An aircraft engine rain enhancement system and aircraft

Abstract

The present invention relates to the technical field of artificial rainmaking devices, and specifically to an aircraft engine rainmaking system and an aircraft. The aircraft engine rainmaking system comprises: an external exhaust device, which is sleeved on the outside of an internal exhaust device; an air bleed port, which is located in the transition area between the combustion chamber and the compressor; a first air bleed branch, which extends to the area sandwiched by the external exhaust device and the internal exhaust device, and the first part of the bleed air is mixed with the high-temperature combustion gas; a second air bleed branch, which extends into the supercharging device, and the second part of the bleed air pushes the rainmaking fuel into the nozzle; a third air bleed branch, which extends into the nozzle, and the nozzle mixes the third part of the bleed air with the rainmaking fuel to spray out combustible gas mist, and the ignition device ignites the combustible gas mist. The aircraft engine rainmaking system provided by the present invention, by setting an artificial rainmaking system relying on the aircraft engine, realizes the single-time single-way long-term operation of the artificial rainmaking aircraft, excellent catalyst combustion effect, free operation position, and flight is not affected by the rainmaking device.

Description

Technical Field

[0001] The invention relates to the technical field of artificial rainfall enhancement devices, and in particular to an aircraft engine rainfall enhancement system and an aircraft. Background Art

[0002] The principle of artificial rainmaking is to choose the right time according to the physical characteristics of different clouds, and use airplanes, rockets, etc. to spread catalysts such as dry ice, silver iodide, and salt powder into the clouds to induce precipitation or increase precipitation.

[0003] Artificial rainmaking usually uses the method of burning rainmaking flares to create precipitation; a flare is a cylindrical pyrotechnic device with a catalyst inside. The agent in the flare produces a large number of catalyst particles during the spraying process after ignition, and enters the cloud in the form of high-temperature free fall or floats into the cloud with air currents.

[0004] In the existing technology, due to the limitation of the volume of the flare, the flare's carrying capacity is insufficient, the operation time is limited to within 1.5 hours, and the range of rainfall that can be intervened is limited; secondly, the combustion inside the flare is unstable, the nucleation rate of the catalyst is low, and the rain-increasing efficiency is poor; the flare on the aircraft is installed at the rear of the wing or the lower part of the fuselage, which affects the normal flight of the aircraft, and the aircraft can only operate in the space within the cloud. At the same time, it is extremely susceptible to strong airflows and is highly dangerous. Summary of the invention

[0005] Therefore, the technical problem to be solved by the present invention is to overcome the defects of the prior art that the flare operation time is short, the combustion is unstable, it can only operate within the cloud, and affects the safe flight of the aircraft, thereby providing an aviation engine rainmaking system and aircraft with a long single-trip operation time, good combustion effect, free operation position, and no impact on the flight of the aircraft.

[0006] In order to solve the above technical problems, the present invention provides an aircraft engine rain enhancement system and an aircraft, comprising:

[0007] A base body, one side of which is open to the outside and is provided with an internal exhaust device;

[0008] The outer exhaust device is sleeved on the outside of the inner exhaust device and is open to the outside; a gap is left between the inner wall of the outer exhaust device and the outer wall of the inner exhaust device;

[0009] A mixing device, arranged at the exhaust outlet of the inner exhaust device;

[0010] A nozzle is disposed in a region sandwiched between the outer exhaust device and the inner exhaust device;

[0011] An ignition device, arranged in the outer exhaust device at one side close to the inner exhaust device;

[0012] A rain-enhancing fuel device is installed inside the aircraft;

[0013] An air bleed port is provided on the base body and is located in a transition area between the combustion chamber and the compressor;

[0014] A first bleed air branch, one end of which is connected to the bleed air port, and the other end of which extends to the area sandwiched by the outer exhaust device and the inner exhaust device, and the mixing device is suitable for mixing the first part of the bleed air with the high-temperature combustion gas;

[0015] A second air bleed branch, one end of which is connected to the air bleed port, and the other end of which extends into the pressurizing device, wherein the pressurizing device is suitable for pressurizing the second part of the bleed air and supplying it into the rain-enhancing fuel device, so that the second part of the bleed air pushes the rain-enhancing fuel into the nozzle;

[0016] The third air bleed branch has one end connected to the air bleed port and the other end extending into the nozzle. The nozzle is suitable for mixing the third part of the bleed air with the rain-increasing fuel and then spraying out combustible gas mist. The ignition device ignites the combustible gas mist.

[0017] Optionally, along the air flow direction, the nozzle is relatively located on the downstream side of the air outlet of the first air branch, and the nozzle is relatively located on the upstream side of the mixing device.

[0018] Optionally, the plurality of nozzles are evenly distributed in the circumferential direction in the area sandwiched by the outer exhaust device and the inner exhaust device;

[0019] The plurality of first air bleed branches are evenly distributed along the circumferential direction.

[0020] Optionally, it also includes: a high-pressure pipeline, one end of which is connected to the boosting device, and the other end extends into the rainmaking fuel device, suitable for supplying the second part of the boosted bleed air.

[0021] Optionally, it also includes: a fuel pipeline, one end of which is connected to the rain-increasing fuel device, and the other end extends into the nozzle, suitable for supplying the rain-increasing fuel.

[0022] Optionally, it also includes: an air induction control valve, which is respectively arranged on the first air induction branch, the second air induction branch, and the third air induction branch, and is suitable for adjusting the air induction amount.

[0023] Optionally, it also includes: a fuel control valve, arranged on the fuel pipeline, suitable for adjusting the supply amount of the rain-increasing fuel;

[0024] The pressurized bleed air control valve is arranged on the high-pressure pipeline and is suitable for adjusting the supply amount of high-pressure bleed air.

[0025] Optionally, the nozzle has an air inlet channel and a fuel channel extending independently from each other;

[0026] The bleed air passage and the fuel passage meet in the mixing chamber;

[0027] The mixing chamber is provided with a spray port opened outwards, which is suitable for spraying the mixture outwards to atomize it.

[0028] Optionally, from the air inlet, the first air branch, the second air branch and the third air branch are combined into the same pipeline and extend to a node, and then branch off from the node and extend independently from each other, which is suitable for simplifying the pipeline arrangement.

[0029] Wherein, a plurality of the air induction control valves are arranged in combination at the node.

[0030] An aircraft comprises an aircraft body and an aircraft engine rain enhancement system as described in any one of the above items arranged inside the aircraft body.

[0031] The technical solution of the present invention has the following advantages:

[0032] 1. The aircraft engine rainmaking system provided by the present invention, by setting up an artificial rainmaking system relying on the aircraft engine, achieves the purpose of long-term single-trip operation of the artificial rainmaking aircraft, excellent catalyst combustion effect, free operation position, and flight is not affected by the rainmaking device; the rainmaking fuel device is arranged inside the aircraft cabin, and the catalyst is sprayed from the engine, the rainmaking operation no longer affects the flight process, and the volume of rainmaking fuel that can be carried by the rainmaking fuel device at a time is much larger than that of the smoke bomb, so the artificial rainmaking operation can be completed in a single flight, and the practicality is strong.

[0033] 2. The aircraft engine rain-making system provided by the present invention realizes inner and outer mixed exhaust by arranging an outer exhaust device which is sleeved on the outer periphery of the original exhaust device, and the first part of the bleed air which is uniformly introduced between the inner and outer exhaust devices, thereby improving the exhaust efficiency, compensating for the defects of low temperature of the first part of the bleed air and low oxygen content of the inner exhaust, and obtaining a mixed airflow which takes both temperature and oxygen content into consideration, thereby ensuring the complete and sufficient combustion of the rain-making fuel and improving the rain-making efficiency; the mixed airflow has a large airflow volume, which can strongly push the rain-making particles to be spread into the atmosphere, thereby improving the rain-making effect; the mixed airflow has a high temperature, and the catalyst is ejected with a large amount of hot air flow, diffuses evenly, and has a wide spreading area, and the mixed airflow acts as a warm rising airflow, thereby further improving the rain-making efficiency.

[0034] 3. In the aircraft engine rain-enhancing system provided by the present invention, the rain-enhancing fuel is ignited by an ignition device in the external exhaust device and then burns. Compared with the spontaneous combustion of the agent in the smoke bomb, the combustion temperature is higher and the volume of the combustion product, i.e., the rain-enhancing particles, is smaller, thereby effectively improving the rain-enhancing effect and efficiency; further, when the rain-enhancing fuel burns in the external exhaust device, a higher pressure is generated, and the direction of action of the pressure is consistent with the direction of the force ejected by the exhaust gas, so that the engine thrust is increased and the flight performance is improved; the flight operation and the rain-enhancing operation promote each other and complement each other, and have extremely high practical value.

[0035] 4. In the aircraft engine rain-enhancing system provided by the present invention, the oxidant used when the rain-enhancing catalyst burns is oxygen in the environment. Compared with the oxidant that needs to be stored inside the flare when the catalyst burns in the flare, the engine rain-enhancing system does not need to pre-install the oxidant, thereby reducing the weight of the rain-enhancing device on the aircraft and improving the flight capability of the aircraft.

[0036] 5. In the aircraft engine rain enhancement system provided by the present invention, multiple ignition devices are evenly distributed on the casing of the external exhaust device along the circumferential direction, so that the ignition range covers the entire exhaust area, the ignition delay period is short, the flame propagates evenly, and the combustion is stable, thereby preventing pressure oscillation and affecting the flight process; multiple first air bleed branches are evenly distributed on the casing of the external exhaust device, which is suitable for multi-channel air bleed in the same period, increasing the air bleed volume of the first part of the air, thereby improving the catalyst combustion efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0038] Figure 1 This is a schematic diagram of the aircraft engine rain enhancement system and aircraft of the present invention;

[0039] Figure 2 This is a working principle diagram of the aircraft engine rain enhancement system and the aircraft of the present invention;

[0040] Figure 3 It is a schematic structural diagram of the nozzle of the present invention.

[0041] Description of reference numerals:

[0042] 1. Base; 2. Internal exhaust device; 3. External exhaust device; 4. Mixing device; 5. Bleed air port; 6. Combustion chamber; 7. Compressor; 8. First bleed air branch; 9. Second bleed air branch; 10. Third bleed air branch; 11. Pressurization device; 12. Rainfall enhancement fuel device; 13. Nozzle; 14. Ignition device; 15. Bleed air outlet; 16. High-pressure pipeline; 17. Fuel pipeline; 18. Fuel control valve; 19. Bleed air control valve; 20. Accessory transmission system; 21. Turbine; 22. Bleed air channel; 23. Fuel channel; 24. Mixing chamber; 25. Nozzle; 26. Pressurization bleed air control valve. DETAILED DESCRIPTION

[0043] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0044] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0045] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0046] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0047] Embodiment 1

[0048] Combination Figure 1-Figure 3 As shown, the aircraft engine rain enhancement system provided in this embodiment includes:

[0049] A base body 1, one side of which is open to the outside and is provided with an internal exhaust device 2;

[0050] The outer exhaust device 3 is sleeved on the outer side of the inner exhaust device 2 and is open to the outside; a gap is left between the inner wall of the outer exhaust device 3 and the outer wall of the inner exhaust device 2;

[0051] A mixing device 4 is provided at the exhaust outlet of the internal exhaust device 2;

[0052] The nozzle 13 is provided in the area sandwiched between the outer exhaust device 3 and the inner exhaust device 2;

[0053] An ignition device 14 is provided in the outer exhaust device 3 at one side close to the inner exhaust device 2;

[0054] A rain enhancement fuel device 12 is provided inside the aircraft;

[0055] The air inlet 5 is provided on the base 1 and is located in the transition area between the combustion chamber 6 and the compressor 7;

[0056] A first air bleed branch 8, one end of which is connected to the air bleed port 5, and the other end of which extends to the area sandwiched by the outer exhaust device 3 and the inner exhaust device 2, and the mixing device 4 is suitable for mixing the first part of the bleed air with the high-temperature combustion gas;

[0057] A second air bleed branch 9, one end of which is connected to the air bleed port 5, and the other end of which extends into a pressure boosting device 11, wherein the pressure boosting device 11 is adapted to supply the second portion of bleed air to the rain-enhancing fuel device 12 after being pressurized, so that the second portion of bleed air pushes the rain-enhancing fuel to be supplied to the nozzle 13;

[0058] The third air bleed branch 10 has one end connected to the air bleed port 5 and the other end extending into the nozzle 13. The nozzle 13 is suitable for mixing the third part of the bleed air with the rain-increasing fuel and then spraying out the combustible gas mist. The ignition device 14 ignites the combustible gas mist.

[0059] Combination Figure 1-Figure 2 As shown, 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 the high-pressure air compressed by the compressor 7, and the bleed air is divided into the first part of bleed air, the second part of bleed air and the third part of bleed air.

[0060] The first bleed air branch 8 is connected with the casing of the external exhaust device 3, so that the first part of the bleed air evenly enters the area sandwiched by the external exhaust device 3 and the internal exhaust device 2; the mixing device 4 mixes the first part of the bleed air with the internal exhaust, i.e., the high-temperature fuel gas. The high-temperature fuel gas has a high temperature but insufficient oxygen content, and the first part of the bleed air has a high oxygen content but a low temperature. The mixed airflow mixes the two airflows, taking into account the airflow temperature value and the oxygen content, so as to achieve a good combustion effect and increase the exhaust flow rate.

[0061] The second air bleed branch 9 is connected with the boosting device 11, and the boosting device 11 is used for air bleed boosting. The second part of the air bleed enters the boosting device 11 evenly from the air bleed port 5 for boosting. The boosted high-pressure air bleed enters the rainmaking fuel device 12. The rainmaking fuel evenly enters the nozzle 13 under the driving force of the high-pressure air bleed.

[0062] The third air bleed branch 10 is connected to the nozzle 13, so that the third part of the bleed air enters the nozzle 13 evenly; inside the nozzle 13, the third part of the bleed air enters the mixing chamber 24 through the bleed air channel 22, and the rain-enhancing fuel enters the mixing chamber 24 through the fuel channel 23; the third part of the bleed air and the rain-enhancing fuel are premixed into a uniform combustible mixture, and then scattered outward from the nozzle 25, so that it is atomized to form a combustible mixture; the nozzle 13 is placed on the downstream side of the bleed air outlet 15 of the first air bleed branch 8 and the upstream side of the mixing device 4, so that the combustible mixture is discharged outward with the flow of the first part of the bleed air and the mixed airflow; the combustible mixture burns under the action of the ignition device 14, and the mixed airflow contains sufficient oxygen and has a high temperature, ensuring that the combustible mixture is fully and completely burned; the combustible mixture burns to form a rain-enhancing catalyst, and the rain-enhancing catalyst is dispersed to form tiny rain-enhancing particles under the action of high temperature, and the mixed airflow strongly pushes the rain-enhancing particles to spread to the outside to increase rain, completing the engine rain-enhancing operation.

[0063] Furthermore, the first part of the bleed air flows through the casing surface of the external exhaust device 3, which can effectively take away the heat generated by the combustion of the rainfall enhancement fuel, play a role in heat dissipation and temperature reduction, and prevent the external exhaust device 3 from being damaged by the combustion.

[0064] In the present embodiment, an artificial rainmaking system relying on an aircraft engine is provided to achieve the purpose of long-term single-trip operation of an artificial rainmaking aircraft, excellent catalyst combustion effect, free operation position, and flight not being affected by the rainmaking device; the rainmaking fuel device 12 is arranged inside the aircraft cabin, and the catalyst is sprayed out from the engine, the rainmaking operation no longer affects the flight process, and the volume of rainmaking fuel that can be carried by the rainmaking fuel device 12 at a time is much larger than that of a smoke bomb, so the artificial rainmaking operation can be completed in a single flight, and the practicality is strong.

[0065] In this embodiment, by providing an outer exhaust device 3 which is sleeved on the outer periphery of the original exhaust device and the first part of the bleed air which is uniformly introduced between the inner and outer exhaust devices 3, inner and outer mixed exhaust is achieved, exhaust efficiency is improved, defects of low temperature of the first part of the bleed air and low oxygen content of the inner exhaust are compensated, and a mixed airflow which takes both temperature and oxygen content into consideration is obtained, thereby ensuring complete and sufficient combustion of the rain-increasing fuel and improving rain-increasing efficiency; the mixed airflow has a large airflow volume, which can strongly push the rain-increasing particles to be spread into the atmosphere, thereby improving the rain-increasing effect; the mixed airflow has a high temperature, and the catalyst is ejected along with a large amount of hot air flow, diffuses evenly, and has a wide spreading area, and the mixed airflow acts as a warm rising airflow, thereby further improving the rain-increasing efficiency.

[0066] In the present embodiment, the rain-enhancing fuel is ignited by the ignition device 14 in the external exhaust device 3 and then burns. Compared with the spontaneous combustion of the agent in the cigarette cartridge, the combustion temperature is higher and the volume of the combustion product, i.e., the rain-enhancing particles, is smaller, thereby effectively improving the rain-enhancing effect and efficiency. Furthermore, when the rain-enhancing fuel burns in the external exhaust device 3, a higher pressure is generated, and the direction of action of the pressure is consistent with the direction of the force ejected by the exhaust gas, so that the engine thrust is increased, and the rain-enhancing operation and the flight process promote each other to improve the performance of rain-enhancing and flight.

[0067] In this embodiment, the oxidant when the rain-enhancing catalyst burns is oxygen in the environment. Compared with the oxidant when the catalyst burns in the flare, which needs to be stored inside the flare, the engine rain-enhancing system does not need to pre-install additional oxidant, thereby reducing the weight of the rain-enhancing device on the aircraft and improving the flight capability of the aircraft.

[0068] Specifically, along the air flow direction, the nozzle 13 is relatively located at the downstream side of the air intake outlet 15 of the first air intake branch 8 , and the nozzle 13 is relatively located at the upstream side of the mixing device 4 .

[0069] Combination Figure 1 As shown, the nozzle 13 is placed on the downstream side of the bleed air outlet 15 of the first bleed air branch 8 and the upstream side of the mixing device 4, so that the first part of the bleed air and the mixing airflow strongly push the combustible mixture to be discharged evenly outward, and then ignite in the external exhaust device 3, preventing the combustible mixture from accumulating near the nozzle 25, thereby affecting the combustion efficiency.

[0070] Specifically, the plurality of nozzles 13 are evenly distributed in the circumferential direction in the area sandwiched between the outer exhaust device 3 and the inner exhaust device 2;

[0071] The plurality of first air bleed branches 8 are evenly distributed along the circumferential direction.

[0072] Combination Figure 1 As shown, a plurality of nozzles 13 are evenly distributed along the circumferential direction between the inner exhaust device 2 and the outer exhaust device 3 to form a uniformly dispersed combustible mixture. At the same time, a plurality of ignition devices 14 are evenly distributed along the circumferential direction on the casing of the outer exhaust device 3, so that the ignition range covers the entire exhaust area, the ignition delay period is short, the flame propagates evenly, and the combustion is stable, thereby preventing pressure oscillations from affecting the flight process; a plurality of first air bleed branches 8 are evenly distributed on the casing of the outer exhaust device 3, which is suitable for multi-channel air bleed in the same period, thereby increasing the air bleed volume of the first part of the air bleed, thereby improving the catalyst combustion efficiency.

[0073] Specifically, it also includes: a high-pressure pipeline 16, one end of which is connected to the boosting device 11, and the other end extends into the rain-enhancing fuel device 12, suitable for supplying the second part of the boosted bleed air.

[0074] Combination Figure 1 As shown, the second part of the bleed air enters the boosting device 11 evenly from the bleed air port 5 for boosting, and the boosted high-pressure bleed air passes through the high-pressure pipeline 16 into the rainmaking fuel device 12; the high-pressure pipeline 16 can stably withstand the internal pipe pressure brought by the second part of the bleed air, thereby realizing the safe and rapid supply of high-pressure bleed air.

[0075] Specifically, it also includes: a fuel pipeline 17, one end of which is connected to the rain-enhancing fuel device 12, and the other end extends into the nozzle 13, suitable for supplying the rain-enhancing fuel.

[0076] Combination Figure 1 As shown, the rain-enhancing fuel enters the nozzle 13 evenly under the driving force of the high-pressure bleed air. During the transportation process, the fuel pipeline is always within the normal working pressure range, ensuring that the fuel supply is leak-free and stable and reliable.

[0077] Specifically, it also includes: an air induction control valve 19, which is respectively arranged on the first air induction branch 8, the second air induction branch 9, and the third air induction branch 10, and is suitable for adjusting the amount of air induction.

[0078] Combination Figure 1 As shown, a plurality of air bleed control valves 19 are combined and integrated into one, and the outlets of the combined valves are respectively connected to the first air bleed branch 8, the second air bleed branch 9 and the third air bleed branch 10, for adjusting the air volume of the first part of air, the second part of air and the third part of air in real time according to demand, so as to realize the precise control of the operation process of the rain enhancement system and improve the practical performance.

[0079] Specifically, it also includes: a fuel control valve 18, which is arranged on the fuel pipeline 17 and is suitable for adjusting the supply amount of the rain-increasing fuel;

[0080] The boost air control valve 26 is provided on the high pressure pipeline 16 and is suitable for adjusting the supply amount of high pressure air.

[0081] Combination Figure 1 As shown, the fuel pipeline 17 and the high-pressure pipeline 16 are respectively provided with a fuel control valve 18 and a pressurized air control valve 26, which are used to adjust the supply of rainmaking fuel and high-pressure air in real time according to demand, so as to achieve precise control of the operation process of the rainmaking system and improve practical performance.

[0082] Specifically, the nozzle 13 has an air inlet passage 22 and a fuel passage 23 extending independently from each other;

[0083] The air induction channel 22 and the fuel channel 23 intersect in the mixing chamber 24;

[0084] The mixing chamber 24 has a spray port 25 open to the outside, which is suitable for spraying the mixture outward to atomize it.

[0085] Combination Figure 3 As shown, the third part of the bleed air enters the mixing chamber 24 through the bleed air channel 22, and the rain-enhancing fuel enters the mixing chamber 24 through the fuel channel 23. The third part of the bleed air and the rain-enhancing fuel are premixed into a uniform combustible mixture, and then ejected outward from the nozzle 25. Since the nozzle 25 is open to the outside, the combustible mixture is scattered along the injection direction and forms a conical liquid film near the nozzle 25. Under the action of external air resistance, the liquid film vibrates and breaks into small droplets, thereby producing an atomization effect to form a combustible mixture.

[0086] Specifically, from the air inlet 5, the first air branch 8, the second air branch 9 and the third air branch 10 are combined into the same pipeline and extend to the node, and then branch off from the node and extend independently from each other, which is suitable for simplifying the pipeline arrangement.

[0087] Wherein, a plurality of the air induction control valves 19 are arranged in combination at the node.

[0088] Combination Figure 1 As shown, since the air source of the first part of the air bleed, the second part of the air bleed and the third part of the air bleed are the same, the starting sections of the first air bleed branch 8, the second air bleed branch 9 and the third air bleed branch 10 are merged, and then branched from the node and extended independently from each other, which simplifies the internal pipeline layout and saves space and cost; in addition, the combination valve is arranged at the node, the air inlet of the combination valve is connected to the starting section of the merged pipeline, and the air outlet is connected to the first air bleed branch 8, the second air bleed branch 9 and the third air bleed branch 10 respectively, so as to achieve efficient regulation of the air bleed volume while reducing the number of valve bodies, thereby reducing the possibility of air leakage and improving the air bleed efficiency.

[0089] An aircraft comprises an aircraft body and an aircraft engine rain enhancement system as described in any one of the above items arranged inside the aircraft body.

[0090] Combination Figure 1-2 As shown, the aircraft engine rain enhancement system is arranged inside the fuselage of the aircraft. During the flight, rain enhancement particles are scattered and sprayed outward from the exhaust port of the aircraft, and the catalyst is strongly pushed and diffused by the mixed exhaust gas. In addition, the temperature of the mixed airflow is high, and the rain enhancement effect is promoted under the dual effects. Furthermore, the combustion of the catalyst in the external exhaust device 3 provides forward thrust, and the flight operation and the rain enhancement operation promote each other and complement each other, which has extremely high practical value.

[0091] Furthermore, an accessory transmission system 20 and a turbine 21 are also provided in the aircraft. The accessory transmission system 20 is used to start the engine, and the turbine 21 has the function of extracting energy from the combustion gas to form shaft power to drive the compressor 7 to compress the airflow.

[0092] Obviously, the above embodiments are merely examples for the purpose of clear explanation, and are not intended to limit the implementation methods. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived from these are still within the scope of protection of the invention.

Claims

1. An aircraft engine rain enhancement system, characterized in that: include: A base body (1) has one side open to the outside and is provided with an internal exhaust device (2); The external exhaust device (3) is sleeved on the outside of the internal exhaust device (2) and is open to the outside; a gap is left between the inner wall of the external exhaust device (3) and the outer wall of the internal exhaust device (2); A mixing device (4) is arranged at the exhaust outlet of the internal exhaust device (2); A nozzle (13) is arranged in a region sandwiched between the outer exhaust device (3) and the inner exhaust device (2); An ignition device (14) is arranged on a side of the outer exhaust device (3) close to the inner exhaust device (2); A rain enhancement fuel device (12) is arranged inside the aircraft; An air inlet (5) is provided on the base (1) and is located in a transition area between the combustion chamber (6) and the compressor (7); A first air bleed branch (8), one end of which is connected to the air bleed port (5), and the other end of which extends to the area sandwiched between the external exhaust device (3) and the internal exhaust device (2), wherein the mixing device (4) is suitable for mixing the first part of the bleed air with the internal exhaust; A second air bleed branch (9), one end of which is connected to the air bleed port (5), and the other end of which extends into a pressure-boosting device (11), wherein the pressure-boosting device (11) is adapted to pressurize the second portion of the bleed air and supply it into the rain-enhancing fuel device (12), so that the second portion of the bleed air pushes the rain-enhancing fuel into the nozzle (13); The third air bleed branch (10) has one end connected to the air bleed port (5) and the other end extending into the nozzle (13). The nozzle (13) is suitable for mixing the third part of the bleed air with the rain-increasing fuel and then spraying out the combustible gas mist. The ignition device (14) ignites the combustible gas mist.

2. The aircraft engine rain enhancement system according to claim 1, characterized in that: Along the air flow direction, the nozzle (13) is relatively located on the downstream side of the bleed air outlet (15) of the first bleed air branch (8), and the nozzle (13) is relatively located on the upstream side of the mixing device (4).

3. The aircraft engine rain enhancement system according to claim 1, characterized in that: The plurality of nozzles (13) are evenly distributed in the circumferential direction in the area sandwiched between the outer exhaust device (3) and the inner exhaust device (2); The plurality of first air bleed branches (8) are evenly distributed along the circumferential direction.

4. The aircraft engine rain enhancement system according to claim 1, characterized in that: Also includes: A high-pressure pipeline (16) is connected to the pressurizing device (11) at one end and extends into the rain-enhancing fuel device (12) at the other end, and is suitable for supplying the second part of the pressurized bleed air.

5. The aircraft engine rain enhancement system according to claim 4, characterized in that: Also includes: A fuel pipeline (17) has one end connected to the rain-enhancing fuel device (12) and the other end extending into the nozzle (13), and is suitable for supplying the rain-enhancing fuel.

6. The aircraft engine rain enhancement system according to claim 5, characterized in that: Also includes: The air induction control valve (19) is respectively arranged on the first air induction branch (8), the second air induction branch (9), and the third air induction branch (10), and is suitable for adjusting the amount of air induction.

7. The aircraft engine rain enhancement system according to claim 6, characterized in that: Also includes: A fuel control valve (18), disposed on the fuel pipeline (17), adapted to adjust the supply amount of the rain-enhancing fuel; Bleed air pressure control valve (26) ， It is arranged on the high-pressure pipeline (16) and is suitable for adjusting the supply amount of pressurized bleed air.

8. The aircraft engine rain enhancement system according to claim 1, characterized in that: The nozzle (13) has an air inlet passage (22) and a fuel passage (23) extending independently from each other. The air induction channel (22) and the fuel channel (23) intersect in the mixing chamber (24); The mixing chamber (24) is provided with a spray port (25) open outwards, which is suitable for spraying the mixture outwards to atomize it.

9. The aircraft engine rain enhancement system according to claim 6, characterized in that: From the air inlet (5), the first air inlet branch (8), the second air inlet branch (9) and the third air inlet branch (10) are combined into a single pipeline and extend to a node, and then branch off from the node and extend independently from each other; Wherein, a plurality of the air induction control valves (19) are arranged in combination at the node.

10. An aircraft, characterized in that: The invention comprises an aircraft body and an aircraft engine rain enhancement system as described in any one of claims 1 to 9 arranged inside the aircraft body.

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