CN111998387A - Method and device for promoting scramjet engine to realize starting ignition - Google Patents
Method and device for promoting scramjet engine to realize starting ignition Download PDFInfo
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- CN111998387A CN111998387A CN202010829851.2A CN202010829851A CN111998387A CN 111998387 A CN111998387 A CN 111998387A CN 202010829851 A CN202010829851 A CN 202010829851A CN 111998387 A CN111998387 A CN 111998387A
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- engine
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- flame stabilizer
- scramjet
- starting ignition
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
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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
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ignition Installations For Internal Combustion Engines (AREA)
Abstract
The invention relates to the technical field of scramjet engines, and discloses a method and a device for promoting a scramjet engine to realize starting ignition, wherein air is injected into the engine in a direction perpendicular to the air flow direction on one side of the inner wall surface of a flame stabilizer of the scramjet engine, the air flow is 15% -30% of the air flow at an engine inlet, and the length of the position of the injected air from the position of the flame stabilizer of the engine is 10% -20% of the total length of the engine. According to the invention, air jet injection is carried out at the rear part of the flame stabilizer of the scramjet engine to generate a shock wave string structure, so that thermodynamic parameters of a flow field are influenced, static pressure and static temperature in the flow field are improved, speed is reduced, efficient mixing of fuel and air is promoted, the injection mode of the fuel or the geometric configuration of the engine is not required to be changed, additional interference is not brought to the work of the engine, the scramjet engine can be promoted to realize starting ignition, and the release of chemical energy of the fuel in a combustion chamber is ensured.
Description
Technical Field
The invention relates to the technical field of scramjet engines, in particular to a method and a device for promoting the scramjet engine to realize starting and ignition.
Background
In the scramjet engine flow passage, air flows through the combustion chamber at supersonic velocity, and the residence time of fuel in the combustion chamber is extremely short, on the order of milliseconds. In order to realize the normal work of the scramjet engine, the conversion of the chemical energy of the fuel into heat energy, namely the starting ignition of the scramjet engine, must be realized. In particular, the use of kerosene fuels which are economical and easy to store requires the realization of the ignition of the kerosene in scramjet engines.
At present, a plurality of methods for promoting the scramjet engine to realize starting ignition are provided, the configuration of a combustion chamber of the engine is changed or a fuel injection mode is optimized, but the combustion performance of the engine is possibly influenced to a greater or lesser extent.
Disclosure of Invention
Based on the problems, the invention provides a method and a device for promoting a scramjet engine to realize starting ignition, which are characterized in that air jet injection is carried out at the rear part of a flame stabilizer of the scramjet engine to generate a shock wave string structure, so that thermodynamic parameters of a flow field are influenced, static pressure and static temperature in the flow field are improved, speed is reduced, efficient mixing of fuel and air is promoted, the injection mode of the fuel or the geometric configuration of the engine is not required to be changed, no additional interference is brought to the working of the engine, the scramjet engine can be promoted to realize starting ignition, and the release of chemical energy of the fuel in a combustion chamber is ensured.
In order to realize the technical effects, the invention adopts the technical scheme that:
a method for promoting a scramjet engine to realize starting ignition is characterized in that air is injected into the engine in a direction perpendicular to the air flow direction on one side of the inner wall surface of a flame stabilizer of the scramjet engine, the air flow is 15% -30% of the air flow of an engine inlet, and the length of the position of the injected air from the position of the flame stabilizer of the engine is 10% -20% of the total length of the engine.
In order to realize the technical effect, the invention also provides a device for promoting the scramjet engine to realize starting ignition, which comprises a flame stabilizer arranged at the front end of a combustion chamber of the scramjet engine, wherein the flame stabilizer is provided with a plurality of fuel injection blocks, the fuel injection blocks are provided with a plurality of spray holes communicated with a fuel delivery device, and the spray holes vertically face to the inner cavity of the flame stabilizer; an air jet tool block for vertically jetting air into the engine combustion chamber is arranged on the combustion chamber, the length of the air jet tool block from the flame stabilizer is 10% -20% of the total length of the engine, and a spark plug is arranged in the flame stabilizer.
Furthermore, a support plate is arranged on the upper wall surface of the flame stabilizer, and the spark plug is positioned at the rear end of the support plate.
Furthermore, the upper wall surface of the flame stabilizer is provided with a concave cavity, and the spark plug is positioned on the concave cavity.
Further, a pilot hydrogen fuel injection block located upstream of the spark plug is provided on the flame holder.
Furthermore, the number of the fuel injection blocks is four, and the four fuel injection blocks are respectively arranged on the upper wall surface or the lower wall surface of the flame stabilizer, wherein one fuel injection block is positioned at the upstream of the pioneer hydrogen fuel injection block.
Furthermore, the fuel injection block, the air jet tool block, the spark plug and the pioneer hydrogen fuel injection block are detachably connected with the engine shell through bolts or screws.
Compared with the prior art, the invention has the beneficial effects that:
1) according to the invention, air jet injection is carried out at the rear part of the flame stabilizer of the scramjet engine to generate a shock wave string structure, so that thermodynamic parameters of a flow field are influenced, static pressure and static temperature in the flow field are improved, speed is reduced, efficient mixing of fuel and air is promoted, starting and ignition of the scramjet engine are promoted, and release of chemical energy of fuel in a combustion chamber is ensured.
2) The method and the device are obviously different from the traditional method for promoting the scramjet engine to realize the starting ignition, and have the advantages that the scramjet engine can be promoted to realize the starting ignition without changing the injection mode of fuel or the geometric configuration of the engine and bringing extra interference to the work of the engine.
Drawings
FIG. 1 is a schematic structural diagram of an apparatus for promoting the realization of starting ignition of a scramjet engine in embodiments 1 and 2;
FIG. 2 is a flow field texture map of the scramjet engine without air jet assist in example 2;
FIG. 3 is a texture shadow of the flow field of the scramjet engine with air jet assist in example 2;
FIG. 4 is a graph of the weighted Mach number and temperature with and without air jet injection in example 2;
FIG. 5 is a graph of the pressure at a monitoring point over time with and without air jet injection in example 2;
FIG. 6 is a flame distribution diagram in the absence of the air jet in example 2;
FIG. 7 is a flame profile for an air jet as practiced in example 2;
wherein, 1, an engine model; 2. a concave cavity; 3. a pioneer hydrogen fuel injection block; 4. a spark plug; 5. air jet frock piece.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to examples and accompanying drawings, and the exemplary embodiments and descriptions thereof are only used for explaining the present invention and are not meant to limit the present invention.
Example 1:
referring to fig. 1, in the method for promoting the scramjet engine to realize starting ignition, air is injected into the scramjet engine in a direction perpendicular to the air flow direction on one side of the inner wall surface of a flame stabilizer of the scramjet engine, the air flow is 15% -30% of the air flow of an engine inlet, and the length of the position of the injected air from the position of the flame stabilizer of the engine is 10% -20% of the total length of the engine.
In the embodiment, air jet injection is carried out at the rear part of the flame stabilizer of the scramjet engine, the air is 295K of normal-temperature air, and the air flow is 15-30% of the air flow at the inlet of the engine.
The device for promoting the scramjet engine to realize starting ignition comprises a flame stabilizer arranged at the front end of a combustion chamber of the scramjet engine, wherein a plurality of fuel injection blocks are arranged on the flame stabilizer, a plurality of spray holes communicated with a fuel conveying device are arranged on the fuel injection blocks, and the spray holes vertically face an inner cavity of the flame stabilizer; an air jet tool block for vertically jetting air into the engine combustion chamber is arranged on the combustion chamber, the length of the air jet tool block from the flame stabilizer is 10% -20% of the total length of the engine, and a spark plug is arranged in the flame stabilizer.
The specific time sequence control process is as follows: the incoming air enters the engine to establish a flow field, then the air jet tool block performs air jet injection into the combustion chamber, and then the fuel injection module performs fuel injection and the spark plug igniter works to perform ignition and then is closed; in the embodiment, the air flow at the inlet of the engine is at supersonic speed, a shock wave string structure is generated when a longitudinal jet flow blocking effect occurs, the temperature and the pressure in a flow field are increased under the influence of the shock wave string structure, the Mach number (speed) is reduced, the efficient mixing of fuel and air is promoted, the scramjet engine is promoted to start and ignite, and the chemical energy release of the fuel in a combustion chamber is realized. The method has the advantages that the method can promote the scramjet engine to realize the starting ignition without changing the injection mode of fuel or the geometrical configuration of the engine and causing additional interference to the operation of the engine.
In the embodiment, the flame stabilizer can adopt the concave cavity or the support plate as a flame stabilizing device, when the upper wall surface of the flame stabilizer is of a concave cavity structure as the flame stabilizing device, the spark plug is positioned on the concave cavity, and the concave cavity can generate a low-speed backflow region to stabilize flame in the flow field establishing process. It should be noted that the main point of the present invention is the effect of the protective air jet on the ignition start, and the present embodiment does not show the relevant illustration and test results of the strut as a flame stabilizer, and the position of the spark plug is not changed, except that the flame stabilizer at the upstream side can be a cavity structure or a strut, so that the spark plug is at the rear end (namely, the downstream side in the incoming flow direction) of the spark plug. When the upper wall surface of the flame stabilizer is provided with the support plate as the flame stabilizing device, the spark plug is positioned at the rear end of the support plate, and the support plate structure can realize the same flame stabilizing effect as the concave cavity.
Example 2:
referring to fig. 1-7, the present example will compare the differences in the flow field structure, the start-up ignition time and the flame distribution of the scramjet engine with and without the action of the jet air through experiments, and confirm the practical application effect brought by the present invention.
In this example, the engine was configured as shown in FIG. 1, and the engine model 1 included a flame holder at the front end of the combustor, the combustor screen inlet interface was 30mm by 150mm, and the overall model length was 1073.19 mm. The engine model 1 adopts kerosene as fuel to carry out injection through the fuel injection block, the total flow of normal-temperature air injected by the air jet tool block 5 is about 27.2% of the flow of an inlet engine, the distance between the jet position and the inlet of a flame stabilizer (the flame stabilizer adopts a concave cavity in the embodiment) is about 198.16mm, and the jet position accounts for about 18.5% of the total length of the engine model 1. The upper wall surface of the flame stabilizer is a concave cavity 2, and two spark plugs 4 are arranged in the flame stabilizer concave cavity 2 in a spreading way and used for igniting the pioneer hydrogen. The cavity 2 is provided with a pioneer hydrogen fuel injection block 3 positioned at the upstream of the spark plug 4, and pioneer hydrogen is injected in the flame stabilizer cavity 2 through the pioneer hydrogen fuel injection block 3 and is ignited by the spark plug 4 in advance, so that the starting and ignition of the engine are facilitated. The number of the fuel injection blocks is four, and the fuel injection blocks are marked as K1, K2, K3 and K4 and are respectively arranged on the upper wall surface or the lower wall surface of the flame stabilizer, wherein one fuel injection block is positioned on the upstream of the pioneer hydrogen fuel injection block 3, and the fuel injection blocks are distributed, so that the high-efficiency mixing of the fuel and the incoming air is facilitated. The fuel injection block, the air jet tool block 5, the spark plug 4 and the pioneer hydrogen fuel injection block 3 are detachably connected with the engine shell through bolts or screws, so that the fuel injection block, the air jet tool block 5, the spark plug 4 and the pioneer hydrogen fuel injection block 3 can be quickly disassembled and assembled conveniently.
The fuel used by the scramjet engine model 1 was kerosene, and the engine model 1 was mounted in a direct-coupled test under incoming flow conditions of an inlet mach number Ma of 2.0, a total temperature Pt of 950k, and a total pressure Pt of 0.8 MPa. The effective time of the experiment is about 400ms, and the time of each time sequence in the experiment process is respectively as follows: the flow field was established for 0.89s, the pioneer hydrogen (used to ignite the kerosene) was injected for 0.93s, the air jet started for 0.96s, the kerosene was injected for 1.02s, the pioneer hydrogen and jet stopped for 1.18s, and the kerosene was shut off at 1.50 s.
The schlieren is used to reflect the wavelike structure in the flow field, and figures 2 and 3 show the schlieren of the flow field with and without jet air injection, respectively. Fig. 2 shows that when air injection is not performed, two oblique shock waves exist in only the region of the cavity 2 in the flow field, and no wave system exists in the region of the flow field behind the cavity 2; fig. 3 shows the wave structure of the flow field during the air jet injection, and it can be seen from the figure that not only are two oblique shock waves present in the region of the cavity 2, but also oblique shock waves are still present in the region behind the cavity 2, which are generated by the action of the air jet. Because the wave system structures in the two flow fields are different, the thermodynamic parameters in the flow fields are different. Fig. 4 shows the curves of the mass-weighted mach number and temperature obtained in the numerical simulation process, and it can be seen from the graph that when the air jet acts on the flow field (with air throtting), the temperature in the flow field increases and the mach number (velocity) decreases. The starting ignition time of the engine is different due to different thermodynamic parameters in the flow field. The start ignition timing of the engine can be obtained from the wall pressure curve variation law, and is generally considered to be the time period from the beginning of the pressure curve climbing to the basic stability. As can be seen from fig. 5, the start-up ignition time of kerosene in the engine is about 5ms with the aid of air jets; the kerosene starting ignition time in the engine without air jet was about 13ms, which was found to be more than doubled by comparison with the air throttle. Because of different starting ignition time, the combustion intensity is different, and the flame distribution in the flow field is naturally different. Fig. 6 and 7 show the flame distribution in the flow field when no air jet injection is performed and when no air jet injection is performed, respectively, and it can be seen from the white areas in the figures that the flame is in the shape of a flame, and when no air jet injection is performed, the flame is weak and only distributed in the cavity 2, and the lower wall surface is either not combusted or is weak; the flame distribution in the engine implementing the air jet is wide, the whole cavity 2 area squats on the flame and has already been wound around the front of the cavity 2.
Through the comparative test in the embodiment, the air is injected into the supersonic flow channel of the scramjet engine through jet flow, a shock wave string structure is generated, the flow field structure is changed, the flow field thermodynamic parameters of a combustion chamber can be influenced, the temperature and the pressure of main flow air are improved, the Mach number (speed) is reduced, the efficient mixing of fuel and air is enhanced, and the purpose of promoting the scramjet engine to start and ignite is further achieved.
The above is an embodiment of the present invention. The embodiments and specific parameters in the embodiments are only for the purpose of clearly illustrating the verification process of the invention and are not intended to limit the scope of the invention, which is defined by the claims, and all equivalent structural changes made by using the contents of the specification and the drawings of the present invention should be covered by the scope of the present invention.
Claims (7)
1. A method of facilitating starting ignition of a scramjet engine, comprising: air is injected into the engine in a direction perpendicular to the air flow direction on one side of the inner wall surface of the flame stabilizer of the scramjet engine, the air flow is 15% -30% of the air flow of an engine inlet, and the length of the air injection position from the position of the flame stabilizer of the engine is 10% -20% of the total length of the engine.
2. An apparatus for facilitating starting ignition of a scramjet engine, the apparatus being adapted to implement the method for facilitating starting ignition of a scramjet engine as recited in claim 1, wherein: the flame stabilizer is arranged at the front end of a combustion chamber of the scramjet engine, a plurality of fuel oil injection blocks are arranged on the flame stabilizer, a plurality of spray holes communicated with a fuel conveying device are arranged on the fuel oil injection blocks, and the spray holes vertically face to an inner cavity of the flame stabilizer; the air jet flow tool block (5) for vertically jetting air into the combustion chamber of the engine is arranged on the combustion chamber, the length of the air jet flow tool block (5) from the flame stabilizer is 10% -20% of the total length of the engine, and a spark plug (4) is arranged in the flame stabilizer.
3. The device for promoting the scramjet engine to realize the starting ignition according to the claim 2, characterized in that: a support plate is arranged on the upper wall surface of the flame stabilizer, and the spark plug (4) is located at the rear end of the support plate.
4. The device for promoting the scramjet engine to realize the starting ignition according to the claim 2, characterized in that: the upper wall surface of the flame stabilizer is provided with a concave cavity (2), and the spark plug (4) is positioned on the concave cavity (2).
5. The device for promoting the starting ignition of the scramjet engine according to any one of claims 2 to 4, wherein: and a pioneer hydrogen fuel injection block (3) positioned at the upstream of the spark plug (4) is arranged on the flame stabilizer.
6. The device for promoting the scramjet engine to realize the starting ignition according to the claim 5, characterized in that: the number of the fuel injection blocks is four, the fuel injection blocks are respectively arranged on the upper wall surface or the lower wall surface of the flame stabilizer, and one fuel injection block is positioned on the upstream of the pioneer hydrogen fuel injection block (3).
7. The device for promoting the scramjet engine to realize the starting ignition according to the claim 5, characterized in that: the fuel injection block, the air jet flow tool block (5), the spark plug (4) and the pioneer hydrogen fuel injection block (3) are detachably connected with the engine shell through bolts or screws.
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| CN202010829851.2A CN111998387A (en) | 2020-08-18 | 2020-08-18 | Method and device for promoting scramjet engine to realize starting ignition |
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| CN202010829851.2A CN111998387A (en) | 2020-08-18 | 2020-08-18 | Method and device for promoting scramjet engine to realize starting ignition |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113137634A (en) * | 2021-06-02 | 2021-07-20 | 厦门大学 | Variable-structure bimodal stamping combustion chamber |
| CN113339844A (en) * | 2021-06-22 | 2021-09-03 | 西安航天动力研究所 | Air hydrogen injection unit and combustion organization method thereof |
| CN115751375A (en) * | 2022-10-09 | 2023-03-07 | 哈尔滨工业大学 | Supersonic speed stable combustion supporting plate for assisting enhanced combustion of electrolyzed water |
| CN116146352A (en) * | 2023-04-23 | 2023-05-23 | 中国空气动力研究与发展中心空天技术研究所 | Ultrafiltration ramjet engine spanwise non-uniform fuel pulse injection device and use method |
| CN116181525A (en) * | 2023-02-07 | 2023-05-30 | 中国人民解放军32804部队 | Device and method for enhancing fuel spray characteristics and chemical activity |
| CN116221778A (en) * | 2023-02-28 | 2023-06-06 | 中国人民解放军32804部队 | Supersonic combustion chamber plasma ignition device and method based on boundary layer air entraining |
| CN116293802A (en) * | 2023-03-14 | 2023-06-23 | 中国空气动力研究与发展中心空天技术研究所 | Super-combustion ramjet engine combustion chamber based on shock wave system ignition and backflow flame stabilization |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113137634A (en) * | 2021-06-02 | 2021-07-20 | 厦门大学 | Variable-structure bimodal stamping combustion chamber |
| CN113137634B (en) * | 2021-06-02 | 2022-04-26 | 厦门大学 | Variable-structure bimodal stamping combustion chamber |
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| CN115751375A (en) * | 2022-10-09 | 2023-03-07 | 哈尔滨工业大学 | Supersonic speed stable combustion supporting plate for assisting enhanced combustion of electrolyzed water |
| CN115751375B (en) * | 2022-10-09 | 2024-05-10 | 哈尔滨工业大学 | Supersonic steady combustion support plate for assisting enhanced combustion of electrolyzed water |
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| CN116181525B (en) * | 2023-02-07 | 2023-08-15 | 中国人民解放军32804部队 | Device and method for enhancing fuel spray characteristics and chemical activity |
| CN116221778A (en) * | 2023-02-28 | 2023-06-06 | 中国人民解放军32804部队 | Supersonic combustion chamber plasma ignition device and method based on boundary layer air entraining |
| CN116221778B (en) * | 2023-02-28 | 2023-09-01 | 中国人民解放军32804部队 | Supersonic combustion chamber plasma ignition device and method based on boundary layer air entraining |
| CN116293802A (en) * | 2023-03-14 | 2023-06-23 | 中国空气动力研究与发展中心空天技术研究所 | Super-combustion ramjet engine combustion chamber based on shock wave system ignition and backflow flame stabilization |
| CN116293802B (en) * | 2023-03-14 | 2024-05-14 | 中国空气动力研究与发展中心空天技术研究所 | Super-combustion ramjet engine combustion chamber based on shock wave system ignition and backflow flame stabilization |
| CN116146352B (en) * | 2023-04-23 | 2023-08-18 | 中国空气动力研究与发展中心空天技术研究所 | Ultrafiltration ramjet engine spanwise non-uniform fuel pulse injection device and use method |
| CN116146352A (en) * | 2023-04-23 | 2023-05-23 | 中国空气动力研究与发展中心空天技术研究所 | Ultrafiltration ramjet engine spanwise non-uniform fuel pulse injection device and use method |
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Application publication date: 20201127 |