CN114184385A - Double-pulse rotor detonation combustion experimental device and method - Google Patents
Double-pulse rotor detonation combustion experimental device and method Download PDFInfo
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- CN114184385A CN114184385A CN202111345660.XA CN202111345660A CN114184385A CN 114184385 A CN114184385 A CN 114184385A CN 202111345660 A CN202111345660 A CN 202111345660A CN 114184385 A CN114184385 A CN 114184385A
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 140
- 238000005474 detonation Methods 0.000 title claims abstract description 74
- 238000000034 method Methods 0.000 title claims abstract description 15
- 239000000446 fuel Substances 0.000 claims abstract description 58
- 238000002347 injection Methods 0.000 claims abstract description 39
- 239000007924 injection Substances 0.000 claims abstract description 39
- 238000006243 chemical reaction Methods 0.000 claims abstract description 18
- 230000008569 process Effects 0.000 claims abstract description 9
- 238000007789 sealing Methods 0.000 claims abstract description 6
- 239000002912 waste gas Substances 0.000 claims abstract description 4
- 230000003993 interaction Effects 0.000 claims description 7
- 239000007789 gas Substances 0.000 claims description 6
- 239000011521 glass Substances 0.000 claims description 4
- 239000007788 liquid Substances 0.000 claims description 3
- 239000000843 powder Substances 0.000 claims description 3
- 238000001816 cooling Methods 0.000 abstract description 9
- 238000002474 experimental method Methods 0.000 abstract description 5
- 238000011161 development Methods 0.000 abstract description 3
- 230000035484 reaction time Effects 0.000 abstract description 2
- 230000008646 thermal stress Effects 0.000 abstract description 2
- 238000007599 discharging Methods 0.000 abstract 1
- 238000004200 deflagration Methods 0.000 description 5
- 230000009977 dual effect Effects 0.000 description 4
- 230000035939 shock Effects 0.000 description 4
- 230000017525 heat dissipation Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 239000000306 component Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010283 detonation spraying Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000001404 mediated effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000037452 priming Effects 0.000 description 1
- 230000000644 propagated effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
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- 238000006467 substitution reaction Methods 0.000 description 1
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- G—PHYSICS
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Abstract
The invention discloses a double-pulse rotor detonation combustion experimental device and a double-pulse rotor detonation combustion experimental method, which relate to the technical field of detonation experiments and comprise a rotor, a high-frequency pulse igniter, a premixed fuel injection port and a combustion chamber; the combustion chamber is provided with a high-frequency pulse igniter and a premixed fuel injection port; the rotor is driven to rotate through a power source, the curvature of the outer side of the rotor is the same as that of the input end of the combustion chamber, and the rotor is in sealing fit with the combustion chamber until detonation combustion is completed in the rotating process. The method comprises the steps of controlling fuel injection by a laser pulse receiver, ionizing and igniting by a high-frequency pulse igniter, cooling by air cooling and discharging waste gas. The invention designs the detonation combustion chamber capable of improving the reaction continuity, and has certain practical significance for the development and application of detonation combustion. Meanwhile, the invention improves the detonation combustion frequency, reduces the DDT reaction time, can realize the cooling of the wall surface of the combustion chamber, and prevents the outer wall of the combustion chamber from deforming due to overhigh thermal stress.
Description
Technical Field
The invention relates to the technical field of detonation experiments, in particular to a double-pulse rotor detonation combustion experimental device and method.
Background
The combustion has modes of detonation combustion, deflagration combustion and the like; in deflagration, the combustion reaction intensity is related to the heat and mass diffusivity in an energy release area, the flame combustion propagation speed is slow, and the propagation mechanism is heat and mass transfer; detonation combustion is an efficient form of chemical energy release by mixing fuel with combustion promoters such as oxygen. The detonation wave generated by detonation can be approximately considered to be formed by a strong shock wave and a chemical reaction area which is immediately followed by the strong shock wave, the shock wave induces the chemical reaction to proceed, and the heat released by the chemical reaction supports the forward propagation of the shock wave. Detonation waves are propagated at high supersonic speed, and can generate extremely high pressure and temperature (the pressure range is 1.5-10 Mpa, and the temperature is greater than 2800K), so the detonation combustion process is approximately an isochoric process, and compared with deflagration combustion, the detonation combustion thermal efficiency is higher.
Therefore, the detonation combustion has wide application prospect in the power propulsion technology. So far, detonation engine research has been greatly advanced. For example: stationary Detonation Engine (SDE), Pulse Detonation Engine (PDE), and Rotary Detonation Engine (RDE). In military use, the power device can be used as a power device of a remote missile and a hypersonic stealth fighter; it can be used for power generation, detonation spraying, detonation combined internal combustion engine, etc.
Compared with deflagration combustion, although the detonation combustion efficiency is high, the combustion is sufficient, the emission pollution is small, the detonation reaction process is more difficult to control, such as the continuity of the detonation reaction, the stability of detonation and detonation in each successful ignition.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a double-pulse rotor detonation combustion experimental device and a double-pulse rotor detonation combustion experimental method, designs a detonation combustion chamber capable of improving reaction continuity and pulse detonation frequency, and has certain practical significance for the development and application of detonation combustion.
The present invention achieves the above-described object by the following technical means.
A double-pulse rotor detonation combustion experimental device comprises a rotor, a high-frequency pulse igniter, a premixed fuel injection port and a combustion chamber; the combustion chamber is provided with a high-frequency pulse igniter and a premixed fuel injection port; the rotor is provided with a first laser signal transmitter and a second laser signal transmitter, and the combustion chamber is provided with a first laser signal receiver and a second laser signal receiver; the signal sent by the first laser signal transmitter is received by the first laser signal receiver, processed by the controller and then sent to the premixed fuel injection port to spray fuel; the signal sent by the second laser signal transmitter is received by the second laser signal receiver, processed by the controller and then sent to the high-frequency pulse igniter to send an ignition instruction; controlling the first laser signal transmitter and the second laser signal transmitter to send out signal time intervals through the controller;
the rotor is driven to rotate through a power source, the curvature of the outer side of the rotor is the same as that of the input end of the combustion chamber, and the rotor is in sealing fit with the combustion chamber until detonation combustion is completed in the rotating process.
Furthermore, the two combustion chambers are arranged adjacently up and down.
Further, the air conditioner also comprises a cold air inlet channel; the cold air inlet channel and the rotor are integrally arranged.
Furthermore, the cold air inlet channel comprises an air inlet channel and an air outlet channel, wherein the air inlet channel is arranged on the power input shaft of the rotor, the air outlet channel is vertically communicated with the air inlet channel, and gas in the air outlet channel can be sprayed into the combustion chamber in the rotating process of the rotor.
Furthermore, the two rotors are symmetrical along the plane of the rotor power input shaft, and the central section of the cold air inlet channel is coplanar with the plane of the rotor power input shaft.
Furthermore, a rib is arranged on the outer side wall of the combustion chamber.
Furthermore, the frequencies of the wireless signals sent by the first laser signal transmitter and the second laser signal transmitter are different, and the first laser signal receiver and the second laser signal receiver can only perform signal interaction with the wireless signals sent by the corresponding first laser signal transmitter and the corresponding second laser signal transmitter.
Furthermore, the premixed fuel injection ports are provided with a plurality of premixed fuel injection ports, and the fuel injected by the premixed fuel injection ports is liquid atomized, or gas powder, or gaseous fuel.
Furthermore, a window is formed in the combustion chamber, a PC plate or transparent glass is filled in the window, and the combustion form is observed through the PC plate or the transparent glass in high-speed photography.
The working method of the pulse detonation combustion experimental device comprises the following steps:
when the rotor runs to the top dead center of the combustion chamber, a first laser signal transmitter on the rotor and a first laser signal receiver on the upper wall surface of the combustion chamber generate signals to interactively emit a premixed fuel injection command, a premixed fuel injection port controls fuel injection time to inject fuel according to a preset program, the rotor continuously rotates for a certain angle until a second laser signal transmitter in the middle of the rotor and a second laser signal receiver on the lower wall surface of the combustion chamber generate signal interaction, and a high-frequency pulse igniter is controlled to rapidly ignite and work to generate detonation combustion;
after the reaction is finished, the running path of the cold air inlet channel passes through the combustion chamber, the sprayed cold air discharges the waste gas after the reaction out of the combustion chamber, and meanwhile, the temperature of the combustion chamber is reduced to prepare for the reaction of the next stage.
Has the advantages that:
1. the curvature of the rotor is the same as that of the input end of the combustion chamber, so that the rotor and the combustion chamber are in sealing fit until detonation combustion is finished in the rotation process of the rotor.
2. The invention designs two combustion chambers, improves ignition release energy and detonation combustion frequency, and the two combustion chambers work alternately, thereby improving the continuity of reaction.
3. And a laser signal transmitter and a laser signal receiver are adopted to control the operation of the premixed fuel injection and high-frequency pulse ignition device.
4. The fins on the outer wall of the combustion chamber can be selected from pin fins, annular ribs or straight ribs for heat dissipation. And needle ribs are arranged near the premixed fuel injection port, and annular ribs and straight ribs can be arranged on other smooth wall surfaces to dissipate heat of the combustion chamber.
5. The cold air intake duct is used for blowing in the cold air cooling to the combustion chamber after detonation, and the cold air intake duct sets up with rotor integration for detonation and cooling continuity are strong, have improved work efficiency.
6. The invention designs the detonation combustion chamber capable of improving the reaction continuity, and has certain practical significance for the development and application of detonation combustion. Meanwhile, the invention improves the detonation combustion frequency, reduces the DDT reaction time, can realize the cooling of the wall surface of the combustion chamber, and prevents the outer wall of the combustion chamber from deforming due to overhigh thermal stress.
7. The probability of successful ignition and detonation is improved by arranging two groups of laser transmitters, laser receivers and high-frequency pulse igniters to act together.
Drawings
FIG. 1 is an enlarged schematic view of a rotor of a dual pulse detonation combustor in accordance with the present invention;
FIG. 2 is an oblique rotor view of a dual pulse detonation combustor in accordance with the present invention;
FIG. 3 is a schematic view of a combustion chamber of a dual pulse detonation combustor in accordance with the present invention;
FIG. 4 is a general schematic view of a dual pulse detonation combustor in accordance with the present invention;
FIG. 5 is a schematic illustration of the internal fuel injection within a combustion chamber according to the present invention;
FIG. 6 is a schematic illustration of detonation combustion within a combustion chamber according to the present disclosure;
FIG. 7 is a schematic view of cooling by air cooling in a combustion chamber according to the present invention.
Reference numerals:
2-a rotor; 3-cold air inlet; 4-a first laser signal transmitter; 5-a second laser signal transmitter; 6-a first laser signal receiver; 7-a second laser signal receiver; 8-high frequency pulse igniter; 9-premixed fuel injection port; 10-a combustion chamber; 11-fins.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "axial," "radial," "vertical," "horizontal," "inner," "outer," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the present invention and for simplicity in description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are not to be considered limiting. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
In the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
A pulse detonation combustion experimental device comprises a rotor 2, a high-frequency pulse igniter 8, a premixed fuel injection port 9 and a combustion chamber 10; the combustion chamber 10 is provided with a high-frequency pulse igniter 8 and a premixed fuel injection port 9; a first laser signal transmitter 4 and a second laser signal transmitter 5 are arranged on the rotor 2, and a first laser signal receiver 6 and a second laser signal receiver 7 are arranged on the combustion chamber 10; wherein, the signal sent by the first laser signal transmitter 4 is received by the first laser signal receiver 6, processed by the controller and then sent to the premixed fuel injection port 9 to inject the fuel; the signal sent by the second laser signal transmitter 5 is received by the second laser signal receiver 7, processed by the controller and then sent to the high-frequency pulse igniter 8 to send an ignition instruction; controlling the first laser signal transmitter 4 and the second laser signal transmitter 5 to send out signal time intervals through a controller; the rotor 2 is driven to rotate by a power source, the curvature of the outer side of the rotor 2 is the same as that of the input end of the combustion chamber 10, and the rotor 2 and the combustion chamber 10 are in sealing fit until detonation combustion is completed in the rotating process.
Specifically, in the rotation process of the rotor 2, after the second laser signal transmitter 5 and the second laser receiver 7 perform signal interaction, the high-frequency pulse igniter 8 sends an ignition instruction to ignite the premixed fuel, and the rotor 2 continues to be in sealing fit with the combustion chamber 10 until the second laser signal transmitter 5 rotates away from the combustion chamber 10, which can also be understood as follows: the second laser signal emitter 5 rotates past the top dead center position where the first laser signal emitter 4 is located.
The invention discloses a double-pulse rotor detonation combustor experimental device which comprises a rotor 2, a cold air inlet 3, a first laser signal transmitter 4, a second laser signal transmitter 5, a first laser signal receiver 6, a second laser signal receiver 7, a high-frequency pulse igniter 8, a premixed fuel injection port 9, a combustor 10 and fins 11.
The rotor 2 is one of the core components of the detonation combustor, and can be manufactured integrally or welded by parts; a rotor power input shaft is arranged below the rotor 2 and drives the rotor 2 to rotate and work by being connected with an external power source; the curvature of the rotor is consistent with that of the input end of the combustion chamber 10, so that the rotor is ensured to form a seal when running to the inlet section of the combustion chamber, and the necessary conditions of detonation combustion are met, such as one end of the high-frequency pulse igniter is sealed, and the other end of the high-frequency pulse igniter is opened.
And at least one high-frequency pulse igniter 8 is arranged in each combustion chamber, and the ignition work of the high-frequency pulse igniter is controlled by the controller.
Direct ignition priming of the premixed gas (to remove some of the highly sensitive fuel) requires very high energy, typically 103～104J magnitude. Thus miningThe high-frequency pulse igniter with high stability and multiple pulses is used for ignition.
The laser signal transmitter and the laser signal receiver are respectively installed on the rotor 2 and at the inner and outer side wall surfaces of the combustion chamber 10. A pair of laser signal transmitters are respectively arranged above the rotor 2, and the laser signal transmitters and a laser signal receiver on the combustion chamber 10 form an automatic control system for controlling the operation of the premixed fuel injection and high-frequency pulse ignition device.
The transmitting module of the laser signal transmitter always outputs high level, namely the module is in a laser transmitting state, the receiving module always judges whether the laser signal is received, and after the signal is received, premixed fuel injection and high-frequency pulse ignition actions are triggered.
The premixed fuel nozzle 9 provides stable premixed fuel, and the medium is guaranteed to be uniformly dispersed in the combustion chamber. The premixed fuel can be in the forms of gas-liquid/gas-powder/gas-solid and the like, and the component proportion can meet detonation combustion; the premixed fuel injection port 9 is provided with a one-way valve protection measure, so that the premixed fuel injection port is prevented from being damaged by high temperature generated by detonation. The premixed fuel injection ports are provided with independent control switches, and the opening number is selected according to experimental conditions.
Fins are arranged on the outer wall of the combustion chamber 10, and the fins on the outer wall of the combustion chamber can be selected from pin fins, annular ribs or straight ribs for heat dissipation. Needle ribs are arranged near the premixed fuel injection port 9, and annular ribs and straight ribs can be arranged on other smooth wall surfaces.
The outer wall of the combustion chamber is in a regular cylinder shape, a hose can be used for being wound around the combustion chamber, circulating cold water is introduced into the hose, and water cooling is adopted for heat dissipation.
The cold air inlet pipeline 3, the hexagonal hole in rotor top is the inlet duct of cold air inlet pipeline 3, injects low temperature cold air into rotor working chamber and combustion chamber through the pipeline of giving vent to anger of two cold air inlet pipeline 3, and amount of wind and wind speed are mediated according to the strong degree of detonation combustion.
With reference to fig. 1 and 2, it can be seen that the rotors 2 are of an axe-shaped structure, the two rotors 2 are symmetrical along the plane of the rotor power input shaft, the central section of the cold air intake passage 3 is coplanar with the plane of the rotor power input shaft, and the outer curvature of the rotors 2 is the same as the curvature of the input end of the combustion chamber 10.
Referring to fig. 3, a three-dimensional boss is arranged at the middle part of the arc-shaped edge of the rotor 2 and used as a mounting substrate of the laser signal transmitter. The laser signal receiver is installed at the inner and outer wall surfaces of the combustion chamber, and referring to fig. 5 and 6, the laser signal transmitter and the laser signal receiver are installed at the same horizontal height.
Referring to fig. 3 and 5, two high-frequency pulse igniters are arranged on one side of the rotor, and the high-frequency pulse igniters are controlled to work by laser signals. The high-frequency pulse igniter works stably, and has great advantages under the working conditions of high temperature and high frequency compared with the conventional spark discharge ignition.
The premixed fuel injection ports which are uniformly distributed are arranged above the combustion chamber, and the combustion chamber is designed to be cylindrical, so that an annular fixed seat is arranged at the joint of the premixed fuel injection ports and the annular combustion chamber.
The working process is as follows:
the power input shaft below the rotor is connected with a power source to provide power for the rotor; the premixed fuel injection port 9 is connected with a premixing tank (fuel required by the experiment is in the premixing tank); when the rotor rotates to the position shown in the figure 5, the rotor 2 and the combustion chamber 10 form a sealed environment, the first laser signal transmitter 4 and the first laser signal receiver 6 generate signal interaction, and the premixed fuel injection port 9 is controlled to be opened, so that fuel is injected into the combustion chamber 10.
And then the rotor 2 continues to rotate by a certain angle, when the rotor moves to the position shown in the figure 6, fuel injection is finished, at the moment, the second laser signal transmitter 5 and the second laser signal receiver 7 generate signal interaction, so that the high-frequency pulse igniter 8 releases energy to ignite premixed fuel, the energy released by the high-frequency pulse igniter provides enough ignition energy for the premixed fuel, the deflagration combustion is quickly transited to the detonation combustion, and the reaction distance of DDT is reduced.
After detonation combustion, the temperature of the combustion chamber rises, the generated high-temperature waste gas stays in the combustion chamber, and when an air outlet pipeline next to the cold air inlet pipeline 3 runs to the position shown in the attached figure 7, the low-temperature cold air (cold quantity Q) is sprayed out1) Absorbing heat and removing exhaust gases from the combustion chamber (Q)2) And preparing for the next reaction process.
The invention improves the ignition release energy and the detonation combustion frequency, and the two combustion chambers work alternately, thereby improving the continuity of the reaction.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (10)
1. A double-pulse rotor detonation combustion experimental device is characterized by comprising a rotor (2), a high-frequency pulse igniter (8), a premixed fuel injection port (9) and a combustion chamber (10); the combustion chamber (10) is provided with a high-frequency pulse igniter (8) and a premixed fuel injection port (9); a first laser signal transmitter (4) and a second laser signal transmitter (5) are arranged on the rotor (2), and a first laser signal receiver (6) and a second laser signal receiver (7) are arranged on the combustion chamber (10); the signal sent by the first laser signal transmitter (4) is received by the first laser signal receiver (6), processed by the controller and then sent to the premixed fuel injection port (9) to inject fuel; the signal sent by the second laser signal transmitter (5) is received by the second laser signal receiver (7), processed by the controller and then sent to the high-frequency pulse igniter (8) to send an ignition instruction; controlling the signal time interval of the first laser signal transmitter (4) and the second laser signal transmitter (5) through a controller;
the rotor (2) is driven to rotate through a power source, the curvature of the outer side of the rotor (2) is the same as that of the input end of the combustion chamber (10), and the rotor (2) is attached to the combustion chamber (10) in a sealing mode until detonation combustion is completed in the rotating process.
2. The double-pulse rotor detonation combustion experimental device as claimed in claim 1, wherein two combustion chambers (10) are arranged adjacently up and down.
3. The double pulse rotor detonation combustion experimental device according to claim 1, characterized by further comprising a cold air inlet (3); the cold air inlet channel (3) and the rotor (2) are integrally arranged.
4. The experimental device of the pulse detonation combustion as claimed in claim 3, characterized in that the cold air inlet channel (3) comprises an inlet channel and an outlet channel, wherein the inlet channel is arranged on the power input shaft of the rotor, the outlet channel is vertically communicated with the inlet channel, and gas in the outlet channel can be injected into the combustion chamber (10) during the rotation of the rotor (2).
5. The experimental device of the pulse detonation combustion as claimed in claim 3, characterized in that the two rotors (2) are symmetrical along the plane of the rotor power input shaft, and the central section of the cold air intake channel (3) is coplanar with the plane of the rotor power input shaft.
6. The double pulse rotor detonation combustion experimental device as claimed in claim 1, characterized in that fins (11) are arranged on the outer side wall of the combustion chamber (10).
7. The double-pulse rotor detonation combustion experimental device as claimed in claim 1, wherein the frequencies of the wireless signals emitted by the first laser signal emitter (4) and the second laser signal emitter (5) are different, and the first laser signal receiver (6) and the second laser signal receiver (7) can only perform signal interaction with the wireless signals emitted by the corresponding first laser signal emitter (4) and the corresponding second laser signal emitter (5).
8. The double-pulse rotor detonation combustion experimental device as claimed in claim 1, wherein the number of the premixed fuel injection ports (9) is several, and the fuel injected by the premixed fuel injection ports (9) is liquid atomized, or gas powder, or gaseous fuel.
9. The double-pulse rotor detonation combustion experimental device as claimed in claim 1, wherein a window is formed in the combustion chamber (10), a PC plate or transparent glass is filled in the window, and a combustion state is observed through the PC plate or the transparent glass by high-speed photography.
10. The working method of the double-pulse rotor detonation combustion experimental device as claimed in any one of claims 1 to 9, characterized by comprising the following steps:
when the rotor (2) runs to the top dead center of the combustion chamber (10), a first laser signal transmitter (4) on the rotor (2) and a first laser signal receiver (6) on the upper wall surface of the combustion chamber (10) generate signals to interactively send out a premixed fuel injection command, a premixed fuel injection port (9) controls fuel injection time to inject fuel according to a preset program, the rotor (2) continues to rotate for a certain angle until a second laser signal transmitter (5) positioned in the middle of the rotor (2) and a second laser signal receiver (7) on the lower wall surface of the combustion chamber (10) generate signal interaction, and a high-frequency pulse igniter (8) is controlled to rapidly ignite and work to generate detonation combustion;
after the reaction is finished, the running path of the cold air inlet channel (3) passes through the combustion chamber (10), the sprayed cold air discharges the waste gas after the reaction out of the combustion chamber (10), and meanwhile, the temperature of the combustion chamber is reduced to prepare for the reaction of the next stage.
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