CN108488004B - Stationary detonation engine based on variable wedge angle - Google Patents
Stationary detonation engine based on variable wedge angle Download PDFInfo
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- CN108488004B CN108488004B CN201810072297.0A CN201810072297A CN108488004B CN 108488004 B CN108488004 B CN 108488004B CN 201810072297 A CN201810072297 A CN 201810072297A CN 108488004 B CN108488004 B CN 108488004B
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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
- F02K7/02—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 the jet being intermittent, i.e. pulse-jet
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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
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
Abstract
The invention discloses a stationary detonation engine based on a variable wedge angle, comprising: the air inlet channel enables incoming flow to generate oblique shock waves so as to increase pressure and temperature; the oblique detonation combustion chamber is used for accommodating incoming flow and fuel mixture and inducing an oblique shock wave through an oblique wedge surface at the rear part so as to ignite mixed gas to generate an oblique detonation wave; the combustion products generated in the combustion chamber further expand and accelerate in a flow passage of the tail nozzle; a fuel injection and atomization system that injects fuel at the front of the combustion chamber to promote mixing of the fuel with the incoming flow while preventing pre-combustion of the incoming flow; the oblique wedge angle control system adjusts the shapes of oblique wedge surface angles and the like in real time according to the pneumatic state of mixed gas of the combustion chamber, so that oblique detonation waves are just fixed at the inlet of the tail nozzle. The invention controls the combustion of mixed gas to be stabilized in the oblique detonation state through the oblique wedge surface control device at the rear part of the combustion chamber, thereby ensuring that the combustion is basically in the optimal state, optimizing the thrust performance of the engine and achieving the effect that the engine can continuously work under the condition of variable working conditions.
Description
Technical Field
The invention relates to a stationary detonation engine based on a variable wedge angle, and belongs to the technical field of supersonic engines.
Background
The power solution of the prior hypersonic aircraft is a difficult problem troubling researchers in many countries, and one of the widely accepted solutions at present is a supersonic combustion ramjet engine, the working principle of which is the characteristic that the total pressure of supersonic airflow is very high, supersonic airflow is introduced into a combustion chamber of the engine to be mixed with fuel for combustion, and combustion products are discharged through a tail nozzle at supersonic speed, so that thrust is generated.
This concept of using the nature of the airflow to simplify the engine structure is good, but also has significant limitations. Experimental results show that the accelerations obtained by the aircraft after the engine has started to operate are very limited, that is to say the scramjet engine is not able to provide a high margin of thrust, on the one hand because when the flight mach number is large to a certain extent, the kinetic energy of the incoming flow is substantially equal to or even exceeds the energy that can be released by complete combustion of the fuel, as can be seen from thermodynamic analysis, at which the thermodynamic efficiency of the engine is too low, and on the other hand, during the scramjet of hypersonic incoming flow, there is a considerable irreversible dissipation of the kinetic energy of the incoming flow to the pressure energy, which greatly limits the research progress of the scramjet engine. It is therefore necessary to search for a more optimal power solution.
In recent years, due to the advantages of higher thermal cycle efficiency, wider flight mach number and the like, the shock-induced composite flame ramjet (schramjet for short) technology gradually draws attention and researches. The technology takes detonation waves as a main combustion mode, the propagation speed of the detonation waves can reach the level of thousands of meters per second, and because no time is available for pressure balance, the combustion process is close to an isochoric process, so that the combustion thermal efficiency is higher than that of a super-combustion isobaric process, and the technology becomes an optimal mode in a currently known supersonic combustion mode. Based on this concept, some scholars propose a stationary oblique knock engine (ODWE). Compared with a scramjet engine, the ODWE has higher propelling efficiency under the condition of higher flying speed, and has a simpler structure and smaller volume, so the ODWE gradually becomes a main research scheme of hypersonic propelling.
In the structural design of ODWE, a great deal of research is carried out on the deformation boundary technology at home and abroad aiming at the complex working conditions such as variable working conditions, variable circulation and the like so as to adapt to the change of various flight conditions. For the working condition of the shrramjet at the non-design point, in order to obtain strong enough shock waves to induce the combustion and explosion shock waves, the traditional method is to adopt an added bluff body to generate the shock waves to ensure that the combustion and explosion shock waves are induced, and the secondary shock waves of the bluff body are induced to burn as a flame stabilizing means. This practice increases the combustion losses and is also technically less controllable, with a greater impact on the overall performance of the system. Therefore, a flexible combustion chamber that can adapt to variable operating conditions and induce a sufficiently strong detonation wave while maintaining low combustion losses must be explored. The present invention has been made based on this idea.
Disclosure of Invention
The purpose of the invention is as follows: in order to overcome the defects in the prior art, the invention provides a stationary detonation engine based on a variable oblique wedge angle, and combustion of mixed gas is excited and controlled to be stabilized in an oblique detonation state through an oblique wedge surface control device at the rear part of a combustion chamber, so that the combustion is basically in an optimal state, the thrust performance of the engine is optimized, the effect that the engine can continuously work under the condition of variable working conditions is achieved, and a feasible solution is provided for engineering application.
The technical scheme is as follows: in order to achieve the purpose, the invention adopts the technical scheme that:
a variable-cammed-wedge-angle-based standing detonation engine, comprising:
the air inlet channel is used for acting with incoming flow to generate shock waves so as to compress air and improve the incoming flow temperature and pressure of the inlet of the oblique detonation combustor;
the oblique detonation combustion chamber is divided into a front half section and a rear half section, the front half section is communicated with an outlet of the air inlet channel, incoming flow is mixed with fuel in the front half section, the rear half section is provided with an oblique wedge surface control device, mixed gas passes through the front half section to form oblique shock waves, and oblique shock wave induction is performed to initiate oblique detonation combustion;
the tail nozzle is communicated with the outlet of the combustion chamber, and combustion products generated in the combustion product combustion chamber further expand and accelerate in a flow passage of the tail nozzle to provide power for the aircraft;
the fuel injection and atomization system comprises a fuel injection and atomization device, wherein the fuel injection and atomization device is used for measuring the incoming flow state of an inlet of a combustion chamber in advance, then the controller is used for calculating the optimal fuel injection speed and angle required on the premise of enhancing the mixing effect and avoiding pre-combustion according to the incoming flow state, and further the fuel injection and atomization device is used for realizing the injection of fuel;
the wedge surface control system comprises a wedge surface control device, a gas state detector and a controller, wherein the gas state detector is used for measuring the gas mixing state of the combustion chamber in advance, then the controller is used for calculating the forms of the wedge surface angle and the like which can induce oblique detonation waves under the condition according to the gas mixing state and enable the oblique detonation waves to be fixed at the outlet of the combustion chamber, and then the wedge surface is adjusted in real time through the wedge surface control device;
the oblique detonation wave feedback system comprises an oblique detonation wave detector, the oblique detonation wave is measured by the oblique detonation wave detector to irradiate the position of the upper wall surface of the oblique detonation combustion chamber, and the position signal is transmitted to a controller, so that the state feedback of the oblique detonation wave is formed.
The variable-wedge-angle-based stationary detonation engine is mainly technically characterized in that the form of a wedge surface is adjusted according to the variation of incoming flow and gas mixing parameters, the stable self-sustaining of oblique detonation waves under variable working conditions is realized, the structure of a combustion chamber is greatly simplified, and the loss is reduced. The internal flow passage of the engine may be of any closed or non-closed shape when viewed in cross-section perpendicular to its axis, and has an inlet and an outlet.
Furthermore, the air inlet channel is internally provided with an inclined or bent channel.
Further, the fuel injection and atomization device can be single or multiple and is arranged on the inner wall of the oblique detonation combustion chamber close to the inlet of the combustion chamber.
Furthermore, the wedge surface control device comprises two wedge surfaces and a telescopic supporting rod positioned at the lower parts of the two wedge surfaces, and the two wedge surfaces, the telescopic supporting rod and the corresponding wedge surface and the telescopic supporting rod and the lower controller are all linked in a hinge mode; the controller controls and realizes the adjustment of forms such as the angle of the wedge surface through the stretching and the rotation of the telescopic supporting rod, and the wedge surface is kept in closed connection with the lower wall surface of the channel while changing the forms.
Furthermore, the oblique detonation wave detector is arranged on one side, close to the outlet of the combustion chamber, of the upper wall surface of the oblique detonation combustion chamber.
Furthermore, the gas state detector is arranged on the inner wall of the inclined detonation combustion chamber in front of the inclined wedge surface control device and mainly detects physical parameters of mixed gas on the upstream of the inclined wedge surface.
Furthermore, the tail nozzle forms an expanding channel, and high-temperature and high-pressure fuel gas generated by the combustion chamber is expanded and accelerated through the tail nozzle, so that thrust is generated.
Has the advantages that: compared with the prior art, the stationary detonation engine based on the variable wedge angle has the following advantages that: 1. by adopting a control system based on the variable wedge angle, the real-time dynamic change of the wedge surface can be realized according to the change of the inflow parameters, so that the stationary adjustment of the oblique detonation wave is realized;
2. the detonation type is adopted to organize combustion, the combustion distance is short, so that the length of a combustion chamber can be greatly shortened, the structural weight of the engine is effectively reduced, and various losses caused by wall surface friction are reduced;
3. the oblique shock wave is adopted to induce the oblique detonation wave for ignition, so that an ignition device of the traditional engine is omitted, and the weight and the structural complexity of the oblique detonation engine are reduced;
4. the range of flight Mach number can be widened by adopting detonation combustion, and the current Mach number upper limit of the traditional engine and the scramjet engine is greatly broken through;
5. combustion is organized in an oblique detonation mode, entropy increase and total pressure loss can be greatly reduced, and therefore the thrust performance of the engine is further optimized.
Drawings
FIG. 1 is a schematic structural diagram of an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a wedge angle control system according to an embodiment of the present invention;
the figure includes: A. the device comprises an air inlet channel, a B oblique detonation combustion chamber, a B1 combustion chamber inlet, a B2 combustion chamber outlet, a C exhaust nozzle, a 1 fuel injection and atomization device, a 2 gas state detector, a 3 controller, a 4 oblique detonation wave detector, a 5 oblique wedge surface control device, a 6 telescopic supporting rod.
Detailed Description
The present invention will be further described with reference to the accompanying drawings and examples.
FIG. 1 shows a variable cam angle based standing detonation engine, comprising: the detonation combustor comprises an air inlet passage A, a detonation combustion chamber B and a tail nozzle C, wherein the air inlet passage A is designed into an inclined or bent passage structure, so that incoming air entering the air inlet passage A can generate inclined shock waves, and different structures such as waverider structures of two shock waves, three shock wave structures and the like can be selected according to different design indexes. The detonation combustor B is provided with a combustor inlet B1 and a combustor outlet B2, wherein the combustor inlet B1 is communicated with the outlet of the air inlet passage A, and the combustor outlet B2 is communicated with the inlet of the tail nozzle C.
In this embodiment, the structure further includes a fuel injection and atomization device 1, a gas state detector 2, a controller 3, an oblique detonation wave detector 4, an oblique wedge surface control device 5, and a telescopic support rod 6. The fuel injection and atomization device 1 is disposed on the wall surface of the front section of the detonation combustion chamber B, through which fuel is rapidly injected and atomized and uniformly mixed with the incoming high-speed gas, and the number of devices, the relative position relationship of the devices and the specific implementation mode are different according to the functions. The oblique wedge surface control device 5 is positioned at the rear end of the detonation combustion chamber B, namely the outlet B2 of the combustion chamber, the rear edge of the oblique wedge surface control device is connected with the lower edge of the inlet of the tail nozzle C, high-speed mixed gas forms stationary oblique detonation waves at an oblique wedge angle, the mixed gas releases energy in a detonation combustion mode through the oblique detonation waves, and combustion products expand in advance at the rear edge of the oblique wedge angle and then enter the tail nozzle C.
The operation of a standing detonation engine based on variable camwedge angle according to an embodiment of the invention is described below with reference to fig. 1.
Hypersonic incoming flow enters the air inlet channel A, multiple oblique shock waves are formed in the air inlet channel A, and through compression of the oblique shock waves, air flow is decelerated and pressurized, and meanwhile static temperature rises. The gas flow then enters the combustion chamber B and the fuel injection and atomization system ejects fuel according to the incoming flow specifications. Studies have shown that both too high and too low stoichiometric ratios of the incoming air mixture cause a loss of performance in the engine, and ideally the stoichiometric ratio of the incoming air mixture is around 1. At the same time, due to the high temperature and pressure of the air stream upon reaching the combustion chamber inlet, proper fuel injection rates and angles are required to avoid pre-combustion of the mixture. Therefore, the fuel injection and atomization system firstly measures the airflow state at the inlet of the combustion chamber, the controller 3 calculates the optimal fuel injection speed and angle under the two conditions of enhancing the mixing effect and avoiding pre-combustion, and then the fuel injection is carried out.
In the front section of the combustion chamber B, the incoming flow and the fuel are sufficiently mixed. In the rear section, oblique shock waves fixed on the oblique wedge surfaces are initiated at the oblique wedge surfaces in the combustion chamber B by high-speed gas mixing, the gas flow is further decelerated and pressurized after the oblique shock waves, simultaneously, the static temperature is further increased, the detonation combustion of the gas mixing is initiated due to the sudden increase of the gas mixing activation energy of the fuel in a short time, and the shock wave induced combustion waves are generated after the shock waves. As the mixed gas energy is further released, the combustion wave increasingly lifts upstream and couples with the shock wave over a very small scale, thereby generating a squint wave that resides on the cammed surface. High-temperature and high-pressure fuel gas generated after the incoming mixed gas is subjected to detonation combustion is further expanded and accelerated through the tail nozzle C, so that thrust required by the aircraft is generated.
The variable-wedge-angle-based stationary detonation engine provided by the embodiment of the invention has the key technology that the angle of the oblique detonation wave is stabilized in a certain proper range, so that the pneumatic loss caused by the impact of the oblique detonation wave on the upper wall surface due to the overlarge angle of the oblique detonation wave or the chemical energy loss caused by the fact that unburnt mixed gas enters the tail nozzle due to the undersize angle of the oblique detonation wave are avoided, and the higher requirement is provided for the control of the angle of the oblique wedge surface. The working principle of the cambering control system is described below with reference to fig. 2.
When the inlet inflow state of the combustion chamber B changes, the state of the oblique detonation wave is necessarily changed, and the sensitive airflow state detector 2, the controller 3 and the oblique detonation wave detector 4 are required for restraining the change. Fig. 2 shows a wedge surface control system based on a telescopic supporting rod. Between two slide wedge faces, all can link through the hinge mode between slide wedge face and the scalable bracing piece 6, the structure of constituteing like this can realize the two-dimensional morphological change of slide wedge face, promptly: when the parameters of the incoming flow change, a gas state detector 2 arranged at the front end of the inclined wedge surface measures various parameters of the incoming flow gas in advance, a controller 3 at the lower end of the inclined wedge surface calculates inclined detonation waves which can be induced under the conditions through the parameters, the inclined detonation waves are made to be just radiated to the inclined wedge surface angle and other forms required by the connection point of the combustion chamber and the tail nozzle, then the controller operates the support rod assembly to make the inclined wedge surface reach the required forms, then the inclined detonation wave detector 4 measures the positions of the inclined detonation waves radiated to the upper wall surface, position signals are fed back to the controller 3, if the formed inclined detonation positions are not consistent with the calculation, the support rod assembly is continuously operated to adjust the inclined wedge surface forms, the forms of the inclined detonation waves are changed, and the operation is repeated in such a circulating mode until the inclined detonation waves approximately meet the calculation requirements.
The above description is only of the preferred embodiments of the present invention, and it should be noted that: it will be apparent to those skilled in the art that various modifications and adaptations can be made without departing from the principles of the invention and these are intended to be within the scope of the invention.
Claims (4)
1. A variable-cammed-wedge-angle based standing detonation engine, comprising:
the air inlet channel enables incoming flow to generate oblique shock waves so as to increase pressure and temperature;
the oblique detonation combustion chamber is communicated with an outlet of the air inlet channel, accommodates incoming flow and fuel to be mixed, and induces an oblique shock wave through an oblique wedge surface at the rear part so as to ignite mixed gas to generate oblique detonation waves;
the tail nozzle is communicated with the outlet of the combustion chamber, and combustion products generated in the combustion chamber further expand and accelerate in a flow passage of the tail nozzle to provide power for the aircraft;
the fuel injection and atomization system comprises a fuel injection and atomization device (1), wherein the fuel injection and atomization device (1) measures the incoming flow state of an inlet of a combustion chamber in advance, then a controller (3) calculates the optimal fuel injection speed and angle required on the premise of enhancing the mixing effect and avoiding pre-combustion according to the incoming flow state, and then the fuel injection and atomization device (1) is used for realizing the injection of fuel;
the wedge surface control system comprises a gas state detector (2), a controller (3) and a wedge surface control device (5), wherein the gas state detector (2) detects the gas mixing state of a combustion chamber in advance, then the controller (3) calculates the wedge surface form capable of inducing oblique detonation waves according to the gas mixing state, the oblique detonation waves are fixed at the outlet of the combustion chamber, and then the wedge surface form is adjusted in real time through the wedge surface control device (5);
the oblique detonation wave feedback system comprises an oblique detonation wave detector (4), the position of the oblique detonation wave emitted to the upper wall surface of the oblique detonation combustion chamber is measured by the oblique detonation wave detector (4), and a position signal is transmitted to a controller (3), so that the state feedback of the oblique detonation wave is formed;
the wedge surface control device (5) comprises two wedge surfaces and a telescopic support rod (6) positioned at the lower parts of the two wedge surfaces, and the two wedge surfaces, the telescopic support rod (6) and the corresponding wedge surface, and the telescopic support rod (6) and the lower controller (3) are connected in a hinge mode; the controller (3) realizes the adjustment of the shape of the wedge surface through the telescopic control of the telescopic supporting rod (6), and the wedge surface is kept in closed connection with the lower wall surface of the channel while changing the shape;
the oblique detonation wave detector (4) is arranged on one side, close to the outlet of the combustion chamber, of the upper wall surface of the oblique detonation combustion chamber;
and the gas state detector (2) is arranged on the inner wall of the inclined detonation combustion chamber in front of the inclined wedge surface control device (5).
2. The variable wedge angle based resident detonation engine of claim 1, wherein the inlet duct has a slanted or curved passage therein.
3. The variable-wedge-angle-based stationary detonation engine according to claim 1, characterized in that the fuel injection and atomization device (1) can be single or multiple and is arranged on an inner wall of a side of the inclined detonation combustion chamber close to a combustion chamber inlet.
4. The variable wedge angle based resident detonation engine of claim 1, wherein the jet nozzle forms a diverging passageway.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109114591A (en) * | 2018-07-25 | 2019-01-01 | 南京理工大学 | It is a kind of to change the combustion chamber for realizing detonation control by wall angle |
| CN111608820A (en) * | 2020-04-30 | 2020-09-01 | 南京理工大学 | Wedge surface structure for controlling oblique detonation waves by utilizing local large-angle wedge surface |
| CN112211749A (en) * | 2020-09-18 | 2021-01-12 | 西北工业大学 | Small solid rocket engine |
| 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 |
| CN113048515A (en) * | 2021-04-08 | 2021-06-29 | 中国人民解放军国防科技大学 | Combustion chamber, engine and aircraft based on supersonic stamping oblique detonation |
| CN114673606B (en) * | 2022-03-29 | 2023-10-17 | 北京理工大学 | Oblique detonation engine adopting plug type spray pipe |
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| JPH07247906A (en) * | 1994-03-07 | 1995-09-26 | Mitsubishi Heavy Ind Ltd | Propulsion device for missile |
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