Fuel Nozzle, Engine and Helicopter

Abstract

The present application relates to a fuel nozzle, an engine and a helicopter. The fuel nozzle includes a fuel inlet pipe and an evaporation pipe connected to each other. The evaporation pipe includes a manifold pipe and an evaporation spray pipe. An air passage and an oil passage are formed on the manifold pipe. One end of the oil passage is communicated with the fuel inlet pipe, and the other end of the oil passage is communicated with the evaporation spray pipe. The air passage is communicated with the oil passage. The evaporation spray pipe is spiral, and a plurality of evaporation spray openings are arranged on the evaporation spray pipe. The fuel nozzle of the present application effectively improves the atomization ability of fuel and the oil-gas mixed fluid.

Description

Technical Field

[0001] The present application relates to the technical fields of aeroengines and gas turbines, and in particular, 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 size, 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 conventional-scale combustion chamber, the combustion chamber of such small and micro gas turbine engines has the characteristics of small characteristic size and large surface-to-volume ratio, resulting in short gas flow residence time and large heat dissipation loss, thus leading to the occurrence of combustion instability.

[0003] Although research work related to the combustion chamber of small and micro gas turbine engines has been carried out at home and abroad, due to cost and space limitations, centrifugal nozzles are basically used for ignition and starting, and evaporation tube type or air atomizing nozzles with simple structures are used for fuel supply. Using this fuel supply method can obtain higher combustion performance under the condition of shorter combustion residence time. Among them, the evaporation tube type annular combustion chamber has many advantages such as low fuel supply pressure, low cost, and light weight. The air atomizing nozzle has the advantages of being able to ensure full and uniform mixing of fuel and air flow.

[0004] With the continuous increase of the pressure 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 has put 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 the inner and outer swirling air flows 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. As 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. Therefore, 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 circular 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] In order 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 and the fuel-gas mixture fluid.

[0009] On the one hand, the present application provides a fuel nozzle, which includes a fuel inlet pipe and an evaporation tube connected to each other. The evaporation tube includes a confluence tube and an evaporation spray tube. An air passage and an oil passage are formed on the confluence tube. One end of the oil passage is connected to the fuel inlet pipe, and the other end of the oil passage is connected to the evaporation spray tube. The air passage is connected to the oil passage. The evaporation spray tube is spiral, and a plurality of evaporation spray openings are provided on the evaporation spray tube.

[0010] In an embodiment of the present application, a throttle ring is provided between the fuel inlet pipe and the evaporation tube, and throttle holes are also provided on the throttle ring. The fuel inlet pipe and the evaporation tube are connected through the throttle holes.

[0011] In an embodiment of the present application, a flow-blocking atomizer is provided between the throttle ring and the evaporation tube. A flow-blocking atomization plate is provided at one end of the flow-blocking atomizer close to the evaporation tube. Atomization spray openings 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 connected to the evaporation tube through the atomization spray openings, and the other end of the flow-blocking atomization chamber is connected to the throttle ring.

[0012] In an embodiment of the present application, the atomization spray openings are arranged in an equidistant array at one end of the flow-blocking atomizer close to the evaporation tube.

[0013] In one embodiment of the present application, the manifold includes an oil circuit sleeve, an air circuit sleeve is sleeved outside the oil circuit sleeve, an intake cavity is formed between the air circuit sleeve and the oil circuit sleeve, a plurality of ventilation holes are provided on the oil circuit sleeve, the intake cavity is communicated with the oil circuit sleeve through the ventilation holes, the oil circuit sleeve forms the oil circuit passage, and the air circuit passage is formed between the air circuit sleeve and the oil circuit sleeve.

[0014] In one embodiment of the present application, the axial direction of the ventilation hole is not parallel to the radial direction of the oil circuit sleeve.

[0015] In one embodiment of the present application, the distance between one end of the ventilation hole located at the outer edge of the oil circuit sleeve and the throttle ring is less than the distance between one end of the ventilation hole located at the inner edge of the oil circuit sleeve and the throttle ring.

[0016] In one embodiment of the present application, the air circuit sleeve is in the shape of a flared hole.

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

[0018] On yet another aspect, a helicopter is provided, which is equipped 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) In the present application, the throttle holes on the throttle ring initially atomize the fuel, then the atomization through the atomization through holes on the flow blocking atomization plate is strengthened, and secondly, the swirling atomization is carried out through the swirling air path of the oil circuit sleeve to form an oil-gas mixed fluid. Finally, the oil-gas mixed fluid undergoes sufficient heat exchange and evaporation inside the evaporation nozzle, that is, multi-stage atomization of the fuel is achieved, greatly improving the fuel atomization effect, significantly reducing the smoke density, and improving the fuel combustion efficiency.

[0021] (2) In the present application, the swirling air path of the oil circuit sleeve can not only perform swirling atomization on the fuel, but also make the gas flow along the pipe wall surface, increasing the contact area and time between the internal fuel and the main wall surface, thereby improving the atomization effect of heat transfer and evaporation.

[0022] (3) In the present application, the spiral evaporation nozzle can preheat the gas at the high temperature of the flame tube while evaporating and atomizing the fuel, making the fuel combustion more complete and the nitrogen oxide emissions lower.

[0023] (4) In this application, the evaporation nozzle arranges evaporation nozzles along the axis of the spiral section of the evaporation nozzle according to a certain rule, so that the oil-gas mixed 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 mixed fluid in the combustion chamber and greatly avoiding the emergence of local high-temperature areas, and promoting better combustion. Description of the Drawings

[0024] In order to more clearly illustrate the technical solutions in the embodiments of this application, the following will briefly introduce the drawings required for the description of the embodiments. 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 also be obtained based on these drawings.

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

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

[0027] Figure 3 is Figure 2 the cross-sectional view at A-A in

[0028] Figure 4 is Figure 2 the schematic diagram of the distribution of the ventilation holes at B-B in

[0029] Figure 5 is a schematic structural diagram of the evaporation tube of the fuel nozzle of this application;

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

[0031] Figure 7 is a schematic structural diagram of the flow-blocking atomizer of the fuel nozzle of this application;

[0032] Figure 8 is the cross-sectional view of the flow-blocking atomizer of the fuel nozzle of this application.

[0033] Explanation of the reference numerals in the drawings of the specification:

[0034] 1, inlet oil pipe; 2, evaporation tube; 3, confluence pipe; 4, evaporation nozzle; 5, gas path; 6, oil path; 7, evaporation nozzle orifice; 8, throttle ring; 9, throttle orifice; 10, flow-blocking atomizer; 11, flow-blocking atomization plate; 12, atomization nozzle orifice; 13, flow-blocking atomization chamber; 14, oil path casing; 15, gas path casing; 16, intake chamber; 17, ventilation hole; 18, first mounting hole; 19, second mounting hole; 20, inner side wall; 21, first end; 22, second end. Detailed Embodiments

[0035] To make the objectives, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application. Apparently, the described embodiments are only a part rather than all of the embodiments of the present application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present application without making creative efforts shall fall within the scope of protection of the present application.

[0036] Embodiment 1

[0037] Referring to Figures 1 to 8 As shown, the fuel nozzle of the present application includes an oil inlet pipe 1 and an evaporation pipe 2 connected to each other. The evaporation pipe 2 includes a manifold pipe 3 and an evaporation spray pipe 4. An air passage 5 and an oil passage 6 are formed on the manifold pipe 3. One end of the oil passage 6 is communicated with the oil inlet pipe 1, and the other end of the oil passage 6 is communicated with the evaporation spray pipe 4. The air passage 5 is communicated with the oil passage 6. The evaporation spray pipe 4 is spiral, and a plurality of evaporation spray openings 7 are provided on the evaporation spray pipe 4.

[0038] The fuel nozzle includes an inlet fuel pipe 1 and an evaporation pipe 2. Fuel enters the evaporation pipe 2 through the inlet fuel pipe 1, and then undergoes evaporation and atomization through the evaporation pipe 2. The atomized fuel is ignited to organize combustion. Further, the evaporation pipe 2 includes a confluence pipe 3 and an evaporation nozzle pipe 4. An air passage 5 and an oil passage 6 are formed on the confluence pipe 3. Air flows through the air passage 5, and fuel flows through the oil passage 6. The confluence pipe 3 is responsible for mixing the air in the air passage 5 with the fuel in the oil passage 6 to form an oil-gas mixed fluid. The oil-gas mixed fluid undergoes heat exchange and evaporation through the evaporation nozzle pipe 4. The atomized fuel is ignited to organize combustion. One end of the oil passage 6 is connected to the inlet fuel pipe 1, so fuel is transported to the oil passage 6 through the inlet fuel pipe 1. The other end of the oil passage 6 is connected to the evaporation nozzle pipe 4, so an oil passage 6 from the inlet fuel pipe 1 to the evaporation nozzle pipe 4 is established. The fuel in the oil passage 6 is mixed with air at the confluence pipe 3. The evaporation nozzle pipe 4 is spiral, and a plurality of evaporation nozzles 7 are provided on the evaporation nozzle pipe 4. In the prior art, the residence time of fuel in the evaporation pipe 2 nozzle is extremely short, so the evaporation and atomization effects of fuel are poor. Compared with the prior art, the evaporation nozzle pipe 4 of the present application is spiral. With the help of the evaporation nozzles 7, the evaporation nozzle pipe 4 of the same length can effectively increase the residence time of fuel in the evaporation nozzle pipe 4, and can effectively improve the evaporation and atomization effects of fuel. Further, when the fuel in the inlet fuel pipe 1 passes through the evaporation pipe 2, since the evaporation pipe 2 is located in the flame tube, the high temperature inside the flame tube will exchange heat with the high temperature of the oil-gas mixed fluid in the evaporation pipe 2, sufficiently enabling the evaporation and atomization of the oil-gas mixed fluid in the evaporation pipe 2. The fuel is atomized to form gas, and the oil-gas mixed fluid finally sprays out through the evaporation nozzles 7 on the evaporation pipe 2 to organize combustion. Among them, the diameter of the evaporation nozzles 7 ranges from 0.2 mm to 0.8 mm, preferably 0.3 mm.

[0039] In one of the embodiments, a throttle ring 8 is provided between the inlet fuel pipe 1 and the evaporation pipe 2, and a throttle hole 9 is further provided on the throttle ring 8. The inlet fuel pipe 1 and the evaporation pipe 2 are connected through the throttle hole 9.

[0040] A throttle ring 8 is provided between the inlet fuel pipe 1 and the evaporation pipe 2, as Figure 6The throttle ring 8 shown has a cylindrical outer edge as a whole. The throttle ring 8 is provided with a first mounting hole 18 and a second mounting hole 19. The first mounting hole 18 is used to connect the fuel inlet pipe 1 to the throttle ring 8, and the second mounting hole 19 is used to connect the throttle ring 8 to the flow-blocking atomizer 10. An inner side wall 20 is formed between the first mounting hole 18 and the second mounting hole 19. A throttle hole 9 is provided at the axis of the throttle ring 8 on the inner side wall 20. The diameter of the throttle hole 9 is 0.5 mm to 1.5 mm, which is set according to the specific actual scenario. The throttle hole 9 is smaller than the pipe diameters at both ends connected to it, so as to facilitate the throttling function of the fuel. After the fuel flows in from the fuel inlet pipe 1, it enters the throttle ring 8. The fuel passes through the throttle hole 9 on the throttle ring 8, the fuel pressure drops, the flow rate increases, the density decreases, and part of the fuel atomizes and flows into the flow-blocking atomizer 10.

[0041] In one embodiment, a flow-blocking atomizer 10 is provided between the throttle ring 8 and the evaporation pipe 2. A flow-blocking atomization plate 11 is provided at one end of the flow-blocking atomizer 10 close to the evaporation pipe 2. An atomization nozzle 12 is provided on the flow-blocking atomization plate 11. A flow-blocking atomization cavity 13 is formed in the flow-blocking atomizer 10. One end of the flow-blocking atomization cavity 13 is communicated with the evaporation pipe 2 through the atomization nozzle 12, and the other end of the flow-blocking atomization cavity 13 is communicated with the throttle ring 8.

[0042] A flow-blocking atomizer 10 is provided between the throttle ring 8 and the evaporation pipe 2. The flow-blocking atomizer 10 is in the shape of a stepped shaft and includes a first end 21 and a second end 22. The first end 21 is the end connected to the throttle ring 8, and the second end 22 is the end connected to the evaporation pipe 2. A flow-blocking atomization plate 11 is provided at one end of the flow-blocking atomizer 10 close to the evaporation pipe 2. An atomization nozzle 12 is provided on the flow-blocking atomization plate 11, that is, an atomization nozzle 12 is provided on the second end 22, as Figure 8 shown. The flow-blocking atomizer 10 is hollowed out to form a flow-blocking atomization cavity 13 (or the flow-blocking atomizer 10 is welded to the flow-blocking atomization plate 11 to form a flow-blocking atomization cavity 13). One end of the flow-blocking atomization cavity 13 is communicated with the evaporation pipe 2 through the atomization nozzle 12, and the other end of the flow-blocking atomization cavity 13 is communicated with the throttle ring 8. After the fuel passes through the throttle hole 9 of the throttle ring 8, it enters the flow-blocking atomization cavity 13 in the flow-blocking atomizer 10. Due to the action of the flow-blocking atomization plate 11, the fuel jet velocity drops after the flow-blocking atomization plate 11, and the fuel is further atomized through the atomization nozzle 12 and sprayed into the oil circuit sleeve 14 on the evaporation pipe 2.

[0043] In one embodiment, the atomization nozzles 12 are arranged in an equidistant array on the flow-blocking atomization plate 11.

[0044] To improve the atomization effect of the flow-blocking atomizer 10 and enhance the atomization uniformity ability, the atomization nozzles 12 on the flow-blocking atomizer 10 are arranged in an equidistant array on the flow-blocking atomization plate 11, as Figure 7 shown. The equidistant array of atomization nozzles 12 can effectively improve the atomization effect and uniformity ability.

[0045] In one embodiment, the manifold 3 includes an oil-way sleeve 14, an air-way sleeve 15 is sleeved outside the oil-way sleeve 14, an air intake cavity 16 is formed between the air-way sleeve 15 and the oil-way sleeve 14, a plurality of ventilation holes 17 are provided on the oil-way sleeve 14, the air intake cavity 16 is communicated with the oil-way sleeve 14 through the ventilation holes 17, the oil-way sleeve 14 forms the oil-way passage, and the air-way sleeve 15 and the oil-way sleeve 14 form the air-way passage.

[0046] The evaporation tube 2 includes a manifold 3 and an evaporation nozzle 4. The manifold 3 includes an oil-way sleeve 14 and an air-way sleeve 15. The air-way sleeve 15 is sleeved on the outer edge of the oil-way sleeve 14, as Figure 3 and Figure 5 shown. The air-way sleeve 15 is open on the side close to the fuel inlet pipe 1, and the air-way sleeve 15 is connected to the oil-way sleeve 14 on the side close to the evaporation nozzle 4 and is in a closed state. An air intake cavity 16 is formed between the air-way sleeve 15 and the oil-way sleeve 14, and a plurality of ventilation holes 17 are provided on the oil-way sleeve 14. The ventilation holes 17 communicate the air intake cavity 16 with the oil-way sleeve 14. The oil-way sleeve 14 forms the oil-way passage, and the air-way sleeve 15 and the oil-way sleeve 14 form the air-way passage. Therefore, the fuel first flows from the fuel inlet pipe 1 and then enters the throttle ring 8. The fuel passes through the throttle holes 9 on the throttle ring 8, the fuel pressure drops, the flow rate increases, the density decreases, part of the fuel is atomized, and flows into the flow-blocking atomizer 10; the fuel enters the flow-blocking atomization cavity 13 in the flow-blocking atomizer 10. Due to the action of the flow-blocking atomization plate 11, the fuel jet slows down after the flow-blocking atomization plate 11, and the fuel is further atomized through the atomization nozzles 12 and sprayed into the oil-way sleeve 14 on the evaporation tube 2; at the same time, air enters the air intake cavity 16, then enters the oil-way sleeve 14 through the ventilation holes 17, and mixes with the fuel to form an oil-gas mixture fluid.

[0047] In one embodiment, the axial direction of the ventilation hole 17 is not parallel to the radial direction of the oil-way sleeve 14.

[0048] To achieve the swirl of the oil-gas mixture fluid, the axial direction of the ventilation hole 17 is not parallel to the radial direction of the oil-way sleeve 14, that is, the axial direction of the ventilation hole 17 is inclined to the radial direction of the oil-way sleeve 14, as Figure 4As shown, a plane perpendicular to the axis of the oil circuit sleeve 14 and passing through one of the ventilation holes 17 is defined as the reference plane. In the reference plane, the plurality of ventilation holes 17 are in a spiral shape as a whole. After the air in the intake cavity 16 enters the oil circuit sleeve 14 through the ventilation holes 17, the direction of the air entering the oil circuit sleeve 14 is along the axis direction of the ventilation holes 17. As Figure 4 the arrow direction in Figure 4 is the swirling direction of the air, and the air forms a swirl. Therefore, the high-speed air flow exerts a shearing effect on the fuel in the oil circuit sleeve 14, causing the fuel to be further atomized. The fuel and air form an oil-gas mixture fluid, and the oil-gas mixture fluid rotates along the swirling direction and advances along the inner wall of the evaporation nozzle 4, and exchanges heat with the high temperature inside the flame tube for evaporation and atomization. Finally, it is ejected from the evaporation nozzle 7 on the evaporation nozzle 4 and organized to burn after ignition.

[0049] In one embodiment, the distance between one end of the ventilation hole 17 located on the outer edge of the oil circuit sleeve 14 and the throttle ring 8 is less than the distance between one end of the ventilation hole 17 located on the inner edge of the oil circuit sleeve 14 and the throttle ring 8.

[0050] Furthermore, taking the cross-section in Figure 5 as the reference, the ventilation hole 17 forms two ends along its axis direction. The distance between one end of the ventilation hole 17 located on the outer edge of the oil circuit sleeve 14 and the throttle ring 8 is less than the distance between one end of the ventilation hole 17 located on the inner edge of the oil circuit sleeve 14 and the throttle ring 8. That is, the ventilation hole 17 is in an inclined state with respect to the axis of the gas circuit sleeve 15. Referring to the reference distance, the swirling effect can be improved and it is convenient for air to enter the oil circuit sleeve 14 from the intake cavity 16. However, at this time, the advancing speed of the fuel will increase. If the evaporation of the oil-gas mixture 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 ventilation hole 17 with respect to the axis of the gas circuit sleeve 15 (equivalent to the advancing speed of the fuel and the heat exchange time of the oil-gas mixture fluid) for design in order to achieve the optimal balance state. Among them, the number and groups of the ventilation holes 17 are set according to actual needs. Figure 5 In Figure 5 , it is set to three groups, with six ventilation holes 17 in each group, for a total of eighteen ventilation holes 17.

[0051] In one embodiment, the gas circuit sleeve 15 is in the shape of a flared hole.

[0052] In order to improve the efficiency of air entering the intake cavity 16, the gas circuit sleeve 15 is set in the shape of a flared hole, which can effectively gather the air into the intake cavity 16 and enter the oil circuit sleeve 14 to be fully mixed with the fuel.

[0053] In one embodiment, one end of the evaporation nozzle 4 far from the manifold pipe 3 is closed.

[0054] One end of the evaporation nozzle 4 is connected to the manifold 3, and the other end of the evaporation nozzle 4, that is, the end of the evaporation nozzle 4 far from the manifold 3, is closed. In this way, the oil-gas mixed fluid in the evaporation nozzle 4 can only flow out from the evaporation nozzle 7, which can effectively improve the atomization ability of the oil-gas mixed fluid.

[0055] In one of the embodiments, at least one set of the evaporation nozzles 4 is evenly arranged along the spiral direction of the evaporation nozzle 4.

[0056] The evaporation nozzle 4 should be set according to the actual situation, such as Figure 5 As shown, the evaporation nozzle 4 is spiral like a thread. Preferably, the number of effective turns is set to four, and two sets of evaporation nozzles 7 are arranged on each turn. Each set of evaporation nozzles 7 is arranged in an equidistant spiral array, which can improve the atomization uniformity of the oil-gas mixed fluid. By arranging the evaporation nozzles 7 along the axis direction of the spiral section of the evaporation nozzle 4 according to a certain rule, the oil-gas mixed fluid is ejected from different positions and different directions of the evaporation nozzle 4 from each nozzle, improving the uniformity of the fuel distribution in the combustion chamber and greatly avoiding the emergence of local high-temperature areas, promoting better combustion. The number and distribution of the evaporation nozzles 7 can be configured according to the fuel flow range of the gas turbine engine.

[0057] The specific process of the fuel flow is as follows:

[0058] As Figure 3 shown, the fuel first flows into the fuel inlet pipe 1 and then enters the throttle ring 8 through the oil passage 6 ( Figure 3 the solid arrow tail of the hollow arrow in the figure). The fuel passes through the throttle holes 9 on the throttle ring 8, the fuel pressure drops, the flow rate increases, the density decreases, and part of the fuel is atomized and flows into the choke atomizer 10; the fuel enters the choke atomization chamber 13 in the choke atomizer 10. Due to the action of the choke atomization plate 11, the fuel jet velocity drops after the choke atomization plate 11, and the fuel is further atomized through the atomization nozzle 12 and sprayed into the oil passage sleeve 14 on the evaporation tube 2; at the same time, the air enters the intake chamber 16 through the air passage 5 ( Figure 3 the dotted arrow tail of the solid arrow in the figure), and then enters the oil passage sleeve 14 through the vent hole 17 and mixes with the fuel to form an oil-gas mixed fluid ( Figure 3 the solid arrow tail of the solid arrow in the figure); the oil-gas mixed fluid flows to the evaporation nozzle 4, is ejected from the evaporation nozzle 7 of the evaporation nozzle 4, and finally ignites and organizes combustion in the flame tube.

[0059] Embodiment 2

[0060] An engine is installed with the fuel nozzle in the first embodiment. For an engine adopting the fuel nozzle in the first embodiment, on the basis that the fuel nozzle improves the atomization ability of fuel and the fuel-gas mixture fluid, it can effectively improve the fuel efficiency of the engine, making the fuel burn more fully and reducing the nitrogen oxide emissions.

[0061] Embodiment 3

[0062] A helicopter is installed with the engine in the second embodiment. For a helicopter adopting the engine in the second embodiment, on the basis that the fuel nozzle improves the atomization ability of fuel and the fuel-gas mixture fluid and improves the fuel efficiency of the engine, it can effectively reduce the fuel cost of the helicopter.

[0063] Note that the above are only the preferred embodiments 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 here. 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: It includes a connected fuel inlet pipe (1) and an evaporation pipe (2). The evaporation pipe (2) includes a manifold pipe (3) and an evaporation nozzle (4). An air passage (5) and an oil passage (6) are formed on the manifold pipe (3). One end of the oil passage (6) is communicated with the fuel inlet pipe (1), and the other end of the oil passage (6) is communicated with the evaporation nozzle (4). The air passage (5) is communicated with the oil passage (6). The evaporation nozzle (4) is spiral, and a plurality of evaporation nozzles (7) are arranged on the evaporation nozzle (4); A throttle ring (8) is arranged between the fuel inlet pipe (1) and the evaporation pipe (2), and a throttle hole (9) is also arranged on the throttle ring (8). The fuel inlet pipe (1) and the evaporation pipe (2) are communicated through the throttle hole (9); A flow blocking atomizer (10) is arranged between the throttle ring (8) and the evaporation pipe (2). A flow blocking atomization plate (11) is arranged at one end of the flow blocking atomizer (10) close to the evaporation pipe (2). An atomization nozzle (12) is arranged on the flow blocking atomization plate (11). A flow blocking atomization chamber (13) is formed in the flow blocking atomizer (10). One end of the flow blocking atomization chamber (13) is communicated with the evaporation pipe (2) through the atomization nozzle (12), and the other end of the flow blocking atomization chamber (13) is communicated with the throttle ring (8).

2. The fuel nozzle according to claim 1, characterized in that: The atomization nozzles (12) are arranged in an equidistant array at one end of the flow blocking atomizer (10) close to the evaporation pipe (2).

3. The fuel nozzle according to claim 2, wherein: The manifold pipe (3) includes an oil passage sleeve (14), and an air passage sleeve (15) is sleeved outside the oil passage sleeve (14). An air inlet chamber (16) is formed between the air passage sleeve (15) and the oil passage sleeve (14). A plurality of ventilation holes (17) are arranged on the oil passage sleeve (14). The air inlet chamber (16) is communicated with the oil passage sleeve (14) through the ventilation holes (17). The oil passage sleeve (14) forms the oil passage, and the air passage is formed between the air passage sleeve (15) and the oil passage sleeve (14).

4. The fuel nozzle according to claim 3, characterized in that: The axial direction of the ventilation holes (17) is not parallel to the radial direction of the oil passage sleeve (14).

5. The fuel nozzle according to claim 4, characterized in that: The distance between one end of the ventilation hole (17) located at the outer edge of the oil passage sleeve (14) and the throttle ring (8) is less than the distance between one end of the ventilation hole (17) located at the inner edge of the oil passage sleeve (14) and the throttle ring (8).

6. The fuel nozzle according to claim 3, wherein: The air passage sleeve (15) is in the shape of a flared hole.

7. An engine, including the fuel nozzle according to any one of claims 1 to 6.

8. A helicopter, including the engine according to claim 7.

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