CN110739602A - Pre-mixing type carbon dioxide pneumatic laser driven by pulse detonation rocket combustion - Google Patents
Pre-mixing type carbon dioxide pneumatic laser driven by pulse detonation rocket combustion Download PDFInfo
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01S—DEVICES USING THE PROCESS OF LIGHT AMPLIFICATION BY STIMULATED EMISSION OF RADIATION [LASER] TO AMPLIFY OR GENERATE LIGHT; DEVICES USING STIMULATED EMISSION OF ELECTROMAGNETIC RADIATION IN WAVE RANGES OTHER THAN OPTICAL
- H01S3/00—Lasers, i.e. devices using stimulated emission of electromagnetic radiation in the infrared, visible or ultraviolet wave range
- H01S3/09—Processes or apparatus for excitation, e.g. pumping
- H01S3/095—Processes or apparatus for excitation, e.g. pumping using chemical or thermal pumping
- H01S3/0951—Processes or apparatus for excitation, e.g. pumping using chemical or thermal pumping by increasing the pressure in the laser gas medium
- H01S3/0953—Gas dynamic lasers, i.e. with expansion of the laser gas medium to supersonic flow speeds
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Abstract
The invention discloses a pre-mixing type carbon dioxide pneumatic laser driven by pulse detonation rocket combustion, which comprises a pulse detonation rocket combustion device, a transition section and CO2A pneumatic laser generating device and an exhaust section. The pulse detonation rocket combustion device is used for generating a high-temperature and high-pressure gas heat source, is used as a total energy source for generating laser at downstream, and comprises a cylindrical shell, an oxidant injection panel and a turbulent flow spiral; the inner cavity of the cylindrical shell forms a pulse detonation combustion chamber. When the oxidant and the fuel are supplied in a pulse detonation combustion chamber in a pulse mode, collide with each other, uniformly mix and ignite, and under the action of the turbulent flow helix, pulse detonation combustion occurs in the pulse detonation combustion chamber; combustion gas is passed through CO2The pneumatic laser generating device generates pulse laser. The invention adopts the pulse detonation rocket combustion device as a pumping source, so that the produced laser has high efficiency and saves energy. When the device is used on a rocket or an aircraft, the device can generate thrust and laser without increasing the load.
Description
Technical Field
The invention relates to CO2The field of pneumatic lasers, in particular to a premixed carbon dioxide pneumatic laser driven by pulse detonation rocket combustion.
Background
The gas laser is a laser with most varieties, widest wavelength distribution area and most applications in a large family of lasers, and has the outstanding advantages of wide wavelength distribution area of a spectral line emitted by the gas laser, high beam quality and high output power.
Basic working principle of gas laser: the pumping source releases energy, gas particles are selectively excited to a certain high energy level, so that particle number inversion between a certain low energy level is formed, an activated medium is generated, laser output is generated through optical cavity resonance, and the energy of the pumping source is converted into optical energy.
The gas dynamic laser can directly convert heat energy into coherent radiation energy, and the heat source form (such as combustion, chemical reaction, electric arc heating, nuclear reaction and the like) is not limited. The rocket type combustion driving pneumatic laser with the fuel and the oxidant utilizes fuel combustion as a pumping source, does not need to provide extra energy from the outside, has the advantages of stable performance, simple structure, small volume, economy, practicability, capability of outputting high-power (up to megawatt) continuous laser and the like although the energy conversion rate (about 1% -2%) of the rocket type combustion driving pneumatic laser is not dominant in the laser, and particularly does not need a large-volume pressure recovery system (such as an ejector) compared with a chemical laser. These outstanding advantages make rocket-type combustion-driven gas-powered lasers readily available as practical intense laser light sources.
Rocket-type combustion driven CO2The pneumatic laser can be driven by hydrocarbon fuel through combustion with oxidant (such as oxygen and air), its consumption is low, and its fuel can be liquid toluene, benzene and kerosene or gaseous acetylene and methane hydrocarbon fuel, and its fuel selection principle is that it contains more carbon and less hydrogen, and is inflammable and explosive, and the water content in the product can be controlled by controlling fuel proportioning2The development of gas dynamic lasers has received great attention.
However, existing conventional rocket-type combustion driven CO2The laser has the following defects to be improved:
1. traditional rocket-type combustion driven CO2Lasers convert the chemical energy of a fuel into thermal energy by isobaric combustion (the form of combustion tissue currently employed in almost all power plants), which is ultimately converted into associated radiant energy (the light energy of the laser). However, it is not limited toThe isobaric combustion is organized combustion in a deflagration mode, the flame propagation speed is low, the thermodynamic cycle efficiency is low, so that the efficiency of converting heat energy into laser is low, and the energy conversion efficiency of the laser produced by the traditional rocket type combustion is about 1-2% generally. From a combustion thermodynamic cycle perspective, detonation combustion can reach 49% under the same conditions compared to a thermodynamic cycle efficiency where detonation is only about 27%, if used for rocket-type combustion driven CO2The laser can greatly improve the laser conversion efficiency.
2. CO driven by conventional rocket combustion2The laser is inefficient in producing laser light, so that when lasers with set output are produced, the required fuel quantity is large, the energy efficiency ratio is low, and the large equipment volume only enables the laser to be used for ground light-emitting experiments due to the low light-emitting rate and the fact that the laser is not specially designed .
3. Conventional rocket-type combustion driven CO2The laser is in a continuous light-emitting working mode, and the system complexity is required to be additionally increased on outputting pulse laser.
Disclosure of Invention
The invention aims to solve the technical problem that pulse detonation rocket combustion driven premixed carbon dioxide pneumatic lasers are provided aiming at the defects of the prior art, the pulse detonation rocket combustion driven premixed carbon dioxide pneumatic lasers adopt a pulse detonation rocket combustion device as a pumping source, and the advantages of high detonation combustion heat release rate and high thermodynamic cycle efficiency are fully utilized, so that high-temperature and high-pressure gas is high in laser efficiency generated by taking the high-temperature and high-pressure gas as the pumping source, energy is saved, when a pulse detonation engine is used as power on a rocket or a rocket-assisted aircraft, machines of a core machine can be reasonably designed to be multipurpose, namely, the pulse detonation rocket combustion device with the same set can be adopted to generate laser and thrust, the process can be realized on the same exhaust device with sets, and can also be connected with different exhaust devices.
In order to solve the technical problems, the invention adopts the technical scheme that:
premixed carbon dioxide pneumatic laser driven by pulse detonation rocket combustion comprises a pulse detonation rocket combustion device, a transition section and CO2A pneumatic laser generating device and an exhaust section.
The pulse detonation rocket combustion device comprises a cylindrical shell, an oxidant injection panel, a fuel injection panel and a turbulence spiral.
The cylindrical inner cavity of the cylindrical shell forms a pulse detonation combustion chamber.
The oxidant injection panel is provided with a plurality of oxidant injection channels along the circumferential direction.
The front end of the cylindrical shell is provided with a fuel injection channel corresponding to oxidant injection along the circumferential direction.
Each oxidant injection channel and each fuel injection channel are switched on and off through an electromagnetic valve.
The turbulent flow spiral is coaxially arranged in the pulse detonation combustion chamber.
CO2The pneumatic laser generating device is connected with the pulse detonation rocket combustion device through a transition section. CO 22The pneumatic laser generating device comprises a rectangular shell, an array spray pipe and an optical cavity which are arranged in the rectangular shell, and a laser outlet is arranged on the rectangular shell corresponding to the optical cavity.
An ignition device is also provided on the cylindrical housing downstream of the fuel injection passage, which ignition device enables pulse ignition.
When all the electromagnetic valves are opened, the oxidant sprayed from the oxidant spraying channel and the fuel sprayed from the fuel spraying channel collide and are uniformly mixed in the pulse detonation combustion chamber. And starting the ignition device, igniting the uniformly mixed oxidant and fuel, and generating pulse detonation combustion in the pulse detonation combustion chamber under the action of the turbulent flow helix. Combustion gas is passed through CO2The pneumatic laser generating device generates pulse laser.
The inner diameter D of the cylindrical shell and the length L of the cylindrical shell need to satisfy that L/D is more than or equal to 20.
The turbulent flow spiral length is between 2D and 10D, and the screw pitch is between 1/2D and 1D.
The plugging ratio of the turbulator helix is 30% to 50%, preferably about 38%.
A shell cooling channel is arranged in the cylindrical shell.
The oxidant is oxygen or air.
The transition section is of a circular torque structure.
The exhaust section is arranged at CO2The tail end of the pneumatic laser generating device is configured according to the working mode of the laser, and is in a reducing configuration only for the purpose of generating laser. When used for both lasing and thrust generation, assume a zoom configuration.
The ignition device is or both of a spark plug and a hot jet.
The invention has the following beneficial effects:
1. the pulse detonation rocket combustion device is used as a pumping source to convert chemical energy of fuel into heat energy of gas, the gas is accelerated through the array spray pipe, the laser is generated through the action of the optical cavity to achieve the purpose of combustion light generation, and simultaneously, the residual gas is discharged from the tail exhaust section2Pneumatic laser level about 1% -2%).
2. Because the efficiency of the produced laser is greatly improved, the required fuel quantity is small and the energy efficiency ratio is high when the laser with the same output quantity is produced, compared with the traditional rocket type combustion driving laser, the fuel can produce more laser or work for a longer time, when the laser is used on the ground, the laser is preferred schemes of producing high-power pulse laser in a smaller space (omitting a pressure recovery system).
3. For the aircraft using the rocket type pulse detonation engine as power, because the proportion of the heat energy of detonation combustion products converted into laser is 1.8-3.6% theoretically, most of the heat energy is still converted into gas kinetic energy to be discharged, sets of pulse detonation rocket combustion devices are adopted, and not only can laser be produced, but also thrust can be produced, so that the energy utilization path of the aircraft is expanded.
4. The aircraft using the rocket type pulse detonation engine as power has the function of generating laser through combustion, and a special laser generation system can be reduced; the laser can be provided for the rocket-borne laser equipment at the same time, such as laser ranging, guidance and the like; the defense and attack capabilities of the aircraft can be increased, such as emitting high-power intense pulse laser to damage (intercept) an incoming target or attack an enemy space target.
Drawings
Fig. 1 shows a schematic structural diagram of a premixed carbon dioxide gas dynamic laser driven by pulse detonation rocket combustion according to the present invention.
FIG. 2 shows an enlarged schematic view of an array nozzle.
Among them are: the fuel injection device comprises a fuel injection channel 1, an oxidant injection panel 2, an oxidant injection channel 3, a panel end cover 4, a shell cooling liquid inlet 5, a spark plug 6, a shell cooling channel 7, a cylindrical shell 8, a turbulent flow spiral 9, a pulse detonation combustor 10, a shell cooling liquid outlet 11, a transition section shell 12, an array spray pipe 13, an optical cavity 14, a laser outlet 15, an exhaust section shell 16 and a material supplementing hole 17.
In addition, in fig. 1: i represents a pulse detonation rocket combustion device; II represents a transition section; III denotes CO2A pneumatic laser generating device; and IV represents an exhaust section.
Detailed Description
The invention is described in further detail with reference to the drawings and the detailed description of the preferred embodiment.
In the description of the present invention, it is to be understood that the terms "left side", "right side", "upper part", "lower part", etc., indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, "", "second", etc., do not represent an important degree of the component parts, and thus are not to be construed as limiting the present invention.
As shown in figure 1, pulse detonation rocket combustion driven premixed carbon dioxide pneumatic lasers comprise a pulse detonation rocket combustion device I, a transition section II and CO which are coaxially arranged from left to right in sequence2A pneumatic laser generating device III and an exhaust section IV.
The pulse detonation rocket combustion device comprises a cylindrical shell 8, an oxidant injection panel 2 and a turbulent helix 9.
The cylindrical interior of the cylindrical housing forms a pulse detonation combustion chamber 10. In order to shorten the detonation distance of the pulse detonation wave and shorten the length of the pulse detonation combustion chamber as much as possible, the inner diameter D of the cylindrical shell and the length L of the cylindrical shell need to satisfy that L/D is more than or equal to 20.
The outer side of the oxidant injection panel is preferably provided with an injection panel cover 4 which connects the circumferential edge of the oxidant injection panel with the front end of the cylindrical casing.
The oxidant injection panel is provided with a plurality of oxidant injection channels 3 along the circumferential direction. Each oxidant injection channel is preferably horizontal, with an inlet end extending out of the injection panel and connected to an oxidant supply system and an outlet end communicating with the pulse detonation combustor. The oxidizing agent is oxygen, air, or the like, and preferably oxygen with a trace amount of nitrogen added thereto.
The front end of the cylindrical shell is provided with a fuel injection channel 1 which is equal to an oxidant injection channel in mathematical theory along the circumferential direction, each fuel injection channel is preferably in a vertical state, the inlet end of each fuel injection channel is connected with a fuel supply system, the outlet end of each fuel injection channel is communicated with the pulse detonation combustor, the provided fuel can be liquid toluene, benzene, kerosene or gaseous acetylene and methane hydrocarbon fuel, the fuel selection principle is that the fuel contains more carbon and less hydrogen and is flammable and explosive, the content of water in a product is controlled by controlling the fuel proportion, generally requires less than 1% of the total mass, and the fuel is easy to obtain.
The jet orifice of each oxidant injection channel and the jet orifice of each fuel injection channel are branches with a main path at the terminal, the front ends of the oxidant injection channels and the fuel injection channels are respectively provided with an electromagnetic valve on the main paths of the oxidant and the fuel, the propellant supply to the pulse detonation combustion chamber is controlled by controlling the on-off of the electromagnetic valves, and the electromagnetic valves are set to fixed on-off frequency, so that the propellant pulse supply to the detonation combustion chamber is realized, the pulse detonation frequency is controlled, and finally, the pulse light-emitting is realized.
A housing cooling channel 7 is provided in the cylindrical housing for the purpose of cooling the pulse detonation rocket combustion device. Preferably, a casing coolant inlet 5 is provided on the upper left side of the cylindrical casing, and a casing coolant outlet 11 is provided on the lower right side of the cylindrical casing.
An ignition device is also provided on the cylindrical housing downstream of the fuel injection passage, which ignition device is capable of pulse ignition, the ignition device is preferably or both of a spark plug and a hot jet, and in the present invention is preferably a spark plug 6, i.e., a high energy detonation, for igniting the propellant entering the pulse detonation combustion chamber 10, thereby forming pulse detonation combustion.
The turbulent spiral is coaxially arranged in the pulse detonation combustion chamber, is actually similar to a thin spring wire, and has the function of increasing the turbulence and shortening the conversion distance from detonation to detonation. The turbulent flow spiral length is between (2-10) D, the spiral pitch is between (1/2-1) D, the blocking ratio is between 30% and 50% (tests show that the blockage ratio is better around 38%), and the spiral turn number can be roughly determined according to the spiral length and the spiral pitch. The blockage ratio refers to the proportion of the turbulent flow spiral in the inner cavity of the cylindrical shell.
CO2The pneumatic laser generating device is connected with the pulse detonation rocket combustion device through a transition section; i.e. for connecting pulse detonation rocket fuelThe device comprises a cylindrical shell and a rectangular shell, and a transition section shell 12 is of a circular torque structure.
CO2The pneumatic laser generating device comprises a rectangular shell, an array spray pipe 13 and an optical cavity 14, wherein the array spray pipe 13 and the optical cavity 14 are arranged in the rectangular shell, and a laser outlet 15 is arranged on the rectangular shell corresponding to the optical cavity.
The array nozzle and the optical cavity are mature prior art, the structure of the array nozzle is shown in figure 2, and gas is accelerated to supersonic speed through the gap of the array nozzle. The feeding hole 17 arranged at the upper end of the array nozzle is used for supplementing insufficient components (such as CO)2、N2Etc.). The optical cavity has a specific geometry that enables the active medium to form an optical resonance that outputs coherent radiation, which is output as laser light from the laser exit. The optical cavity is preferably flanged to the exhaust section housing 16 in the exhaust section.
Transition section for connecting a cylindrical housing and a CO in a pulse detonation combustion device2The transition section shell 12 of the rectangular shell in the pneumatic laser generating device is of a circular torque structure, so that rectification is facilitated. The transition section shell comprises an upstream circular section and a downstream rectangular section, the longitudinal sectional area of the downstream rectangular section is not more than the circular sectional area of the tail part of the pulse detonation rocket combustion device, and the theoretical areas of the upstream circular section and the downstream rectangular section are equal and are better.
The exhaust section is arranged at CO2The tail end of the pneumatic laser generating device and the exhaust section shell 16 can be provided with different configurations according to the use function, and the tail end and the exhaust section shell can be in a reducing configuration only for the purpose of generating laser and can be in a contracting and expanding configuration when being used for generating laser and generating thrust simultaneously.
When all the electromagnetic valves are opened, the oxidant sprayed from the oxidant spraying channel and the fuel sprayed from the fuel spraying channel collide and are uniformly mixed in the pulse detonation combustion chamber; starting an ignition device, igniting the uniformly mixed oxidant and fuel, and generating pulse detonation combustion in the pulse detonation combustion chamber under the action of the turbulent flow helix; combustion gas is passed through CO2The pneumatic laser generating device generates pulse laser.
Referring to fig. 1, in a pulse detonation rocket combustion driven premixed carbon dioxide gas-driven laser according to the present invention, pulsesHigh-temperature high-pressure gas (the main component is CO) generated by detonation combustion of impact detonation combustion device2、N2And H2O) is CO2Working medium of the gas dynamic laser. Due to N2The vibration relaxation time of the molecule is very long, so that the main function of the molecule is to store vibration energy; n is a radical of2Vibrational energy level of molecule and CO2The high vibration energy level of the molecule is subjected to vibration coupling; and CO2The number of particles of low vibration level of the molecule is determined by the catalyst H2The deactivation of O is maintained at an equilibrium concentration near the translation temperature.
When the high-temperature mixed gas is rapidly expanded and accelerated through the array nozzle 13, the heat energy of the gas is rapidly changed into the kinetic energy of the gas, and the molecular translation temperature is rapidly reduced. CO 22The number of the molecular particles with the medium and low energy levels is also sharply reduced due to the rapid relaxation. High-level populations relax slowly and are "frozen" to maintain a high population density. This difference in relaxation rates is referred to as differential relaxation. Differential relaxation leads to CO2The high energy level population density exceeds the low energy level population density, which creates the necessary condition for generating stimulated radiation, i.e., the condition for population inversion. A medium satisfying such a condition is called an activation medium. Due to CO2High energy level molecule and N2Resonance coupling of molecular vibration energy, and continuous supplement of high-energy-level particle number; due to CO2Low energy level molecule and catalyst H2The resonance coupling of O molecules and the continuous evacuation of low-level particles represent the continuous stimulated radiation. The active medium is then optically resonated by the optical cavity 14 to obtain amplification and coherent radiation output, and the laser light is finally output from the laser exit 15.
As the combustion process in the pulse detonation combustor 10 is changed from -like isobaric combustion to approximately isochoric combustion, the energy release rate and the thermodynamic cycle efficiency are obviously improved, and CO can be used2The pneumatic laser generating device provides stronger high-temperature high-pressure gas.
Referring to FIG. 1, the CO of the present invention2The part III of the pneumatic laser generating device also comprises a transition section 12 which is burnt by a flange and pulse detonationThe device is connected, actually, round-square structures are used for connecting a detonation combustion device and a pneumatic laser, high-temperature and high-pressure gas is led to the array spray pipe 13, the gas expands and accelerates after passing through the array spray pipe to form supersonic low-pressure airflow which is inconvenient to discharge, the exhaust section 16 has the function of enabling the device to exhaust smoothly so as to work continuously, the device is in a reducing configuration when only laser is produced, partial kinetic energy of the supersonic airflow is recovered to pressure potential energy, the pressure is recovered to be close to the atmospheric pressure so as to be convenient to discharge, and the device is in a reducing configuration when laser is produced and thrust is also produced, namely the kinetic energy of gas discharge is continuously utilized while the conversion from heat energy to light energy is realized.
Although the preferred embodiments of the present invention have been described in detail, the present invention is not limited to the details of the embodiments, and various equivalent modifications can be made within the technical spirit of the present invention, and the scope of the present invention is also within the scope of the present invention.
Claims (9)
1, pulse detonation rocket combustion driven premixed carbon dioxide pneumatic laser, characterized by comprising a pulse detonation rocket combustion device, a transition section, and CO2The device comprises a pneumatic laser generating device and an exhaust section;
the pulse detonation rocket combustion device comprises a cylindrical shell, an oxidant injection panel, a fuel injection panel and a turbulent flow spiral;
the cylindrical inner cavity of the cylindrical shell forms a pulse detonation combustion chamber;
the oxidant injection panel is provided with a plurality of oxidant injection channels along the circumferential direction;
a fuel injection channel corresponding to oxidant injection is arranged at the front end of the cylindrical shell along the circumferential direction;
each oxidant injection channel and each fuel injection channel are switched on and off through an electromagnetic valve;
the turbulent flow spiral is coaxially arranged in the pulse detonation combustion chamber;
CO2the pneumatic laser generating device is connected with the pulse detonation rocket combustion device through a transition section; CO 22The pneumatic laser generating device comprises a rectangular shell, an array spray pipe and an optical cavity which are arranged in the rectangular shell, and a laser outlet is arranged on the rectangular shell corresponding to the optical cavity;
the cylindrical shell positioned at the downstream of the fuel injection channel is also provided with an ignition device which can realize pulse ignition;
when all the electromagnetic valves are opened, the oxidant sprayed from the oxidant spraying channel and the fuel sprayed from the fuel spraying channel collide and are uniformly mixed in the pulse detonation combustion chamber; starting an ignition device, igniting the uniformly mixed oxidant and fuel, and generating pulse detonation combustion in the pulse detonation combustion chamber under the action of the turbulent flow helix; combustion gas is passed through CO2The pneumatic laser generating device generates pulse laser.
2. The pulse detonation rocket combustion driven premixed carbon dioxide pneumatic laser according to claim 1, characterized in that: the inner diameter D of the cylindrical shell and the length L of the cylindrical shell need to satisfy that L/D is more than or equal to 20.
3. The pulse detonation rocket combustion driven premixed carbon dioxide pneumatic laser according to claim 2, characterized in that: the turbulent flow spiral length is between 2D and 10D, and the screw pitch is between 1/2D and 1D.
4. The pulse detonation rocket combustion driven premixed carbon dioxide pneumatic laser of claim 3, characterized in that: the plugging ratio is 30% to 50%, preferably about 38%.
5. The pulse detonation rocket combustion driven premixed carbon dioxide pneumatic laser according to claim 1, characterized in that: a shell cooling channel is arranged in the cylindrical shell.
6. The pulse detonation rocket combustion driven premixed carbon dioxide pneumatic laser according to claim 1, characterized in that: the oxidant is oxygen or air.
7. The pulse detonation rocket combustion driven premixed carbon dioxide pneumatic laser according to claim 1, characterized in that: the transition section is of a circular torque structure.
8. The pulse detonation rocket combustion driven premixed carbon dioxide pneumatic laser according to claim 1, characterized in that: the exhaust section is arranged at CO2The tail end of the pneumatic laser generating device is configured according to the working mode of the laser, and is in a reducing configuration only when used for generating laser; when used for both lasing and thrust generation, assume a zoom configuration.
9. The pulse detonation rocket combustion driven premixed carbon dioxide pneumatic laser device according to claim 1, wherein the ignition device is or two of spark plug and hot jet.
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| CN113969849A (en) * | 2021-09-26 | 2022-01-25 | 中国人民解放军战略支援部队航天工程大学 | Single-nozzle rocket engine with modular design |
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