CN108869095B - Boundary suction control method with stable and self-sustaining supersonic detonation - Google Patents
Boundary suction control method with stable and self-sustaining supersonic detonation Download PDFInfo
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- CN108869095B CN108869095B CN201810627038.XA CN201810627038A CN108869095B CN 108869095 B CN108869095 B CN 108869095B CN 201810627038 A CN201810627038 A CN 201810627038A CN 108869095 B CN108869095 B CN 108869095B
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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
- F02K7/14—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 with external combustion, e.g. scram-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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
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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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
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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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/35—Combustors or associated equipment
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Abstract
The invention provides a supersonic detonation stable self-sustaining boundary suction control method, wherein a scramjet engine in the method comprises an air inlet channel, an isolation section, a combustion chamber and a supersonic jet pipe, wherein a heat jet hole for jetting out heat jet flow in a heat jet pipe is arranged in the combustion chamber, a plurality of suction holes are formed in the inner walls of the combustion chamber at the front and rear of the heat jet hole, and all the suction holes are communicated with a suction pump through pipelines; when the hot jet is used for knocking in supersonic air flow and detonating, the suction pump and the suction hole are used for sucking the air flow of the boundary layer in the combustion chamber in a suction mode, and meanwhile the hot jet is sprayed to realize detonation. When detonation is initiated, the suction pump is started, and air flow in a boundary layer low-speed area in the combustion chamber is sucked through the suction hole, so that the interaction of detonation wave and the boundary layer is restrained from generating combustion front transmission, the influence of the boundary layer on the detonation of the detonation wave is eliminated, and the detonation wave can realize dynamic stable transmission in the combustion chamber.
Description
Technical Field
The invention relates to the technical field of self-sustained propagation control of detonation waves in supersonic airflow, in particular to a method for realizing dynamic stable self-sustained propagation of detonation waves in supersonic airflow, which provides a feasible design scheme for realizing complete detonation combustion in a detonation engine.
Background
Scramjet engines (Scramjet) perform well under high mach (Ma > 5) flight conditions and have become the preferred option for hypersonic aircraft propulsion systems. However, in combination with current research and the U.S. X-51A flight test, it is known that the acceleration performance of the scramjet validator is not significant and the net thrust is small. Therefore, based on the current research, improvement of engine thrust performance is urgently required. The scramjet engine is designed according to the Brayton isobaric combustion cycle, whose thermodynamic cycle efficiency is much lower than that of detonation combustion, which approximates an isochoric cycle. Thus, if knocking combustion, even partial knocking combustion, can be achieved in the supersonic air flow, the thrust performance of the engine is highly likely to be greatly improved.
Scramjet engines have gradually moved to engineering applications, but new scramjet engine concept designs based on detonation combustion have not been reported. With relatively sophisticated engineering experience of scramjet engines, using detonation combustion in the combustion chamber instead of an isobaric combustion mode enables a detonation-based combustion engine to be implemented as quickly as possible relative to other types of detonation engines. Han Xu et al Cai Xiaodong et al Liang Jianhan et al and Chen Weijiang et al developed experimental and numerical simulation studies for detonation by using thermal jet in supersonic gas flow, which helped to deepen understanding of detonation in supersonic gas flow in combustion chamber. In these basic studies, a separate fuel and oxidizer supply hot jet tube was used for hot jet injection and ignition initiation, without regard to specific engine applications. In addition, for dynamic stability control of knocking in supersonic airflow, cai Xiaodong et al have conducted numerical simulation studies, demonstrating that the thermal jet injection can achieve a dynamic stability control function of knocking in supersonic airflow to a certain extent, but does not involve a specific thermal jet control method.
In the prior art, the influence of a boundary layer in a combustion chamber of a detonation base engine is quite obvious, and in the process of igniting and detonating detonation combustion waves by using hot jet, shock waves and the boundary layer interact, so that the detonation strength is weakened, detonation waves after detonation are transmitted forward due to the influence of the boundary layer, the effective utilization of the detonation waves is seriously influenced, and the thrust performance of the engine is reduced.
Disclosure of Invention
Aiming at the defects in the background technology, the invention provides a boundary suction control method with stable and self-sustaining supersonic detonation. The invention aims at the super-combustion ramjet engine with the detonation base, optimizes the structural scheme of the thermal jet detonation wave, and realizes the effective detonation and residence of the detonation wave.
A supersonic detonation stable self-sustaining boundary suction control method comprises an air inlet channel, an isolation section, a combustion chamber and a supersonic jet pipe, wherein a heat jet hole for jetting hot jet in a heat jet pipe is arranged in the combustion chamber of the supersonic detonation stable self-sustaining boundary suction control method, a plurality of suction holes are formed in the inner walls of the combustion chamber in front of and behind the heat jet hole, and all the suction holes are communicated with a suction pump through pipelines;
when the hot jet is used for knocking in supersonic air flow and detonating, the suction pump and the suction hole are used for sucking the air flow of the boundary layer in the combustion chamber in a suction mode, and meanwhile the hot jet is sprayed to realize detonation. According to the invention, the suction hole is formed in the inner wall surface of the combustion chamber, the suction pump is started during detonation, and the air flow in the boundary layer low-speed area in the combustion chamber is sucked through the suction hole, so that the interaction of detonation wave and the boundary layer is restrained from generating combustion front transmission, the influence of the boundary layer on the detonation of the detonation wave is eliminated, and the detonation wave can realize dynamic stable transmission in the combustion chamber.
Further, in the present invention: in the flight process, the equivalence ratio of premixed gas of the air inlet channel can be adjusted according to the supersonic incoming flow speed, so that the CJ detonation combustion speed of the detonation wave is equal to the supersonic incoming flow speed.
Further, in the present invention: when the hot jet is adopted to perform detonation in the supersonic airflow, the suction strength of the suction pump can be determined according to the supersonic incoming flow speed.
In the invention, the following components are added: the oxidant of the thermal jet pipe is air, an air inlet hole for the air to enter is formed in the upstream wall surface of the air inlet channel, and the air inlet hole is connected to the thermal jet pipe through an air inlet channel; the combustion agent of the thermal jet pipe adopts fuel carried on an aircraft; the oxidant and the combustion agent are mixed in the thermal jet pipe and then are ignited to be sprayed out through the thermal jet pipe, so that thermal jet generation is realized.
The fuel injection hole of the air inlet channel is arranged at the upstream of the air inlet channel, so that the mixing distance and time between fuel and supersonic air inflow after shock wave compression can be effectively increased. The fuel and the supersonic velocity incoming flow compressed by the shock wave form supersonic velocity premixed incoming flow in the air inlet, the supersonic velocity premixed incoming flow enters the combustion chamber through the air inlet and the isolation section, and the heat jet is sprayed into the combustion chamber to induce the formation of bow shock waves in the supersonic velocity premixed incoming flow, so that supersonic velocity premixed gas is detonated, and the resident detonation combustion wave is formed. The pressure and temperature of the gas after detonation combustion rise and enter the supersonic jet pipe to generate thrust.
A scramjet engine based on detonation combustion comprises an air inlet channel, an isolation section, a combustion chamber and a supersonic jet pipe, wherein a heat jet hole for jetting hot jet in a heat jet pipe is arranged in the combustion chamber, a plurality of suction holes are formed in the inner walls of the combustion chamber in front of and behind the heat jet hole, and all the suction holes are communicated with a suction pump through pipelines.
Further, the aperture of the suction hole is about 1/10 of the aperture of the heat jet hole.
Further, the suction holes are distributed on the inner wall of the combustion chamber in an equidistant array.
The beneficial technical effects of the invention are as follows:
in the equal-straight-pipe combustion chamber with wall suction, the detonation initiation is induced by adopting the thermal jet, the detonation wave overdriving propagation in supersonic velocity incoming flow is performed, the expansion of post products is accelerated by suction, the back pressure of the post is reduced, the overdriving degree of the detonation wave is reduced, and finally the dynamic stable self-sustaining propagation is realized. According to the invention, the detonation wave dynamic stability is finally realized through the interaction of the thermal jet flow and the suction, so that multiple detonations and detonation quenching are avoided, and the method is particularly important for realizing the combustion control of detonation in supersonic airflow.
The invention eliminates the influence of a boundary layer through the interaction of the thermal jet flow and suction, realizes the effective detonation and residence of detonation waves, effectively generates thrust, and improves the integral thrust performance of the engine.
Drawings
FIG. 1 is a schematic structural diagram of a scramjet engine based on detonation combustion;
in the figure:
1. an air inlet channel; 2. an isolation section; 3. a combustion chamber; 4. a supersonic nozzle; 5. an inlet port fuel injection hole; 6. a thermal jet aperture; 7. and a suction hole.
FIG. 2 is a schematic diagram of a detonation combustor with suction supersonic thermal jet detonation
Detailed Description
In order to make the technical scheme and advantages of the present invention more apparent, the present invention will be further described in detail with reference to the accompanying drawings and examples. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
The invention provides a supersonic detonation stable self-sustaining boundary suction control method, which can realize effective detonation of supersonic combustible gas in a combustion chamber through suction and hot jet detonation in a novel supersonic detonation ramjet engine based on detonation combustion, and ensure the resident of detonation waves, thereby finally realizing stable thrust performance.
Referring to fig. 1 and 2, fig. 1 is a schematic structural diagram of a novel scramjet engine based on detonation combustion, and fig. 2 is a schematic diagram of a detonation combustion chamber of a supersonic thermal jet detonation mode with suction effect. The novel scramjet engine based on detonation combustion mainly comprises an air inlet channel 1, an isolation section 2, a combustion chamber 3 and a supersonic jet pipe 4, wherein a heat jet hole 6 for jetting hot jet in a heat jet pipe is arranged in the combustion chamber 3, a plurality of suction holes 7 are formed in the inner walls of the combustion chamber in front of and behind the heat jet hole 6, and all the suction holes 7 are communicated with a suction pump (not shown in the figure) through pipelines, so that suction is guaranteed to be performed simultaneously and reliably. Wherein: the aperture of the suction hole 7 is about 1/10 of the aperture of the heat jet hole 6. The suction holes are distributed on the inner wall of the combustion chamber 3 in a 7 equidistant array.
In the flight process, the equivalence ratio of premixed gas of the air inlet channel can be adjusted according to the supersonic incoming flow speed, so that the CJ detonation combustion speed of the detonation wave is equal to the supersonic incoming flow speed.
When the hot jet is used for knocking and bursting in the supersonic air flow, the intensity of suction of the suction pump can be determined according to the speed of supersonic incoming flow when the hot jet is used for knocking and bursting in the supersonic air flow. And sucking the air flow of the boundary layer in the combustion chamber by a suction pump and a suction hole in a suction mode, and spraying a hot jet at the same time to realize detonation. According to the invention, the suction hole is formed in the inner wall surface of the combustion chamber, the suction pump is started during detonation, and the air flow in the boundary layer low-speed area in the combustion chamber is sucked through the suction hole, so that the interaction of detonation wave and the boundary layer is restrained from generating combustion front transmission, the influence of the boundary layer on the detonation of the detonation wave is eliminated, and the detonation wave can realize dynamic stable transmission in the combustion chamber.
In the invention, the following components are added: the oxidant of the thermal jet pipe is air, and an air inlet hole (not shown in the figure) for the air to enter is formed in the upstream wall surface of the air inlet channel, and is connected to the thermal jet pipe through an air inlet channel; the combustion agent of the thermal jet pipe adopts fuel carried on an aircraft; the oxidant and the combustion agent are mixed in the thermal jet pipe and then are ignited to be sprayed out through the thermal jet pipe, so that thermal jet generation is realized.
The fuel injection hole 5 of the air inlet channel is arranged at the upstream of the air inlet channel 1, so that the mixing distance and time between the fuel and the supersonic air inflow after shock wave compression can be effectively increased. The fuel and the supersonic velocity incoming flow compressed by the shock wave form supersonic velocity premixed incoming flow in the air inlet, the supersonic velocity premixed incoming flow enters the combustion chamber through the air inlet and the isolation section, and the heat jet is sprayed into the combustion chamber to induce the formation of bow shock waves in the supersonic velocity premixed incoming flow, so that supersonic velocity premixed gas is detonated, and the resident detonation combustion wave is formed. The pressure and temperature of the gas after detonation combustion rise and enter the supersonic jet pipe to generate thrust.
Firstly, fuel injection is carried out on the upstream wall surface of an air inlet channel, and the fuel injection and the supersonic air inflow are mixed; meanwhile, according to the incoming flow speed measured by a airspeed tube (conventionally arranged) at the front end of the aircraft, the strength of suction is determined, and the wall air flow of the combustion chamber is sucked through a suction pump and a suction hole; meanwhile, the relative dynamic stable combustion of the detonation wave in the combustion chamber is realized through the active control of the thermal jet flow according to the incoming flow condition.
According to the invention, jet detonation combustion chamber is realized by sucking the boundary layer in the scramjet ramjet based scramjet combustion, so that high-efficiency detonation wave and settlement of detonation wave can be realized in the combustion of the scramjet combustion engine, and the thrust performance of the engine is improved.
In view of the foregoing, it will be evident to those skilled in the art that these embodiments are thus presented in terms of a simplified form, and that these embodiments are not limited to the particular embodiments disclosed herein.
Claims (9)
1. A supersonic detonation stable self-sustaining boundary suction control method is characterized in that: the scramjet engine comprises an air inlet channel, an isolation section, a combustion chamber and a supersonic jet pipe, wherein a heat jet hole for jetting hot jet in a heat jet pipe is arranged in the combustion chamber, a plurality of suction holes are formed in the inner walls of the combustion chamber in front of and behind the heat jet hole, and all the suction holes are communicated with a suction pump through pipelines;
when detonation in supersonic air flow is performed by adopting the hot jet, the air flow of a boundary layer in a combustion chamber is sucked in a sucking mode through a suction pump and a suction hole, and meanwhile, the hot jet is sprayed to realize detonation;
when detonation in supersonic airflow is carried out by adopting hot jet, the suction strength of the suction pump is determined according to the supersonic incoming flow speed.
2. The supersonic detonation stabilization self-sustaining boundary suction control method of claim 1, wherein: the fuel injection hole of the air inlet channel is arranged on the upstream wall surface of the air inlet channel, the fuel and the supersonic velocity incoming flow compressed by shock waves form supersonic velocity premixed incoming flow in the air inlet channel, the supersonic velocity premixed incoming flow enters the combustion chamber through the air inlet channel and the isolation section, and the heat jet flow is injected into the combustion chamber and then induced to form bow shock waves in the supersonic velocity premixed incoming flow, so that supersonic velocity premixed gas is detonated to form resident detonation combustion waves, the pressure and the temperature of the gas after detonation combustion are raised, and the gas enters the supersonic velocity jet pipe to generate thrust.
3. The supersonic detonation stabilization self-sustaining boundary suction control method of claim 2, wherein: in the flight process, according to the ultrasonic incoming flow speed measured by the airspeed tube at the front end of the aircraft, the equivalence ratio of premixed gas in the air inlet channel is adjusted, and the CJ detonation combustion speed of the detonation wave is ensured to be equal to the ultrasonic incoming flow speed.
4. The supersonic detonation stabilization self-sustaining boundary suction control method of claim 1, wherein: the aperture of the suction hole is 1/10 of the aperture of the heat jet hole.
5. The supersonic detonation stabilization self-sustaining boundary suction control method of claim 1, wherein: the suction holes are distributed on the inner wall of the combustion chamber in an equidistant array.
6. A scramjet engine based on detonation combustion, characterized by: the device comprises an air inlet channel, an isolation section, a combustion chamber and a supersonic jet pipe, wherein a heat jet hole for jetting hot jet in a heat jet pipe is arranged in the combustion chamber, a plurality of suction holes are formed in the inner walls of the combustion chamber in front of and behind the heat jet hole, and all the suction holes are communicated with a suction pump through pipelines; when detonation in supersonic air flow is performed by adopting the hot jet, the air flow of a boundary layer in a combustion chamber is sucked in a sucking mode through a suction pump and a suction hole, and meanwhile, the hot jet is sprayed to realize detonation; when detonation in supersonic airflow is carried out by adopting hot jet, the suction strength of the suction pump is determined according to the supersonic incoming flow speed.
7. The scramjet engine based on detonation combustion of claim 6, wherein: the aperture of the suction hole is 1/10 of the aperture of the heat jet hole.
8. The scramjet engine based on detonation combustion of claim 6, wherein: the suction holes are distributed on the inner wall of the combustion chamber in an equidistant array.
9. The scramjet engine based on detonation combustion of claim 6, wherein: an upstream wall surface of the air inlet is provided with an air inlet fuel injection hole; the oxidant of the thermal jet pipe is air, an air inlet hole for the air to enter is formed in the upstream wall surface of the air inlet channel, and the air inlet hole is connected to the thermal jet pipe through an air inlet channel; the combustion agent of the thermal jet pipe adopts fuel carried on an aircraft; the oxidant and the combustion agent are mixed in the thermal jet pipe and then are ignited to be sprayed out through the thermal jet pipe, so that thermal jet generation is realized.
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| CN110566999B (en) * | 2019-09-20 | 2020-07-28 | 清华大学 | Combustion chamber thermal protection wall surface structure utilizing fuel oil self-suction sweating cooling |
| CN112761817B (en) * | 2021-01-28 | 2022-06-24 | 北京理工大学 | Oblique detonation engine combustion chamber spray pipe integrated control method and device |
| CN113062802B (en) * | 2021-04-09 | 2022-04-26 | 北京航空航天大学 | Suction type air inlet channel for separating boundary layer and modeling method thereof |
| CN114321980B (en) * | 2022-01-07 | 2023-05-16 | 中国人民解放军国防科技大学 | Injection mixing control method and device for knocking self-sustaining stability in supersonic airflow |
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| US6637187B2 (en) * | 2000-09-08 | 2003-10-28 | Techland Research, Inc. | Rotary inlet flow controller for pulse detonation combustion engines |
| RU2323247C2 (en) * | 2003-08-01 | 2008-04-27 | Дзе Проктер Энд Гэмбл Компани | Fuel for jet engine, gas turbine, rocket engine and diesel engine |
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| WO2014200605A2 (en) * | 2013-03-15 | 2014-12-18 | Transtar Group, Ltd | Core reactor and system |
| CN106460518A (en) * | 2013-11-04 | 2017-02-22 | Mbda法国简易股份公司 | Axial fluid machine and method for power extraction |
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