CN114812927A - Measuring device for detonation wave velocity and structure under action of liquid drops and control method thereof - Google Patents
Measuring device for detonation wave velocity and structure under action of liquid drops and control method thereof Download PDFInfo
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- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L23/00—Devices or apparatus for measuring or indicating or recording rapid changes, such as oscillations, in the pressure of steam, gas, or liquid; Indicators for determining work or energy of steam, internal-combustion, or other fluid-pressure engines from the condition of the working fluid
- G01L23/22—Devices or apparatus for measuring or indicating or recording rapid changes, such as oscillations, in the pressure of steam, gas, or liquid; Indicators for determining work or energy of steam, internal-combustion, or other fluid-pressure engines from the condition of the working fluid for detecting or indicating knocks in internal-combustion engines; Units comprising pressure-sensitive members combined with ignitors for firing internal-combustion engines
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Abstract
The invention provides a measuring device for detonation wave velocity and structure under the action of liquid drops and a control method thereof. The triggering time sequences of the liquid drop generator, the igniter and the high-speed camera are uniformly controlled by the high-precision signal generator, so that liquid drops with different micro-explosion degrees and Weber numbers interact with the detonation waves in different development stages; the propagation speed and the structure of the detonation wave at different development stages are measured when liquid drops exist by comprehensively using a high-frequency pressure sensor, a high-speed shadow, a schlieren and a three-dimensional flame reconstruction technology based on stereoscopic laser induced fluorescence.
Description
Technical Field
The invention relates to the fields of detonation combustion, detonation propulsion and the like, in particular to a measuring device for detonation wave velocity and structure under the action of liquid drops and a control method thereof.
Background
Detonation combustion is distinguished from slow combustion and is essentially a process that achieves extremely fast chemical reactions with a lower entropy increase. Because the detonation combustion process is similar to isochoric combustion, the detonation combustion process has higher thermal cycle efficiency than isobaric combustion, and in addition, because the leading shock wave can pre-compress the reactant, namely the detonation wave has better self-supercharging effect, if the detonation wave is used on an engine, a supercharging component can be omitted, and the structure is simplified. Based on the above theoretical advantages, detonation combustion and detonation propulsion become one of the research hotspots in the current aerospace power field.
At present, a Pulse detonation engine (PDE for short) is mature aiming at a propelling scheme based on detonation combustion, and especially, the PDE using liquid fuel has a more realistic meaning for practical engineering application. However, droplets remaining in the fuel spray at normal temperature may cause oscillations in the velocity of the detonation wave and structural changes due to the limit of the atomization level. Meanwhile, the leading shock wave in the detonation wave also influences the crushing, micro-explosion and combustion of the liquid drops. Therefore, in the two-phase detonation combustion, the interaction of the evaporation and micro-explosion of liquid drops and the propagation of detonation waves is the main characteristic, and the understanding of the action mechanism is the key for promoting the application research and development of the detonation engine.
At present, limited by research methods and observation means, the action mechanism of liquid drops on key characteristics such as local cell structure of detonation waves, flame surface form, reaction zone thickness, detonation wave speed and the like in the detonation process is lack of sufficient understanding. Therefore, the invention provides a device for measuring the propagation speed and the structure of the detonation wave under the action of the liquid drops and a control method thereof, and the device can capture the influence of the liquid drops on the propagation and the structural characteristics of the detonation wave in different development stages by comprehensively using various measurement means, is beneficial to solving the problems of frequency attenuation of the high-frequency two-phase detonation wave, detonation failure and the like, and has important significance for promoting the development and the application of a two-phase detonation engine.
Disclosure of Invention
Technical problem to be solved
When the two-phase detonation engine runs at a high frequency, the performance advantages of the two-phase detonation engine are reduced due to the problems of detonation wave frequency attenuation and detonation failure, and the key to the problems of detonation wave frequency attenuation and detonation failure is insufficient understanding of the interaction mechanism of liquid drops and detonation waves at present. Therefore, the invention provides a device for measuring the propagation speed and structure of the detonation wave under the action of liquid drops and a control method thereof, which comprehensively use a high-frequency pressure sensor, a high-speed shadow, a schlieren and a three-dimensional flame reconstruction technology based on stereoscopic laser induced fluorescence to measure the structure and propagation speed of the detonation wave when the liquid drops exist, and provide support for researching the interaction mechanism of liquid drop crushing, atomization and initiation and propagation of the detonation wave.
In order to achieve the purpose, the invention adopts the technical scheme that:
a device for measuring propagation speed of detonation waves and cell structures under action of liquid drops and a control method thereof comprise a main body heating cavity, a temperature control device, a detonation tube supply and control system, a liquid drop generation and control device, a test system and a control method.
The main body heating cavity and the temperature control device are composed of a heating cavity, a resistance wire, a heat insulation sleeve, a temperature controller and a glass observation window. The heating cavity is heated through a resistance wire; the heat insulation sleeve prevents heat loss and keeps the temperature in the heating cavity stable; the temperature controller displays the temperature of the heating cavity, controls the temperature and simulates different wall temperatures of the detonation engine in the actual operation process; the glass observation window is used for shadow, schlieren and flame self-luminescence observation.
The detonation tube supply and control system is composed of a ethylene bottle, an air bottle, an ethylene path electromagnetic valve, an air path electromagnetic valve, a detonation tube, a nitrogen bottle, a spark plug and a computer. The ethylene bottle and the air bottle are used for storing high-pressure fuel and oxidant, and the mixing equivalence ratio can be adjusted by changing the supply pressure of the air bottle; the ethylene path electromagnetic valve and the air path electromagnetic valve are respectively used for controlling the opening and closing of the fuel and oxidant gas cylinders; ethylene and air are mixed and then are fed into a detonation tube; the detonation tube is a tubular device with one closed end, and a detonation reinforcing structure is arranged in the detonation tube and used for generating and transmitting detonation waves; the nitrogen cylinder is used for providing isolation and purge gas; the spark plug is used for ignition, and the ignition energy is less than 50 mJ; the computer is used for uniformly controlling the triggering of the electromagnetic valve and the ignition signal of the spark plug, and further controlling the triggering time of the detonation wave.
The droplet generating device comprises two types: a hanging droplet generating device and a flying droplet generating device; the liquid drop generating device with the suspension method comprises a hanging wire, a stepping motor, a ball screw moving rod and a heat insulation sleeve, wherein liquid drops are suspended on the hanging wire, the liquid drops are controlled to be thrown into a detonation tube in a heating cavity through the stepping motor, the throwing height of the liquid drops is adjusted through the ball screw moving rod, the heat insulation sleeve prevents the thermal environment in the cavity from influencing the evaporation of the liquid drops in advance before the test is started, the liquid drops can be placed in an optical observation area in the heating cavity, detonation waves are triggered when the liquid drops are subjected to micro-explosion, the micro-explosion liquid drops interact with the detonation waves, and the structure and the speed of the detonation waves when the micro-explosion liquid drops exist are measured; the droplet generating device of the flying droplet method is composed of a stepping motor, a ball screw moving rod and a droplet generator, and is different from the droplet generating device of the suspension method in that droplets are generated by the droplet generating device, the droplets are directly dripped into a detonation tube by the flying droplet method through the stepping motor, the droplet generating device can generate micro-scale droplets, the diameter of the droplets can be adjusted, and the droplet generating device is used for measuring the propagation speed and the structure of detonation waves when the droplets with different Weber numbers exist. The liquid drop control device mainly comprises a stepping motor controller, and the dripping time and the throwing height of the liquid drops can be controlled through the stepping motor controller, so that the liquid drops are ensured to accurately pass through the detonation wave.
The test system consists of a pressure sensor, a thermocouple, a pressure/temperature signal acquisition instrument, a plurality of groups of light sources, a multi-probe optical fiber image transmission bundle and a high-speed camera. The pressure sensor and the thermocouple are fixed through a sensor mounting hole on the detonation tube, the pressure/temperature signal acquisition instrument is used for acquiring and analyzing pressure/temperature signals, the temperature signals are used for measuring the real temperature in the heating cavity, and the pressure signals are used for measuring the propagation speed of the detonation wave. The system comprises a plurality of groups of light sources, a multi-probe optical fiber image transmission bundle and a high-speed camera, wherein the non-contact optical test system is formed by the light sources, the multi-probe optical fiber image transmission bundle and the high-speed camera together, and the propagation speed and the structure of the detonation wave in the presence of liquid drops with different Weber numbers and micro-explosion degrees are comprehensively observed through an optical observation area by comprehensively using a high-speed shadow, a schlieren and a three-dimensional flame reconstruction technology based on stereoscopic laser induced fluorescence.
Selecting initial conditions of the test, including key characteristic parameters of liquid drops and detonation waves and environmental conditions, and uniformly controlling the triggering time sequences of the liquid drop generator, the igniter and the high-speed camera by the high-precision signal generator to enable liquid drops with different micro-explosion degrees and Weber numbers to act on the detonation waves in different development stages; the propagation speed and the structure of the detonation wave under the action of the liquid drops are measured by comprehensively using a high-frequency pressure sensor, a high-speed shadow, a schlieren and a three-dimensional flame reconstruction technology based on stereoscopic laser induced fluorescence.
The main body heating cavity and the temperature control device are used for heating the detonation tube, and the influence of the wall temperature on the liquid drop evaporation and the micro-explosion degree in the actual operation process of the detonation engine is simulated; and adjusting the heating temperature to obtain liquid drops with different evaporation and micro-explosion degrees, and measuring the detonation wave structure and the propagation speed of the detonation wave when the detonation wave sweeps across the liquid drops under different micro-explosion conditions by using a non-contact optical diagnosis system and a pressure sensor.
Comprehensively using high-speed schlieren, shadow and a three-dimensional flame reconstruction technology non-contact optical test method based on stereoscopic laser induced fluorescence, carrying out high-time and high-spatial-resolution flow field observation on the process of the interaction of liquid drops and detonation waves, and capturing the structure of the detonation waves in the process of the interaction of the liquid drops and the detonation waves; the quick response pressure sensors are axially arranged at different positions of the detonation tube, and the distance between the two pressure sensors and the pressure peak time difference of the detonation wave captured by the two pressure sensors are utilized to measure the propagation speed of the detonation wave when the detonation wave sweeps across the liquid drop.
Setting a corresponding trigger time sequence according to the time required by the micro-explosion of the liquid drop measured by the schlieren technology, controlling the detonation wave to sweep the micro-explosion liquid drop, and measuring the structure and the speed of the detonation wave by using a high-speed camera and a pressure sensor; the time sequence of dropping of the liquid drops, initiation of the detonation waves and shooting of the camera is strictly controlled through the same high-precision controller, so that the liquid drops interact with the detonation waves in different development stages, and the propagation speed and the structure of the detonation waves in different development stages when the detonation waves pass through the liquid drops are measured.
Generating detonation waves with different strengths by adjusting conditions such as the mixture equivalence ratio, the initial pressure and the like; according to the time required by micro-explosion of the liquid drops measured by the schlieren technology, the corresponding trigger time sequences of the liquid drop generating device, the spark plug, the high-speed camera and the like are set, so that the liquid drops interact with flame/detonation waves with different development stages and different intensities, and the speed and the structure of the interaction of the flame/detonation waves and the liquid drops in the different development stages are measured by utilizing the shadow, the schlieren and the three-dimensional flame reconstruction technology based on the stereoscopic laser induced fluorescence.
Has the advantages that:
by adopting the measuring device for the propagation speed of the detonation wave and the cell structure under the action of the liquid drops and the control method thereof, provided by the invention, the cell structure of the detonation wave after the liquid drops are swept can be observed with higher time and spatial resolution by combining non-contact optical test methods such as high-speed shadow, schlieren and three-dimensional flame reconstruction technology based on stereoscopic laser induced fluorescence, and more detailed characteristics can be captured; the propagation speed of the detonation wave passing through the liquid drop can be measured by combining a high-frequency pressure sensor; by combining the abundant testing methods, the influence characteristics of the liquid drops on the propagation process of the detonation waves can be more comprehensively observed; the invention can provide a certain research basis for developing a high-efficiency two-phase detonation engine high-frequency stable operation control strategy.
Drawings
FIG. 1 is a schematic diagram illustrating the characteristics of the effect of micro-detonation of liquid droplets on initiation of a two-phase detonation wave in accordance with the present invention;
FIG. 2 is a diagram of a droplet microexplosion and detonation combustion experimental system (example 1) of the present invention;
FIG. 3 is a schematic diagram of the experimental control method for interaction between liquid drops and detonation waves (example 2) according to the present invention;
wherein, 1 is an incomplete atomized liquid drop group, 2 is a liquid drop crushing process, 3 is a local hot spot, 4 is a liquid drop micro-explosion, 5 is a filling process, 6 is a slow combustion to detonation transition stage, 7 is a stepping motor controller, 8 is a stepping motor, 9 is a ball screw moving rod, 10 is a detonation tube, 11 is a heat insulation plate, 12 is a resistance wire, 13 is a glass observation window, 14 is a heat insulation sleeve, 15 is a pressure/temperature signal acquisition instrument, 16 is a hanging wire, 17-1 is a suspension method liquid drop, 17-2 is a flying drop method liquid drop, 18 is a liquid drop generator, 19 is a temperature controller, 20 is an optical observation area, 21 is a computer, 22 is a thermocouple, 23 is a spark plug, 24 is a pressure sensor, 25 is a heating cavity, 26 is a heat insulation sleeve, 27-1 is an air path electric control valve, 27-2 is an ethylene path electric control valve, 28 is a nitrogen bottle, 29 is an air bottle, 30 is a vinyl bottle, 31 is a plurality of groups of light sources, 32 is a high-speed camera, 33 is a multi-probe optical fiber image transmission bundle, 34 is a gas phase detonation wave, 35 is a slow combustion wave stage, 36 is a turbulent flame acceleration stage, 37 is an over-drive detonation stage, and 38 is a stable detonation stage.
Detailed Description
The invention is further described with reference to the accompanying drawings and the specific implementation process.
Referring to fig. 1, in the present phase, due to the limitation of atomization level, the two-phase detonation combustion is limited, the problem of incomplete atomization of kerosene spray at normal temperature exists, and the incompletely atomized droplet group 1 enables combustion heat release after detonation to be in a discrete mode, so that oscillation of detonation wave propagation speed is caused, and as the particle size of droplets increases, the loss of detonation wave speed is larger, the cell structure also becomes irregular, and the propagation stability of detonation wave is reduced; particularly, when the engine runs at high frequency, the stable propagation boundary of the detonation wave becomes narrow, and residual liquid drops can cause the local decoupling of the detonation wave, so that detonation combustion failure is caused. Meanwhile, under the action of the front guide shock wave, a liquid drop crushing process 2 can occur, the crushed liquid drops can generate liquid drop micro-explosion 4 under the action of a flame surface following the shock wave, the liquid drops can form a local hot spot 3 in a high-temperature environment through micro-explosion combustion, the local hot spot is favorable for forming local over-drive detonation, and then the detonation wave is promoted to be detonated again. It can be seen that in detonation combustion, the existence of liquid drops has great influence on the propagation speed of detonation waves and the cell structure, so that the liquid drops need to be measured to search for a stable operation method of high-frequency two-phase detonation combustion.
Example 1:
referring to fig. 2, in the present example, a hanging droplet generating apparatus is used, which includes a stepping motor 8, a ball screw moving rod 9, a heat insulating jacket 14, and a hanging wire 16. The suspension method liquid drop 17-1 is extended into an optical observation area of the detonation tube by using a stepping motor controller 7, a stepping motor 8 and a ball screw moving rod 9, and the extending depth can be controlled by the stepping motor controller 7. The droplets are heated by a heating chamber 25 with a resistance wire 12, the heating temperature is controlled by a temperature controller 19, and the temperature of the heating chamber is monitored by a thermocouple 22 in real time. The time at which the droplet begins to microexplosion is measured by optical observation of the zone 20, using schlieren technique. The detonation tube 10 uses ethylene/air to generate detonation waves, and uses the time of micro-explosion of liquid drops as reference, and uses the computer 21 to control the supply of fuel and oxidant and the triggering of ignition signals, so as to ensure the interaction between the detonation waves and the micro-explosion liquid drops. And observing the cell structure when the detonation wave passes through the micro-detonation liquid drop through the optical observation area 20 by using a three-dimensional flame reconstruction technology based on stereoscopic laser induced fluorescence and a high-speed shadow and schlieren test method. The velocity of the detonation wave when passing through the micro-detonation liquid drop is calculated by using the distance between the two pressure sensors arranged near the optical observation area 20 and the arrival time difference of the pressure wave peak of the detonation wave. The temperature of the heating cavity 25 is changed by the temperature controller 19 to obtain liquid drops with different micro-explosion degrees, and the structure and the propagation speed of the detonation wave under different conditions are tested.
Example 2:
referring to fig. 3, in the present example, the droplet 17-2 is suspended on the droplet generator 18, the droplet generator 18 controls the droplet 17-2 to be thrown into the detonation tube 10 with the initial temperature set, the detonation tube 10 uses ethylene/air to initiate detonation waves, and the computer 21 controls the trigger timing of the droplet 17-2 falling and the gas phase detonation wave 34 initiating, so that the droplet interacts with the flame/detonation waves in different development stages, such as a slow burning wave stage 35, a turbulent flame acceleration stage 36, an over-drive detonation stage 37 and a steady detonation stage 38. The propagation speed and the cell structure of the detonation wave are measured by the pressure/temperature signal acquisition instrument 15 and the three-dimensional optical diagnostic system (comprising a plurality of groups of light sources 31, a multi-probe optical fiber image transmission bundle 33 and a high-speed camera 32). The supply pressure of an ethylene/air bottle is changed to obtain a limit equivalence ratio close to stable propagation of detonation waves, near-limit conditions in a detonation chamber under the high-frequency working condition of an engine are simulated, and the influence of liquid drops on the detonation wave structure and the propagation speed under corresponding conditions is tested. The droplet generator 18 is used to change the droplet size and the propagation velocity and cell structure of the detonation wave passing through the droplets of different Weber numbers are measured using the above-described test and control method.
While the present invention has been described in detail and with reference to the drawings and the detailed description thereof, it is not intended to limit the invention to the embodiment, but it is possible for those skilled in the art to make various changes and modifications without departing from the spirit of the invention.
Claims (6)
1. A measuring device for detonation wave velocity and structure under action of liquid drops and a control method thereof comprise a main body heating cavity, a temperature control device, a detonation tube supply and control system, a liquid drop generation and control device, a test system and a control method, and are characterized in that: selecting initial conditions of the test, including key characteristic parameters of the liquid drops and the detonation waves and environmental conditions, and uniformly controlling the triggering time sequences of the liquid drop generator, the igniter and the high-speed camera by the high-precision signal generator to enable the liquid drops with different micro-explosion degrees and Weber numbers to act on the detonation waves in different development stages; the propagation speed and the structure of the detonation wave under the action of the liquid drops are measured by comprehensively using a high-frequency pressure sensor, a high-speed shadow, a schlieren and a three-dimensional flame reconstruction technology based on stereoscopic laser induced fluorescence.
The main body heating cavity and the temperature control device are used for heating the detonation tube, and the influence of the wall temperature on the liquid drop evaporation and the micro-explosion degree in the actual operation process of the detonation engine is simulated; and adjusting the heating temperature to obtain liquid drops with different evaporation and micro-explosion degrees, and measuring the detonation wave structure and the propagation speed of the detonation wave when the detonation wave sweeps across the liquid drops under different micro-explosion conditions by using a non-contact optical diagnosis system and a pressure sensor.
Comprehensively using high-speed schlieren, shadow and a three-dimensional flame reconstruction technology non-contact optical test method based on stereoscopic laser induced fluorescence, carrying out high-time and high-spatial-resolution flow field observation on the process of the interaction of liquid drops and detonation waves, and capturing the structure of the detonation waves in the process of the interaction of the liquid drops and the detonation waves; the quick response pressure sensors are axially arranged at different positions of the detonation tube, and the distance between the two pressure sensors and the pressure peak time difference of the detonation wave captured by the two pressure sensors are utilized to measure the propagation speed of the detonation wave when the detonation wave sweeps across the liquid drop.
Setting a corresponding trigger time sequence according to the time required by the micro-explosion of the liquid drop measured by the schlieren technology, controlling the detonation wave to sweep the micro-explosion liquid drop, and measuring the structure and the speed of the detonation wave by using a high-speed camera and a pressure sensor; the time sequence of dropping of the liquid drops, initiation of the detonation waves and shooting of the camera is strictly controlled through the same high-precision controller, so that the liquid drops interact with the detonation waves in different development stages, and the propagation speed and the structure of the detonation waves in different development stages when the detonation waves pass through the liquid drops are measured.
2. The near-limit two-phase detonation wave propagation stability measuring device and the control method thereof according to claim 1, characterized in that: the main body heating cavity and the temperature control device are composed of a heating cavity, a resistance wire, a heat insulation sleeve, a temperature controller and a glass observation window. The heating cavity is heated through a resistance wire; the heat insulation sleeve prevents heat loss and keeps the temperature in the heating cavity stable; the temperature controller displays the temperature of the heating cavity, controls the temperature and simulates different wall temperatures of the detonation engine in the actual operation process; the glass observation window is used for shadow, schlieren and flame self-luminescence observation.
3. The near-limit two-phase detonation wave propagation stability measuring device and the control method thereof according to claim 1, characterized in that: the detonation tube supply and control system is composed of a ethylene bottle, an air bottle, an ethylene path electromagnetic valve, an air path electromagnetic valve, a detonation tube, a nitrogen bottle, a spark plug and a computer. The ethylene bottle and the air bottle are used for storing high-pressure fuel and oxidant, and the mixing equivalence ratio can be adjusted by changing the supply pressure of the air bottle; the ethylene path electromagnetic valve and the air path electromagnetic valve are respectively used for controlling the opening and closing of the fuel and oxidant gas cylinders; ethylene and air are mixed and then are fed into a detonation tube; the detonation tube is a tubular device with one closed end, and a detonation reinforcing structure is arranged in the detonation tube and used for generating and transmitting detonation waves; the nitrogen cylinder is used for providing isolation and purge gas; the spark plug is used for ignition, and the ignition energy is less than 50 mJ; the computer is used for uniformly controlling the triggering of the electromagnetic valve and the ignition signal of the spark plug, and further controlling the triggering time of the detonation wave.
4. The near-limit two-phase detonation wave propagation stability measuring device and the control method thereof according to claim 1, characterized in that: the droplet generating device comprises two types: a hanging droplet generating device and a flying droplet generating device; the liquid drop generating device with the suspension method comprises a hanging wire, a stepping motor, a ball screw moving rod and a heat insulation sleeve, wherein liquid drops are suspended on the hanging wire, the liquid drops are controlled to be thrown into a detonation tube in a heating cavity through the stepping motor, the throwing height of the liquid drops is adjusted through the ball screw moving rod, the heat insulation sleeve prevents the thermal environment in the cavity from influencing the evaporation of the liquid drops in advance before the test is started, the liquid drops can be placed in an optical observation area in the heating cavity, detonation waves are triggered when the liquid drops are subjected to micro-explosion, the micro-explosion liquid drops interact with the detonation waves, and the structure and the speed of the detonation waves when the micro-explosion liquid drops exist are measured; the droplet generating device of the flying droplet method is composed of a stepping motor, a ball screw moving rod and a droplet generator, and is different from the droplet generating device of the suspension method in that droplets are generated by the droplet generating device, the droplets are directly dripped into a detonation tube by the flying droplet method through the stepping motor, the droplet generating device can generate micro-scale droplets, the diameter of the droplets can be adjusted, and the droplet generating device is used for measuring the propagation speed and the structure of detonation waves when the droplets with different Weber numbers exist. The liquid drop control device mainly comprises a stepping motor controller, and the dripping time and the throwing height of the liquid drops can be controlled through the stepping motor controller, so that the liquid drops are ensured to accurately pass through the detonation wave.
5. The near-limit two-phase detonation wave propagation stability measuring device and the control method thereof according to claim 1, characterized in that: the test system consists of a pressure sensor, a thermocouple, a pressure/temperature signal acquisition instrument, a plurality of groups of light sources, a multi-probe optical fiber image transmission bundle and a high-speed camera. The pressure sensor and the thermocouple are fixed through a sensor mounting hole on the detonation tube, the pressure/temperature signal acquisition instrument is used for acquiring and analyzing pressure/temperature signals, the temperature signals are used for measuring the real temperature in the heating cavity, and the pressure signals are used for measuring the propagation speed of the detonation wave. The system comprises a plurality of groups of light sources, a multi-probe optical fiber image transmission bundle and a high-speed camera, wherein the non-contact optical test system is formed by the light sources, the multi-probe optical fiber image transmission bundle and the high-speed camera together, and the propagation speed and the structure of the detonation wave in the presence of liquid drops with different Weber numbers and micro-explosion degrees are comprehensively observed through an optical observation area by comprehensively using a high-speed shadow, a schlieren and a three-dimensional flame reconstruction technology based on stereoscopic laser induced fluorescence.
6. The near-limit two-phase detonation wave propagation stability measuring device and the control method thereof according to claim 1, characterized in that: the control method generates detonation waves with different strengths by adjusting conditions such as the mixture equivalence ratio, the initial pressure and the like; according to the time required by micro-explosion of the liquid drops measured by the schlieren technology, the corresponding trigger time sequences of the liquid drop generating device, the spark plug, the high-speed camera and the like are set, so that the liquid drops interact with flame/detonation waves with different development stages and different intensities, and the speed and the structure of the interaction of the flame/detonation waves and the liquid drops in the different development stages are measured by utilizing the shadow, the schlieren and the three-dimensional flame reconstruction technology based on the stereoscopic laser induced fluorescence.
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| US20080078359A1 (en) * | 2006-09-28 | 2008-04-03 | Jeffrey Barrett | Method and system for closed loop combustion control of a lean-burn reciprocating engine using ionization detection |
| CN109374915A (en) * | 2018-11-22 | 2019-02-22 | 西北工业大学 | Flame Propagation speed measurement method based on the spontaneous light characteristic of flame |
| CN110207801A (en) * | 2019-05-14 | 2019-09-06 | 西北工业大学 | Detonation wave three-dimensional structure reconstructing system based on Shadow Techniques |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080078359A1 (en) * | 2006-09-28 | 2008-04-03 | Jeffrey Barrett | Method and system for closed loop combustion control of a lean-burn reciprocating engine using ionization detection |
| CN109374915A (en) * | 2018-11-22 | 2019-02-22 | 西北工业大学 | Flame Propagation speed measurement method based on the spontaneous light characteristic of flame |
| CN110207801A (en) * | 2019-05-14 | 2019-09-06 | 西北工业大学 | Detonation wave three-dimensional structure reconstructing system based on Shadow Techniques |
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| 张义宁;王家骅;张靖周;: "两相多循环爆震波特性研究", 航空动力学报, no. 05 * |
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