CN110707521A - Premixed carbon dioxide pneumatic laser driven by continuous rotation detonation rocket combustion - Google Patents
Premixed carbon dioxide pneumatic laser driven by continuous rotation detonation rocket combustion Download PDFInfo
- Publication number
- CN110707521A CN110707521A CN201911042324.0A CN201911042324A CN110707521A CN 110707521 A CN110707521 A CN 110707521A CN 201911042324 A CN201911042324 A CN 201911042324A CN 110707521 A CN110707521 A CN 110707521A
- Authority
- CN
- China
- Prior art keywords
- laser
- detonation
- continuous rotation
- fuel
- rocket
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- 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
-
- 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
- H01S3/14—Lasers, i.e. devices using stimulated emission of electromagnetic radiation in the infrared, visible or ultraviolet wave range characterised by the material used as the active medium
- H01S3/22—Gases
- H01S3/223—Gases the active gas being polyatomic, i.e. containing two or more atoms
- H01S3/2232—Carbon dioxide (CO2) or monoxide [CO]
Abstract
The invention discloses a premixed carbon dioxide pneumatic laser driven by combustion of a continuous rotation detonation rocket, which comprises a continuous rotation detonation combustion device, a transition section and CO2A pneumatic laser generating device and an exhaust section. The continuous rotation detonation combustion device is used for generating a high-temperature and high-pressure gas heat source which is used as a total energy source for downstream laser output; comprising a housing, a central cone, a rotating detonation combustor and an injection panel. The transition section enables the fuel gas after the combustion device to adapt to the change of configuration, and the fuel gas smoothly flows through the array spray pipe with the minimum total pressure loss. CO 22The pneumatic laser generating device comprises an array nozzle and an optical cavity. The exhaust section enables the product gas after light emitting to be rapidly exhausted to the outside. The invention adopts the continuous rotation detonation rocket combustion device as a pumping source, so the efficiency of the produced laser is high, and the energy is saved. Can be used on a rocket or a rocket-assisted aircraft, and can produce the rocket without increasing the load of the rocket or the rocket-assisted aircraftGenerates thrust and can generate laser. And can also be used as a high-power continuous strong laser light source on the ground.
Description
Technical Field
The invention relates to CO2The field of pneumatic lasers, in particular to a premixed carbon dioxide pneumatic laser driven by continuous rotation detonation rocket combustion.
Background
The gas laser is a laser with the most varieties, the widest wavelength distribution area and the widest application in the laser family. Its outstanding advantage is: the wavelength distribution area of the emitted spectral line is wide, the quality of the light beam is high and the output power is high. Compared with other lasers, the gas laser also has the advantages of high conversion efficiency, simple structure, low manufacturing cost and the like, thereby being widely applied.
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 fuel and 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 (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 huge pressure recovery system (such as an ejector) compared with a chemical laser, so that the rocket-type combustion driving pneumatic laser can easily become a practical strong laser light source.
Rocket-type combustion driven CO2The pneumatic laser can be driven by common hydrocarbon fuel through a method of combustion with oxidant (such as oxygen and air), the consumption is low, the fuel can be liquid toluene, benzene and kerosene or gaseous acetylene and methane hydrocarbon fuel, the fuel is selected as the principle that the fuel contains more carbon and less hydrogen and is flammable and explosive, and the water content in the product is controlled by controlling the fuel proportion. The laser can not only output continuous wave high-power laser and be used for laser propulsion and other purposes requiring continuous high-power laser, but also has a wavelength suitable for damaging a far infrared detector (for laser damage). Thus rocket-like combustion drives CO2The 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, isobaric combustion is organized as a deflagrationCombustion, flame propagation speed is slow, thermodynamic cycle efficiency is low, so the efficiency of converting heat energy into laser is low, and the energy conversion efficiency of laser produced through traditional rocket type combustion is usually about 1% -2%. 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 combustion2Since the laser output from the laser is inefficient, the amount of fuel required for generating a laser of a set output is large, and the energy efficiency ratio is low. And because the light-emitting rate is low and the special design is not carried out, the large equipment volume ensures that the equipment is only used for ground light-emitting experiments.
Disclosure of Invention
The technical problem to be solved by the invention is to provide a continuous rotation detonation rocket combustion driven premixing type carbon dioxide pneumatic laser aiming at the defects of the prior art, wherein the continuous rotation detonation rocket combustion driven premixing type carbon dioxide pneumatic laser adopts a continuous rotation detonation rocket combustion device as a pumping source, and fully utilizes the advantages of high detonation combustion heat release rate and high thermodynamic cycle efficiency, so that high-temperature and high-pressure gas is used as the pumping source to produce high laser efficiency, and energy is saved. When the rotary detonation engine is used as power on a rocket or a rocket-assisted aircraft, the multiple purposes of the core engine can be realized through reasonable design, namely the same set of continuous rotary detonation rocket combustion device is adopted, so that the laser can be produced, the thrust can be produced, the process can be realized on the same set of exhaust device, and the process can also be realized by connecting different exhaust devices. When the laser is used on the ground, the laser can be used for generating high-power continuous laser.
In order to solve the technical problems, the invention adopts the technical scheme that:
a premixed carbon dioxide pneumatic laser driven by continuous rotation detonation rocket combustion comprises a continuous rotation detonation combustion device, a transition section and CO2A pneumatic laser generating device and an exhaust section.
The continuous rotary detonation combustor includes a housing, a central cone, a rotary detonation combustor, and an injection panel.
The shell is cylindrical and is coaxially sleeved on the periphery of the central cone. The central cone comprises a cylindrical portion and a conical portion which are coaxially arranged.
A rotary detonation combustion chamber is formed between the outer wall surface of the cylindrical part and the inner wall surface of the shell, and the longitudinal section of the rotary detonation combustion chamber is annular.
The jetting panel is respectively connected with the end part of the shell and the end part of the cylindrical part, a fuel jetting channel and an oxidant jetting channel are arranged on the jetting panel, a fuel jetting port of the fuel jetting channel and an oxidant jetting port of the oxidant jetting channel can be intersected, and the intersection point is positioned in the rotary detonation combustion chamber.
The housing is provided with an ignition device for igniting the fuel ejected from the fuel ejection port and the oxidant ejected from the oxidant ejection port. Wherein the oxidant is oxygen or air.
CO2The 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.
Transition section for connecting a continuous rotary detonation combustion device and CO2The pneumatic laser generating device is characterized in that the tip of the conical part faces the transition section. The exhaust section can make the product gas discharge outside fast after the light-emitting.
Annular width δ and minimum length L of a rotary detonation combustor in a rotary detonation combustorminThe following calculation formula is satisfied:
delta is more than or equal to 0.5 lambda, and delta is more than or equal to d when liquid fuel is adopted.
Wherein h is*＝(12±5)λ
In the formula, lambda is the cell size corresponding to the mixed gas of the rotary detonation combustion chamber under the chamber pressure, and d is the minimum diameter of the fuel liquid drop.
The circumference l of the rotary knocking combustion chamber satisfies the following calculation formula:
wherein h is the height of the mixture in the rotary detonation combustor and is approximately equal to the height h of the detonation wave*。UjThe injection speed depends on the incoming flow speed of the oxidant. D is the propagation speed of the detonation wave.
A shell cooling liquid channel is arranged in the shell.
A cone cooling liquid channel is arranged in the central cone.
The outer side of the jetting panel is provided with a shell end cover, a fuel hydrops cavity and an oxidant buffer cavity are arranged in the shell end cover, the fuel hydrops cavity is respectively connected with the fuel supply system and the fuel jetting channel, and the oxidant buffer cavity is respectively connected with the oxidant supply system and the oxidant jetting channel.
The ignition device is one or two of a spark plug and a hot jet.
The transition section is a circular torque structure and comprises an upstream circular section and a downstream rectangular section, the upstream circular section is connected with the continuous rotation detonation combustion device, and the downstream rectangular section is connected with the CO2The pneumatic laser generating device is connected. The longitudinal sectional area of the downstream rectangular section does not exceed the circular sectional area of the tail part of the continuous rotation detonation combustion device.
The configuration of the exhaust section is dependent upon the mode of operation of the laser, and the exhaust section is of a reduced configuration when used solely for laser production. When the laser and the thrust are generated, the exhaust section is in a zooming configuration.
The invention has the following beneficial effects:
1. the continuous rotation detonation rocket combustion device is used as a pumping source, chemical energy of fuel is converted into heat energy of fuel gas, the fuel gas is accelerated through the array spray pipe, laser is generated under the action of the optical cavity, the purpose of combustion light generation is achieved, and meanwhile residual fuel gas is discharged from the tail exhaust section. Because the continuous rotation detonation combustion technology is adopted, the continuous rotation detonation is one of detonation combustionThe realization form has the characteristics of continuous working and continuous output besides the characteristics of detonation combustion. The working mode is a continuous rotation detonation rocket combustion mode when the fuel carries the oxidant and the fuel. The detonation combustion consumes unburned mixture in a mode of coupling shock wave and combustion wave, the propagation speed can reach thousands of meters per second, and extremely high gas pressure (more than 15-55atm) and gas temperature (more than 2800K) can be generated. Because the detonation wave transmission speed is very high, the subsequent combustion process can be regarded as an isochoric combustion process, so that the thermodynamic cycle efficiency is very high, the produced laser has high efficiency, and the production efficiency can be almost doubled (the existing rocket type combustion drives CO)2Pneumatic laser level about 1-2%).
2. Because the efficiency of the produced laser is greatly improved, when the laser with the same output quantity is produced, the required fuel quantity is small, the energy efficiency ratio is high, and compared with the traditional combustion driving laser, the same fuel can produce more lasers or work for a longer time. When used on the ground, it is a preferred solution to generate high power continuous laser in a small space (omitting the pressure recovery system).
3. For the aircraft taking the rocket type continuous rotation 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, the same set of continuous rotation detonation rocket combustion device is adopted, not only can laser be produced, but also thrust can be produced, and therefore the energy utilization path of the aircraft is expanded.
4. The rocket type continuous rotation detonation engine powered aircraft 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 continuous laser to damage (intercept) an incoming target or attack an enemy space target.
Drawings
Fig. 1 shows a schematic structure diagram of a premixed carbon dioxide gas dynamic laser driven by continuous rotation detonation rocket combustion in the invention.
FIG. 2 shows a schematic diagram of the configuration of the array nozzle.
Among them are: 1 oxidant injection channel, 2 cone cooling liquid inlet, 3 fuel injection channel, 4 cone cooling liquid outlet, 5 injection panel, 6 shell cooling liquid inlet, 7 spark plug, 8 hot jet inlet, 9 shell, 10 rotary detonation combustor, 11 shell cooling liquid outlet, 12 central cone, 13 transition section shell, 14 array spray pipe, 15 optical cavity, 16 laser outlet and 17 exhaust section shell; 18 feed holes.
In fig. 1, i denotes a continuous rotation knocking combustion device; II represents a transition section; III denotes CO2A pneumatic laser generating device; and IV represents an exhaust section.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific preferred embodiments.
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, and that "first", "second", etc., do not represent an important degree of the component parts, and thus are not to be construed as limiting the present invention. The specific dimensions used in the present example are only for illustrating the technical solution and do not limit the scope of protection of the present invention.
As shown in figure 1, the premixed carbon dioxide pneumatic laser driven by the continuous rotation detonation rocket combustion comprises a continuous rotation detonation 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 continuous rotation detonation combustion device is a pumping source and is CO2And the pneumatic laser generating device III provides the high-temperature and high-pressure gas after combustion as the total energy for downstream laser generation.
The continuous rotary detonation combustion device comprises a housing 9, a central cone 12, a rotary detonation combustion chamber 10 and an injection panel 5.
The shell is cylindrical and is coaxially sleeved on the periphery of the central cone.
A housing coolant passage is provided in the housing for cooling the rotary detonation combustion device. Preferably, the left side of the upper part of the shell is provided with a shell cooling liquid inlet 6, and the right side of the lower part of the shell is provided with a shell cooling liquid outlet 11.
An ignition device, preferably one or both of a spark plug and a heat jet, is also provided on the housing. In the present invention, the ignition device comprises both a spark plug and a hot jet, i.e. both a spark plug 7 and a hot jet inlet 8 are provided in the upper part of the housing.
The spark plug 7 and the hot jet inlet 8 provide two initiation modes for detonation, namely spark plug high energy ignition initiation and hot jet initiation. When the ignition is carried out, an optional ignition mode is available.
The central cone comprises a cylindrical portion and a conical portion which are coaxially arranged. The left side of the cylindrical portion is preferably aligned with the left side of the housing. A gap between the outer wall surface of the cylindrical part and the inner wall surface of the shell forms a rotary detonation combustion chamber, and the longitudinal section of the rotary detonation combustion chamber is annular and is a place for rotary detonation combustion.
The overall laser size is determined by the size of the upstream rotary detonation combustor, the annular width δ (i.e., the gap between the central conical cylindrical portion and the housing) and the minimum length L of the rotary detonation combustor in the rotary detonation combustorminThe following calculation formula is satisfied:
delta is more than or equal to 0.5 lambda, and delta is more than or equal to d when liquid fuel is adopted;
wherein h is*＝(12±5)λ
In the formula, lambda is the cell size corresponding to the mixed gas of the rotary detonation combustion chamber under the chamber pressure, and d is the minimum diameter of the fuel liquid drop.
The circumference l of the rotary knocking combustion chamber satisfies the following calculation formula:
wherein h is the height of the mixture in the rotary detonation combustor and is approximately equal to the height h of the detonation wave*；UjThe jet velocity is mainly determined by the incoming flow velocity of oxidant (air) and is at most sonic; d is the propagation speed of the detonation wave.
The fuel and oxidant mixing process is mainly affected by the injection mode and injection pressure drop, when the injection pressure drop is Pf/P c2 and Pox/PcWhen 3, the obtained detonation wave has good stability. PfFor the pressure, P, of the fuel in the injection chamberoxPressure of oxidant in injection cavity, PcIs the rotational detonation combustion chamber pressure.
A cone cooling liquid channel is preferably arranged in the central cone, and comprises a cone cooling liquid inlet 2 and a cone cooling liquid outlet 4.
The injection panel is connected to the end of the housing and the end of the cylindrical portion (i.e., the left side alignment end), respectively.
The injection panel is preferably provided with fuel injection channels 3 and oxidant injection channels 1 which are distributed along the circumference and equal in number, fuel outlets of the fuel injection channels and oxidant outlets of the oxidant injection channels can intersect, preferably are perpendicular, and the intersection point is located in the rotary detonation combustion chamber.
The injection panel 5 provides a rotating detonation combustion chamber with propellant continuously.
The outer side of the jetting panel is provided with a shell end cover, a fuel hydrops cavity and an oxidant buffer cavity are arranged in the shell end cover, the fuel hydrops cavity is respectively connected with the fuel supply system and the fuel jetting channel, and the oxidant buffer cavity is respectively connected with the oxidant supply system and the oxidant jetting channel.
The arrangement of the fuel hydropneumatic chamber and the oxidant buffer chamber can keep the continuous and stable injection of the propellant.
The cone coolant inlet 2 and the cone coolant outlet 4 preferably protrude from the injection face plate and the housing end cap, respectively, for the addition or removal of cone coolant.
The ignition device is used for igniting the fuel sprayed from the fuel spraying port and the oxidant sprayed from the oxidant spraying port. Wherein the oxidant comprises oxygen or air, preferably oxygen with trace amounts of nitrogen added. The fuel can be liquid toluene, benzene, kerosene, or gaseous acetylene, methane hydrocarbon fuel, the fuel is selected as the principle that the fuel contains more carbon and less hydrogen, is inflammable and explosive, the water content in the product is controlled by controlling the fuel proportion, and the water content is generally required to be less than 1 percent of the total mass
The oxidant, fuel such as methane or acetylene, is easily obtained.
CO2The pneumatic laser generating device comprises a rectangular shell, an array nozzle 14 and an optical cavity 15, wherein the array nozzle 14 and the optical cavity 15 are arranged in the rectangular shell, and a laser outlet 16 is arranged on the rectangular shell corresponding to the optical cavity. The longitudinal section of the rectangular shell is rectangular, and the optical cavity is also referred to as an optical resonant cavity for short.
The array nozzle 14 and the optical cavity 15 are well known in the art, and the structure of the array nozzle is shown in fig. 2, and gas is accelerated to supersonic speed through the gap of the array nozzle. The upper end of the array nozzle is provided with a feeding hole 18 for feeding insufficient components (such as CO)2、N2Etc.). The optical cavity 15 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 16. The optical cavity 15 is preferably flanged to an exhaust section housing 17 in the exhaust section.
The transition section is used for connecting a cylindrical shell and CO in a continuous rotation detonation combustion device2The tip of the conical part faces the transition section, so that rectification is facilitated.
The transition section casing 13 is preferably of a circular torque structure, so that the fuel gas after the combustion device is adapted to the change of configuration, and smoothly flows through the array nozzle with the minimum total pressure loss.
The transition section comprises an upstream circular section and a downstream rectangular section, the upstream circular section is connected with the continuous rotation detonation combustion device, and the downstream rectangular section is connected with the CO2Pneumatic laser generator connection. The longitudinal sectional area of the downstream rectangular section is not more than the circular sectional area of the tail part of the continuous rotation detonation combustion device, and the longitudinal sectional area of the downstream rectangular section is equal to the circular sectional area of the tail part of the continuous rotation detonation combustion device, so that the continuous rotation detonation combustion device is more preferable.
The exhaust section is arranged at CO2The tail end of the pneumatic laser generating device and the exhaust section shell 17 can be provided with different configurations according to use functions, and are in a reducing configuration only for laser generating application and can be in a contracting and expanding configuration when being used for laser generating and thrust generating at the same time.
Referring to FIG. 1, premixed CO driven by combustion of a continuous rotation detonation rocket in accordance with the present invention2In the gas dynamic laser, the rotary detonation combustion device knocks and burns the generated high-temperature high-pressure gas (the main component is CO)2、N2And H2O) is CO2And a working medium of a laser generating device III. 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 14, 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 H2Resonance coupling of O molecules, low-level populationIs continuously evacuated, thus representing a continuous stimulated emission. The active medium is then optically resonated by the optical cavity 15 to obtain amplification and coherent radiation output, and the laser light is finally output from the laser exit 16.
As the combustion process in the rotary detonation combustor 10 is changed from ordinary isobaric combustion to approximate isovolumetric 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. Compared with the traditional combustion chamber, the rotary detonation combustion chamber 10 has shorter size, thereby reducing the overall size of the gas dynamic laser and being beneficial to the miniaturization of the gas dynamic laser.
Referring to FIG. 1, the transition piece housing 13 of the present invention, which is flanged to the continuous rotary detonation combustor, is essentially a circular torque structure for connecting the rotary detonation combustor to the CO2And the pneumatic laser generating device is used for introducing high-temperature and high-pressure gas to the array nozzle 14. After passing through the array spray pipe, gas is expanded and accelerated to form supersonic low-pressure airflow which is inconvenient to discharge, the exhaust section has the function of enabling the device to exhaust smoothly so as to work continuously, the device is in a reduction configuration when only laser is generated, and partial kinetic energy of the supersonic airflow is recovered to pressure potential energy to enable the pressure to be recovered to be close to atmospheric pressure; the laser generator is in a zooming configuration when generating laser and thrust, so that the kinetic energy discharged by gas 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. The utility model provides a continuous rotation knockings rocket combustion driven mixes formula carbon dioxide gas dynamic laser in advance which characterized in that: comprises a continuous rotation detonation combustion device, a transition section and CO2A pneumatic laser generating device and an exhaust section;
the continuous rotation detonation combustion device comprises a shell, a central cone, a rotation detonation combustion chamber and an injection panel;
the shell is cylindrical and is coaxially sleeved on the periphery of the central cone; the central cone comprises a cylindrical part and a conical part which are coaxially arranged;
a rotary detonation combustion chamber is formed between the outer wall surface of the cylindrical part and the inner wall surface of the shell, and the longitudinal section of the rotary detonation combustion chamber is annular;
the jetting panel is respectively connected with the end part of the shell and the end part of the cylindrical part, a fuel jetting channel and an oxidant jetting channel are arranged on the jetting panel, a fuel jetting port of the fuel jetting channel and an oxidant jetting port of the oxidant jetting channel can be intersected, and the intersection point is positioned in the rotary detonation combustion chamber;
the casing is provided with an ignition device for igniting the fuel jetted from the fuel jetting port and the oxidant jetted from the oxidant jetting port; wherein the oxidant is oxygen or air;
CO2the 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;
transition section for connecting a continuous rotary detonation combustion device and CO2The tip of the conical part faces the transition section; the exhaust section can make the product gas discharge outside fast after the light-emitting.
2. The continuous rotation detonation rocket combustion driven premixed carbon dioxide pneumatic laser as claimed in claim 1, wherein: annular width δ and minimum length L of a rotary detonation combustor in a rotary detonation combustorminThe following calculation formula is satisfied:
delta is more than or equal to 0.5 lambda, and delta is more than or equal to d when liquid fuel is adopted;
wherein h is*＝(12±5)λ
In the formula, lambda is the cell size corresponding to the mixed gas of the rotary detonation combustion chamber under the chamber pressure, and d is the minimum diameter of the fuel liquid drop.
3. The continuous rotation detonation rocket combustion driven premixed carbon dioxide pneumatic laser device according to claim 2, characterized in that: the circumference l of the rotary knocking combustion chamber satisfies the following calculation formula:
wherein h is the height of the mixture in the rotary detonation combustor and is approximately equal to the height h of the detonation wave*；UjThe injection speed is determined by the incoming flow speed of the oxidant; d is the propagation speed of the detonation wave.
4. The continuous rotation detonation rocket combustion driven premixed carbon dioxide pneumatic laser as claimed in claim 1, wherein: a shell cooling liquid channel is arranged in the shell.
5. The continuous rotation detonation rocket combustion driven premixed carbon dioxide pneumatic laser as claimed in claim 1, wherein: a cone cooling liquid channel is arranged in the central cone.
6. The continuous rotation detonation rocket combustion driven premixed carbon dioxide pneumatic laser as claimed in claim 1, wherein: the outer side of the jetting panel is provided with a shell end cover, a fuel hydrops cavity and an oxidant buffer cavity are arranged in the shell end cover, the fuel hydrops cavity is respectively connected with the fuel supply system and the fuel jetting channel, and the oxidant buffer cavity is respectively connected with the oxidant supply system and the oxidant jetting channel.
7. The continuous rotation detonation rocket combustion driven premixed carbon dioxide pneumatic laser as claimed in claim 1, wherein: the ignition device is one or two of a spark plug and a hot jet.
8. The continuous rotation detonation rocket combustion driven premixed carbon dioxide pneumatic laser as claimed in claim 1, wherein: the transition section is a circular torque structure and comprises an upstream circular section and a downstream rectangular section, the upstream circular section is connected with the continuous rotation detonation combustion device, and the downstream rectangular section is connected with the CO2The pneumatic laser generating device is connected; the longitudinal sectional area of the downstream rectangular section does not exceed the circular sectional area of the tail part of the continuous rotation detonation combustion device.
9. The continuous rotation detonation rocket combustion driven premixed carbon dioxide pneumatic laser as claimed in claim 1, wherein: the structure of the exhaust section is determined according to the working mode of the laser, and when the exhaust section is only used for producing laser, the exhaust section is in a reduction configuration; when the laser and the thrust are generated, the exhaust section is in a zooming configuration.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911042324.0A CN110707521B (en) | 2019-10-30 | 2019-10-30 | Premixed carbon dioxide pneumatic laser driven by continuous rotation detonation rocket combustion |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911042324.0A CN110707521B (en) | 2019-10-30 | 2019-10-30 | Premixed carbon dioxide pneumatic laser driven by continuous rotation detonation rocket combustion |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110707521A true CN110707521A (en) | 2020-01-17 |
| CN110707521B CN110707521B (en) | 2020-12-29 |
Family
ID=69202764
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911042324.0A Active CN110707521B (en) | 2019-10-30 | 2019-10-30 | Premixed carbon dioxide pneumatic laser driven by continuous rotation detonation rocket combustion |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110707521B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110718843A (en) * | 2019-10-30 | 2020-01-21 | 中国人民解放军战略支援部队航天工程大学 | Air-breathing type continuous rotation detonation combustion driven premixing type carbon dioxide pneumatic laser |
| CN111525390A (en) * | 2020-04-27 | 2020-08-11 | 中国人民解放军国防科技大学 | Gas-phase gain nanoparticle generation device and laser |
| CN112467506A (en) * | 2020-11-20 | 2021-03-09 | 中国工程物理研究院应用电子学研究所 | Direct liquid cooling high-power laser gain device based on fuel jet combustion pump |
| CN114811654A (en) * | 2022-06-15 | 2022-07-29 | 清航空天(北京)科技有限公司 | Pressure-stabilizing flow-equalizing self-cooling continuous rotation detonation ramjet engine with radial oil supply |
| CN114877378A (en) * | 2022-06-02 | 2022-08-09 | 清航空天(北京)科技有限公司 | Inner ring detonation combustion chamber |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3898584A (en) * | 1972-11-09 | 1975-08-05 | Messerschmitt Boelkow Blohm | Gas dynamic laser device and method of operating such a device |
| DE2618357A1 (en) * | 1976-04-27 | 1977-11-17 | Messerschmitt Boelkow Blohm | GAS DYNAMIC CO DEEP 2 LASER |
| US4100507A (en) * | 1976-02-28 | 1978-07-11 | Messerschmitt-Bolkow-Blohm Gmbh | Method for exciting a gas dynamic CO2 laser and apparatus for performing the method |
| WO2001051433A1 (en) * | 1999-11-11 | 2001-07-19 | Kelly Space & Technology, Inc. | Nitrous oxide/fuel monopropellants |
| US20120192546A1 (en) * | 2011-01-28 | 2012-08-02 | General Electric Company | Catalytic Converter for a Pulse Detonation Turbine Engine |
| US8322263B2 (en) * | 2008-11-20 | 2012-12-04 | Lasermax, Inc. | Laser weapon system and method |
| CN103972771A (en) * | 2013-08-23 | 2014-08-06 | 中国人民解放军国防科学技术大学 | Circulating type laser |
| CN104153884A (en) * | 2014-08-06 | 2014-11-19 | 西安热工研究院有限公司 | Rotary knocking gas turbine |
| CN105351113A (en) * | 2015-11-30 | 2016-02-24 | 清华大学 | Rocket based combined engine |
| CN108708788A (en) * | 2018-05-29 | 2018-10-26 | 中国人民解放军国防科技大学 | Double-combustion-chamber ramjet engine and hypersonic aircraft |
| CN108757179A (en) * | 2018-05-29 | 2018-11-06 | 中国人民解放军国防科技大学 | Combined cycle engine and hypersonic aircraft |
| CN109184953A (en) * | 2018-11-07 | 2019-01-11 | 厦门大学 | A kind of rocket type rotation pinking punching press combined engine |
| CN109931628A (en) * | 2019-03-27 | 2019-06-25 | 北京理工大学 | It is a kind of based on the ring cavity eddy flow of the combustion chamber RDE to spray structure |
-
2019
- 2019-10-30 CN CN201911042324.0A patent/CN110707521B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3898584A (en) * | 1972-11-09 | 1975-08-05 | Messerschmitt Boelkow Blohm | Gas dynamic laser device and method of operating such a device |
| US4100507A (en) * | 1976-02-28 | 1978-07-11 | Messerschmitt-Bolkow-Blohm Gmbh | Method for exciting a gas dynamic CO2 laser and apparatus for performing the method |
| DE2618357A1 (en) * | 1976-04-27 | 1977-11-17 | Messerschmitt Boelkow Blohm | GAS DYNAMIC CO DEEP 2 LASER |
| WO2001051433A1 (en) * | 1999-11-11 | 2001-07-19 | Kelly Space & Technology, Inc. | Nitrous oxide/fuel monopropellants |
| US8322263B2 (en) * | 2008-11-20 | 2012-12-04 | Lasermax, Inc. | Laser weapon system and method |
| US20120192546A1 (en) * | 2011-01-28 | 2012-08-02 | General Electric Company | Catalytic Converter for a Pulse Detonation Turbine Engine |
| CN103972771A (en) * | 2013-08-23 | 2014-08-06 | 中国人民解放军国防科学技术大学 | Circulating type laser |
| CN104153884A (en) * | 2014-08-06 | 2014-11-19 | 西安热工研究院有限公司 | Rotary knocking gas turbine |
| CN105351113A (en) * | 2015-11-30 | 2016-02-24 | 清华大学 | Rocket based combined engine |
| CN108708788A (en) * | 2018-05-29 | 2018-10-26 | 中国人民解放军国防科技大学 | Double-combustion-chamber ramjet engine and hypersonic aircraft |
| CN108757179A (en) * | 2018-05-29 | 2018-11-06 | 中国人民解放军国防科技大学 | Combined cycle engine and hypersonic aircraft |
| CN109184953A (en) * | 2018-11-07 | 2019-01-11 | 厦门大学 | A kind of rocket type rotation pinking punching press combined engine |
| CN109931628A (en) * | 2019-03-27 | 2019-06-25 | 北京理工大学 | It is a kind of based on the ring cavity eddy flow of the combustion chamber RDE to spray structure |
Non-Patent Citations (3)
| Title |
|---|
| GEORGE LEE 等: "Gain and Power of CO2 Gasdynamic Lasers", 《AIAA JOURNAL》 * |
| 刘世杰: "连续旋转爆震波结构、传播模态及自持机理研究", 《中国博士学位论文全文数据库 工程科技II辑》 * |
| 王增辉 等: "冲压式气动激光器掺混燃烧数值分析及优化", 《电子机械工程》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110718843A (en) * | 2019-10-30 | 2020-01-21 | 中国人民解放军战略支援部队航天工程大学 | Air-breathing type continuous rotation detonation combustion driven premixing type carbon dioxide pneumatic laser |
| CN111525390A (en) * | 2020-04-27 | 2020-08-11 | 中国人民解放军国防科技大学 | Gas-phase gain nanoparticle generation device and laser |
| CN111525390B (en) * | 2020-04-27 | 2021-10-01 | 中国人民解放军国防科技大学 | Gas-phase gain nanoparticle generation device and laser |
| CN112467506A (en) * | 2020-11-20 | 2021-03-09 | 中国工程物理研究院应用电子学研究所 | Direct liquid cooling high-power laser gain device based on fuel jet combustion pump |
| CN112467506B (en) * | 2020-11-20 | 2022-03-01 | 中国工程物理研究院应用电子学研究所 | Direct liquid cooling high-power laser gain device based on fuel jet combustion pump |
| CN114877378A (en) * | 2022-06-02 | 2022-08-09 | 清航空天(北京)科技有限公司 | Inner ring detonation combustion chamber |
| CN114811654A (en) * | 2022-06-15 | 2022-07-29 | 清航空天(北京)科技有限公司 | Pressure-stabilizing flow-equalizing self-cooling continuous rotation detonation ramjet engine with radial oil supply |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110707521B (en) | 2020-12-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110707521B (en) | Premixed carbon dioxide pneumatic laser driven by continuous rotation detonation rocket combustion | |
| CN110718843B (en) | Air-breathing type continuous rotation detonation combustion driven premixing type carbon dioxide pneumatic laser | |
| CN112879178B (en) | Solid rocket ramjet based on detonation combustion | |
| CN114001374A (en) | Gas-liquid two-phase dual-fuel rotary detonation combustion chamber | |
| JPH0656132B2 (en) | Gas compressor for jet engine | |
| CN110425045B (en) | Continuous rotation detonation engine | |
| CN110739600B (en) | Pre-mixing type carbon dioxide pneumatic laser driven by air-breathing type pulse detonation combustion | |
| CN110739602B (en) | Pre-mixing type carbon dioxide pneumatic laser driven by pulse detonation rocket combustion | |
| CN116025484B (en) | Continuous detonation solid rocket engine system based on solid powder | |
| US4097820A (en) | Lasers | |
| CN216244410U (en) | Gas-liquid two-phase dual-fuel rotary detonation combustion chamber | |
| CN107218155B (en) | A kind of pulse ignite in advance can steady operation detonation engine | |
| US4013976A (en) | Gas dynamic lasers | |
| US20120192546A1 (en) | Catalytic Converter for a Pulse Detonation Turbine Engine | |
| CN220453713U (en) | Powder spraying mechanism and rotary detonation engine | |
| CN220453715U (en) | Injection structure, combustion system and rotary detonation engine | |
| US20240133473A1 (en) | Anti-back-transfer intake structure for rotating detonation combustion chamber | |
| CN114017205B (en) | Rocket power device and rocket | |
| US11655980B2 (en) | Piloted rotating detonation engine | |
| KR102599921B1 (en) | Nozzle for combustor, combustor, and gas turbine including the same | |
| CN114109654B (en) | Solid-liquid mixed engine and aircraft | |
| KR102415892B1 (en) | Micromixer and combustor having the same | |
| RU2493412C1 (en) | Liquid propellant rocket engine | |
| CN115427675A (en) | Pulse detonation jet engine | |
| RU70346U1 (en) | THRUST ROCKET ENGINE MIXING CHAMBER HEAD |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |