CN112523898A - Device and method for harmless treatment of large-flow toxic propellant oxygen-enriched gas - Google Patents
Device and method for harmless treatment of large-flow toxic propellant oxygen-enriched gas Download PDFInfo
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- CN112523898A CN112523898A CN202011311154.4A CN202011311154A CN112523898A CN 112523898 A CN112523898 A CN 112523898A CN 202011311154 A CN202011311154 A CN 202011311154A CN 112523898 A CN112523898 A CN 112523898A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/52—Injectors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
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Abstract
The invention provides a large-flow toxic propellant oxygen-enriched gas innocent treatment device and a method, the treatment device comprises a combustion chamber, wherein a switching device, a connecting section I, a connecting section II, a connecting section III and the combustion section in the combustion chamber adopt a sandwich water-cooling structure and are used for thermal protection of the combustion chamber, and an injection support plate, an injection ring I and an injection ring II adopt sandwich structures and are used for injecting fuel into the combustion chamber and combusting the fuel with high-temperature oxygen-enriched gas in the combustion chamber to generate low-toxicity or non-toxicity high-temperature gas. The device and the method are used for reducing toxicity or performing harmless treatment on a large amount of toxic oxygen-enriched gas generated by half-system test run of the oxygen-enriched gas generator of the normal-temperature propellant afterburning engine, can realize effective real-time treatment on hundreds of kilograms of high-temperature oxygen-enriched toxic gas per second, and have the advantages of simple structure, small scale, short construction period and lower cost compared with the traditional neutralization method.
Description
Technical Field
The invention belongs to the technical field of toxic gas treatment, and particularly relates to a large-flow toxic propellant oxygen-enriched fuel gas harmless treatment device and method.
Background
In recent years, with the continuous development of liquid rocket engine technology, higher requirements on high thrust, high efficiency and low cost of a normal-temperature propellant rocket engine are provided, and therefore, a more advanced normal-temperature propellant afterburning cycle engine needs to be researched. Semi-system testing of gas generators and turbopumps is an essential research test in the development of this type of engine.
The propellant of this type of engine is generally unsym-dimethylhydrazine ((CH)3)2NH2) And dinitrogen tetroxide (N)2O4) The two substances are toxic propellants, the product generated by the gas generator in the high-mixing-ratio oxygen-enriched combustion state is still very high in toxicity, and the gas contains a large amount of nitrogen oxides, so that the direct discharge causes serious pollution to the environment, and therefore, the toxic oxygen-enriched gas of hundreds of kilograms per second needs to be effectively treated in the semi-system test process of the gas generator. In order to realize the real-time treatment of the toxic oxygen-enriched fuel gas, reduce the equipment scale and cost and shorten the development period, a large-flow toxic propellant oxygen-enriched fuel gas harmless treatment device and a method are designed.
Disclosure of Invention
In order to reduce the pollution degree of a large amount of toxic gas generated by a high-thrust normal-temperature propellant afterburning engine oxygen-rich generator in a research test process to the environment, the inventor of the invention carries out intensive research and provides a large-flow toxic propellant oxygen-rich gas harmless treatment device and method.
The technical scheme provided by the invention is as follows:
according to the first aspect, the high-flow toxic propellant oxygen-enriched gas innocent treatment device comprises a combustion chamber, wherein the combustion chamber comprises a switching device, an injection support plate, a connection I section, an injection I ring, a connection II section, an injection II ring, a connection III section, a combustion section and a combustion chamber outlet which are sequentially connected, and the switching device is used for being connected with a front section decompression chamber to input high-temperature low-pressure oxygen-enriched gas; the injection support plate, the injection I ring and the injection II ring are of a sandwich structure, and fuel is introduced into the sandwich structure and is used for injecting the fuel into the combustion chamber and combusting the fuel with high-temperature oxygen-enriched gas in the combustion chamber to generate low-toxicity or non-toxic high-temperature gas; the combustion section provides a combustion space for the high-temperature oxygen-enriched gas, and gas products after combustion pass through the throat part and are discharged from the outlet of the combustion chamber.
In a second aspect, a harmless treatment method for a large-flow toxic propellant oxygen-enriched fuel gas is implemented by the treatment device of the first aspect, and comprises the following steps:
the high-pressure high-temperature oxygen-enriched gas generated by the gas generator is depressurized and then enters the combustion chamber through the switching device, the fuel enters the combustion chamber through the injection support plate, the injection I ring and the injection II ring in an axial, radial and tangential injection mode and is mixed with the oxygen-enriched gas for combustion, and finally the low-toxicity or nontoxic high-temperature gas generated by combustion is discharged from the outlet of the combustion chamber through the throat.
According to the device and the method for the harmless treatment of the large-flow toxic propellant oxygen-enriched gas, provided by the invention, the following beneficial effects are achieved:
(1) according to the treatment device and the method provided by the invention, the high-pressure high-temperature oxygen-enriched gas generated by the gas generator is depressurized and then enters the combustion chamber, the oxygen-enriched gas is converted into low-toxicity or non-toxic high-temperature gas in the combustion chamber by utilizing a secondary low-pressure combustion technology, and then the low-toxicity or non-toxic high-temperature gas is discharged into the atmosphere after being sprayed with water and cooled; the treatment device and the treatment method have high treatment efficiency, can realize the real-time effective treatment of hundreds of kilograms of high-temperature oxygen-enriched toxic gas per second, can effectively reduce the influence of the toxic gas on the environment, and can ensure the reliable operation of the research test of the engine. Compared with the traditional neutralization method, the treatment device has the advantages of simple structure, small scale, short construction period and lower cost;
(2) according to the processing device, axial, radial and radial + tangential fuel injection is adopted from front to back in sequence, and a multi-dimensional injection method is utilized, so that energy is not released in a centralized manner, and combustion stability is facilitated; the mixing of fuel and oxygen-enriched fuel gas is facilitated, the combustion efficiency is improved, and an ideal treatment effect is achieved;
(3) according to the processing device, the liquid collecting ring in the injection I ring and/or the injection II ring is of a layered runner structure, so that fuel can be uniformly distributed in the liquid collecting ring, the condition that the fuel is not uniformly distributed, the mixing ratio distribution of the outlets of the nozzles is not uniform, the combustion is not uniform, even the combustion is unstable, and the local nozzles are ablated or the structure of a combustion section is damaged when the combustion is serious can be avoided;
(4) in the treatment device, the cooling water outlet faces the outlet direction of the combustion chamber, and the cooling water is sprayed to the outlet of the combustion chamber when flowing out of the interlayer water cooling structure to form a water curtain which can be used for treating products such as NO after gas combustion2Cooling and dissolving to further reduce the pollution components discharged into the atmosphere;
(5) according to the processing device, the incoming flow is decompressed by the decompression chamber, and the accurate control of the gas flow decompression process is realized by adopting a pneumatic shock wave control technology in the supersonic shock wave section, so that the decompression amplitude is large, the equipment scale is small, and the effect of quickly decompressing the gas flow is realized; secondly, a stepped pressure reduction design idea of a pneumatic flow channel and a porous damping plate is adopted, so that the load of a pressure control structure in the flow channel in the pressure reduction process is reduced, the reliability and the safety of a system are improved, and the influence of the shock wave central flow effect on the uniformity of a flow field is weakened to the greatest extent; thirdly, a low-speed rectification design idea is adopted, the average speed of the flow field is reduced by arranging a sudden expansion structure in front of the rectification plate, and the rectification process of the gas flow is completed under the condition that the speed of the flow field is lower than the designed speed of the flow field, so that the flow distance required by rectification is greatly shortened; finally, a convergence structure is arranged behind the rectification structure, and the average speed of the flow field is finely adjusted to a design value, so that the accuracy of the speed of the flow field is improved, the difference between the flow speed of the edge area and the flow speed of the center is reduced, and the flow quality of a fuel gas outlet is improved.
Drawings
FIG. 1 is a schematic view showing the structure of a treating apparatus according to a preferred embodiment of the present invention;
FIG. 2 shows a schematic structure of a tangential straight flow nozzle formed by opening a hole on the inner side (injection wall) of a liquid collecting ring in a preferred embodiment of the invention;
FIG. 3 is a schematic view of the configuration of the injection ring I and/or injection ring II collector rings in a preferred embodiment of the present invention;
FIG. 4 shows a schematic view of the construction of a decompression chamber in a preferred embodiment of the invention;
FIG. 5 is a graph showing the change in pressure in the combustion section in embodiment 1;
fig. 6 shows a graph of the change in the fuel flow rate of the combustion section in example 1.
Description of the reference numerals
1-a switching device; 2-an injection support plate; 3-connecting the I section; 4-injection of ring I; 5-connecting the II section; 6-injection of ring II; 7-joining segment III; 8-a combustion section; 9-throat; 10-a combustion chamber outlet; 11-a flow-equalizing cavity; 12-an annular groove; 13-a partition plate; 14-flow equalizing hole; 15-annular rib plate; 21-an inlet flange; 22-supersonic laser band; 23-a porous damping plate; 24-sudden expansion step; 25-straight section; 26-front fairing; 27-bearing ring; 28-rear fairing; 29-converging end face; 30-a convergence section; 31-outlet flange.
Detailed Description
The features and advantages of the present invention will become more apparent and appreciated from the following detailed description of the invention.
According to a first aspect of the invention, a large-flow toxic propellant oxygen-enriched gas innocent treatment device is provided, and comprises a combustion chamber, as shown in fig. 1, wherein the combustion chamber comprises a switching device 1, an injection support plate 2, a connecting I section 3, an injection I ring 4, a connecting II section 5, an injection II ring 6, a connecting III section 7, a combustion section 8 and a combustion chamber outlet 10 which are connected in sequence, wherein the switching device 1 is used for being connected with a front section decompression chamber to input high-temperature low-pressure oxygen-enriched gas; the injection support plate 2, the injection I ring 4 and the injection II ring 6 are of a sandwich structure, and fuel is introduced into the sandwich structure and is used for injecting the fuel into the combustion chamber and combusting the fuel with high-temperature oxygen-enriched gas in the combustion chamber to generate low-toxicity or nontoxic high-temperature gas (NOx); the combustion section 8 provides sufficient combustion space for high-temperature oxygen-enriched gas, and gas products after combustion are discharged from an outlet 10 of the combustion chamber through a throat part 9.
In a preferred embodiment, each section of the combustion chamber is sealed by adopting a detachable flange connecting structure and a graphite winding pad; alternatively, the combustion chamber is integrally formed by additive manufacturing techniques.
In a preferred embodiment, the injection support plate 2 comprises a liquid collecting ring and 4-8 support plates, the number of the support plates extends into the combustion chamber, the support plates are uniformly distributed along the circumferential direction, and a plurality of groups of self-impact direct-current nozzles are arranged on the leeward wall surface of each support plate. The front edge of the support plate is of a blunt body structure, and the support plate is made of high-temperature alloy materials suitable for the high-temperature oxygen-enriched environment.
The injection I ring 4 and the injection II ring 6 comprise liquid collecting rings, the inner walls of the liquid collecting rings are injection walls, at least one circle of direct current nozzles vertical to the wall surface are circumferentially arranged on the injection walls of the injection I ring 4, and the circumferential angles of adjacent circles of nozzles are staggered by 0-45 degrees; at least one circle of straight-flow nozzles vertical to the wall surface and at least one circle of tangential straight-flow nozzles are circumferentially arranged on the injection wall of the injection II ring 6, the tangential straight-flow nozzles face the outlet direction of the combustion chamber, and the adjacent circles of nozzles are circumferentially staggered by 0-45 degrees.
The self-impact type direct-current injection and the direct-current injection vertical to the wall surface are adopted, and enough penetration depth is ensured; the tangential direct current injection is adopted to ensure that the rotational flow flows uniformly close to the wall surface to form a liquid film so as to protect the wall surface of the downstream combustion chamber; in order to achieve the technical effect, the injection pressure drop of the injection support plate 2, the injection I ring 4 and the injection II ring 6 is 0.5-2 MPa and is not higher than the pressure in the combustion chamber.
The self-impact type direct-current nozzle, the vertical wall-surface direct-current nozzle and the tangential direct-current nozzle can be commercially available products or formed by opening holes in a support plate or an injection wall. Fig. 2 shows a schematic view of the structure of the tangential flow nozzle formed by opening a hole on the inner side (injection wall) of the liquid collecting ring.
Furthermore, the injection support plate 2, the injection I ring 4 and the injection II ring 6 are fragile structures, so that the injection support plate, the injection I ring 4 and the injection II ring are designed to be modularized detachable structures, when part of structures are damaged, only damaged structural sections need to be replaced, and product maintenance is facilitated.
Further, as shown in fig. 3, the injection ring I4 and/or the injection ring II 6 have a layered flow channel structure, and include a flow equalizing chamber 11 and an annular groove 12, the flow equalizing chamber 11 is located at the periphery of the annular groove 12, a partition plate 13 is disposed between the two and is communicated with the flow equalizing chamber through a flow equalizing hole 14 formed in the partition plate 13, the annular groove 12 is formed in an annular rib 15 formed in the inner side of the partition plate 13, and a hole is formed in the bottom of the annular groove 12 or a nozzle is installed in the annular groove 12, so as to inject fuel into the combustion chamber. When the hole opening mode is adopted, the hole opening direction at the bottom of the annular groove 12 is changed to form a direct current nozzle or a tangential direct current nozzle vertical to the wall surface; when the nozzle mounting mode is adopted, the direction of the nozzle is changed to form a straight-flow nozzle or a tangential straight-flow nozzle vertical to the wall surface.
When fuel is input into the liquid collecting ring from the outside, the fuel firstly enters the flow equalizing cavity 11, is mixed in the flow equalizing cavity 11, enters the annular groove 12 through the flow equalizing hole 14, is further mixed and is then sprayed out. The design of the layered flow channel of the liquid collecting ring can ensure that fuel is uniformly distributed in the liquid collecting ring, so that the phenomenon that fuel is not uniformly distributed, the mixing ratio distribution of the outlet of a nozzle is not uniform, the combustion is not uniform, even unstable combustion occurs, and the ablation of a local nozzle or the structural damage of a combustion section can be caused in serious conditions.
In a preferred embodiment, the adapter 1, the connection I section 3, the connection II section 5, the connection III section 7 and the combustion section 8 are of a sandwich water-cooled structure.
Furthermore, cooling water in the combustion section 8 interlayer water-cooling structure flows against the air flow, cooling water in other connecting sections can flow against the air flow or flow along the air flow, and the cooling water has certain flow and flow velocity, so that the cooling reliability is ensured.
In a preferred embodiment, the divergence angle of the link I section 3, the link II section 5 and the link III section 7 is less than 15 °, preferably from 10 ° to 15 °. The connecting section has an expansion angle within the range, so that the mixing of the radial oxygen-enriched gas and the fuel is facilitated, and if the expansion angle is too small and smaller than the range, the mixing effect of the radial oxygen-enriched gas and the fuel is poor; if the divergence angle is too large and larger than the range, the axial space is too small, the fuel injection area is too concentrated, and the injections in different forms interfere with each other, which is not favorable for stable combustion.
The combustion section 8 comprises a straight section and a convergent section, and the convergent angle of the convergent section is 15-90 degrees. The combustion section 8 is used for ensuring that the residence time of the fuel gas in the section is more than 10ms so as to realize sufficient combustion.
The outlet 10 of the combustion chamber is of a micro-expansion structure, and the expansion angle is less than 7 degrees, preferably 4-5 degrees. The expansion area ratio and the expansion angle of the outlet of the combustion chamber are as small as possible, unnecessary thrust generated by the combustion chamber is reduced as much as possible, and the fixing difficulty of the combustion chamber is increased.
In a preferred embodiment, the cooling water outlets of the adapter 1, the connection I section 3, the connection II section 5, the connection III section 7 and the combustion section 8 face the outlet direction of the combustion chamber, and the cooling water is sprayed to the outlet 10 of the combustion chamber when flowing out of the interlayer water cooling structure to form a water curtain which can be used for burning products such as NO after gas combustion2And the temperature is reduced for dissolution, so that the pollution components discharged into the atmosphere are further reduced.
In the invention, the fuel is unsymmetrical dimethylhydrazine aqueous solution, and the mass ratio of unsymmetrical dimethylhydrazine to water is 1: (0-2.5). The mixing process of the unsym-dimethylhydrazine and the water is ensured to be uniform, and the unsym-dimethylhydrazine and the water can be mixed well in a storage tank in advance or can be mixed and supplied in real time. The fuel is sprayed into the combustion chamber through the injection support plate 2, the injection I ring 4 and the injection II ring 6 according to the proportion of (4-6): (2-3): (2-3), most of fuel can enter the oxygen-enriched fuel gas central area through the injection of the support plate in the proportioning mode, the mixing ratio of fuel gas and fuel in the central area is reduced, the combustion temperature of the central area is increased, and the oxygen-enriched fuel gas treatment effect is improved; properly reduce the fuel proportion of the edge area, improve the mixing ratio of the gas and the fuel of the edge area, reduce the temperature of the gas of the edge area and be beneficial to the thermal protection of a combustion section.
In the present invention, the processing apparatus further includes a decompression chamber, as shown in fig. 4, the decompression chamber is a revolving structure, and includes an inlet flange 21, a supersonic shock wave section 22, a straight section 25, a convergent end face 30, and a convergent end face 31 in the air flow direction;
said inlet flange 21 is intended to introduce a flow of gas generated by the gas generator, accelerated to sonic velocity through the engine nozzle;
the supersonic speed shock wave section 22 is a conical expansion section, the gas flow is accelerated to a supersonic speed state through expansion, at least one porous damping plate 23 is arranged in the middle of the supersonic speed shock wave section 22, the gas flow generates a positive shock wave in the middle of a flow field in front of the porous damping plate 23 by matching the flow speed with the ambient pressure, the gas flow is preliminarily decompressed, and the gas flow is converted from the supersonic speed state to a subsonic speed state; the plate surface of the porous damping plate 23 is perpendicular to the axis of the decompression chamber, and is used for converting the gas flow from a subsonic state to a supersonic state again, forming a secondary shock wave at the downstream of the porous damping plate 23, performing secondary accurate decompression on the gas flow, reducing the total pressure to be close to a design value, and primarily rectifying the gas flow;
a sudden expansion step 24 is arranged between the supersonic shock wave section 22 and the straight section 25, the inner diameter of the sudden expansion step 24 is larger than the inner diameter of the large end of the supersonic shock wave section 22 and is equal to the inner diameter of the straight section 25, and the sudden expansion step 24 is used for reducing the average flow velocity of the gas flow;
at least one rectifying plate is arranged in the straight section 25, and through holes are formed in the rectifying plates and used for rectifying the airflow in a flow passage with the average speed lower than the designed average speed, so that the radial speed difference of the airflow is greatly reduced, and the flow uniformity is greatly improved;
the convergent end face 30 is used for reducing the flow velocity difference between the center and the edge area of the flow field, increasing the average velocity of the gas flow to a design value, and discharging the gas flow from the convergent end face 31.
In a preferred embodiment, the divergence angle of the supersonic laser band 22 is in the range of 10 ° to 40 °.
In a preferred embodiment, 1 porous damping plate 23 is arranged in the middle of the supersonic shock wave band 22. Two fairing panels, a forward fairing panel 26 and an aft fairing panel 28 as shown in FIG. 4, are disposed within the straight section 25.
Aiming at the pressure reduction of 3-50 MPa, the aperture ratio of the porous damping plate 23 is 20-40%, the aperture ratio of the rectifying plate is 10-25%, and the flow velocity of the fuel gas flow in the straight section 25 is 30-50 m/s.
In a preferred embodiment, the inlet flange 21, the supersonic shock wave section 22, the straight section 25, the converging end face 30 and the converging end face 31 are connected by a detachable flange structure, or are integrally formed by an additive manufacturing technology.
In a preferred embodiment, the decompression chamber further comprises bearing rings 27, the bearing rings 27 are sleeved on the straight sections 25, and a limiting space for moving or fixing the whole decompression chamber by an external device is formed between the adjacent bearing rings 27.
According to a second aspect of the present invention, there is provided a method for harmless treatment of a large flow rate toxic propellant oxygen-enriched fuel gas, which is implemented by the treatment apparatus of the first aspect, comprising:
high-pressure high-temperature oxygen-enriched gas generated by the gas generator is depressurized and then enters a combustion chamber through a switching device 1, fuel (aqueous solution of unsym-dimethylhydrazine) enters the combustion chamber through an injection support plate 2, an injection I ring 4 and an injection II ring 6 in a multi-dimensional injection mode with multiple dimensions such as axial direction, radial direction and tangential direction, is mixed with the oxygen-enriched gas for combustion, and finally low-toxicity or nontoxic high-temperature gas (NOx) generated by combustion is discharged from a combustion chamber outlet 10 through a throat part 9, preferably is discharged into the atmosphere after water spray cooling auxiliary treatment; the switching device 1, the connection I section 3, the connection II section 5, the connection III section 7 and the combustion section 8 all adopt an interlayer water cooling structure to ensure that the product structure is reliable.
Wherein, the decompression process is implemented through the decompression chamber, which is specifically as follows:
high-temperature and high-pressure oxygen-enriched gas flow generated by a normal-temperature propellant semi-system test is accelerated to sonic speed through a spray pipe and then enters an inlet flange 21, the gas flow is further accelerated to reach a supersonic speed state through expansion in a supersonic speed shock wave section 22, through matching of flow speed and environmental pressure, normal shock waves are generated in the middle of a flow field at the front section of the supersonic speed shock wave section 22 by the gas flow, the gas flow parameters after the normal shock waves are subjected to sudden change, the gas flow is converted into a subsonic speed state from the supersonic speed state, the total pressure is greatly reduced, the flow speed is reduced, the flow speed of a central flow and the flow speed of a side area;
the middle part of the supersonic shock wave section 22 is provided with a porous damping plate 23, when subsonic gas flow passes through the position, the main gas flow is converted into a plurality of branches and enters the small holes of the porous damping plate respectively, the subsonic state of the gas flow is converted into the supersonic state again when the gas flow passes through the small holes of the porous damping plate, secondary shock waves are formed at the downstream of the small holes, the flow parameters of the gas flow are mutated again when the gas flow passes through the shock waves, and the total pressure of the gas flow is reduced to be close to the design value. The partial flow is secondarily distributed when the main flow flows through the porous damper, so that the gas flow is primarily rectified;
a sudden expansion step 24 is arranged between the supersonic shock wave section 22 and the straight section 25, the average flow velocity of the gas flow is suddenly reduced when the gas flow passes through the position, the radial velocity difference of the flow is greatly reduced when the gas flow passes through the rectifying plate, and the flow uniformity is greatly improved;
then, the fuel gas flows through the convergent end face 29 and enters the convergent section 30, the fuel gas flow velocity near the wall surface of the flow channel is increased rapidly in the process, the flow velocity difference between the center and the edge area is further reduced, the flow quality of the fuel gas flow is further improved, and the fuel gas flow flows into the downstream through the outlet flange 31 to be subjected to non-toxic treatment.
Examples
Example 1
The combustion chamber is adopted to implement high-temperature high-pressure oxygen-enriched fuel gas harmless treatment, wherein the number of the injection support plates 2 is 8, the injection support plates are uniformly distributed along the circumferential direction, and a plurality of groups of self-impact direct-current nozzles are arranged on the leeward wall surface of each support plate; 3 circles of direct current nozzles vertical to the wall surface are arranged on the injection wall of the injection I ring 4, the adjacent circles of nozzles are staggered by 30 degrees in the circumferential direction, 2 circles of direct current nozzles vertical to the wall surface and 1 circle of tangential direct current nozzles are arranged on the injection wall of the injection II ring 6, and the adjacent circles of nozzles are staggered by 30 degrees in the circumferential direction; the injection pressure drop of the injection support plate 2, the injection ring I4 and the injection ring II 6 is 1 MPa; the liquid collecting rings of the injection I ring 4 and the injection II ring 6 are both of a layered runner structure shown in figure 3, and the proportion of fuel injected into the combustion chamber by the injection support plate 2, the injection I ring 4 and the injection II ring 6 is 6: 2: 2. switching device 1, connect I section 3, connect II section 5, connect III section 7 and combustion section 8 and adopt intermediate layer water-cooling structure, and the angle of expansion of connecting I section 3, connecting II section 5 and connecting III section 7 is 10, and 8 exports of combustion section are little for expanding the structure, and the angle of expansion is 4.
The oxygen-enriched gas harmless treatment device is adopted to complete a semi-system test of an oxygen-enriched gas generator and a turbine pump of an engine, the engine is normally started in the test process, the oxygen-enriched gas drives a turbine and then enters the gas treatment device, the oxygen-enriched gas and afterburning fuel are mixed and combusted in a combustion section after pressure reduction and speed reduction, stable pressure is established in the combustion section and finally discharged from an outlet of a combustion chamber, high-temperature gas is absorbed by cooling water sprayed out of the periphery of the harmless treatment device and then discharged into the atmosphere after temperature reduction, obvious combustion flame in water mist can be seen at the outlet of the combustion section in the test process, no reddish brown gas is seen in the stable combustion process, and the pressure and the fuel flow of the combustion section are respectively shown in figures.
The invention has been described in detail with reference to specific embodiments and illustrative examples, but the description is not intended to be construed in a limiting sense. Those skilled in the art will appreciate that various equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its embodiments without departing from the spirit and scope of the present invention, which fall within the scope of the present invention. The scope of the invention is defined by the appended claims.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (13)
1. The high-flow toxic propellant oxygen-enriched gas innocent treatment device is characterized by comprising a combustion chamber, wherein the combustion chamber comprises a switching device (1), an injection support plate (2), a connecting section I (3), an injection ring I (4), a connecting section II (5), an injection ring II (6), a connecting section III (7), a combustion section (8) and a combustion chamber outlet (10) which are sequentially connected, wherein the switching device (1) is used for being connected with a front section decompression chamber to input high-temperature low-pressure oxygen-enriched gas; the injection support plate (2), the injection I ring (4) and the injection II ring (6) are of a sandwich structure, and fuel is introduced into the sandwich structure and is used for injecting the fuel into the combustion chamber and combusting the fuel with high-temperature oxygen-enriched gas in the combustion chamber to generate low-toxicity or non-toxic high-temperature gas; the combustion section (8) provides a combustion space for the high-temperature oxygen-enriched gas, and gas products after combustion are discharged from an outlet (10) of the combustion chamber through a throat part (9).
2. The processing unit according to claim 1, wherein the sections of the combustion chamber are sealed by detachable flange connection structures and graphite wound gaskets; alternatively, the combustion chamber is integrally formed by additive manufacturing techniques.
3. The treatment device according to claim 1, characterized in that the injection support plate (2) comprises a liquid collecting ring and 4-8 support plates, the support plates extend into the combustion chamber and are uniformly distributed along the circumferential direction, and a plurality of groups of self-impact direct-current nozzles are arranged on the leeward wall surface of each support plate.
4. The processing device according to claim 1, wherein the injection I-ring (4) comprises a liquid collecting ring, the inner wall of the liquid collecting ring is an injection wall, at least one circle of straight-flow nozzles with vertical wall surfaces is circumferentially arranged on the injection wall of the injection I-ring (4), and adjacent circles of nozzles are circumferentially staggered by 0-45 degrees.
5. The treatment plant according to claim 1, characterized in that the injection ring II (6) comprises a liquid collecting ring, at least one circle of vertical-wall-surface straight nozzles and at least one circle of tangential straight nozzles are circumferentially arranged on the injection wall of the injection ring II (6), the tangential straight nozzles face the outlet direction of the combustion chamber, and adjacent circles of nozzles are circumferentially staggered by 0-45 degrees.
6. The processing device according to claim 1, wherein the injection pressure drop of the injection support plate (2), the injection I ring (4) and the injection II ring (6) is 0.5-2 MPa and not higher than the pressure in the combustion chamber.
7. The processing device according to claim 1, wherein the liquid collecting ring in the injection ring I (4) and/or the injection ring II (6) is of a layered flow channel structure and comprises a flow equalizing cavity (11) and an annular groove (12), the flow equalizing cavity (11) is located at the periphery of the annular groove (12), a partition plate (13) is arranged between the flow equalizing cavity and the annular groove, the flow equalizing cavity is communicated with the annular groove through a flow equalizing hole (14) formed in the partition plate (13), the annular groove (12) is formed in an annular rib plate (15) on the inner side of the partition plate (13), and a hole is formed in the bottom of the annular groove (12) or a nozzle is installed on the annular groove to inject fuel into the combustion chamber.
8. The processing device according to claim 1, characterized in that the transition device (1), the connection I section (3), the connection II section (5), the connection III section (7) and the combustion section (8) are of a sandwich water-cooled structure.
9. The processing device according to claim 1, characterized in that the divergence angle of the connection I section (3), the connection II section (5) and the connection III section (7) is less than 15 °; and/or
The combustion section (8) comprises a straight section and a convergence section, the convergence angle of the convergence section is 15-90 degrees, and the residence time of fuel gas in the section is more than 10 ms; and/or
The combustion chamber outlet (10) is of a micro-expansion structure, and the expansion angle is smaller than 7 degrees.
10. The treatment device according to claim 8, wherein the cooling water outlets in the adapter (1), the connection I section (3), the connection II section (5), the connection III section (7) and the combustion section (8) face the outlet direction of the combustion chamber, and the cooling water is sprayed out of the interlayer water cooling structure to the outlet (10) of the combustion chamber to form a water curtain for cooling and dissolving the products generated after the gas combustion.
11. A harmless treatment method of oxygen-enriched gas with a large flow rate toxic propellant, which is implemented by the treatment device of one of claims 1 to 10, and comprises the following steps:
high-pressure high-temperature oxygen-enriched gas generated by the gas generator is depressurized and then enters the combustion chamber through the switching device (1), fuel enters the combustion chamber through the injection support plate (2), the injection I ring (4) and the injection II ring (6) in an axial, radial and tangential injection mode and is mixed with the oxygen-enriched gas for combustion, and low-toxicity or nontoxic high-temperature gas generated by final combustion is discharged from an outlet (10) of the combustion chamber through a throat (9).
12. The process according to claim 11, wherein the fuel is an aqueous unsymmetrical dimethylhydrazine solution, and the mass ratio of unsymmetrical dimethylhydrazine to water is 1: (0-2.5).
13. The process according to claim 11, characterized in that the fuel is injected into the combustion chamber by the injection support plate (2), the injection ring I (4) and the injection ring II (6) in proportions (4-6): (2-3): (2-3).
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114718768A (en) * | 2022-04-02 | 2022-07-08 | 西安航天动力试验技术研究所 | High-temperature high-pressure high-speed large-flow-density oxygen-enriched gas treatment system and method |
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| CN107514644A (en) * | 2017-07-27 | 2017-12-26 | 西安航天动力研究所 | Dinitrogen tetroxide/Hydrazine propellant waste gas and liquids treatment burner and control method |
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| CN102022225A (en) * | 2010-12-30 | 2011-04-20 | 北京航空航天大学 | Test unit for hydrogen-rich/ oxygen-rich gas multinozzle gas-gas injector |
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| CN104633709A (en) * | 2014-12-11 | 2015-05-20 | 清华大学 | Thermal protection method of porous medium jetting support plate leading edge nose cone |
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