CN112594737B - Oblique detonation wave stationary control method and variable-geometry combustion chamber - Google Patents
Oblique detonation wave stationary control method and variable-geometry combustion chamber Download PDFInfo
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- CN112594737B CN112594737B CN202011435494.8A CN202011435494A CN112594737B CN 112594737 B CN112594737 B CN 112594737B CN 202011435494 A CN202011435494 A CN 202011435494A CN 112594737 B CN112594737 B CN 112594737B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
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- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N5/00—Systems for controlling combustion
- F23N5/26—Details
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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
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Abstract
The invention provides an oblique detonation wave stationary control method and a variable geometry combustion chamber, wherein an engine in the method comprises an air suction type air inlet channel, the variable geometry combustion chamber, a tail nozzle and a control system; the combustion chamber comprises an adjustable inner wall and a fixed outer wall, and is designed in an integrated manner by adopting a geometric structure; the front part of the inner wall is connected with an air inlet channel, a movable inflection point and a rear tail nozzle; supersonic combustible gas gets into the combustion chamber through the intake duct compression, produces oblique detonation wave through the oblique blasting of outer wall second to give monitored signal transmission for output control module with the contained angle between the section around the adjustment combustion chamber inner wall, the expansion angle of the mobile inflection point position of control and jet-tail pipe, form sustainable resident oblique detonation wave in the messenger combustion chamber, the detonation combustion products gets into the supersonic velocity jet-pipe, produces thrust. The invention can effectively control the movement interval of the detonation position, automatically control the optimization of the path, reduce the difficulty of improvement and expansion in engineering application, has more flexible space design and improves the operability of practical application.
Description
Technical Field
The invention relates to the technical field of air-breathing hypersonic propulsion, in particular to a method for controlling the setting of oblique detonation waves. In addition, the invention also relates to a variable geometry combustion chamber based on the oblique detonation wave stationary control method.
Background
One of the important development directions of hypersonic aircraft is higher flight mach number and greater maneuverability. This puts higher demands on the performance of the aircraft propulsion system. However, the conventional power technology cannot meet the requirement of hypersonic flight at present. According to the thermodynamic theory analysis, the pressure of the heat release area is improved, and the method has obvious effect on improving the performance of various engines. The detonation combustion improves the pressure of a heat release area through shock wave compression, and can realize higher thermal cycle efficiency in principle.
In recent decades, researchers have proposed three propulsion schemes based on detonation combustion: pulse detonation, rotational detonation, and oblique detonation, and extensive research on related problems has been conducted. The oblique detonation can organize combustion in the hypersonic incoming flow, and the technical breakthrough of air-breathing hypersonic propulsion with the Mach number of 10 or above is hopeful to be realized. Conventional engine configurations and combustion organization approaches are no longer suitable due to the introduction of detonation waves in the combustion chamber.
The technical difficulty in organizing oblique detonation combustion comes from two aspects: stable ignition and stable detonation wave. The problem that oblique detonation waves possibly caused by unsteady inflow lower combustion chamber inner walls cannot be fixed in combustion is solved. The prior art discloses a plurality of schemes, and the basic ideas can be summarized into three types: 1. adjusting the unsteady incoming flow to a quasi-steady state; 2. adopting a configuration without an inner wall; 3. and controlling the interaction position of the oblique detonation wave and the inner wall.
Based on the prior art scheme provided by the idea 1, an additional control system is often required to be arranged to suppress the unsteady state of the incoming flow and realize the active control of the incoming flow so as to keep the incoming flow within the design combustion chamber in a stationarity range. The scheme is forced to arrange a large amount of additional equipment, and the self weight and the design complexity of the engine are inevitably increased; based on the scheme provided by the idea 2, a new combustion chamber configuration is provided, the influence of the inner wall on oblique detonation waves in a constant incoming flow environment is eliminated, however, in the face of unsteady incoming flow, the applicability of the new configuration is weakened, and a plurality of new uncontrollable problems can occur; the scheme of this application is based on thought 3, is the improvement scheme that proposes on the basis of traditional structure. The technical solution proposed based on idea 3 that has been disclosed so far includes the following implementation manners: 1. the wedge is initiated to the developments adjustable. The action positions of the oblique detonation waves and the inner wall are controlled by adjusting the angle of the oblique detonation; 2. a thermal fluidic device is provided. The influence of the inner wall on oblique detonation waves is weakened by utilizing the thermal jet; and 3, adjusting the detonation position of the oblique detonation wave. The action positions of the oblique detonation waves and the inner wall are indirectly controlled by dynamically adjusting the positions; the disadvantages of the presently disclosed embodiments are: the dynamic control scheme has a monotonous adjusting means, completely depends on the adjustment of the detonation wedge, and has a limited regulation and control interval for the oblique detonation; an additional detonation system is arranged in the hot jet scheme, so that a more complex wave system structure is inevitably formed while the influence of the inner wall is weakened, and the stability of detonation combustion is not facilitated to a certain extent; and the above-mentioned scheme has not offered the corresponding solution to the transient out of control that oblique detonation wave probably appears. Therefore, on the premise of not setting a complex configuration, how to simplify an additional control system as much as possible, improve the standing control capability of the oblique detonation wave, and reduce the technical difficulty is a technical problem to be solved by the technical personnel in the field at present.
The information disclosed in this background section is only for enhancement of understanding of the general background of the invention and should not be taken as an acknowledgement or any form of suggestion that this information forms the prior art already known to a person skilled in the art.
Disclosure of Invention
Aiming at the defects in the background technology, the invention provides an oblique detonation wave stationing control method, which realizes the stationing control of the detonation wave. Another object of the present invention is to provide a variable geometry combustion chamber based on a skewed detonation wave stationary control method.
In order to achieve the purpose, the invention provides the following technical scheme:
the oblique detonation wave stationary control method is characterized in that an engine in the method comprises an air suction type air inlet channel, a variable geometry combustion chamber, a tail nozzle and a control system; the upstream of the combustion chamber is connected with an air inlet, and the downstream of the combustion chamber is connected with a tail nozzle; the three are designed integrally by adopting a geometric structure without obvious boundary. The combustion chamber comprises an adjustable inner wall and a fixed outer wall, the inner wall of the combustion chamber is divided into a front section and a rear section, the front section is connected with the inner wall of the air inlet channel, the rear section is connected with the inner wall of the tail nozzle, the front section and the rear section are connected by adopting a movable inflection point, and an explosion wave drainage channel penetrating through the upper part and the lower part of the inflection point is arranged; the outer wall comprises two inclined wedges, the inlet of the combustion chamber is a first inclined wedge, and the downstream position is a second inclined wedge; the control system comprises a detonation wave monitor, an action controller, a control valve, a regulating device and a circuit for transmitting signals between devices; the action controller comprises a signal input module, a signal processor and an output control module; the detonation wave monitor is arranged on the inner wall and the fixed outer wall of the combustion chamber;
supersonic combustible gas is compressed through an air inlet channel and enters a combustion chamber, and is detonated through an outer wall to generate an oblique detonation wave, and a detonation wave monitor monitors an oblique detonation wave signal in real time and transmits the signal to an action controller; a signal input module in the action controller receives signals of the detonation wave monitor, the control valve and the adjusting device and transmits the signals to a signal processor; the signal processor analyzes the signal and then sends a control signal to the output control module, and the output control module operates the control valve and the adjusting device according to the control signal; the adjustable angle adjusting device is used for adjusting an included angle between the front section and the rear section of the inner wall of the combustion chamber and controlling the position of the movable inflection point and the expansion angle of the tail nozzle, so that a sustainable and stable oblique detonation wave is formed in the combustion chamber, and detonation combustion products enter the supersonic velocity nozzle to generate thrust.
Preferably, the inner wall of the front section of the combustion chamber is provided with a first detonation wave monitor, a second detonation wave monitor and a third detonation wave monitor which are used for monitoring the action positions of the inclined detonation wave surface and the inner wall, and the three monitors are longitudinally distributed along the incoming flow direction; the outer wall of the combustion chamber is provided with a detonation wave monitor IV for monitoring the detonation position of the oblique detonation wave; the first detonation wave monitor and the second detonation wave monitor are arranged at the upstream close to the drainage channel; the third detonation wave monitor is arranged at the upstream close to the inflection point; and the fourth detonation wave monitor is arranged at the middle section of the second wedge on the fixed outer wall and is close to the upstream position of the inflection point moving stroke.
Preferably, the motion controller is provided with two modes: an automatic control mode and a manual control mode.
Preferably, the operation method of the motion controller in two modes is as follows: the automatic control mode is defaulted, when the action controller receives a signal but does not make a corresponding control action, the automatic control is judged to be invalid, the manual control mode is automatically switched, and a driver or an operator is prompted to perform manual control.
The invention provides a variable geometry combustion chamber based on an oblique detonation wave stationary control method.
A variable geometry combustion chamber based on an oblique detonation wave stationary control method comprises an air suction type air inlet channel, a variable geometry combustion chamber, a tail nozzle and a control system; the upstream of the combustion chamber is connected with an air inlet channel, and the downstream of the combustion chamber is connected with a tail nozzle; the three parts adopt an integrated design that the geometric structure has no obvious boundary, the combustion chamber comprises an adjustable inner wall and a fixed outer wall, the inner wall of the combustion chamber is divided into a front section and a rear section, the front section is connected with the inner wall of the air inlet channel, the rear section is connected with the inner wall of the tail nozzle, the front section and the rear section are connected by a movable inflection point, and a drainage channel is arranged near the inflection point; the adjustable inner wall is provided with a rotatable first adjusting point, an inflection point, a third adjusting point, a rotatable fourth adjusting point and a movable wall surface between the points, the first adjusting point is fixedly connected with the inner wall of the air inlet channel, the fourth adjusting point is fixedly connected with the tail nozzle, the first adjusting point is connected with the inflection point through the movable wall surface, the inflection point is connected with the third adjusting point through the movable wall surface, and the third adjusting point is connected with the fourth adjusting point through the movable wall surface; the outer wall comprises two inclined wedges, the inlet of the combustion chamber is a first inclined wedge, and the downstream position is a second inclined wedge; the control system comprises a detonation wave monitor, an action controller, a control valve, a regulating device and a circuit for transmitting signals between devices; the action controller comprises a signal input module, a signal processor and an output control module; the inner wall and the outer wall of the combustion chamber are both provided with detonation wave monitors;
preferably, the inflection point is used as a vertex between the front section and the rear section of the inner wall of the combustion chamber, the movable wall surfaces on two sides of the inflection point are obtuse angles on two sides of the included angle, and the theoretical value range is 90-180 degrees.
Preferably, the value of the obtuse angle is changed by simultaneously adjusting the positions of the front section and the rear section of the inner wall of the combustion chamber.
Preferably, the value of the obtuse angle is changed by respectively adjusting the positions of the front section and the rear section of the inner wall of the combustion chamber.
Preferably, a three-hole drainage channel is arranged near the inflection point of the adjustable inner wall, two holes at the upstream position of the inflection point are used for absorbing unstable detonation waves, and holes at the downstream position of the inflection point are used for discharging detonation products. The distribution state, the cross-sectional shape and the number of the channels can be set according to actual conditions.
Preferably, the fixed outer wall is provided with a first wedge and a second wedge which are smooth planes, the first wedge is positioned at the inlet of the combustion chamber, and the second wedge is positioned at the downstream position; the angle difference of the included angles between the two oblique clefts is 5-15 degrees. Under the same rectangular coordinate system, the angle of the first wedge is smaller than the minimum angle of the front section of the inner wall of the combustion chamber, and the length of the first wedge is smaller than the length of the second wedge.
The beneficial technical effects of the invention are as follows:
1. the control means is various.
The existing scheme excessively depends on the oblique angle for regulating and controlling the action position of the detonation wave and the inner wall. The scheme of the application realizes the control of four key parameters by using two movable ends and one configuration change: inflow angle, inflection point position, divergence angle and length of the detonation induction zone. The movable inflection point controls the inflow angle and the inflection point position, and the movable end positioned at the downstream realizes the independent control of the expansion angle of the spray pipe. The length of the initiation induction zone can be reduced by the double-oblique wedges on the outer side, so that the movement interval of the initiation position is effectively controlled.
In addition, still set up the detonation wave and excrete the passageway, utilized the supplementary regulation and control process of the characteristic of detonation wave self. The structure control and the self characteristic of the detonation wave increase the reliability of the whole control system.
2. And automatically controlling path optimization.
In the prior art, the state of the detonation wave is monitored, and the state parameters of the gas are monitored. The simultaneous input of multiple signals puts higher requirements on the specific implementation of the control system. The gas state and the flow field velocity are continuous variables that change with time, and control equipment with high configuration precision and strong processing capacity is required. The application does not monitor the incoming flow state, only monitors the detonation wave state, and has single signal input source and clear and controllable path.
The non-monitoring gas state is further explained: (1) the focus on oblique knocking is different. The gas state is monitored, so that the initiation and wave system structure of the detonation wave are pre-judged, and corresponding adjustment actions are performed. The method is based on a great amount of theoretical research of oblique detonation, and adopts a brand new visual angle. Broadening the focus from stability of wave system structure to stability of combustion itself, and therefore monitoring the gas state is not an essential means; (2) various control means. The structure of the detonation wave cannot be predicted without detecting the gas state, so that the information about the detonation wave completely adopts real-time feedback. The cost of simplifying the control system is the increased demand on the control capability. This application utilizes beneficial effect 1 the control means (structure regulation and control + detonation wave self characteristic), promoted the regulation and control ability of system greatly.
3. More sufficient improvement space
Previous solutions have focused on implementing modifications in the lip mask portion. The space of the lip shroud is relatively limited, which greatly limits the design and expansion capabilities of the control scheme. The control system of this application sets up at inner wall (or organism), and the space is more abundant, and improvement and the extension degree of difficulty when having reduced engineering application are designed more in a flexible way, maneuverability when having improved practical application. In addition, the lip cover does not need to be additionally arranged, the design size can be smaller, the structure can be simpler, and the dead weight of the engine can be effectively reduced.
Drawings
FIG. 1 is a schematic structural diagram of a variable geometry combustion chamber based on an oblique detonation wave stationary control method;
FIG. 2 is a schematic structural diagram of a variable geometry combustor control system;
in the figure: 1. an air inlet channel; 2. a combustion chamber; 3. a tail nozzle; 4. fixing the outer wall; 5. a first setpoint; 6. an inflection point; 7. a third setpoint; 8. a fourth set point; 9. oblique detonation waves; 10. a fuel injection hole; 11. oblique shock waves; 12. a motion controller; 13. a drainage channel; 14. a first detonation wave monitor; 15. a second detonation wave monitor; 16. a third detonation wave monitor; 17. and a fourth detonation wave monitor.
Detailed Description
In order to make the technical scheme and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The invention provides an oblique detonation wave stationing control method, which realizes the stationing control of detonation waves. Referring to fig. 1 and 2, fig. 1 is a schematic structural diagram of a variable geometry combustion chamber based on a skewed detonation wave stationary control method, and fig. 2 is a schematic structural diagram of a variable geometry combustion chamber control system. An oblique detonation wave stationary control method, the engine in the method includes the air intake duct 1, changes the combustion chamber 2 of the geometric shape, the tail nozzle 3, control system; the upstream of the combustion chamber 2 is connected with the air inlet 1, and the downstream is connected with the tail nozzle 3; the combustion chamber 2, the air inlet channel 1 and the tail nozzle 3 adopt an integrated design without obvious division on the geometrical structure, the combustion chamber 2 comprises an adjustable inner wall and a fixed outer wall 4, the inner wall of the combustion chamber 2 is divided into a front section and a rear section, the front section is integrated with the inner wall of the air inlet channel 1, the rear section is integrated with the inner wall of the tail nozzle 3, the front section and the rear section are connected by an inflection point 6, and a drainage channel 13 is arranged near the inflection point 6; the control system comprises a detonation wave monitor, a motion controller 12, a control valve, a regulating device and a circuit for transmitting signals between devices; the motion controller 12 comprises a signal input module, a signal processor and an output control module; the inner wall and the fixed outer wall 4 of the combustion chamber 2 are both provided with detonation wave monitors;
when supersonic combustible gas enters the combustion chamber 2 through the air inlet channel to be detonated to generate oblique detonation waves 9, the detonation wave monitor monitors signals of the oblique detonation waves 9 in real time and transmits the signals to the action controller 12; the signal input module of the motion controller 12 receives signals of the detonation wave monitor, the control valve and the adjusting device and transmits the signals to the processor; the processor sends a control signal to the output control module after analyzing the signal, and the output control module operates the control valve and the adjusting device according to the control signal; the expansion angle for adjusting the angle between the inner walls and controlling the inflection point 6 and the tail nozzle 3 is adjusted, so that the supersonic combustible gas forms a sustainable fixed oblique detonation wave 9 in the combustion chamber 2, and high-temperature combustion products behind the oblique detonation wave 9 enter the supersonic nozzle to generate thrust.
Preferably, the inner wall of the front section of the combustion chamber 2 is provided with a first detonation wave monitor 14, a second detonation wave monitor 15 and a third detonation wave monitor 16 which are used for monitoring the action positions of the inclined detonation wave surface and the inner wall and are longitudinally distributed along the incoming flow direction, and the outer wall of the combustion chamber 2 is provided with a fourth detonation wave monitor 17 for monitoring the detonation position of the inclined detonation wave; the first detonation wave monitor 14 and the second detonation wave monitor 15 are arranged close to the upstream of the drainage channel 13; the third detonation wave monitor 16 is arranged immediately upstream of the inflection point 6; and the fourth detonation wave monitor 17 is arranged at the middle section of the second oblique wedge of the fixed outer wall 4 and is close to the upstream position of the inflection point moving stroke.
Preferably, the motion controller 12 is provided with two modes: an automatic control mode and a manual control mode.
Preferably, the operation method of the motion controller 12 in two modes is: the automatic control mode is defaulted, when the action controller receives a signal but does not make a corresponding control action, the automatic control is judged to be invalid, the manual control mode is automatically switched, and a driver or an operator is prompted to perform manual control.
The invention provides a variable geometry combustion chamber based on an oblique detonation wave stationary control method.
A variable geometry combustion chamber based on an oblique detonation wave stationary control method comprises an air suction type air inlet channel 1, a variable geometry combustion chamber 2, a tail nozzle 3 and a control system; the upstream of the combustion chamber 2 is connected with the air inlet 1, and the downstream is connected with the tail nozzle 3; the combustion chamber 2, the air inlet channel 1 and the tail nozzle 3 adopt an integrated design without obvious division on the geometrical structure, the combustion chamber 2 comprises an adjustable inner wall and a fixed outer wall, the inner wall of the combustion chamber 2 is divided into a front section and a rear section, the front section is integrated with the inner wall of the air inlet channel, the rear section is integrated with the inner wall of the tail nozzle, the front section and the rear section are connected by an inflection point 6, and a drainage channel 13 is arranged near the inflection point 6; the adjustable inner wall is provided with a rotatable first adjusting point 5, an inflection point 6, a third adjusting point 7, a rotatable fourth adjusting point 8 and a movable wall surface, the first adjusting point 5 is fixedly connected with the inner wall of the air inlet 1, the fourth adjusting point 8 is fixedly connected with the tail nozzle 3, the first adjusting point 5 is connected with the inflection point 6 through the movable wall surface, the inflection point 6 is connected with the third adjusting point 7 through the movable wall surface, and the third adjusting point 7 is connected with the fourth adjusting point 8 through the movable wall surface; the control system comprises a detonation wave monitor, a motion controller 12, a control valve, a regulating device and a circuit for transmitting signals between devices; the motion controller 12 comprises a signal input module, a signal processor and an output control module; the inner wall and the outer wall of the combustion chamber 2 are both provided with detonation wave monitors;
preferably, the front section and the rear section of the inner wall of the combustion chamber 2 form an obtuse angle with an included angle between two sides, wherein the included angle is an inflection point 6, and the theoretical value range is 90-180 degrees.
Preferably, the value of the obtuse angle is changed by simultaneously adjusting the positions of the front section and the rear section of the inner wall of the combustion chamber.
Preferably, the value of the obtuse angle is changed by respectively adjusting the positions of the front section and the rear section of the inner wall of the combustion chamber.
Preferably, a three-hole drainage channel 13 is provided near the inflection point 6 of the adjustable inner wall, two holes at positions upstream of the inflection point 6 are used for absorbing the destabilized detonation wave, and two holes at positions downstream of the inflection point 6 are used for removing the detonation products. The distribution state, the cross-sectional shape and the number of the channels can be set according to actual conditions.
Preferably, the fixed outer wall is provided with a first wedge and a second wedge which are smooth planes, the first wedge is positioned at the inlet of the combustion chamber 2, and the second wedge is positioned at the downstream position; the angle difference between the two wedges is 5-15 degrees, under the same rectangular coordinate system, the angle of the first wedge is smaller than the minimum angle of the front section of the inner wall of the combustion chamber, and the length of the first wedge is smaller than that of the second wedge.
The working principle is as follows:
and 2, interacting the oblique detonation wave 9 with the inner wall in the process of propagating the oblique detonation wave downstream. At the moment, the influence of the inner wall on the detonation wave is relatively weak, and regulation and control are not needed. When the third detonation wave monitor 16 detects a detonation wave signal, the inflection point position can be adjusted without adjusting, and only the divergence angle is increased. Controlling until the signal of the third detonation wave monitor 16 disappears, and stopping the control action;
and 3, when the second detonation wave monitor 15 detects a detonation wave signal, opening the discharge channel 13 adjacent to the second detonation wave monitor 15 and a control valve positioned at the rear section of the inner wall to induce the contact position to move downstream. And if the second detonation wave monitor 15 still continuously outputs the detonation wave signal, increasing the divergence angle. If the mitigation still fails, the location of the inflection point 6 is adjusted. Regulating and controlling the priority: control valve > divergence angle > inflection point. Controlling until the signal of the second detonation wave monitor 15 disappears, and then returning to the step 2;
and 4, when the first detonation wave monitor 14 detects the detonation wave signal, the phenomenon of instability of the detonation wave is serious. Opening a control valve adjacent to the first detonation wave monitor 14, adjusting the inflection point 6 and the divergence angle at the same time until the signal of the third detonation wave monitor 16 disappears, and returning to the step 3;
and 5, in the adjusting process, if the fourth 17 signal of the detonation wave monitor disappears, indicating that the detonation is invalid. Immediately terminating the adjusting action in the step 2-4, returning to the step 1, and preferentially controlling the detonation of the oblique detonation wave;
and 6, in addition, when any monitor outputs a signal but the controller does not output a corresponding control action, switching the input signal source into a manual control mode and sending a prompt signal. The control action is manually completed.
The control method and variable geometry combustor described herein are suitable for use in conventional precursor compression-blending based oblique detonation engines; the application is not limited to a shock wave compression form, the inner wall is shown as a straight line section in fig. 1, the air inlet channel section belongs to shock wave compression and can also be represented as a curve, namely, isentropic compression, or a combination of two compression forms, including a combination of shock wave compression and isentropic compression under a three-dimensional condition.
In summary, although the present invention has been described with reference to the preferred embodiments, it should be understood that various changes and modifications can be made by those skilled in the art without departing from the spirit and scope of the invention.
Claims (10)
1. The oblique detonation wave stationary control method is characterized in that an engine in the method comprises an air suction type air inlet channel, a variable geometry combustion chamber, a tail nozzle and a control system; the upstream of the combustion chamber is connected with an air inlet, the downstream of the combustion chamber is connected with a tail nozzle, and the three are integrally designed by adopting a geometric structure without obvious boundary; the combustion chamber comprises an adjustable inner wall and a fixed outer wall, wherein the inner wall is divided into a front section and a rear section, the front section is connected with the inner wall of the air inlet channel, the rear section is connected with the inner wall of the tail nozzle, the front section and the rear section are connected by adopting a movable inflection point, and the front section and the rear section are provided with an explosion wave discharge channel which penetrates through the upper part and the lower part of the inflection point; the outer wall comprises two inclined wedges, the inlet of the combustion chamber is a first inclined wedge, and the downstream position is a second inclined wedge; the control system comprises a detonation wave monitor, an action controller, a control valve, a regulating device and a circuit for transmitting signals between devices; the action controller comprises a signal input module, a signal processor and an output control module; the detonation wave monitor is arranged on the inner wall and the fixed outer wall of the combustion chamber;
the supersonic combustible gas is compressed by the air inlet channel and enters the combustion chamber, and is detonated by the second oblique cleft on the outer wall to generate oblique detonation waves, and the detonation wave monitor monitors oblique detonation wave signals in real time and transmits the signals to the action controller; a signal input module in the action controller receives signals of the detonation wave monitor, the control valve and the adjusting device and transmits the signals to a signal processor; the signal processor analyzes the signal and then sends a control signal to the output control module, and the output control module operates the control valve and the adjusting device according to the control signal; the adjustable angle adjusting device is used for adjusting an included angle between the front section and the rear section of the inner wall of the combustion chamber and controlling the position of the movable inflection point and the expansion angle of the tail nozzle, so that a sustainable and stable oblique detonation wave is formed in the combustion chamber, and detonation combustion products enter the supersonic velocity nozzle to generate thrust.
2. The oblique detonation wave stationary control method according to claim 1, characterized in that a first detonation wave monitor, a second detonation wave monitor and a third detonation wave monitor for monitoring interaction positions of an oblique detonation wave surface and an inner wall are arranged at a front section of the inner wall of the combustion chamber, the three monitors are longitudinally distributed along an incoming flow direction, and a fourth detonation wave monitor for monitoring initiation positions of the oblique detonation wave is arranged on the outer wall of the combustion chamber; the first detonation wave monitor and the second detonation wave monitor are arranged at the upstream close to the drainage channel; the third detonation wave monitor is arranged at the upstream close to the inflection point; and the fourth detonation wave monitor is arranged at the middle section of the second wedge on the fixed outer wall and is close to the upstream position of the inflection point moving stroke.
3. The oblique detonation wave stationing control method as claimed in claim 1, characterized in that the motion controller is provided with two modes: an automatic control mode and a manual control mode.
4. The oblique detonation wave stationing control method as claimed in claim 3, wherein the two modes of operation of the motion controller are: the automatic control mode is defaulted, when the action controller receives a signal but does not make a corresponding control action, the automatic control is judged to be invalid, the manual control mode is automatically switched, and a driver or an operator is prompted to perform manual control.
5. A variable geometry combustion chamber based on an oblique detonation wave stationary control method is characterized in that: the variable geometry combustion chamber comprises an air suction type air inlet channel, a variable geometry combustion chamber, a tail nozzle and a control system; the upstream of the combustion chamber is connected with an air inlet channel, the downstream of the combustion chamber is connected with a tail nozzle, and the three are integrally designed by adopting a geometric structure without obvious boundary; the combustion chamber comprises an adjustable inner wall and a fixed outer wall, the inner wall of the combustion chamber is divided into a front section and a rear section, the front section is connected with the inner wall of the air inlet channel, the rear section is connected with the inner wall of the tail nozzle, the front section and the rear section are connected by adopting a movable inflection point, and a drainage channel is arranged near the inflection point; the adjustable inner wall is provided with a rotatable first adjusting point, an inflection point, a third adjusting point, a rotatable fourth adjusting point and a movable wall surface between the points, the first adjusting point is fixedly connected with the inner wall of the air inlet channel, the fourth adjusting point is fixedly connected with the tail nozzle, the first adjusting point is connected with the inflection point through the movable wall surface, the inflection point is connected with the third adjusting point through the movable wall surface, and the third adjusting point is connected with the fourth adjusting point through the movable wall surface; the outer wall comprises two inclined wedges, the inlet of the combustion chamber is a first inclined wedge, and the downstream position is a second inclined wedge; the control system comprises a detonation wave monitor, an action controller, a control valve, a regulating device and a circuit for transmitting signals between devices; the action controller comprises a signal input module, a signal processor and an output control module; and the detonation wave monitors are arranged on the inner wall and the outer wall of the combustion chamber.
6. The variable geometry combustor based on the oblique detonation wave stationary control method according to claim 5, characterized in that an inflection point is formed between the front section and the rear section of the inner wall of the combustor as a vertex, movable wall surfaces at two sides of the inflection point are obtuse angles at two sides of an included angle, and the theoretical value range is 90-180 degrees.
7. The variable geometry combustion chamber based on the oblique detonation wave stationary control method according to claim 6, characterized in that the value of the obtuse angle is changed by adjusting the positions of the front section and the rear section of the inner wall of the combustion chamber simultaneously.
8. The variable geometry combustion chamber based on the oblique detonation wave stationary control method according to claim 6, characterized in that the value of the obtuse angle is changed by adjusting the positions of the front section and the rear section of the inner wall of the combustion chamber respectively.
9. The variable geometry combustor based on the oblique detonation wave stationary control method of claim 5, wherein a three-hole exhaust channel is provided near an inflection point of the adjustable inner wall, two holes at an upstream position of the inflection point are used for absorbing the destabilized detonation wave, and holes at a downstream position of the inflection point are used for exhausting detonation products.
10. The variable geometry combustion chamber based on the oblique detonation wave stationary control method as claimed in claim 5, wherein the fixed outer wall is provided with a first oblique wedge and a second oblique wedge which are smooth planes, the first oblique wedge is positioned at the inlet of the combustion chamber, and the second oblique wedge is positioned at the downstream position; the angle difference between the two oblique wedges is 5-15 degrees; under the same rectangular coordinate system, the angle of the first wedge is smaller than the minimum angle of the front section of the inner wall of the combustion chamber, and the length of the first wedge is far smaller than that of the second wedge.
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