A fuel nozzle structure with high reliability for high-altitude ignition in aviation

Abstract

The present invention belongs to the field of aircraft engine technology and discloses a fuel nozzle structure for aviation with high high-altitude ignition reliability. The structure comprises a nozzle body, an adapter, an atomizer, a swirler, a nozzle nut, a fuel take-off nozzle, and a hot air take-off nozzle. The nozzle body has two independent fuel channels and a hot air channel, each connecting the fuel take-off nozzle and the hot air take-off nozzle, respectively. The other end of the fuel channel is connected to the adapter. The fuel enters the adapter from axial flow and is then converted into radial flow within the adapter. The outlet of the adapter is connected to the inlet of the atomizer. After entering the atomizer, the fuel is atomized and enters an annular cavity. After being rectified by the swirler, the hot air generates a tangential velocity opposite to the rotation direction of the oil mist in the annular cavity and enters the annular cavity to mix with the oil mist. The present invention controls the addition of a stream of hot air to heat the fuel through a one-way valve structure, thereby reducing the surface tension and viscosity of the fuel, reducing the fuel surface density (SMD), and improving the quality of the fuel atomization. The invention can also adjust the oil-to-air ratio at the nozzle outlet, increase the oxygen content, and improve combustion efficiency.

Description

Technical Field

[0001] The invention belongs to the technical field of aviation engines and relates to a fuel nozzle structure, in particular to an aviation fuel nozzle structure with high high-altitude ignition reliability. Background Art

[0002] As a key component of aircraft engines, the fuel nozzle atomizes liquid fuel. Atomization increases the contact area between the fuel and air, improving the heat and mass exchange rate during combustion, accelerating the combustion process, and ensuring combustion performance. Depending on their structure, fuel nozzles can be categorized as direct-injection, centrifugal, evaporation tube, and pneumatic atomizing nozzles. The fuel nozzles described in this invention are centrifugal.

[0003] High-altitude ignition tests are a key measure of aircraft engine design reliability. At high altitudes, the air is thin and oxygen-poor. Furthermore, the surface tension and viscosity of fuel are both high at low temperatures. High surface tension strengthens the cohesion of fuel molecules, making them less likely to break apart. High viscosity increases internal friction and thickens the oil film. Both factors increase the fuel's Sauter Mean Diameter (SMD) and deteriorate atomization quality. Summary of the Invention

[0004] In order to ensure the high-altitude ignition reliability of aircraft engines, the present invention provides a fuel nozzle structure with high high-altitude ignition reliability for aviation based on a centrifugal nozzle structure, which can effectively improve the success rate of engine high-altitude ignition and increase ignition reliability.

[0005] The technical solutions of the present invention are as follows:

[0006] A fuel nozzle structure with high reliability for high-altitude ignition in aviation includes a nozzle body, an adapter, a sprayer, a swirler, a nozzle nut, a fuel take-off nozzle, and a hot air take-off nozzle. The nozzle body forms a rectifying cavity with one end connected to the adapter and the sprayer and the other end connected to the fuel take-off nozzle and the hot air take-off nozzle. The nozzle nut is assembled to the nozzle body by threads and fixes the adapter, the sprayer, and the swirler. The nozzle body has two independent fuel channels and hot air channels, which are respectively connected to the fuel take-off nozzle and the hot air take-off nozzle. The other end of the fuel channel is connected to the adapter. After entering the adapter from axial flow, the fuel is converted into radial flow within the adapter. The outlet of the adapter is connected to the inlet of the sprayer. After entering the sprayer, the fuel is atomized and enters an annular cavity. The side wall of the annular cavity is the inner wall of the swirler, and the rear end of the annular cavity is the outlet of the sprayer. The other end of the hot air channel is connected to the outside of the swirler. After being rectified by the swirler, the hot air generates a tangential velocity opposite to the rotation direction of the oil mist in the annular cavity and enters the annular cavity to mix with the oil mist. The outlet of the annular cavity is connected to the fuel injection port of the fuel nozzle structure.

[0007] Furthermore, the fuel passage and the hot air passage are separated by a short distance, so that the fuel is preheated by heat conduction through the hot air passage when flowing in the fuel passage.

[0008] Furthermore, it also includes a one-way valve, which is arranged in the hot air intake nozzle. When the hot air intake enters the hot air intake nozzle and the hot air pressure is greater than the internal pressure of the flame tube, the one-way valve is in an open state; when no gas flows into the hot air end, the internal pressure of the flame tube is greater than the pressure in the hot air channel, and the one-way valve is closed to ensure the sealing of the engine.

[0009] Furthermore, a tangential groove is provided at the inlet of the sprayer to ensure that the fuel produces an eccentric effect on the nozzle axis after entering the spray chamber inside the sprayer, generating a kinetic moment about the axis; the diameter of the spray chamber continues to decrease, and the tangential flow velocity of the fuel continues to increase, ensuring fuel atomization.

[0010] Furthermore, the nozzle nut includes a nozzle nut seat and a nozzle nut sleeve. The nozzle nut seat is connected to the nozzle body through an internal thread. The nozzle nut sleeve is a one-way cylindrical structure with an end face and is axially connected to the nozzle nut seat. There is a brazing seam between the nozzle nut seat and the nozzle nut sleeve.

[0011] Furthermore, a side wall hole is opened on the side wall of the nozzle nut sleeve; after the external air flow flows in from the side wall hole, a part of it flows out from the end hole opened on the end face of the nozzle nut sleeve, and after flowing out, it is in the same direction as the spray direction, and the other part is converted into radial flow from the internal flow channel of the nozzle nut sleeve, and after encountering the fuel spray, it is deflected to flow along the spray direction.

[0012] Furthermore, the hot air passes through the hot air channel into the large annular cavity with a large space formed by the middle section of the nozzle body and the rear section of the nozzle nut, then enters the small annular cavity with a narrow and long space formed by the front end side of the nozzle body and the inner wall of the nozzle nut, then enters the radial annular cavity formed by the front end of the nozzle body, the inner side of the nozzle nut and the outer side of the swirler, and finally enters the swirler and then enters the annular cavity.

[0013] Furthermore, the large annular cavity is a pressure-equalizing cavity, and the hot air flows evenly from the large annular cavity into the small annular cavity. The inner cavity of the nozzle nut is designed as a stepped contraction structure, and the airflow velocity is improved in the small annular cavity, thereby increasing the fluid-solid heat exchange effect and heating the nozzle body. The hot air completes the flow direction conversion of the airflow in the radial annular cavity, and the hot air flow changes from axial flow to radial flow. After the hot air flows from the tangential swirl groove of the swirler into the annular cavity composed of the swirler and the sprayer, it obtains a tangential velocity exactly opposite to the fuel rotation direction.

[0014] Compared with the prior art, the advantages of the present invention are:

[0015] In a high-altitude environment, the present invention controls the addition of a stream of hot air to heat the fuel through a one-way valve structure, thereby reducing the surface tension and viscosity of the fuel, reducing the SMD of the fuel, and improving the quality of fuel atomization. At the same time, by adjusting the amount of hot air, the oil-to-air ratio at the nozzle outlet is adjusted, the oxygen content is increased, the chemical reaction speed is accelerated, and the combustion efficiency is improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following is a brief introduction to the drawings required for use in the embodiments. It should be understood that the following drawings only show certain embodiments of the present invention and should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without creative work.

[0017] Figure 1 Schematic diagram of the structure of an embodiment of the present invention;

[0018] Figure 2 A cross-sectional view of the structure of an embodiment of the present invention;

[0019] Figure 3 A cross-sectional view of the structure of an embodiment of the present invention;

[0020] Figure 4 Schematic diagram of the structure of the nozzle body;

[0021] Figure 5 Schematic diagram of the structure of the nozzle nut;

[0022] Figure 6 Schematic diagram of the structure of the adapter;

[0023] Figure 7 Schematic diagram of the structure of the sprayer;

[0024] Figure 8 Schematic diagram of the structure of the cyclone;

[0025] Figure 9 Schematic diagram of the structure of the oil filter;

[0026] Figure 10 It is a structural diagram of a one-way valve;

[0027] Figure 11 It is a schematic diagram of the structure of the lock ring;

[0028] In the figure, 1 is the nozzle body, 2 is the nozzle nut, 3 is the adapter, 4 is the sprayer, 5 is the cyclone, 6 is the gasket, 7 is the oil filter, 8 is the fuel nozzle, 9 is the gasket, 10 is the first retaining ring, 11 is the hot air nozzle, 12 is the one-way valve, 13 is the positioning ring, 14 is the second retaining ring, and 15 is the locking ring.

[0029] 101—large annular cavity, 102—small annular cavity, 103—radial annular cavity, 104—annular cavity;

[0030] 21 - air inlet chamber, 22 - oil inlet chamber, 23 - atomization chamber, 24 - hot air channel, 25 - fuel channel, 26 - screw plug, 27 - first circumferential weld, 28 - plug, 29 - second circumferential weld;

[0031] 31—nozzle nut seat, 32—nozzle nut sleeve, 33—brazed seam, 34—side wall hole, 35—end hole, 36—internal flow channel. DETAILED DESCRIPTION

[0032] This section is an embodiment of the present invention, which is used to explain and illustrate the technical solution of the present invention. In the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other.

[0033] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate directions or positional relationships for the purposes of the accompanying drawings, and are intended only to facilitate the description of the present invention and simplify the description, rather than to indicate or imply that the device or case referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention. In addition, the terms "first", "second" and the like are used for descriptive purposes only, and should not be understood as indicating or implying relative importance or implying the number of technical features indicated. Thus, features defined as "first", "second" and the like may explicitly or implicitly include more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0034] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be interpreted broadly. For example, they may refer to fixed, detachable, or integrated connections; mechanical or point connections; direct or indirect connections through an intermediary; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0035] A fuel nozzle structure with high reliability for high-altitude ignition in aviation, comprising a nozzle body 1, an adapter 3, an atomizer 4, a swirler 5, a nozzle nut 2, a fuel take-over nozzle 8, and a hot air take-over nozzle 11. The nozzle body 1 forms a rectifying cavity with one end connected to the adapter 3 and the atomizer 4 and the other end connected to the fuel take-over nozzle 8 and the hot air take-over nozzle 11. The nozzle nut 2 is assembled with the nozzle body 1 through threads and fixes the adapter 3, the atomizer 4, and the swirler 5. The nozzle body 1 has two independent fuel channels and hot air channels, which are connected to the fuel take-over nozzle 8 and the hot air take-over nozzle 11 respectively. The fuel channel is also connected to the nozzle body 1. One end is connected to the adapter 3. After the fuel enters the adapter 3 from axial flow, it is converted into radial flow inside the adapter 3. The outlet of the adapter 3 is connected to the inlet of the sprayer 4. After entering the sprayer 4, the fuel is atomized and enters the annular cavity 104. The side wall of the annular cavity 104 is the inner wall of the swirler 5, and the rear end of the annular cavity 104 is the outlet of the sprayer 4. The other end of the hot air channel is connected to the outside of the swirler 5. After being rectified by the swirler 5, the hot air generates a tangential velocity opposite to the rotation direction of the oil mist in the annular cavity 104 and enters the annular cavity 104 to mix with the oil mist. The outlet of the annular cavity 104 is connected to the fuel injection port of the fuel nozzle structure.

[0036] The fuel passage and the hot air passage are separated by a short distance, so that the fuel is preheated by heat conduction in the hot air passage when flowing in the fuel passage.

[0037] It also includes a one-way valve 12, which is arranged in the hot air intake nozzle 11. When the hot air intake enters the hot air intake nozzle 11 and the hot air pressure is greater than the internal pressure of the flame tube, the one-way valve 12 is in an open state; when no gas flows into the hot air end, the internal pressure of the flame tube is greater than the pressure in the hot air channel, and the one-way valve 12 is closed to ensure the sealing of the engine.

[0038] A tangential groove is provided at the inlet of the sprayer 4 to ensure that the fuel has an eccentric effect on the nozzle axis after entering the spray chamber inside the sprayer 4, generating a kinetic moment about the axis; the diameter of the spray chamber is continuously reduced, and the tangential flow velocity of the fuel is continuously increased to ensure fuel atomization.

[0039] The nozzle nut 2 includes a nozzle nut seat 31 and a nozzle nut sleeve 32. The nozzle nut seat 31 is connected to the nozzle body 1 through an internal thread. The nozzle nut sleeve 32 is a one-way cylindrical structure with an end face and is axially connected to the nozzle nut seat 31. There is a brazing seam 33 between the nozzle nut seat 31 and the nozzle nut sleeve 32.

[0040] A side wall hole 34 is opened on the side wall of the nozzle nut sleeve 32; after the external air flow flows in from the side wall hole 34, a part of it flows out from the end hole 35 opened on the end face of the nozzle nut sleeve 32, and flows in the same direction as the spray after flowing out, and the other part turns into radial flow from the internal flow channel 36 of the nozzle nut sleeve 32, and after encountering the fuel spray, it is deflected to flow along the spray direction.

[0041] After the hot air passes through the hot air channel and enters the large annular cavity 101 formed by the middle section of the nozzle body 1 and the rear section of the nozzle nut 2, it enters the small annular cavity 102, a narrow and long space formed by the front end side of the nozzle body 1 and the inner wall of the nozzle nut 2, and then enters the radial annular cavity 103 formed by the front end of the nozzle body 1, the inner side of the nozzle nut 2 and the outer side of the swirler 5, and finally enters the swirler 5 and then enters the annular cavity 104.

[0042] The large annular cavity 101 is a pressure-equalizing cavity, and hot air flows evenly from the large annular cavity 101 into the small annular cavity 102. The inner cavity of the nozzle nut is designed with a stepped contraction structure, which increases the airflow velocity in the small annular cavity, enhances the fluid-solid heat exchange effect, and heats the nozzle body; the hot air completes the flow direction conversion of the airflow in the radial annular cavity 103, and the hot air flow changes from axial flow to radial flow; after the hot air flows from the tangential swirl groove of the swirler 5 into the annular cavity 104 formed by the swirler 5 and the sprayer 4, it obtains a tangential velocity exactly opposite to the swirl direction of the fuel.

[0043] The following is another embodiment of the present invention.

[0044] A fuel nozzle structure with high reliability of high-altitude ignition for aviation, such as Figures 1-9 As shown, it includes a nozzle body 1, a nozzle nut 2, an adapter 3, a sprayer 4, a swirler 5, a gasket 6, an oil filter 7, a fuel pipe nozzle 8, a gasket 9, a retaining ring 10, a hot air pipe nozzle 11, a one-way valve 12, a positioning ring 13, and a retaining ring 14.

[0045] The nozzle body 1 is machined from a structural steel forging and features a flow chamber 23 for mounting the adapter 3, atomizer 4, and gasket 6; an inlet chamber 21 for connecting the fuel supply nozzle and the hot air intake nozzle; and a fuel channel 25 and a hot air channel 24 of equal diameter for transporting fuel and hot air, respectively. After the internal piping is machined, the near-wall surface of the nozzle body 1 must be sealed. A screw plug 26 is assembled to the upper pipe of the nozzle body 1 and welded with argon arc welding for one cycle, forming a first circumferential weld 27. A plug 28 is assembled to the lower pipe of the nozzle body 1 and welded with argon arc welding for one cycle, forming a second circumferential weld 29.

[0046] The nozzle nut 2 is used to secure the adapter 3, sprayer 4, and swirler 5. The nozzle nut 2 is formed by vacuum brazing a nozzle nut swivel 31 and a nozzle nut sleeve 32, forming a brazed seam 33. Both are made of high-temperature alloy rods. The nozzle nut sleeve 32 has a hole in its sidewall, allowing airflow to flow in through the sidewall hole 34. A portion of the airflow exits through the nut's end hole 35, essentially in the same direction as the spray. The remaining portion of the airflow exits through the nut's internal flow channel 36, initially flowing radially before being redirected in the direction of the spray upon encountering the fuel spray.

[0047] The gaskets 6 and 9 are made of soft metal and are properly deformed during assembly to ensure sealing.

[0048] After the one-way valve 12 and the positioning ring 13 are processed, the matching surfaces are subjected to coloring inspection to ensure the smoothness of the matching surfaces and the effective sealing of the nozzle.

[0049] After the locking ring 15 is unfolded, Figure 11 As shown, during assembly, the lock ring is bent into a circle, the first surface 41 is bent outward to fit closely against the side wall of the nozzle nut, and the second surface 42 is bent inward to the groove of the nozzle body, as shown in FIG. Figure 3 Finally, ensure that the threads of the nozzle nut 2 and the nozzle body 1 are completely locked after assembly to prevent the threads from loosening after the engine is running.

[0050] After the fuel nozzle is assembled, the large annular cavity 101 formed by the nozzle body and the nozzle nut, the small annular cavity 102, the radial annular cavity 103, and the annular cavity 104 composed of the swirler, the sprayer, and the nozzle nut are naturally formed through which the hot air flows.

[0051] The design principle of the present invention is:

[0052] The present invention designs a fuel nozzle structure with high reliability for high-altitude ignition for aviation. A hot air flow path is provided inside the nozzle body so that the fuel is preheated when flowing in the pipeline. Secondly, the hot air at the fuel outlet plays two roles on the fuel. First, it ensures that the oil film continues to thin through shear force after encountering the fuel. Second, the increase in temperature causes the surface tension and viscosity of the fuel to decrease, further accelerating the fuel breakage. A one-way valve is provided at the hot air intake nozzle. When the hot air is connected, the valve is in the open state. After the hot air is closed, the one-way valve is closed to ensure the sealing of the nozzle. An oil filter is provided at the fuel inlet nozzle to ensure the cleanliness of the fuel and avoid problems such as uneven temperature distribution in the combustion chamber and substandard engine performance due to oil line blockage. The nozzle and the nozzle body are connected by threads, and a gasket made of soft metal is assembled between the two to ensure sealing. The nozzle nut is connected to the nozzle body by threads and is positioned using a locking plate.

[0053] The working process of the present invention is as follows:

[0054] When the engine is working, the fuel enters the fuel take-over nozzle from the fuel supply pipe and first passes through the oil filter to filter out excess matter, flows through the fuel pipeline inside the nozzle body, flows to the adapter, and then flows into the spray chamber through the tangential groove of the sprayer and is ejected from the nozzle; hot air enters the hot air take-over nozzle from the air supply pipe, flows through the one-way valve and the hot air pipeline inside the nozzle body, and after flowing out of the pipeline, flows into the large annular cavity, small annular cavity and axial annular cavity formed by the nozzle body and the nozzle nut in sequence, flows through the swirl hole of the swirler to obtain a tangential velocity opposite to that of the fuel spray, and forms an air film after the annular cavity formed by the swirler, sprayer and nozzle nut is fully accelerated, and finally mixes with the fuel at the nozzle and exchanges heat.

[0055] After exiting the nozzle body's internal duct, the hot air undergoes five stages: first, it flows through the large annular cavity formed by the nozzle body and nozzle nut, forming a pressure-equalizing cavity. It then flows evenly into the small annular cavity formed by the nozzle nut and nozzle body. The nozzle nut's internal cavity is designed with a stepped contraction structure, increasing the airflow velocity within the small annular cavity, enhancing fluid-solid heat exchange and heating the nozzle body. At the same time, the small-area flow channel effectively filters excess matter. Next, the airflow direction is converted from axial to radial in the radial annular cavity formed by the nozzle nut and nozzle body. After flowing from the tangential swirl groove of the swirler into the annular cavity formed by the swirler and atomizer, the hot air acquires a tangential velocity that is exactly opposite to the swirl direction of the fuel, ensuring that the hot air subsequently shears and mixes with the fuel, maximizing heat exchange and enhancing atomization. Finally, the hot air flows through the annular cavity formed by the swirler, atomizer, and nozzle nut, where it intersects and mixes with the fuel flowing out of the swirler. The nozzle nut has a larger inner diameter than the swirler, causing the annular cavity area to contract in the middle, ensuring that the hot air ultimately flows out as a high-speed air film.

[0056] The present invention increases the hot air flow path on the nozzle body through the one-way valve control, ensuring that when the engine is ignited in a high-altitude, low-temperature and oxygen-deficient state, the fuel SMD is effectively reduced, the atomization quality is higher, and the oil-gas ratio is close to the chemically appropriate oil-gas ratio, thereby effectively improving the engine reliability.

Claims

1. A fuel nozzle structure with high reliability for high-altitude ignition for aviation, characterized in that: The nozzle body (1) comprises a nozzle body (1), an adapter (3), an atomizer (4), a swirler (5), a nozzle nut (2), a fuel take-over nozzle (8) and a hot air take-over nozzle (11). The nozzle body (1) forms a rectifying cavity with one end connected to the adapter (3) and the atomizer (4) and the other end connected to the fuel take-over nozzle (8) and the hot air take-over nozzle (11). The nozzle nut (2) is assembled with the nozzle body (1) through a thread and fixes the adapter (3), the atomizer (4) and the swirler (5). The nozzle body (1) has two independent fuel channels and hot air channels, which are connected to the fuel take-over nozzle (8) and the hot air take-over nozzle (11) respectively. The other end of the fuel channel is connected to the adapter (3). The adapter (3) is a device for distributing fuel oil to the fuel oil. The fuel oil flows into the adapter (3) from an axial direction and is converted into a radial flow in the adapter (3). The outlet of the adapter (3) is connected to the inlet of the sprayer (4). The fuel oil enters the sprayer (4) and is atomized and enters the annular cavity (104). The side wall of the annular cavity (104) is the inner wall of the cyclone (5). The rear end of the annular cavity (104) is the outlet of the sprayer (4). The other end of the hot air channel is connected to the outside of the cyclone (5). After being rectified by the cyclone (5), the hot air generates a tangential velocity opposite to the rotation direction of the oil mist in the annular cavity (104) and enters the annular cavity (104) to mix with the oil mist. The outlet of the annular cavity (104) is connected to the fuel injection port of the fuel nozzle structure. The fuel channel and the hot air channel are separated by a short distance, so that the fuel is preheated by heat conduction through the hot air channel when flowing in the fuel channel; The hot air passes through the hot air passage and enters the large annular cavity (101) which is a large space formed by the middle section of the nozzle body (1) and the rear section of the nozzle nut (2), then enters the small annular cavity (102) which is a narrow and long space formed by the front side of the nozzle body (1) and the inner wall of the nozzle nut (2), then enters the radial annular cavity (103) formed by the front end of the nozzle body (1), the inner side of the nozzle nut (2) and the outer side of the cyclone (5), finally enters the cyclone (5), and then enters the annular cavity (104); The large annular cavity (101) is a pressure-equalizing cavity, and hot air flows evenly from the large annular cavity (101) into the small annular cavity (102). The inner cavity of the nozzle nut is designed as a stepped contraction structure, and the airflow velocity is increased in the small annular cavity, thereby increasing the fluid-solid heat exchange effect and heating the nozzle body; the hot air completes the flow direction conversion of the airflow in the radial annular cavity (103), and the hot air flow changes from axial flow to radial flow; after the hot air flows from the tangential swirl groove of the swirler (5) into the annular cavity (104) composed of the swirler (5) and the sprayer (4), it obtains a tangential velocity that is exactly opposite to the swirl direction of the fuel.

2. The fuel nozzle structure with high reliability of high-altitude ignition for aviation according to claim 1, characterized in that: The invention also includes a one-way valve (12), which is arranged in the hot air intake nozzle (11). After the hot air intake enters the hot air intake nozzle (11), and the hot air pressure is greater than the pressure inside the flame tube, the one-way valve (12) is in an open state; when no gas flows into the hot air end, the pressure inside the flame tube is greater than the pressure in the hot air channel, and the one-way valve (12) is closed to ensure the sealing of the engine.

3. The fuel nozzle structure with high reliability of high-altitude ignition for aviation according to claim 1, characterized in that: The sprayer (4) is provided with a tangential groove at the inlet to ensure that the fuel produces an eccentric effect on the nozzle axis after entering the spray chamber in the sprayer (4), thereby generating a kinetic moment about the axis; the diameter of the spray chamber is continuously reduced, and the tangential flow velocity of the fuel is continuously increased, thereby ensuring the atomization of the fuel.

4. The fuel nozzle structure with high reliability of high-altitude ignition for aviation according to claim 1, characterized in that: The nozzle nut (2) includes a nozzle nut seat (31) and a nozzle nut sleeve (32). The nozzle nut seat (31) is connected to the nozzle body (1) via an internal thread. The nozzle nut sleeve (32) is a one-way cylindrical structure with an end face and is axially connected to the nozzle nut seat (31). A brazing seam (33) is provided between the nozzle nut seat (31) and the nozzle nut sleeve (32).

5. The fuel nozzle structure with high reliability of high-altitude ignition for aviation according to claim 4, characterized in that: A side wall hole (34) is formed on the side wall of the nozzle nut sleeve (32); after the external air flow flows in from the side wall hole (34), a portion of the air flow flows out from the end hole (35) formed on the end face of the nozzle nut sleeve (32), and flows in the same direction as the spray direction after the air flow flows out; the other portion of the air flow turns into a radial flow in the internal flow channel (36) of the nozzle nut sleeve (32), and is deflected to flow in the spray direction after encountering the fuel spray.

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