CN117770040B - An aircraft engine rain enhancement system and aircraft - Google Patents
An aircraft engine rain enhancement system and aircraft Download PDFInfo
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- CN117770040B CN117770040B CN202410005925.9A CN202410005925A CN117770040B CN 117770040 B CN117770040 B CN 117770040B CN 202410005925 A CN202410005925 A CN 202410005925A CN 117770040 B CN117770040 B CN 117770040B
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- 239000000446 fuel Substances 0.000 claims abstract description 73
- 238000002485 combustion reaction Methods 0.000 claims abstract description 36
- 238000002156 mixing Methods 0.000 claims abstract description 33
- 239000003595 mist Substances 0.000 claims abstract description 8
- 239000007921 spray Substances 0.000 claims abstract description 5
- 230000007704 transition Effects 0.000 claims abstract description 5
- 239000000203 mixture Substances 0.000 claims description 10
- 238000011144 upstream manufacturing Methods 0.000 claims description 5
- 238000005507 spraying Methods 0.000 claims description 4
- 230000001965 increasing effect Effects 0.000 abstract description 26
- 239000003054 catalyst Substances 0.000 abstract description 22
- 239000007789 gas Substances 0.000 abstract description 20
- 238000001556 precipitation Methods 0.000 abstract description 16
- 230000000694 effects Effects 0.000 abstract description 10
- 239000002737 fuel gas Substances 0.000 abstract description 5
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 10
- 238000000034 method Methods 0.000 description 10
- 239000001301 oxygen Substances 0.000 description 10
- 229910052760 oxygen Inorganic materials 0.000 description 10
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- 239000007800 oxidant agent Substances 0.000 description 8
- 230000001590 oxidative effect Effects 0.000 description 8
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- 230000001105 regulatory effect Effects 0.000 description 3
- 239000000779 smoke Substances 0.000 description 3
- 230000001174 ascending effect Effects 0.000 description 2
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- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000002269 spontaneous effect Effects 0.000 description 2
- JKFYKCYQEWQPTM-UHFFFAOYSA-N 2-azaniumyl-2-(4-fluorophenyl)acetate Chemical compound OC(=O)C(N)C1=CC=C(F)C=C1 JKFYKCYQEWQPTM-UHFFFAOYSA-N 0.000 description 1
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 1
- 229910021612 Silver iodide Inorganic materials 0.000 description 1
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- 230000017525 heat dissipation Effects 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
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- Exhaust Gas After Treatment (AREA)
Abstract
The invention relates to the technical field of artificial precipitation devices, in particular to an aeroengine precipitation system and an aircraft. The rain increasing system of the aeroengine comprises an outer exhaust device sleeved outside an inner exhaust device, an air entraining port located in a transition area between a combustion chamber and a gas compressor, a first air entraining branch extending into a clamped area between the outer exhaust device and the inner exhaust device, a first part of air entraining and high-temperature fuel gas being mixed, a second air entraining branch extending into a supercharging device, the second part of air entraining pushing rain increasing fuel to be fed into a nozzle, a third air entraining branch extending into the nozzle, the nozzle mixing the third part of air entraining and the rain increasing fuel to spray out combustible gas mist, and an ignition device igniting the combustible gas mist. According to the rain enhancement system of the aero-engine, provided by the invention, the artificial rain enhancement system based on the aero-engine is arranged, so that the artificial rain enhancement aircraft can operate for a long time in a single way, the catalyst combustion effect is excellent, the operation position is free, and the flight is not influenced by the rain enhancement device.
Description
Technical Field
The invention relates to the technical field of artificial precipitation devices, in particular to an aeroengine precipitation system and an aircraft.
Background
The principle of artificial precipitation is to select proper time according to the physical characteristics of different cloud layers, and spread catalysts such as dry ice, silver iodide, salt powder and the like into the cloud by using aircrafts, rocket projectiles and the like to promote the precipitation of the cloud layers or increase the precipitation amount.
The artificial precipitation is usually formed by burning a precipitation-increasing flame bomb, wherein the flame bomb is a cylindrical initiating explosive device internally provided with a catalyst, and the medicament in the flame bomb generates a large amount of catalyst particles in the injection process after ignition and falls into the cloud or floats into the cloud layer along with air flow in a high-temperature free falling mode.
In the prior art, the volume of the flame bomb is limited, the bomb carrying amount of the flame bomb is insufficient, the operation time is limited to be within 1.5 hours, the rainfall range capable of being interfered is limited, the combustion in the flame bomb is unstable, the nucleation rate of a catalyst is low, the rain increasing efficiency is poor, the flame bomb on the aircraft is arranged at the rear part of a wing or the lower part of the aircraft body, the normal flight of the aircraft is influenced, the aircraft can only operate in a cloud space, and meanwhile, the aircraft is extremely easily influenced by strong airflow and has high danger.
Disclosure of Invention
Therefore, the invention aims to overcome the defects of short flame bomb operation time, unstable combustion, operation in the cloud and influence on the safe flight of an aircraft in the prior art, and further provides the aircraft engine rain increasing system and the aircraft, which have the advantages of long single-pass operation time, good combustion effect, free operation position and unaffected aircraft flight.
In order to solve the technical problems, the invention provides an aircraft engine rain increasing system and an aircraft, comprising:
A base body, one side of which is outwardly opened and provided with an inner exhaust device;
the outer exhaust device is sleeved outside the inner exhaust device and is arranged in an outward opening way, and a gap is reserved between the inner wall of the outer exhaust device and the outer wall of the inner exhaust device;
the mixing device is arranged at an exhaust outlet of the inner exhaust device;
the nozzle is arranged in the clamped area of the outer exhaust device and the inner exhaust device;
the ignition device is arranged at one side of the outer exhaust device, which is close to the inner exhaust device;
The rain-increasing fuel device is arranged in the aircraft;
the air inlet is arranged on the base body and is positioned in a transition area between the combustion chamber and the air compressor;
a first bleed air branch, one end of which is connected with the bleed air port, and the other end of which extends into the clamped area of the outer exhaust device and the inner exhaust device, wherein the mixing device is suitable for mixing a first part of bleed air and high-temperature fuel gas;
One end of the second air-entraining branch is connected with the air-entraining port, the other end of the second air-entraining branch extends into the pressurizing device, and the pressurizing device is suitable for pressurizing a second part of air-entraining and then supplying the second part of air-entraining into the rain-increasing fuel device so that the second part of air-entraining pushes the rain-increasing fuel to be supplied into the nozzle;
And one end of the third air-entraining branch is connected with the air-entraining port, the other end of the third air-entraining branch extends into the nozzle, the nozzle is suitable for mixing the third part of air-entraining with the rain-increasing fuel and then spraying out the combustible gas mist, and the ignition device ignites the combustible gas mist.
Optionally, the nozzle is located relatively downstream of the bleed air outlet of the first bleed air branch in the direction of airflow flow, and the nozzle is located relatively upstream of the blending device.
Optionally, the plurality of nozzles are uniformly distributed in the clamped area of the outer exhaust device and the inner exhaust device along the circumferential direction;
the plurality of first bleed air branches are uniformly distributed along the circumferential direction.
Optionally, the system further comprises a high-pressure pipeline, one end of which is connected with the pressurizing device, and the other end of which extends into the rain-enhancing fuel device and is suitable for supplying the pressurized second part of the air entraining.
Optionally, the device further comprises a fuel pipeline, one end of which is connected with the rain-enhancing fuel device, and the other end of which extends into the nozzle and is suitable for supplying the rain-enhancing fuel.
Optionally, the system further comprises bleed air control valves which are respectively arranged on the first bleed air branch, the second bleed air branch and the third bleed air branch and are suitable for adjusting the bleed air quantity.
Optionally, the system further comprises a fuel control valve, a control valve and a control valve, wherein the fuel control valve is arranged on the fuel pipeline and is suitable for adjusting the supply quantity of the rain-increasing fuel;
the pressurizing bleed air control valve is arranged on the high-pressure pipeline and is suitable for adjusting the supply quantity of the high-pressure bleed air.
Optionally, the nozzle is internally provided with a bleed air channel and a fuel channel which are arranged in an extending way independently;
The bleed air channel and the fuel channel meet in a mixing chamber;
the mixing chamber has an outwardly opening spray orifice adapted to spray the mixture outwardly to atomize it.
Optionally, from the bleed port, the first bleed branch, the second bleed branch and the third bleed branch are combined into the same pipeline to extend to a node, and are bifurcated from the node and extend independently of each other, so that pipeline arrangement is simplified.
Wherein, a plurality of bleed air control valves are arranged at the node in a combined way.
An aircraft comprising a fuselage and an aeroengine raining system according to any one of the preceding claims disposed inside the fuselage.
The technical scheme of the invention has the following advantages:
1. according to the rain enhancement system of the aeroengine, the purpose that a single-pass long-time operation of the artificial rain enhancement aircraft is achieved through the artificial rain enhancement system depending on the aeroengine, the catalyst is good in combustion effect, free in operation position and free in flight, the rain enhancement fuel device is arranged in an aircraft cabin, the catalyst is sprayed out of the engine, the rain enhancement operation does not influence the flight process any more, the single-pass portable rain enhancement fuel volume of the rain enhancement fuel device is far greater than that of a smoke bomb, the artificial rain enhancement operation can be completed through single flight, and the practicability is high.
2. According to the rain increasing system of the aeroengine, the outer exhaust device sleeved on the periphery of the original exhaust device and the first part of air entraining agent uniformly introduced between the inner exhaust device and the outer exhaust device are arranged, so that mixed exhaust of the inner exhaust device and the outer exhaust device is realized, exhaust benefits are improved, the defects of low temperature of the first part of air entraining agent and low oxygen content of the inner exhaust device are overcome, blended air flow taking both temperature and oxygen content into consideration is obtained, complete and sufficient combustion of the rain increasing fuel is ensured, the rain increasing efficiency is improved, the air flow of the blended air flow is large, the rain increasing particles can be forced to be broadcasted into the atmosphere, the rain increasing effect is improved, the temperature of the blended air flow is high, the catalyst is sprayed out along with a large amount of hot air flow, the diffusion is uniform, the broadcasting area is wide, and the blended air flow is used as warm ascending air flow, and the rain increasing efficiency is further improved.
3. The rain increasing system of the aeroengine provided by the invention has the advantages that the rain increasing fuel is burnt in the outer exhaust device after being ignited by the ignition device, compared with the combustion mode of spontaneous combustion of the medicament in the smoke bomb, the combustion temperature is higher, the volume of combustion products, namely the rain increasing particles is smaller, and further the rain increasing effect and efficiency are effectively improved.
4. According to the rain increasing system of the aeroengine, provided by the invention, the oxidant in the combustion of the rain increasing catalyst is oxygen in the environment, and compared with the oxidant in the combustion of the catalyst in the flame bomb, the oxidant in the combustion of the catalyst in the flame bomb is required to be stored in the flame bomb, and the engine rain increasing system does not need to be additionally preloaded with the oxidant, so that the weight of a rain increasing device on an aircraft is reduced, and the flying capacity of the aircraft is improved.
5. According to the rain increasing system for the aeroengine, the plurality of ignition devices are uniformly distributed on the casing of the outer exhaust device along the circumferential direction, so that the ignition range covers the whole exhaust area, the ignition delay period is short, flames are uniformly spread, combustion is stable, and further, the influence on the flying process is avoided, the plurality of first air-entraining branches are uniformly distributed on the casing of the outer exhaust device, the multi-channel air-entraining is suitable for being carried out in the same period, the air-entraining amount of the first part of air-entraining is improved, and the combustion efficiency of a catalyst is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic illustration of an aircraft engine rain enhancement system and aircraft of the present invention;
FIG. 2 is a schematic diagram of the operation of the aircraft engine rain enhancement system of the present invention;
FIG. 3 is a schematic view of the structure of the nozzle of the present invention.
Reference numerals illustrate:
1. the device comprises a base body, 2, an inner exhaust device, 3, an outer exhaust device, 4, a mixing device, 5, a gas-entraining port, 6, a combustion chamber, 7, a gas compressor, 8, a first gas-entraining branch, 9, a second gas-entraining branch, 10, a third gas-entraining branch, 11, a supercharging device, 12, a rain-increasing fuel device, 13, a nozzle, 14, an ignition device, 15, a gas-entraining outlet, 16, a high-pressure pipeline, 17, a fuel pipeline, 18, a fuel control valve, 19, a gas-entraining control valve, 20, an accessory transmission system, 21, a turbine, 22, a gas-entraining channel, 23, a fuel channel, 24, a mixing chamber, 25, a jet orifice, 26 and a supercharging gas-entraining control valve.
Detailed Description
The following description of the embodiments of the present invention will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the invention are shown. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, unless explicitly stated or limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected, mechanically connected, electrically connected, directly connected, indirectly connected via an intervening medium, or in communication between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
In addition, the technical features of the different embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.
Example 1
1-3, The rain enhancement system for the aero-engine provided in this embodiment includes:
a base body 1, one side of which is outwardly opened and provided with an inner exhaust device 2;
The outer exhaust device 3 is sleeved outside the inner exhaust device 2 and is arranged in an outward opening way, and a gap is reserved between the inner wall of the outer exhaust device 3 and the outer wall of the inner exhaust device 2;
the mixing device 4 is arranged at the exhaust outlet of the inner exhaust device 2;
a nozzle 13 provided in a region between the outer exhaust device 3 and the inner exhaust device 2;
An ignition device 14 provided in the outer exhaust device 3 at a side close to the inner exhaust device 2;
a rain-enhancing fuel device 12 disposed inside the aircraft;
an air inlet 5 which is arranged on the base body 1 and is positioned in a transition area between the combustion chamber 6 and the air compressor 7;
A first bleed air branch 8, one end of which is connected to the bleed air port 5 and the other end of which extends into the clamped region of the outer exhaust 3 and the inner exhaust 2, the mixing device 4 being adapted to mix a first portion of bleed air with hot gas;
A second bleed air branch 9, one end of which is connected with the bleed air port 5, and the other end of which extends into a supercharging device 11, wherein the supercharging device 11 is suitable for pressurizing a second part of bleed air and then feeding the second part of bleed air into the rain-increasing fuel device 12 so that the second part of bleed air pushes the rain-increasing fuel to be fed into the nozzle 13;
And one end of a third air-entraining branch 10 is connected with the air-entraining port 5, the other end of the third air-entraining branch extends into the nozzle 13, the nozzle 13 is suitable for mixing a third part of air-entraining with the rain-increasing fuel and then spraying out combustible gas mist, and the ignition device 14 ignites the combustible gas mist.
As shown in fig. 1-2, the bleed air position is the transition area between the outlet of the compressor 7 and the inlet of the combustion chamber 6, the air source is high-pressure air compressed by the compressor 7, and the bleed air is divided into a first part of bleed air, a second part of bleed air and a third part of bleed air.
The first bleed air branch 8 is communicated with the casing of the outer exhaust device 3, so that a first part of bleed air uniformly enters the clamped area of the outer exhaust device 3 and the inner exhaust device 2, the blending device 4 mixes the first part of bleed air with the inner exhaust gas, namely high-temperature fuel gas, the high-temperature fuel gas is high in temperature but insufficient in oxygen content, the first part of bleed air is high in oxygen content but low in temperature, the blending air mixes the two air flows, the air flow temperature value and the oxygen content are taken into consideration, the combustion effect is good, and the exhaust flow is improved.
The second bleed air branch 9 is communicated with the pressurizing device 11, the pressurizing device 11 is used for pressurizing the bleed air, the second part of the bleed air uniformly enters the pressurizing device 11 from the bleed air port 5 for pressurizing, the pressurized high-pressure bleed air is introduced into the rain-increasing fuel device 12, and the rain-increasing fuel uniformly enters the nozzle 13 under the action of the pushing force of the high-pressure bleed air.
The third air-entraining branch 10 is communicated with the nozzle 13 to enable the third part of air-entraining to uniformly enter the nozzle 13, the third part of air-entraining enters the mixing chamber 24 through the air-entraining channel 22, the rain-increasing fuel enters the mixing chamber 24 through the fuel channel 23, the third part of air-entraining and the rain-increasing fuel are premixed into a uniform combustible mixture, and then are scattered outwards from the air-jet outlet 25 to be atomized to form combustible mixed gas, the nozzle 13 is arranged on the downstream side of the air-entraining outlet 15 of the first air-entraining branch 8, the upstream side of the mixing device 4 is enabled to enable the combustible mixed gas to be discharged outwards along with the flow of the first part of air-entraining and the mixed gas, the combustible mixed gas is combusted under the action of the ignition device 14, the mixed gas contains enough oxygen and has high temperature, the combustible mixed gas is guaranteed to be fully and completely combusted, the combustible mixed gas is combusted to form a rain-increasing catalyst, the rain-increasing catalyst is scattered under the high temperature to form tiny rain-increasing particles, and the mixed gas forcedly pushes the rain-increasing particles to be sown to the outside to increase the rain, and the engine is completed.
Further, the first part of air-entraining flows through the surface of the casing of the outer exhaust device 3, so that heat generated by combustion of the rain-increasing fuel can be effectively taken away, the effect of heat dissipation and temperature reduction is achieved, and the outer exhaust device 3 is prevented from being damaged by combustion.
In the embodiment, the purpose that the artificial precipitation aircraft can work for a long time in a single way, the catalyst combustion effect is good, the operation position is free, and the flight is not influenced by the precipitation device is achieved by arranging the artificial precipitation system based on the aeroengine, the precipitation fuel device 12 is arranged in the aircraft cabin, the catalyst is sprayed out of the engine, the precipitation operation does not influence the flight process any more, the volume of the precipitation fuel carried by the precipitation fuel device 12 in a single way is far greater than that of a smoke bomb, and the artificial precipitation operation can be completed in a single flight, so that the practicability is high.
In the embodiment, through arranging the outer exhaust device 3 sleeved on the periphery of the original exhaust device and the first part of air entraining which is uniformly introduced between the inner exhaust device 3 and the outer exhaust device 3, the mixed exhaust of the inner and outer culverts is realized, the exhaust benefit is improved, the defects of low temperature of the first part of air entraining and low oxygen content of the inner exhaust are overcome, the blended air with both temperature and oxygen content is obtained, the complete and sufficient combustion of the rain-increasing fuel is ensured, the rain-increasing efficiency is improved, the air flow of the blended air is high, the rain-increasing particles can be forced to be broadcasted into the atmosphere, the rain-increasing effect is improved, the temperature of the blended air is high, the catalyst is sprayed along with a large amount of hot air flow, the broadcasting area is wide, and the blended air is used as warm ascending air flow, and the rain-increasing efficiency is further improved.
In this embodiment, the rain-enhancing fuel is ignited by the ignition device 14 in the outer exhaust device 3, and then burns, compared with the combustion mode of spontaneous combustion of the medicament in the cartridge, the combustion temperature is higher, the volume of the combustion product, namely the rain-enhancing particles, is smaller, and further, the rain-enhancing effect and efficiency are effectively improved, and further, when the rain-enhancing fuel burns in the outer exhaust device 3, higher pressure is generated, the acting direction of the pressure is consistent with the direction of the exhaust spraying force, so that the thrust of the engine is increased, and the rain-enhancing operation and the flying process are mutually promoted, so that the performance of the rain-enhancing and flying is improved.
In this embodiment, the oxidant during the combustion of the rain-enhancing catalyst is oxygen in the environment, and compared with the oxidant during the combustion of the catalyst in the bomb, the oxidant needs to be stored in the bomb, and the engine rain-enhancing system does not need to be additionally preloaded with the oxidant, so that the weight of the rain-enhancing device on the aircraft is reduced, and the flying capability of the aircraft is improved.
In particular, the nozzle 13 is located relatively downstream of the bleed air outlet 15 of the first bleed air branch 8 in the direction of flow of the air stream, and the nozzle 13 is located relatively upstream of the mixing device 4.
As shown in connection with fig. 1, the nozzle 13 is placed on the downstream side of the bleed air outlet 15 of the first bleed air branch 8 and on the upstream side of the mixing device 4, so that the first part of the bleed air, the mixing air flow, forcefully pushes the combustible mixture to be discharged evenly outwards, and subsequently fires in the outer exhaust device 3, preventing the combustible mixture from accumulating in the vicinity of the ejection orifice 25, thus affecting the combustion efficiency.
Specifically, the plurality of nozzles 13 are uniformly distributed in the circumferential direction in the sandwiched areas of the outer exhaust device 3 and the inner exhaust device 2;
a plurality of said first bleed air branches 8 are distributed uniformly in the circumferential direction.
The multiple nozzles 13 are uniformly distributed between the inner exhaust device 2 and the outer exhaust device 3 along the circumferential direction to form uniformly dispersed combustible mixed gas, meanwhile, the multiple ignition devices 14 are uniformly distributed on the casing of the outer exhaust device 3 along the circumferential direction, so that the ignition range covers the whole exhaust area, the ignition delay period is short, flame is uniformly spread, combustion is stable, pressure oscillation is prevented, the flying process is influenced, the multiple first air-entraining branches 8 are uniformly distributed on the casing of the outer exhaust device 3, and the multiple first air-entraining branches are suitable for carrying out multi-channel air-entraining in the same period, and improve the air-entraining amount of the first part of air-entraining, thereby improving the combustion efficiency of the catalyst.
Specifically, the system also comprises a high-pressure pipeline 16, one end of which is connected with the pressurizing device 11, and the other end of which extends into the rain-enhancing fuel device 12 and is suitable for supplying the pressurized second part of the air entraining.
With the combination shown in fig. 1, the second part of the bleed air uniformly enters the pressurizing device 11 from the bleed air port 5 for pressurizing, the pressurized high-pressure bleed air is introduced into the rain-enhancing fuel device 12 through the high-pressure pipeline 16, and the high-pressure pipeline 16 can stably bear the pressure of the inner pipe caused by the second part of the bleed air, so that the safe and rapid supply of the high-pressure bleed air is realized.
Specifically, the device also comprises a fuel pipeline 17, one end of which is connected with the rain-enhancing fuel device 12, and the other end of which extends into the nozzle 13 and is suitable for supplying the rain-enhancing fuel.
With reference to fig. 1, the rain-enhancing fuel uniformly enters the nozzle 13 under the action of the pushing force of the high-pressure air entraining, and the fuel pipeline is always in the normal working pressure range in the conveying process, so that no leakage is ensured during fuel supply, and the device is stable and reliable.
The device specifically comprises a bleed air control valve 19 which is respectively arranged on the first bleed air branch 8, the second bleed air branch 9 and the third bleed air branch 10 and is suitable for adjusting the bleed air quantity.
As shown in fig. 1, the plurality of bleed air control valves 19 are combined and integrated into a whole, and outlets of the combination valves are correspondingly connected with the first bleed air branch 8, the second bleed air branch 9 and the third bleed air branch 10 respectively, so that the bleed air amounts of the first bleed air, the second bleed air and the third bleed air are regulated and controlled in real time according to requirements, the accurate control of the operation process by the rain enhancement system is realized, and the practicability is improved.
Specifically, the device also comprises a fuel control valve 18, which is arranged on the fuel pipeline 17 and is suitable for adjusting the supply quantity of the rain-increasing fuel;
a pressurized bleed air control valve 26, which is arranged on the high-pressure line 16 and is adapted to regulating the supply of high-pressure bleed air.
As shown in fig. 1, the fuel pipeline 17 and the high-pressure pipeline 16 are respectively and correspondingly provided with a fuel control valve 18 and a pressurizing air-entraining control valve 26, so that the supply quantity of the rain-increasing fuel and the high-pressure air-entraining is regulated and controlled in real time according to the requirements, the accurate control of the operation process of the rain-increasing system is realized, and the practicability is improved.
Specifically, the nozzle 13 has a bleed air channel 22 and a fuel channel 23 which are arranged to extend independently;
The bleed air channel 22 meets the fuel channel 23 in a mixing chamber 24;
the mixing chamber 24 has an outwardly open spout 25 adapted to spray the mixture outwardly to atomize it.
As shown in fig. 3, the third part of the air-entraining enters the mixing chamber 24 through the air-entraining channel 22, the rain-increasing fuel enters the mixing chamber 24 through the fuel channel 23, the third part of the air-entraining and the rain-increasing fuel are premixed into a uniform combustible mixture, and then the uniform combustible mixture is ejected outwards from the ejection outlet 25, and as the ejection outlet 25 is opened outwards, the combustible mixture is scattered along the ejection direction, a conical liquid film is formed near the ejection outlet 25, and the liquid film is vibrated and broken under the action of external air resistance to form small liquid drops, so that an atomization effect is generated, and the combustible mixture is formed.
Specifically, from the bleed port 5, the first bleed branch 8, the second bleed branch 9 and the third bleed branch 10 merge into the same pipeline to extend to a node, and branch from the node and extend independently of each other, so that the pipeline arrangement is simplified.
Wherein a plurality of said bleed air control valves 19 are provided in combination at said nodes.
In addition, the combined valve is arranged at the node, the air inlet of the combined valve is communicated with the starting section pipeline which is arranged in a merging way, and the air outlet is respectively communicated with the first air-entraining branch 8, the second air-entraining branch 9 and the third air-entraining branch 10, so that the efficient air-entraining quantity adjustment is realized, the number of valve bodies is reduced, the possibility of air-entraining leakage is further reduced, and the air-entraining benefit is improved.
An aircraft comprising a fuselage and an aeroengine raining system according to any one of the preceding claims disposed inside the fuselage.
The rain increasing system of the aeroengine is arranged in the aircraft body, in the flying process, rain increasing particles are scattered and sprayed outwards from the exhaust port of the aircraft, the catalyst is strongly pushed and diffused by the mixing exhaust gas, the temperature of the mixing air flow is high, the rain increasing effect is promoted under the double effects, further, the combustion of the catalyst in the outer exhaust device 3 provides forward thrust, the flying operation and the rain increasing operation are mutually promoted, the two operations complement each other, and the aeroengine has extremely high practical value.
Further, an accessory transmission system 20 and a turbine 21 are also arranged in the aircraft, the accessory transmission system 20 is used for starting the engine, and the turbine 21 has the function of extracting energy in the fuel gas to form shaft power so as to drive the compressor 7 to compress airflow.
It is apparent that the above examples are given by way of illustration only and are not limiting of the embodiments. Other variations or modifications of the above teachings will be apparent to those of ordinary skill in the art. It is not necessary here nor is it exhaustive of all embodiments. And obvious variations or modifications thereof are contemplated as falling within the scope of the present invention.
Claims (10)
1. An aircraft engine raining system, comprising:
a base body (1) with one side opened outwards and provided with an inner exhaust device (2);
The outer exhaust device (3) is sleeved outside the inner exhaust device (2) and is arranged in an outward opening way, and a gap is reserved between the inner wall of the outer exhaust device (3) and the outer wall of the inner exhaust device (2);
the mixing device (4) is arranged at the exhaust outlet of the inner exhaust device (2);
a nozzle (13) provided in a region between the outer exhaust device (3) and the inner exhaust device (2);
the ignition device (14) is arranged at one side, close to the inner exhaust device (2), of the outer exhaust device (3);
a rain-enhancing fuel device (12) arranged inside the aircraft;
the air outlet (5) is arranged on the base body (1) and is positioned in a transition area between the combustion chamber (6) and the air compressor (7);
A first bleed air branch (8) with one end connected to the bleed air port (5) and the other end extending into the clamped region of the outer exhaust (3) and the inner exhaust (2), the blending means (4) being adapted to mix a first portion of bleed air with the inner exhaust;
A second bleed air branch (9) with one end connected with the bleed air port (5) and the other end extending into a pressurizing device (11), wherein the pressurizing device (11) is suitable for pressurizing a second part of bleed air and then feeding the second part of bleed air into the rain-increasing fuel device (12) so that the second part of bleed air pushes the rain-increasing fuel to be fed into the nozzle (13);
And one end of the third air-entraining branch (10) is connected with the air-entraining port (5), the other end of the third air-entraining branch extends into the nozzle (13), the nozzle (13) is suitable for mixing the third part of air-entraining with the rain-increasing fuel and then spraying out the combustible gas mist, and the ignition device (14) ignites the combustible gas mist.
2. The aircraft engine raining system according to claim 1, characterized in that the nozzle (13) is located relatively downstream of the bleed air outlet (15) of the first bleed air branch (8) in the direction of airflow flow, the nozzle (13) being located relatively upstream of the blending device (4).
3. The aircraft engine raining system according to claim 1, wherein a plurality of the nozzles (13) are distributed uniformly in the circumferential direction in the clamped region of the outer exhaust (3) and the inner exhaust (2);
The plurality of first bleed air branches (8) are uniformly distributed along the circumferential direction.
4. The aircraft engine raining system according to claim 1, further comprising a high-pressure line (16) which is connected at one end to the pressurizing device (11) and which extends into the raining fuel device (12) at the other end, adapted to feed the pressurized second portion of bleed air.
5. The aircraft engine raining system of claim 4, further comprising a fuel line (17) connected at one end to the raining fuel device (12) and extending into the nozzle (13) at the other end adapted to supply the raining fuel.
6. The aircraft engine raining system according to claim 5, further comprising bleed air control valves (19) respectively provided on the first bleed air branch (8), the second bleed air branch (9) and the third bleed air branch (10) and adapted to adjust the bleed air amount.
7. The aircraft engine raining system according to claim 6, further comprising a fuel control valve (18) provided on the fuel line (17) adapted to regulate the supply of the raining fuel;
a pressurized bleed air control valve (26) , is provided on the high-pressure line (16) and is adapted to regulate the supply of pressurized bleed air.
8. The aircraft engine raining system according to claim 1, characterized in that the nozzle (13) has inside it bleed air channels (22) and fuel channels (23) which are arranged extending independently of each other;
-the bleed air channel (22) meets the fuel channel (23) in a mixing chamber (24);
The mixing chamber (24) has an outwardly open spout (25) adapted to spray the mixture outwardly to atomize it.
9. The aircraft engine raining system according to claim 6, characterized in that from the bleed air port (5) the first bleed air branch (8), the second bleed air branch (9) and the third bleed air branch (10) merge into the same line extending to a node, branching off from the node and extending independently of each other;
wherein a plurality of bleed air control valves (19) are arranged at the nodes in a combined manner.
10. An aircraft comprising a fuselage and an aircraft engine raining system according to any one of claims 1 to 9 disposed inside the fuselage.
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| CN112602519A (en) * | 2020-12-24 | 2021-04-06 | 青海大学 | Sound wave rain enhancement system based on flight carrier |
| CN213719076U (en) * | 2020-11-13 | 2021-07-20 | 青海大学 | Fixed wing unmanned aerial vehicle increases rain device |
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| US20100001089A1 (en) * | 2008-07-01 | 2010-01-07 | Arturo Vazquez Serrano | Methods and systems for promoting precipitation from moisture-bearing atmospheric formations |
| US20210352856A1 (en) * | 2018-07-09 | 2021-11-18 | The United States Of America, As Represented By The Secretary Of Agriculture | Aerial electrostatic system for weather modification |
| GB2606645B (en) * | 2019-10-16 | 2023-05-24 | Gkn Aerospace Services Ltd | Air craft fluid release system |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN213719076U (en) * | 2020-11-13 | 2021-07-20 | 青海大学 | Fixed wing unmanned aerial vehicle increases rain device |
| CN112602519A (en) * | 2020-12-24 | 2021-04-06 | 青海大学 | Sound wave rain enhancement system based on flight carrier |
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