Fuel nozzle, engine and helicopter

Abstract

The present application relates to a fuel nozzle, an engine and a helicopter. The fuel nozzle includes an oil inlet pipe and an evaporation pipe which are connected to each other. A swirler is connected between the oil inlet pipe and the evaporation pipe. The swirler includes an air path casing and an oil path casing. The air path casing is connected to the outer edge of the oil path casing. The air path casing is connected to the evaporation pipe, and the oil inlet pipe is connected to the oil path casing. An oil path passage is formed in the oil path casing, and an air path passage is formed between the air path casing and the oil path casing. The oil path casing is provided with a swirl hole and a blade. The swirl hole connects the air path passage and the oil path passage. The axial direction of the swirl hole is not parallel to the radial direction of the oil path casing. The distance between one end of the swirl hole located at the outer edge of the oil path casing and the evaporation pipe is greater than the distance between one end of the swirl hole located at the inner edge of the oil path casing and the evaporation pipe. The rotation direction of the blade is consistent with the rotation direction of the swirl hole, thereby realizing multi-stage swirl and effectively improving the atomization ability of the fuel nozzle.

Description

Technical Field

[0001] The present application relates to the technical fields of aeroengines and gas turbines, and particularly to a fuel nozzle, an engine, and a helicopter. Background Art

[0002] Small and micro aeroengines and gas turbines have been a research hotspot at home and abroad in recent years, and have the advantages of small volume, light weight, large output energy, high density, etc. The design of the combustion chamber is a key link in a gas turbine engine. Compared with a combustion chamber of a conventional scale, the combustion chamber of such a small and micro gas turbine engine has the characteristics of a small characteristic size and a large surface-to-volume ratio, resulting in a short gas flow residence time and a large heat dissipation loss, thereby leading to the occurrence of combustion instability.

[0003] Although relevant research work on the combustion chambers of small and micro gas turbine engines has been carried out at home and abroad, due to cost and space limitations, a centrifugal nozzle is basically used for ignition starting, and an evaporative tube type or an air atomizing nozzle with a simple structure is used for fuel supply. Using this fuel supply method can obtain higher combustion performance under the condition of a short combustion residence time. Among them, the annular combustion chamber of the evaporative tube type has many advantages such as low fuel supply pressure, low cost, and light weight. The air atomizing nozzle has the advantages of ensuring sufficient and uniform mixing of fuel and air flow.

[0004] With the continuous increase of the compression ratio and temperature rise of the gas turbine engine combustion chamber, and due to the relaxation of the fuel specification of the gas turbine, problems such as smoking, carbon deposition, and high wall temperature in the combustion chamber are particularly serious. The development of high-performance engines puts forward some higher requirements for the fuel supply system: complete combustion in a shorter combustion zone to shorten the length of the combustion chamber and reduce its weight; higher ignition performance and lean blowout range; lower pollutant emissions to meet the requirements of low-pollution emissions of future aero gas turbines.

[0005] The structure of the traditional air atomizing nozzle causes the fuel to be affected by the shear forces of two internal and external swirling airflows during the downstream flow process, forming relatively small atomized particles. The disadvantage of this air atomizing nozzle is that primary atomization is likely to result in poor fuel atomization quality, which in turn leads to uneven temperature distribution and affects the combustion efficiency of the entire combustion chamber.

[0006] The basic principle of the traditional evaporation tube nozzle is that after the evaporation tube is heated, when the fuel flows through the evaporation tube, it is evaporated into fuel mist upon heating and mixes with air to form atomized gas, enabling ignition and successful combustion in the combustion chamber. The quality of fuel atomization depends on the wall temperature of the evaporation tube, the residence time of the fuel in the evaporation tube, and the heating area of the fuel. However, due to the structural limitations of the engine, the current evaporation tube is too short. Since the gas flow velocity in the evaporation tube is too fast, the fuel is quickly blown out of the evaporation tube by the gas flow, and the residence time of the fuel in the evaporation tube is extremely short. Consequently, the heating time of the fuel is short and the effect is poor, and the degree of evaporation and atomization of the fuel is very low. Moreover, the evaporation tube is a smooth-walled round tube, without any device to reduce the fuel flow velocity or any facility to increase the fuel heating.

[0007] Therefore, the atomization effects of traditional air atomizing nozzles and evaporation tube nozzles are relatively poor. Summary of the Invention

[0008] To solve the above technical problems, the present application provides a fuel nozzle, an engine, and a helicopter, which can improve the atomization ability of the fuel nozzle.

[0009] On the one hand, the present application provides a fuel nozzle. The fuel nozzle includes an oil inlet pipe and an evaporation tube connected to each other. A swirler is connected between the oil inlet pipe and the evaporation tube. The swirler includes a gas path sleeve and an oil path sleeve. The gas path sleeve is connected to the outer edge of the oil path sleeve. The gas path sleeve is connected to the evaporation tube, and the oil inlet pipe is connected to the oil path sleeve. An oil path passage is formed inside the oil path sleeve, and a gas path passage is formed between the gas path sleeve and the oil path sleeve. The oil path sleeve is provided with swirl holes and blades. The swirl holes connect the gas path passage and the oil path passage. The axial direction of the swirl holes is not parallel to the radial direction of the oil path sleeve. The distance between the end of the swirl hole located at the outer edge of the oil path sleeve and the evaporation tube is greater than the distance between the end of the swirl hole located at the inner edge of the oil path sleeve and the evaporation tube. The rotation direction of the blades is consistent with the rotation direction of the swirl holes.

[0010] In an embodiment of the present application, a plurality of the blades are connected between the gas path sleeve and the oil path sleeve, and the swirl holes are evenly distributed between two adjacent blades.

[0011] In an embodiment of the present application, a throttle ring is provided between the oil inlet pipe and the oil path sleeve, and throttle holes are further provided on the throttle ring. The oil inlet pipe and the oil path sleeve are connected through the throttle holes.

[0012] In one embodiment of the present application, a flow-blocking atomizer is provided between the throttle ring and the oil circuit casing. A flow-blocking atomization plate is provided at one end of the flow-blocking atomizer close to the oil circuit casing. Atomization nozzles are provided on the flow-blocking atomization plate. A flow-blocking atomization chamber is formed in the flow-blocking atomizer. One end of the flow-blocking atomization chamber is communicated with the oil circuit casing through the atomization nozzles, and the other end of the flow-blocking atomization chamber is communicated with the throttle ring.

[0013] In one embodiment of the present application, a nozzle seat is installed on the outer edge of the fuel inlet pipe. A connecting sleeve is connected between the nozzle seat and the gas circuit casing. A plurality of ventilation holes are provided on the outer edge of the connecting sleeve. The connecting sleeve, the gas circuit casing, the fuel inlet pipe, the throttle ring, and the flow-blocking atomizer form the gas circuit passage. One end of the gas circuit passage is communicated with the ventilation holes, and the other end of the gas circuit passage is communicated with the swirl holes.

[0014] In one embodiment of the present application, the evaporation tube includes a confluence tube and an evaporation spray tube. The confluence tube is connected to the gas circuit casing. A plurality of evaporation nozzles are provided on the evaporation spray tube.

[0015] In one embodiment of the present application, the confluence tube is in the shape of a flared hole. The end with a larger opening of the confluence tube is connected to the gas circuit casing, and the end with a smaller opening of the confluence tube is connected to the evaporation spray tube.

[0016] In one embodiment of the present application, the evaporation spray tube is spiral.

[0017] On the other hand, an engine is provided, which is installed with the above fuel nozzle.

[0018] On yet another hand, a helicopter is provided, which is installed with the above engine.

[0019] The above fuel nozzle technical solution of the present application has the following advantages compared with the prior art:

[0020] (1) After air enters the swirler in the present application, the swirling gas path formed by the swirl holes on the swirler performs primary swirling atomization on the fuel in the oil circuit passage; the swirling gas path formed by the blades on the swirler performs secondary swirling atomization on the fuel flowing into the confluence tube. That is, multi-stage atomization of the fuel is realized, greatly improving the fuel atomization effect, significantly reducing the smoke density, and improving the combustion efficiency of the fuel; in addition, by providing a multi-stage swirler to increase the atomization stage, the fuel atomization effect is further improved.

[0021] (2) The swirling gas path formed by the swirler in the present application can not only perform swirling atomization on the fuel, but also make the gas flow along the pipe wall, increasing the contact area and time between the internal fuel and the main body wall, thereby enhancing the atomization effect of heat transfer evaporation.

[0022] (3) In this application, the spiral evaporation nozzle can preheat the gas at the high temperature of the combustion chamber while evaporating and atomizing the fuel, making the fuel burn more fully and reducing the nitrogen oxide emissions.

[0023] (4) In this application, by arranging the evaporation nozzles along the axis of the spiral section of the evaporation nozzle according to a certain rule, the oil-gas mixture fluid is ejected from each nozzle at different positions and in different directions of the evaporation nozzle, improving the uniformity of the distribution of the oil-gas mixture fluid in the combustion chamber and greatly avoiding the emergence of local high-temperature areas, thus promoting better combustion. Description of the Drawings

[0024] In order to more clearly illustrate the technical solutions in the embodiments of this application, the drawings required for the description of the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of this application. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0025] Figure 1 is a schematic structural view of the fuel nozzle of this application;

[0026] Figure 2 is a front view of the air atomizing fuel nozzle of this application;

[0027] Figure 3 is Figure 2 a cross-sectional view taken along line A-A in

[0028] Figure 4 is a schematic structural view of the swirler of the fuel nozzle of this application;

[0029] Figure 5 is a cross-sectional view of the swirl holes on the swirler of the fuel nozzle of this application;

[0030] Figure 6 is a schematic structural view of the throttle ring of the fuel nozzle of this application;

[0031] Figure 7 is a schematic structural view of the choke atomizer of the fuel nozzle of this application;

[0032] Figure 8 is a cross-sectional view of the choke atomizer of the fuel nozzle of this application;

[0033] Figure 9 is a schematic structural view of the evaporation tube of the fuel nozzle of this application.

[0034] Explanation of the Reference Numerals in the Drawings of the Specification:

[0035] 1. Oil inlet pipe; 2. Evaporator pipe; 3. Vortex finder; 4. Gas casing; 5. Oil casing; 6. Oil passage; 7. Gas passage; 8. Swirl hole; 9. Blade; 10. Throttle ring; 11. Throttle hole; 12. choke atomizer; 13. choke atomizer plate; 14. Atomizer nozzle; 15. choke atomizer chamber; 16. Nozzle seat; 17. Connecting sleeve; 18. Air vent; 19. Manifold; 20. Evaporator nozzle; 21. Evaporator nozzle; 22. First mounting hole; 23. Second mounting hole; 24. Inner wall; 25. First end; 26. Second end. DETAILED DESCRIPTION

[0036] In order to make the purpose, technical solutions and advantages of this application clearer, the technical solutions in the embodiments of this application will be clearly and completely described below in conjunction with the drawings in the embodiments of this application. Obviously, the described embodiments are only part of the embodiments of this application, not all of them. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0037] Embodiment 1

[0038] Reference Figures 1 to 9 As shown, the fuel nozzle of the present application comprises an oil inlet pipe 1 and an evaporation pipe 2 connected to each other, a vortex finder 3 is connected between the oil inlet pipe 1 and the evaporation pipe 2, the vortex finder 3 comprises an air sleeve 4 and an oil sleeve 5, the air sleeve 4 is connected to the outer edge of the oil sleeve 5, the air sleeve 4 is connected to the evaporation pipe 2, the oil inlet pipe 1 is connected to the oil sleeve 5, an oil passage 6 is formed in the oil sleeve 5, and an air passage 6 is formed between the air sleeve 4 and the oil sleeve 5 7. A swirl hole 8 and a blade 9 are provided on the oil sleeve 5. The swirl hole 8 connects the gas passage 7 and the oil passage 6. The axial direction of the swirl hole 8 is not parallel to the radial direction of the oil sleeve 5. The distance between one end of the swirl hole 8 located at the outer edge of the oil sleeve 5 and the evaporator tube 2 is greater than the distance between one end of the swirl hole 8 located at the inner edge of the oil sleeve 5 and the evaporator tube 2. The rotation direction of the blade 9 is consistent with the rotation direction of the swirl hole 8.

[0039] The fuel nozzle of the present application realizes multi-stage swirl of intake air. The fuel injection body specifically includes an oil inlet pipe 1 and an evaporation pipe 2. The oil inlet pipe 1 and the evaporation pipe 2 are connected to each other to form a passage for fuel circulation. The oil inlet pipe 1 is used to supply oil into the evaporation pipe 2, and the evaporation pipe 2 is used to atomize and eject the fuel. A swirler 3 is connected between the oil inlet pipe 1 and the evaporation pipe 2, and the swirler 3 is used to realize multi-stage swirl of intake air. Specifically, the swirler 3 includes an air path sleeve 4 and an oil path sleeve 5, which are connected to each other. The air path sleeve 4 is connected to the outer edge of the oil path sleeve 5. Preferably, the air path sleeve 4 and the oil path sleeve 5 have the same length. The diameter of the air path sleeve 4 is larger than that of the oil path sleeve 5, and the air path sleeve 4 and the oil path sleeve 5 are coaxially arranged. The oil path sleeve 5 is used for fuel circulation, and the air path sleeve 4 is used for air circulation. The air in the air path sleeve 4 and the fuel in the oil path sleeve 5 converge at the swirler 3. Among them, an oil path passage 6 is formed in the oil path sleeve 5, and an air path passage 7 is formed between the air path sleeve 4 and the oil path sleeve 5. The air path sleeve 4 on the swirler 3 is connected to the evaporation pipe 2, and the oil path sleeve 5 on the swirler 3 is connected to the oil inlet pipe 1. The fuel in the oil inlet pipe 1 reaches the oil path passage 6 formed by the oil path sleeve 5 on the swirler 3, converges with the air in the air path passage 7 in the air path sleeve 4 to form an oil-gas mixture fluid, and the oil-gas mixture fluid further flows to the evaporation pipe 2. A swirl hole 8 and a blade 9 are arranged on the oil path sleeve 5, and both the swirl hole 8 and the blade 9 play a role in swirling, such as Figure 4 the blade swirl direction shown. The swirl hole 8 connects the air path passage 7 and the oil path passage 6, so as to realize the mixing of the air in the air path passage 7 and the fuel in the oil path passage 6. Further, the axial direction of the swirl hole 8 is not parallel to the radial direction of the oil path sleeve 5, that is, the axial direction of the swirl hole 8 is not allowed to be parallel to the radial direction of the oil path sleeve 5. If the axial direction of the swirl hole 8 is parallel to the radial direction of the oil path sleeve 5, it cannot play a role in swirling, and the effect of multi-stage swirl cannot be realized. That is, the axial direction of the swirl hole 8 is inclined to the radial direction of the oil path sleeve 5, such as Figure 5As shown, a plane perpendicular to the axis of the oil circuit sleeve 5 and passing through one of the swirl holes 8 is defined as the reference plane. In the reference plane, the plurality of swirl holes 8 are integrally spiral. After the air enters the oil circuit sleeve 5 through the swirl holes 8, the direction of the air entering the oil circuit sleeve 5 is along the axis direction of the swirl holes 8, and the air forms a swirl. Therefore, the high-speed air flow exerts a shearing effect on the fuel in the oil circuit sleeve 5, causing the fuel to be further atomized. The fuel and the air form an oil-gas mixed fluid, and the oil-gas mixed fluid finally enters the evaporation nozzle 20 along the swirl direction and rotates forward along the inner wall of the pipe. It exchanges heat with the high temperature inside the flame tube for evaporation and atomization, and finally is ejected from the evaporation nozzle 21 on the evaporation nozzle 20 and organized to burn after ignition. In addition, the swirl hole 8 forms two ends along its axis direction. The distance between one end of the swirl hole 8 located at the outer edge of the oil circuit sleeve 5 and the evaporation tube 2 is greater than the distance between one end of the swirl hole 8 located at the inner edge of the oil circuit sleeve 5 and the evaporation tube 2. In the plane passing through the axis of the oil circuit sleeve 5, the swirl hole 8 is inclined with respect to the axis of the oil circuit sleeve 5. The inclined state is referred to as the distance described above, which can improve the swirl effect and facilitate the air to enter the oil circuit sleeve 5. However, at this time, the forward speed of the fuel will be increased. If the evaporation of the oil-gas mixed fluid is too ideal, it will cause the occurrence of backfire and spontaneous combustion phenomena. Therefore, it is necessary to match the evaporation degree of the oil mixture fluid and the inclination angle of the swirl hole 8 with respect to the axis of the oil circuit sleeve 5 (equivalent to the forward speed of the fuel and the heat exchange time of the oil-gas mixed fluid) for design in order to achieve the optimal balance state. The configuration of this distance is for the cooperation between the swirl hole 8 and the blade 9 to improve the multi-stage swirl effect. Further, the swirl direction of the blade 9 is consistent with the swirl direction of the swirl hole 8. First, when the air flows from the air passage 7 on the air circuit sleeve 4 to the swirler 3, the air forms two passages in the swirler 3. One passage is that a part of the air flowing through the blade 9 will enter the oil passage 6 through the swirl hole 8; the other passage is that the air swirls through the blade 9, that is, the air will generate a swirl under the structure of the blade 9 after entering the swirler 3, and the swirled air flows through the air passage 7 to the evaporation tube 2. Therefore, the swirl air path formed by the swirler 3 through the swirl hole 8 performs primary swirl atomization on the fuel in the oil passage 6; the swirl air path formed by the blade 9 on the swirler 3 performs secondary swirl atomization on the fuel flowing into the confluence tube 19 to form an oil-gas mixed fluid. The oil-gas mixed fluid has achieved a good atomization effect before reaching the evaporation tube 2. Therefore, the swirl hole 8 and the blade 9 on the swirler 3 effectively pre-atomize the fuel and the oil-gas mixed fluid. The fuel is atomized to form gas.

[0040] In one of the embodiments, a plurality of the blades 9 are connected between the air circuit sleeve 4 and the oil circuit sleeve 5, and the swirl holes 8 are evenly distributed between two adjacent blades 9.

[0041] The oil casing 5 is provided with swirl holes 8 and blades 9. Furthermore, the blades 9 are arranged between the oil casing 5 and the gas casing 4, and the blades 9 are connected to the oil casing 5 and the gas casing 4. Multiple blades 9 and swirl holes 8 can be provided. Multiple blades 9 are evenly distributed between the oil casing 5 and the gas casing 4, and are arranged equidistantly in a spiral array. The swirl holes 8 are provided between two adjacent blades 9, and multiple swirl holes 8 are provided. The swirl holes 8 between each two adjacent blades 9 form a group of swirl holes 8. Multiple groups of swirl holes 8 are arranged equidistantly in a spiral array, such as Figure 4 As shown, the multiple groups of swirl holes 8 and the multiple blades 9 are all arranged in a spiral equidistant manner, and the rotation direction of the swirl holes 8 is consistent with the rotation direction of the blades 9, which can effectively improve the swirl effect of the air, further improve the shearing ability of the air on the fuel, and improve the atomization ability of the fuel and / or the oil-gas mixed fluid. Furthermore, the vortex finder can use a multi-stage vortex finder to further improve the fuel atomization effect.

[0042] In one embodiment, a throttle ring 10 is provided between the oil inlet pipe 1 and the oil casing 5 , and a throttle hole 11 is further provided on the throttle ring 10 . The oil inlet pipe 1 and the oil casing 5 are connected through the throttle hole 11 .

[0043] A throttle ring 10 is provided between the oil inlet pipe 1 and the oil line casing 5. Figure 6 The throttle ring 10 shown has a cylindrical outer edge as a whole. The throttle ring 10 is provided with a first mounting hole 22 and a second mounting hole 23. The first mounting hole 22 is used to connect the oil inlet pipe 1 with the throttle ring 10, and the second mounting hole 23 is used to connect the throttle ring 10 with the flow-blocking atomizer 12. An inner side wall 24 is formed between the first mounting hole 22 and the second mounting hole 23. A throttle hole 11 is provided at the axis of the throttle ring 10 on the inner side wall 24. The diameter of the throttle hole 11 is 0.5 mm to 1.5 mm, and is set according to the specific actual scene. The fuel flows into the throttle ring 10 after flowing from the oil inlet pipe 1. The fuel passes through the throttle hole 11 on the throttle ring 10, and the fuel pressure drops, the flow rate increases, the density decreases, and part of the fuel is atomized and flows into the flow-blocking atomizer 12.

[0044] In one embodiment, a flow-blocking atomizer 12 is arranged between the throttling ring 10 and the oil circuit sleeve 5, and a flow-blocking atomizer plate 13 is arranged at one end of the flow-blocking atomizer 12 close to the oil circuit sleeve 5, and an atomizing nozzle 14 is arranged on the flow-blocking atomizing plate 13. A flow-blocking atomizing chamber 15 is formed in the flow-blocking atomizer 12, and one end of the flow-blocking atomizing chamber 15 is connected to the oil circuit sleeve 5 through the atomizing nozzle 14, and the other end of the flow-blocking atomizing chamber 15 is connected to the throttling ring 10.

[0045] A flow restrictor atomizer 12 is provided between the throttle ring 10 and the oil circuit sleeve 5. The flow restrictor atomizer 12 is in the shape of a stepped shaft and includes a first end 25 and a second end 26. The first end 25 is the end connected to the throttle ring 10, and the second end 26 is the end connected to the oil circuit sleeve 5. A flow restrictor atomizing plate 13 is provided at one end of the flow restrictor atomizer 12 close to the oil circuit sleeve 5. An atomizing nozzle 14 is provided on the flow restrictor atomizing plate 13, that is, the atomizing nozzle 14 is provided on the second end 26. As Figure 7 and Figure 8 shown, the flow restrictor atomizer 12 is hollowed to form a flow restrictor atomizing cavity 15 (or the flow restrictor atomizer 12 is welded to the flow restrictor atomizing plate 13 to form the flow restrictor atomizing cavity 15). One end (the second end 26) of the flow restrictor atomizing cavity 15 is communicated with the oil circuit sleeve 5 through the atomizing nozzle 14, and the other end (the first end 25) of the flow restrictor atomizing cavity 15 is communicated with the throttle ring 10. After the fuel passes through the throttle hole 11 of the throttle ring 10, it enters the flow restrictor atomizing cavity 15 in the flow restrictor atomizer 12. Due to the action of the flow restrictor atomizing plate 13, the fuel flow velocity decreases after the fuel jet passes through the flow restrictor atomizing plate 13, and the fuel is further atomized through the atomizing nozzle 14 and sprayed into the oil circuit sleeve 5 on the evaporation tube 2. Further, in order to improve the atomizing effect of the flow restrictor atomizer 12 and enhance the uniform atomizing ability, the atomizing nozzles 14 are arranged in an equidistant array on the flow restrictor atomizing plate 13. As Figure 7 shown, the equidistant array of the atomizing nozzles 14 can effectively improve the atomizing effect and the uniform ability.

[0046] In one embodiment, a nozzle seat 16 is installed on the outer edge of the fuel inlet pipe 1. A connecting sleeve 17 is connected between the nozzle seat 16 and the air circuit sleeve 4. A plurality of ventilation holes 18 are provided on the outer edge of the connecting sleeve 17. An air circuit passage 7 is formed among the connecting sleeve 17, the air circuit sleeve 4, the fuel inlet pipe 1, the throttle ring 10, and the flow restrictor atomizer 12. One end of the air circuit passage 7 is communicated with the ventilation holes 18, and the other end of the air circuit passage 7 is communicated with the swirl hole 8.

[0047] A throttle ring 10 and a baffle atomizer 12 are connected in sequence between the oil inlet pipe 1 and the oil circuit sleeve 5 of the vortex finder 3. The fuel in the oil inlet pipe 1 first passes through the throttle ring 10, passes through the baffle atomizer 12, and then reaches the oil circuit sleeve 5 of the vortex finder 3, and finally mixes with the air at the oil circuit sleeve 5 to form an oil-gas mixed fluid and then flows to the evaporator tube 2. A nozzle seat 16 is installed on the outer edge of the oil inlet pipe 1. The nozzle seat 16 is used to install the fuel nozzle on the corresponding component. The nozzle seat 16 is in the shape of a stepped shaft. A connecting sleeve 17 is arranged between the outer edge of the nozzle seat 16 and the gas path sleeve 4 of the vortex finder 3. The connecting sleeve 17 is sleeved on the outer edges of the oil inlet pipe 1, the throttle ring 10 and the choke atomizer 12, and the connecting sleeve 17 is on the same axis as the axis of the oil inlet pipe 1, the throttle ring 10 and the choke atomizer 12. One end of the connecting sleeve 17 is connected to the outer edge of the nozzle seat 16, and the other end of the connecting sleeve 17 is connected to the gas path sleeve 4. A plurality of vent holes 18 are arranged on the connecting sleeve 17. The plurality of vent holes 18 are arranged in an equidistant array along the circumference of the connecting sleeve 17, and multiple rows can be arranged. An air path 7 is formed between the connecting sleeve 17, the air path sleeve 4, the oil inlet pipe 1, the throttle ring 10, and the flow-blocking atomizer 12. One end of the air path 7 is connected to the vent hole 18, and the other end of the air path 7 is connected to the swirl hole 8. In the actual working process, the air in the two channels formed by the combustion chamber casing and the flame tube casing of the engine enters the air path 7 formed between the connecting sleeve 17, the air path sleeve 4, the oil inlet pipe 1, the throttle ring 10, the flow-blocking atomizer 12, and the swirl device 3 through the vent hole 18 on the connecting sleeve 17, and then flows to the swirl device 3 for swirl, and finally forms an oil-gas mixed fluid and flows to the evaporation tube 2.

[0048] In one embodiment, the evaporation tube 2 includes a confluence pipe 19 and an evaporation nozzle 20 . The confluence pipe 19 is connected to the gas circuit sleeve 4 . The evaporation nozzle 20 is provided with a plurality of evaporation nozzles 21 .

[0049] The evaporation tube 2 includes a confluence pipe 19 and an evaporation nozzle 20. The confluence pipe 19 is connected to the gas line sleeve 4. The confluence pipe 19 connected to the gas line sleeve 4 is responsible for converging one path of air (air in the gas line 7) passing through the vortex finder 3 and one path of oil-gas mixed fluid (oil-gas mixed fluid of fuel and air confluenced through the swirl hole 8) to form a new oil-gas mixed fluid, which further flows to the evaporation nozzle 20. The oil-gas mixed fluid that finally flows into the evaporation nozzle 20 is sprayed toward the flame tube through the evaporation nozzle 21 on the evaporation nozzle 20. Further, when the fuel in the oil inlet pipe 1 passes through the evaporation pipe 2, since the evaporation pipe 2 is located in the flame tube, the internal high temperature of the flame tube will exchange heat with the high temperature of the oil-gas mixed fluid in the evaporation pipe 2, so that the oil-gas mixed fluid in the evaporation pipe 2 is fully evaporated and atomized, and the oil-gas mixed fluid is finally sprayed out through the evaporation nozzle 21 on the evaporation pipe 2 to organize combustion. Among them, the diameter of the evaporation nozzle 21 is 0.2mm-0.8mm, preferably 0.3mm.

[0050] In one of the embodiments, the manifold 19 has a trumpet-shaped hole, and the end with a larger opening of the manifold 19 is connected to the gas path sleeve 4, and the end with a smaller opening of the manifold 19 is connected to the evaporation nozzle 20.

[0051] The manifold 19 is arranged in a trumpet-shaped hole. The end with a larger opening of the manifold 19 is connected to the gas path sleeve 4, and the end with a smaller opening of the manifold 19 is connected to the evaporation nozzle 20, so that one path of air (the air in the gas path 7) passing through the swirler 3 and one path of oil-gas mixture fluid (the oil-gas mixture fluid of fuel and air converging through the swirl holes 8) can effectively converge and flow to the evaporation nozzle 20.

[0052] In one of the embodiments, the end of the evaporation nozzle 20 far from the manifold 19 is closed.

[0053] One end of the evaporation nozzle 20 is connected to the manifold 19, and the other end of the evaporation nozzle 20, that is, the end of the evaporation nozzle 20 far from the manifold 19, is closed. In this way, the oil-gas mixture fluid in the evaporation nozzle 20 can only flow out from the evaporation nozzle opening 21, which can effectively improve the atomization ability of the oil-gas mixture fluid.

[0054] In one of the embodiments, the evaporation nozzle 20 is spiral.

[0055] The evaporation nozzle 20 should be set according to the actual situation. As Figure 9 shown, the evaporation nozzle 20 is spiral like a thread. Preferably, the number of effective turns is set to four, and two groups of evaporation nozzle openings 21 are arranged on each turn. Each group of evaporation nozzle openings 21 is arranged in an equidistant spiral array, which can improve the atomization uniformity of the oil-gas mixture fluid. By arranging the evaporation nozzle openings 21 along the axis direction of the spiral section of the evaporation nozzle 20 according to a certain rule, the oil-gas mixture fluid is ejected from different positions and different directions of the evaporation nozzle 20 from each nozzle opening, which improves the uniformity of the fuel distribution in the combustion chamber and greatly avoids the occurrence of local high-temperature areas, promoting better combustion. The number and distribution of the evaporation nozzle openings 21 can be configured according to the fuel flow range of the gas turbine engine.

[0056] The specific process of fuel flow is as follows:

[0057] As Figure 3As shown in the figure, fuel first flows into the throttle ring 10 from the fuel inlet pipe 1. The fuel passes through the throttle holes 11 on the throttle ring 10, where the fuel pressure drops, the flow rate increases, the density decreases, and part of the fuel atomizes and flows into the choke atomizer 12. The fuel enters the choke atomization chamber 15 inside the choke atomizer 12. Due to the action of the choke atomization plate 13, after the fuel jet passes the choke atomization plate 13, the fuel flow rate drops, and the fuel is further atomized through the atomization nozzle 14 and sprayed into the oil circuit sleeve 5 on the swirler 3. At the same time, air passes through the ventilation holes 18 on the connecting sleeve 17 and flows through the air circuit passage 7 ( Figure 3 the solid arrow and the dotted arrow tail in it) to the air circuit passage 7 on the swirler 3, which divides into two paths. One path is that part of the air flowing through the blade 9 will enter the oil circuit passage 6 through the swirl holes 8 ( Figure 3 the hollow arrow and the solid arrow tail in it); the other path is that the air swirls through the blade 9, that is, after the air enters the swirler 3, it will generate a swirl under the structure of the blade 9, and the swirled air flows through the air circuit passage 7 to the evaporation tube 2. Therefore, the swirl air path formed by the swirl holes 8 on the swirler 3 performs primary swirl atomization on the fuel in the oil circuit passage 6; the swirl air path formed by the blade 9 on the swirler 3 performs secondary swirl atomization on the fuel flowing into the confluence pipe 19 to form an oil-gas mixture fluid ( Figure 3 the solid arrow and the solid arrow tail in it); the oil-gas mixture fluid flows to the evaporation nozzle 20 and is sprayed out of the evaporation nozzle 20 through the evaporation nozzle 21 of the evaporation nozzle 20, and finally ignites and organizes combustion in the combustion chamber.

[0058] Embodiment Two

[0059] An engine is equipped with the fuel nozzle in Embodiment One. For the engine adopting the fuel nozzle in Embodiment One, on the basis that the fuel nozzle improves the atomization ability of the fuel and the oil-gas mixture fluid through multi-stage swirl, it can effectively improve the fuel efficiency of the engine, make the fuel burn more fully, and reduce the nitrogen oxide emissions.

[0060] Embodiment Three

[0061] A helicopter is equipped with the engine in Embodiment Two. For the helicopter adopting the engine in Embodiment Two, on the basis that the fuel nozzle improves the atomization ability of the fuel and the oil-gas mixture fluid and improves the fuel efficiency of the engine through multi-stage swirl, it can effectively reduce the fuel cost of the helicopter.

[0062] Note that the above is only the preferred embodiment of the present application and the technical principles applied. Those skilled in the art will understand that the present application is not limited to the specific embodiments described herein, and various obvious changes, re-adjustments and substitutions can be made by those skilled in the art without departing from the protection scope of the present application. Therefore, although the present application has been described in detail through the above embodiments, the present application is not limited to the above embodiments only. Without departing from the concept of the present application, more other equivalent embodiments can be included, and the scope of the present application is determined by the scope of the appended claims.

Claims

1. A fuel nozzle, characterized in that: The invention comprises an oil inlet pipe (1) and an evaporator pipe (2) which are connected to each other, a vortex finder (3) being connected between the oil inlet pipe (1) and the evaporator pipe (2), the vortex finder (3) comprising an air sleeve (4) and an oil sleeve (5), the air sleeve (4) being connected to the outer edge of the oil sleeve (5), the air sleeve (4) being connected to the evaporator pipe (2), the oil inlet pipe (1) being connected to the oil sleeve (5), an oil passage (6) being formed in the oil sleeve (5), and an air passage (7) being formed between the air sleeve (4) and the oil sleeve (5); The oil circuit sleeve (5) is provided with a swirl hole (8) and a blade (9); the swirl hole (8) connects the gas circuit passage (7) and the oil circuit passage (6); the axial direction of the swirl hole (8) is not parallel to the radial direction of the oil circuit sleeve (5); the distance between the end of the swirl hole (8) located at the outer edge of the oil circuit sleeve (5) and the evaporator tube (2) is greater than the distance between the end of the swirl hole (8) located at the inner edge of the oil circuit sleeve (5) and the evaporator tube (2); and the rotation direction of the blade (9) is consistent with the rotation direction of the swirl hole (8).

2. The fuel nozzle according to claim 1, wherein: A plurality of blades (9) are connected between the gas circuit sleeve (4) and the oil circuit sleeve (5), and the swirl holes (8) are evenly distributed between two adjacent blades (9).

3. The fuel nozzle according to claim 1, characterized in that: A throttling ring (10) is provided between the oil inlet pipe (1) and the oil circuit sleeve (5), and a throttling hole (11) is also provided on the throttling ring (10). The oil inlet pipe (1) and the oil circuit sleeve (5) are connected via the throttling hole (11).

4. The fuel nozzle according to claim 3, characterized in that: A flow-blocking atomizer (12) is arranged between the throttling ring (10) and the oil circuit sleeve (5); a flow-blocking atomizer plate (13) is arranged at one end of the flow-blocking atomizer (12) close to the oil circuit sleeve (5); an atomizing nozzle (14) is arranged on the flow-blocking atomizer plate (13); a flow-blocking atomizing chamber (15) is formed in the flow-blocking atomizer (12); one end of the flow-blocking atomizing chamber (15) is connected to the oil circuit sleeve (5) through the atomizing nozzle (14); and the other end of the flow-blocking atomizing chamber (15) is connected to the throttling ring (10).

5. The fuel nozzle according to claim 4, characterized in that: A nozzle seat (16) is installed on the outer edge of the oil inlet pipe (1), a connecting sleeve (17) is connected between the nozzle seat (16) and the air sleeve (4), a plurality of vent holes (18) are arranged on the outer edge of the connecting sleeve (17), the air sleeve (4) and the oil inlet pipe (1), the throttle ring (10) and the flow-blocking atomizer (12) form the air path (7), one end of the air path (7) is connected to the vent hole (18), and the other end of the air path (7) is connected to the swirl hole (8).

6. The fuel nozzle according to claim 1, characterized in that: The evaporation pipe (2) comprises a converging pipe (19) and an evaporation nozzle (20); the converging pipe (19) is connected to the gas circuit sleeve (4); and the evaporation nozzle (20) is provided with a plurality of evaporation nozzles (21).

7. The fuel nozzle according to claim 6, characterized in that: The manifold pipe (19) is in the shape of a flared hole. The end with a larger opening of the manifold pipe (19) is connected to the air path sleeve (4), and the end with a smaller opening of the manifold pipe (19) is connected to the evaporation spray pipe (20).

8. The fuel nozzle according to claim 6 or 7, characterized in that: The evaporation spray pipe (20) is spiral-shaped.

9. An engine, comprising the fuel nozzle according to any one of claims 1 to 8.

10. A helicopter, comprising the engine according to claim 9.

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