fuel is concentrated on the center of the vortex and the spiral arm of the vortex causes the problem that the fuel and the air are difficult to realize uniform mixing at a molecular level.
The invention provides a fuel injection device of a hypersonic speed scramjet engine, comprising:
a detonator device;
an injection channel;
a fuel-explosive pellet disposed in the injection passage;
the detonation device is used for detonating the fuel-explosive pellets to enable the fuel to form fuel-air mixed aerosol in the air flow inside the super-combustion engine.
In some embodiments, the injection passage is a cavity comprising a loading aperture and a firing aperture;
the emission hole is provided with a valve;
the concave cavity is arranged on the wall surface of the scramjet engine behind the scramjet engine lip.
In some embodiments, the cavity is of the same order of magnitude and slightly smaller than the cross-sectional dimension of the scramjet wall.
In some embodiments, the cavity is located proximate to the overfire engine lip.
In some embodiments, one or more of the cavities are present.
In some embodiments, the cavity is disposed in one or more of the four walls of the scramjet engine.
In some embodiments, the injection channel is a Y-type injection channel comprising two loading holes and one emission hole;
a nozzle facing the emission hole is arranged at the junction of the two loading holes; and a high-pressure gas injection device is arranged at the nozzle.
In some embodiments, the injection passage is disposed on an upper wall surface of the scramjet engine behind the scramjet engine lip; the emission hole faces downwards.
In some embodiments, the diameter of the fuel-explosive pellet is comparable to the diameter of the injection channel.
In some embodiments, there are one or more of the injection channels.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
the most important difficulty in achieving supersonic combustion is achieving complete fuel-air mixing quickly on a millisecond timescale from when the supersonic airflow enters the engine to before combustion. The methods currently employed are all based on shear layer mixing. These methods, either shear layer wake or swirl, or fuel side injection, do not achieve the uniform mixing of fuel and air required for adequate combustion on a millisecond timescale with reasonable total pressure losses. Too long mixing time and insufficient mixing uniformity are two problems which are difficult to circumvent in the prior art and cannot meet the requirements of supersonic combustion. This is determined by the fact that the shear layer vortex rotational velocity is lower than the supersonic main flow velocity and the non-uniformity of the mass distribution inside the vortex. The invention adopts micro explosion to realize that fuel is injected into supersonic airflow in the super-combustion engine to form fuel-air mixed aerosol with air, can realize rapid and efficient fuel-air mixing required by supersonic combustion within millisecond time scale, overcomes the difficulty of the prior art, and can meet the requirement of hypersonic combustion.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
FIG. 1 is a schematic view of the solution of the present invention for the detonation of the wall surface of a scramjet engine in example 2.
Fig. 2 is a schematic structural view of a fuel injection device in the solution of the wall surface explosion and scattering of the scramjet engine in embodiment 2 of the present invention.
FIG. 3 is a schematic view showing the explosive throwing of the fuel in the air stream in example 2 of the present invention.
Fig. 4 is a schematic view showing the structure of a fuel injection device in the case where fuel is explosively thrown in an air stream in example 2 of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example 1
As shown in fig. 1, the present embodiment proposes a fuel injection device of a hypersonic-velocity-supersonic-speed-supersonic-combustion engine, including:
a detonator device;
an injection channel;
a fuel-explosive pellet disposed in the injection passage;
the detonation device is used for detonating the fuel-explosive pellets to enable the fuel to form fuel-air mixed aerosol in the air flow inside the super-combustion engine.
The fuel injection device of the hypersonic speed super-combustion engine has the core idea that the fuel is injected into the hypersonic speed airflow in the hypersonic speed super-combustion engine at a high speed by utilizing the characteristic of high-speed injection of substances in the explosion process, so that uniform mixing is realized. It has been shown in the literature that the velocity of the injected material during an explosion can reach the order of thousands of meters per second, sufficient to uniformly inject fuel into the supersonic air stream inside a scramjet engine on a time scale of tens of microseconds to 1 millisecond to form a fuel-air mixed aerosol. The technology in which fuel and air are exploded to form an aerosol is a relatively mature prior art, and thus the present invention is not concerned with specific explosive materials and charging techniques. The invention realizes the fuel injection into supersonic airflow inside the super-combustion engine to form fuel-air mixed aerosol by applying the technologies to the super-combustion engine.
Example 2
On the basis of the embodiment 1, the embodiment adopts a wall surface explosion throwing scheme of a hyper-combustion engine to realize the fuel injection device of the hypersonic velocity hyper-combustion engine, as shown in fig. 1 and 2, the injection channel is a concave cavity, and the concave cavity comprises an elastic loading hole and an emission hole;
the emission hole is provided with a valve;
the concave cavity is arranged on the wall surface of the scramjet engine behind the scramjet engine lip.
The working principle is as follows:
step 1, setting a cavity, as shown in fig. 2; wherein, the following steps are optional:
(1) the size of the cavity is in the same order of magnitude as the cross-sectional size of the wall surface of the scramjet engine and is slightly smaller than the cross-sectional size of the wall surface of the scramjet engine.
(2) The cavity is located proximate to the scramjet lip.
(3) The cavity may be one or more depending on the characteristics of the particular explosive charge.
(4) The recessed cavity is disposed in one or more of the four walls of the scramjet engine.
Step 2, closing the valve and filling fuel-explosive pellets from the pellet loading hole of the concave cavity; wherein, the following steps are optional:
the volume of the fuel-explosive pellet is similar to the volume of the cavity.
And 3, realizing micro explosion in the cavity after the detonating device detonates the fuel-explosive pellets, and injecting the fuel from the emission hole to the air flow in the super-combustion engine through the micro explosion to form fuel-air mixed aerosol. In the scheme of explosion injection on the wall surface of the super-combustion engine, after explosion injection is finished each time, fuel-explosive pellets are filled in the charge holes of the concave cavities again through the valves.
And 4, igniting the fuel-air mixed aerosol to form hypersonic combustion. The fuel-air mixed aerosol formed by the continuous detonation injection can be ignited by the flame already existing in the air flow of the scramjet engine, so that the step 4 can be automatically realized after the scramjet engine is ignited.
Example 3
On the basis of embodiment 1, the present embodiment implements a fuel injection device of a hypersonic-speed super-combustion engine by an explosion injection scheme of fuel in an air flow, as shown in fig. 3 and 4, the injection channel is a Y-shaped injection channel, and the Y-shaped injection channel comprises two loading holes and one emission hole;
a nozzle facing the emission hole is arranged at the junction of the two loading holes; and a high-pressure gas injection device is arranged at the nozzle.
The working principle is as follows:
step 1, setting a spraying channel as shown in fig. 4; wherein, the following steps are optional:
(1) the injection channel is arranged on the upper wall surface of the scramjet engine behind the scramjet engine lip; the emission hole faces downwards
(2) One or more of the injection channels.
Step 2, filling fuel-explosive pellets into the two charging holes of the injection channel; wherein, the following steps are optional:
the fuel-explosive pellets have a diameter comparable to the diameter of the injection passage and are readily detonated in the air stream inside the scramjet engine.
And 3, jetting high-pressure gas towards the jetting hole by the high-pressure gas jetting device through the nozzle, jetting the fuel-explosive pellets into the air flow in the scramjet engine by using the high-pressure gas, and then detonating the fuel-explosive pellets by the detonating device to realize micro explosion, so that fuel-air mixed aerosol is formed in the air flow in the scramjet engine. The fuel is injected in the air flow in an explosion mode, and continuous loading of fuel-explosive pellets can be achieved through the high-pressure gas injection device.
And 4, igniting the fuel-air mixed aerosol to form hypersonic combustion. The fuel-air mixed aerosol formed by the continuous detonation injection can be ignited by the flame already present in the scramjet engine air flow, so step 4 can be automatically realized after the scramjet engine is ignited.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A fuel injection apparatus for a hypersonic scramjet engine, the fuel injection apparatus comprising:
a detonator device;
a jet channel;
a fuel-explosive pellet disposed in the injection passage;
the detonation device is used for detonating the fuel-explosive pellets to enable the fuel to form fuel-air mixed aerosol in the air flow inside the super-combustion engine.
2. The fuel injection apparatus of the hypersonic scramjet engine of claim 1, wherein said injection passage is a cavity comprising a charge hole and a discharge hole;
the emission hole is provided with a valve;
the concave cavity is arranged on the wall surface of the scramjet engine behind the scramjet engine lip.
3. The fuel injection apparatus of the hypersonic scramjet engine of claim 2, wherein said cavity is of the same order of size as, and slightly smaller than, the cross-sectional dimensions of the scramjet engine walls.
4. The fuel injection apparatus of a hypersonic scramjet engine of claim 2, wherein said cavity is located proximate to the scramjet lip.
5. The fuel injection apparatus of a hypersonic scramjet engine of claim 2, wherein said cavity is one or more.
6. The fuel injection apparatus of a hypersonic scramjet engine of claim 5, wherein said re-entrant cavity is provided in one or more of the four walls of the scramjet engine.
7. The fuel injection apparatus of the hypersonic hyper-fuel engine of claim 1, wherein the injection channel is a Y-type injection channel comprising two loading holes and one emission hole;
a nozzle facing the emission hole is arranged at the junction of the two loading holes; and a high-pressure gas injection device is arranged at the nozzle.
8. The fuel injection apparatus of a hypersonic scramjet engine as recited in claim 7, wherein said injection passage is provided in an upper wall surface of the scramjet engine behind a scramjet engine lip; the emission hole faces downwards.
9. The fuel injection apparatus of the hypersonic scramjet engine of claim 8, wherein said fuel-explosive pellet has a diameter comparable to the diameter of the injection passage.
10. The fuel injection apparatus of the hypersonic engine of any of claims 7 to 9, wherein there are one or more of said injection passages.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210201571.6A CN114320609B (en) | 2022-03-03 | 2022-03-03 | Fuel injection device of hypersonic-speed and scramjet engine |
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| CN202210201571.6A CN114320609B (en) | 2022-03-03 | 2022-03-03 | Fuel injection device of hypersonic-speed and scramjet engine |
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| CN114320609B true CN114320609B (en) | 2022-06-07 |
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