An oil supply device

Abstract

This application provides a fuel supply device belonging to the field of aero-engine technology. It includes an ignition nozzle, a general nozzle, a main fuel line manifold, and an auxiliary fuel line manifold. The auxiliary fuel line manifold has a semi-annular structure and connects to multiple auxiliary fuel line branches. The main fuel line manifold has a full-annular structure and connects to multiple main fuel line branches. The ignition nozzle is connected to both the auxiliary and main fuel line branches, and the general nozzle is connected to the main fuel line branches. The ignition nozzle has an internal ignition structure. Both the ignition nozzle and the general nozzle have main and auxiliary fuel lines. When the engine speed increases from the start-up state to low operating conditions, only the auxiliary fuel line manifold supplies fuel. As the engine speed increases, the auxiliary and main fuel line manifolds supply fuel simultaneously. The main fuel line equivalence ratio of the ignition nozzle and the general nozzle is equivalent, and the auxiliary fuel line equivalence ratio of the ignition nozzle and the general nozzle is equivalent. This application's solution improves fuel atomization quality under low operating conditions and widens the ignition and shutdown boundaries.

Description

Technical Field

[0001] This application relates to the field of aircraft engine technology, and in particular to a fuel supply device. Background Technology

[0002] With the increasing thrust of aero-engines, the requirements for combustion chamber fuel supply are constantly rising. Zoned fuel nozzles can effectively balance high fuel-air ratio combustion chamber ignition and low-temperature stability with high-efficiency, low-smoke combustion performance under high-temperature conditions. However, to further expand the low-temperature boundary, it is necessary to improve combustion stability by enhancing atomization quality under low-temperature conditions. Existing technologies often achieve higher fuel pressure by reducing the flow rate of secondary nozzles, but this method leads to a smaller secondary stage flow rate under high-temperature conditions, affecting combustion efficiency. Furthermore, currently, traditional electric nozzles are mostly located on the outer ring of the flame tube, primarily using single or dual-nozzle assembly schemes. The matching of the nozzle installation position with the flow field and fuel atomization field will further affect the combustion chamber ignition performance. Summary of the Invention

[0003] In view of this, the present application provides a fuel supply device to improve fuel atomization quality under low operating conditions, widen the main combustion chamber ignition point and quenching boundary, improve the quality of the full-ring flame, and at the same time ensure that the combustion chamber has high combustion efficiency, better combustion stability and more reasonable outlet temperature distribution under high operating conditions.

[0004] This application provides a fuel supply device, which includes an ignition nozzle, a general nozzle, a main fuel line, and a secondary fuel line. The secondary fuel line is configured as a semi-circular structure, and the main fuel line is configured as a full-circular structure. Multiple main fuel line branches are connected to the main fuel line, and multiple secondary fuel line branches are connected to the secondary fuel line. One side of the ignition nozzle is connected to the secondary fuel line branch, and the other side of the ignition nozzle is connected to the main fuel line branch. The general nozzle is connected to the main fuel line branch. The ignition nozzle has an ignition structure inside, and both the ignition nozzle and the general nozzle have a main fuel line and a secondary fuel line.

[0005] When the engine is upgraded from the self-starting state to a low operating condition, the low operating condition is when the relative equivalent speed of the engine high-pressure rotor is less than 60%, only the auxiliary oil circuit main pipe supplies oil, and the ignition nozzle is working; when the relative equivalent speed of the engine high-pressure rotor is greater than or equal to 60%, the auxiliary oil circuit main pipe and the main oil circuit main pipe supply oil simultaneously, the ignition nozzle and the general nozzle work simultaneously, the main oil circuit equivalent ratio of the ignition nozzle and the general nozzle is equivalent, and the auxiliary oil circuit equivalent ratio of the ignition nozzle and the general nozzle is equivalent.

[0006] According to a specific implementation of this application, the ignition nozzle is provided with a first-stage pre-filming swirler, and a first secondary-stage fuel passage is provided on the outside of the first-stage pre-filming swirler. The first secondary-stage fuel passage is connected to the secondary fuel circuit branch pipe through the secondary-stage fuel inlet of the ignition nozzle. A first oblique cut hole is provided circumferentially on the side of the first secondary-stage fuel passage near the first-stage pre-filming swirler. A first secondary-stage swirler is provided on the outside of the first secondary-stage fuel passage, and a first primary-stage fuel passage is provided on the outside of the first secondary-stage swirler. The first primary-stage fuel passage is connected to the main fuel circuit branch pipe through the main-stage fuel inlet of the ignition nozzle. A plurality of first fuel injection ports are circumferentially connected downstream of the first primary-stage fuel passage.

[0007] The first secondary fuel channel has a first annular electrode on its secondary fuel nozzle surface, and a second annular electrode is provided at the secondary swirl channel where the first secondary swirler is installed. The first annular electrode and the second annular electrode constitute the ignition structure.

[0008] According to a specific implementation of this application, a contraction-expansion structure is provided downstream of the primary cyclone channel where the first-stage pre-filming cyclone is installed. The contraction-expansion structure is located on the side wall of the primary cyclone channel, and the profile of the contraction-expansion structure first contracts and then expands along the gas flow direction.

[0009] According to a specific implementation of an embodiment of this application, the general nozzle is provided with a second main stage fuel passage and a second secondary stage fuel passage. A plurality of second fuel injection ports are circumferentially connected to the downstream of the second main stage fuel passage. The inlet of the second secondary stage fuel passage is connected to the second main stage fuel passage. The second main stage fuel passage is connected to the main fuel circuit branch pipe through the main stage fuel inlet of the general nozzle. The general nozzle is also provided with a second first-stage pre-filming swirler and a second second-stage swirler. The second first-stage pre-filming swirler is located inside the second secondary stage fuel passage, and the second second-stage swirler is located outside the second secondary stage fuel passage. The second secondary stage fuel passage is provided with a second oblique cut hole circumferentially on the side near the second first-stage pre-filming swirler.

[0010] According to a specific implementation of this application, the axial angle is the angle between the component of the axis of the first oblique cut hole on the normal plane at the position of the first oblique cut hole on the inner wall of the first-stage vortex channel and the inner wall of the first-stage vortex channel, and the circumferential angle is the angle between the component of the axis of the first oblique cut hole on the tangential plane at the position of the first oblique cut hole on the inner wall of the first-stage vortex channel and the normal plane at the position of the first oblique cut hole on the inner wall of the first-stage vortex channel.

[0011] According to one specific implementation of this application, the circumferential angle of the first oblique cut hole is opposite to the installation angle of the first primary pre-filming hydrocyclone.

[0012] According to a specific implementation of the embodiments of this application, the blade installation angle of the first secondary hydrocyclone is opposite to that of the first primary pre-filming hydrocyclone, and / or the blade installation angle of the second secondary hydrocyclone is opposite to that of the second primary pre-filming hydrocyclone.

[0013] According to a specific implementation of an embodiment of this application, the first oblique cut holes are uniformly arranged on the sidewall of the first secondary fuel passage, and / or the second oblique cut holes are uniformly arranged on the sidewall of the second secondary fuel passage.

[0014] According to a specific implementation of an embodiment of this application, the ignition nozzle and the auxiliary oil line main pipe are located on the same side, and both the ignition nozzle and the general nozzle are arranged in a semi-circular configuration.

[0015] According to one specific implementation of the embodiments of this application, the ignition nozzle and the general nozzle are arranged in an alternating manner.

[0016] Beneficial effects

[0017] The fuel supply device in this embodiment can achieve ignition and combustion assistance functions by setting an ignition structure inside the ignition nozzle. According to the actual working conditions of the main combustion chamber, the ignition nozzle can be eliminated on the flame tube, breaking through the limitations of traditional single / dual ignition nozzles and significantly widening the ignition and extinguishing boundaries. When using low operating conditions (the relative equivalent speed of the engine high-pressure rotor is <60%), only the ignition nozzle works, which increases the fuel flow and fuel supply pressure of a single nozzle and improves the fuel atomization quality. At the same time, it ensures that under high operating conditions, the equivalence ratio of the main fuel circuit and the auxiliary fuel circuit of the ignition nozzle and the general nozzle are respectively equivalent, so as to ensure that the combustion efficiency, combustion stability and outlet temperature field of the combustion chamber meet the design requirements. The reasonable arrangement of the ignition nozzle and the general nozzle can improve the quality of the full-ring flame. Attached Figure Description

[0018] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 This is an overall structural diagram of an oil supply device according to an embodiment of the present invention;

[0020] Figure 2This is a structural diagram of an ignition nozzle according to an embodiment of the present invention;

[0021] Figure 3 This is a structural diagram of a general nozzle according to an embodiment of the present invention.

[0022] In the diagram: 1. Ignition nozzle; 2. General nozzle; 3. Auxiliary fuel line main pipe; 4. Auxiliary fuel line branch pipe; 5. Main fuel line main pipe; 6. Main fuel line branch pipe; 7. Ignition nozzle secondary stage fuel inlet; 8. Ignition nozzle primary stage fuel inlet; 9. General nozzle primary stage fuel inlet; 10. First stage pre-filming cyclone; 11. First secondary stage fuel passage; 12. First oblique cut hole; 13. Primary stage cyclone passage; 14. Contraction-expansion structure; 15. First and second stage cyclones; 16. First annular electrode; 17. Second annular electrode; 18. First primary stage fuel passage; 19. First fuel injection port; 20. Second secondary stage fuel passage; 21. Second primary stage fuel passage; 22. Second oblique cut hole; 23. Second fuel injection port. Detailed Implementation

[0023] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0024] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0025] It should be noted that various aspects of embodiments within the scope of the appended claims are described below. It will be apparent that the aspects described herein can be embodied in a wide variety of forms, and any particular structure and / or function described herein is merely illustrative. Based on this application, those skilled in the art will understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects set forth herein can be used to implement the device and / or practice the method. Additionally, this device and / or method can be implemented using structures and / or functionalities other than one or more of the aspects set forth herein.

[0026] It should also be noted that the illustrations provided in the following embodiments are only schematic representations of the basic concept of this application. The drawings only show the components related to this application and are not drawn according to the actual number, shape and size of the components in the actual implementation. In the actual implementation, the form, quantity and proportion of each component can be arbitrarily changed, and the layout of the components may also be more complex.

[0027] Furthermore, specific details are provided in the following description to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the described aspects can be practiced without these specific details.

[0028] This application provides an oil supply device, which is described below with reference to... Figures 1 to 3 Provide a detailed description.

[0029] In one embodiment, refer to Figure 1 The device includes an ignition nozzle 1, a general nozzle 2, a main oil line 5, and a secondary oil line 3. The secondary oil line 3 is configured as a semi-circular structure, and the main oil line 5 is configured as a full-circular structure. Multiple main oil line branch pipes 6 are connected to the main oil line 5, and multiple secondary oil line branch pipes 4 are connected to the secondary oil line 3. One side of the ignition nozzle 1 is connected to the secondary oil line branch pipe 4, and the other side of the ignition nozzle 1 is connected to the main oil line branch pipe 6. The general nozzle 2 is connected to the main oil line branch pipe 6. The ignition nozzle 1 has an ignition structure inside. Both the ignition nozzle 1 and the general nozzle 2 have main oil lines and secondary oil lines.

[0030] When the engine is upgraded from the self-starting state to a low operating condition, the low operating condition is when the relative equivalent speed of the engine high-pressure rotor is less than 60%, only the auxiliary oil circuit main pipe 3 supplies oil, and the ignition nozzle 1 works; when the relative equivalent speed of the engine high-pressure rotor is greater than or equal to 60%, the auxiliary oil circuit main pipe 3 and the main oil circuit main pipe 5 supply oil simultaneously, the ignition nozzle 1 and the general nozzle 2 work simultaneously, the main oil circuit equivalent ratio of the ignition nozzle 1 and the general nozzle 2 is equivalent, and the auxiliary oil circuit equivalent ratio of the ignition nozzle 1 and the general nozzle 2 is equivalent.

[0031] In this embodiment, the fuel supply device achieves ignition and combustion assistance functions by setting an ignition structure inside the ignition nozzle 1. Based on the actual working conditions of the main combustion chamber, the ignition nozzle on the flame tube can be eliminated, breaking through the limitations of traditional single / dual ignition nozzles and significantly widening the ignition and extinguishing boundaries. Under low operating conditions (engine high-pressure rotor relative equivalent speed < 60%), only the ignition nozzle 1 operates, increasing the fuel flow rate and supply pressure of a single nozzle and improving fuel atomization quality. Simultaneously, under high operating conditions, the equivalence ratio of the main fuel circuit of the ignition nozzle 1 and the general nozzle 2 is equivalent in both the main and auxiliary fuel circuits, ensuring that the combustion efficiency, combustion stability, and outlet temperature field of the combustion chamber meet design requirements. The reasonable arrangement of the ignition nozzle 1 and the general nozzle 2 improves the quality of the full-ring flame. Furthermore, the structure in this embodiment eliminates the semi-ring auxiliary fuel circuit main pipe 3, which is beneficial for weight reduction.

[0032] In practical implementation, the ignition nozzle 1 is equipped with a secondary fuel inlet 7 and a primary fuel inlet 8, which are connected to the secondary fuel line branch pipe 4 and the primary fuel line branch pipe 6 respectively via connectors. The general nozzle 2 is equipped with a primary fuel inlet 9, which is connected to the primary fuel line branch pipe 6 via a connector. The arrangement of the two nozzles must match the main pipe structure and can be adjusted according to actual needs, such as staggered or semi-circular arrangement, to ensure that the flame connection effect meets the usage requirements.

[0033] In practice, for example, the ratio of ignition nozzle 1 to general nozzle 2 is 1:1. The actual number of ignition nozzle 1 and general nozzle 2 installed is usually determined by the engine's actual operating needs. When the engine speed increases from the starting state to a low operating condition (engine high-pressure rotor relative equivalent speed < 60%), only the auxiliary oil circuit main pipe 3 supplies oil, and the secondary stage of ignition nozzle 1 operates. As the engine speed increases, the main oil circuit main pipe 5 supplies oil, and the main and secondary stages of ignition nozzle 1 and general nozzle 2 operate simultaneously, completing a full-ring flame.

[0034] Reference Figure 2The ignition nozzle 1 is provided with a first-stage pre-filming swirler 10. A first-stage secondary fuel passage 11 is provided on the outside of the first-stage pre-filming swirler 10. The first-stage secondary fuel passage 11 is connected to the secondary fuel line branch pipe 4 through the secondary fuel inlet 7 of the ignition nozzle. A first oblique hole 12 is provided circumferentially on the side of the first-stage secondary fuel passage 11 near the first-stage pre-filming swirler 10. A first-stage secondary swirler 15 is provided on the outside of the first-stage secondary fuel passage 11. A first-stage primary fuel passage 18 is provided on the outside of the first-stage secondary swirler 15. The first-stage primary fuel passage 18 is connected to the primary fuel line branch pipe 6 through the primary fuel inlet 8 of the ignition nozzle. A plurality of circumferentially distributed first fuel injection ports 19 are connected circumferentially downstream of the first-stage primary fuel passage 18 to ensure fuel supply needs under heavy operating conditions. When the engine is under low operating conditions (the relative conversion speed of the high-pressure rotor is <60%), the secondary fuel flows out from the first oblique cut hole 12 at a certain angle. Under the action of the first-stage pre-filming swirling air, an oil film is formed on the inner wall of the first-stage swirling channel 13. The oil film is broken and atomized at the nozzle orifice under the shearing action of the first-stage pre-filming swirler 10 and the first and second-stage swirlers 15 to form an oil mist.

[0035] The first secondary fuel passage 11 has a first annular electrode 16 on its secondary fuel nozzle surface, and a second annular electrode 17 is provided at the secondary swirl channel where the first secondary swirler 15 is installed. The first annular electrode 16 and the second annular electrode 17 constitute the ignition structure. An electric arc is formed by the interaction of the first annular electrode 16 and the second annular electrode 17. The electric arc contacts and ignites the fuel mist downstream of the primary swirl channel 13, ensuring the single-nozzle ignition performance and realizing the ignition-assisted combustion function. Depending on the actual working conditions of the main combustion chamber, the ignition nozzle can be omitted from the flame tube.

[0036] In one embodiment, refer to Figure 2 A contraction-expansion structure 14 is provided downstream of the first-stage swirling channel 13, where the first-stage pre-filming swirling device 10 is installed. The contraction-expansion structure 14 is located on the sidewall of the first-stage swirling channel 13, and its profile first contracts and then expands along the gas flow direction. By providing the contraction-expansion structure 14, the film-forming path can be extended, the oil film thickness reduced, and fuel quality improved. The expansion section guides the fuel. The angle of the contraction section of the contraction-expansion structure 14 is slightly smaller than the axial angle of the first oblique cut hole 12, and the angle of the expansion section is smaller than the angle of the contraction section, thus guiding the fuel and ensuring that the fuel can contact the arc formed by the interaction of the first annular electrode 16 and the second annular electrode 17, achieving single-nozzle ignition.

[0037] Reference Figure 3The general nozzle 2 is provided with a second main stage fuel passage 21 and a second secondary stage fuel passage 20. A plurality of second fuel injection ports 23 are uniformly connected circumferentially downstream of the second main stage fuel passage 21. The inlet of the second secondary stage fuel passage 20 is connected to the second main stage fuel passage 21. The second main stage fuel passage 21 is connected to the main fuel line branch pipe 6 through the main stage fuel inlet 9 of the general nozzle. The general nozzle 2 is also provided with a second first-stage pre-filming swirler and a second second-stage swirler. The second first-stage pre-filming swirler is located inside the second secondary stage fuel passage 20, and the second second-stage swirler is located outside the second secondary stage fuel passage 20. The second secondary stage fuel passage 20 is provided with a second oblique cut hole 22 circumferentially on the side of the second secondary stage fuel passage 20 near the second first-stage pre-filming swirler.

[0038] In this embodiment, the secondary fuel inlet connector is omitted from the general nozzle 2, and the second secondary fuel passage 20 is connected to the second main fuel passage 21. When the main fuel line 5 supplies fuel, the secondary fuel is obtained by the main stage. The fuel distribution between the main stage and the secondary stage can be controlled by adjusting the angle and diameter of the second oblique hole 22 to ensure that the main fuel line equivalence ratio of the general nozzle 2 and the ignition nozzle 1 is equivalent, and the secondary fuel line equivalence ratio is equivalent, thereby ensuring that the engine has high combustion efficiency and reasonable temperature distribution under high operating conditions.

[0039] In practice, both the first primary fuel passage 18 and the second primary fuel passage 21 are configured as direct-injection primary fuel passages.

[0040] The first oblique cut hole 12 has an axial angle and a circumferential angle. The axial angle is the angle between the component of the axis of the first oblique cut hole 12 on the normal plane at the position of the first oblique cut hole 12 on the inner wall surface of the first-stage swirling channel 13 and the inner wall surface of the first-stage swirling channel 13. The circumferential angle is the angle between the component of the axis of the first oblique cut hole 12 on the tangential plane at the position of the first oblique cut hole 12 on the inner wall surface of the first-stage swirling channel 13 and the normal plane at the position of the first oblique cut hole 12 on the inner wall surface of the first-stage swirling channel 13. The circumferential angle of the first oblique cut hole 12 is opposite to the installation angle of the first-stage pre-filming swirler 10, which can reduce the fuel film thickness and improve the fuel film atomization quality.

[0041] In specific implementation, the second oblique cut hole 22 also has a circumferential angle and an axial angle. The circumferential angle of the second oblique cut hole 22 is opposite to the installation angle of the second-stage pre-filming cyclone, which can reduce the fuel film thickness and improve the fuel film atomization quality.

[0042] In one embodiment, the blade installation angle of the first secondary hydrocyclone 15 is opposite to that of the first primary pre-filming hydrocyclone 10, and / or the blade installation angle of the second secondary hydrocyclone is opposite to that of the second primary pre-filming hydrocyclone. By setting the installation angles of the two hydrocyclones to be opposite, it can be ensured that the oil film is broken and atomized at the nozzle mouth under the action of swirling shear.

[0043] In one embodiment, the first oblique holes 12 are uniformly arranged on the sidewall of the first secondary fuel passage 11, and / or the second oblique holes 22 are uniformly arranged on the sidewall of the second secondary fuel passage 20.

[0044] In one embodiment, the ignition nozzle 1 and the auxiliary oil line main pipe 3 are located on the same side, and both the ignition nozzle 1 and the general nozzle 2 are semi-circular.

[0045] In one embodiment, the ignition nozzle 1 and the general nozzle 2 are arranged in an alternating pattern.

[0046] The fuel supply device in this embodiment of the application supplies fuel in the following manner: When the engine speed increases from the starting state to a low operating state (the relative equivalent speed of the engine high-pressure rotor is <60%), only the auxiliary fuel line main pipe 3 supplies fuel, and the secondary stage of the ignition nozzle 1 operates. During ignition, the arc discharge ignites the atomized fuel in the secondary stage. As the engine speed increases, the main fuel line main pipe 5 supplies fuel, and the main and secondary stages of the ignition nozzle 1 and the general nozzle 2 operate simultaneously to complete a full-ring flame. The equivalence ratio of the main fuel line of the ignition nozzle 1 and the general nozzle 2 is equivalent, and the equivalence ratio of the auxiliary fuel line is also equivalent.

[0047] In the embodiments provided by this invention, the ignition process does not require the participation of the ignition nozzle. Fuel droplets, guided by the contraction-expansion structure 14, contact the arc generated by the first annular electrode 16 and the second annular electrode 17 inside the nozzle, completing single-nozzle ignition. Simultaneously, the rational arrangement of the ignition nozzle 1 and the general nozzle 2 helps improve the full-ring flame performance. When the engine transitions from the self-starting state to a low-load condition (engine high-pressure rotor relative conversion speed < 60%), only the auxiliary fuel line main pipe 3 supplies fuel. Fuel enters the first secondary fuel passage 11 from the auxiliary fuel line branch pipe 4, passes through the first oblique cut hole 12, and enters the first-stage swirling passage 13. Under the action of swirling air, an oil film forms on the inner wall of the passage, which is then broken up at the fuel nozzle nozzle orifice by the shearing action of the first and second-stage swirling air, forming an oil mist. When the engine is in ignition mode, only the secondary stage of the ignition nozzle 1 supplies fuel. By reducing the number of working nozzles, the single-nozzle fuel flow rate is increased, thereby increasing the fuel supply pressure, improving fuel atomization quality, and widening the ignition boundary. When the engine is nearing shutdown, the fuel supply flow is low, with only the secondary stage of ignition nozzle 1 supplying fuel. This increases the fuel supply flow of a single nozzle, significantly enhancing combustion stability and widening the flameout boundary. When the engine is operating under high-pressure conditions, the main fuel line 5 and the secondary fuel line 3 supply fuel simultaneously, and all nozzles are operational. The general nozzle 2 adjusts the fuel distribution between the main and secondary stages through oblique cuts, ensuring that its equivalence ratio with the main and secondary fuel lines of ignition nozzle 1 is equal, thus ensuring efficient combustion and a reasonable outlet temperature distribution. Through these measures, this device improves the single-nozzle ignition performance, widens the ignition and flameout boundaries of the combustion chamber, and guarantees combustion efficiency and temperature distribution under high-pressure conditions.

[0048] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An oil supply device, characterized in that, The device includes an ignition nozzle (1), a general nozzle (2), a main oil line main pipe (5), and a secondary oil line main pipe (3). The secondary oil line main pipe (3) is configured as a semi-circular structure, and the main oil line main pipe (5) is configured as a full-circular structure. Multiple main oil line branch pipes (6) are connected to the main oil line main pipe (5), and multiple secondary oil line branch pipes (4) are connected to the secondary oil line main pipe (3). One side of the ignition nozzle (1) is connected to the secondary oil line branch pipe (4), and the other side of the ignition nozzle (1) is connected to the main oil line branch pipe (6). The general nozzle (2) is connected to the main oil line branch pipe (6). The ignition nozzle (1) is provided with an ignition structure inside. Both the ignition nozzle (1) and the general nozzle (2) are provided with a main oil line and a secondary oil line. When the engine is in a self-starting state and the operating condition is increased to a low operating condition, the low operating condition is when the relative equivalent speed of the engine high-pressure rotor is less than 60%, only the auxiliary oil circuit main pipe (3) supplies oil, and the ignition nozzle (1) works; when the relative equivalent speed of the engine high-pressure rotor is greater than or equal to 60%, the auxiliary oil circuit main pipe (3) and the main oil circuit main pipe (5) supply oil at the same time, the ignition nozzle (1) and the general nozzle (2) work at the same time, the main oil circuit equivalent ratio of the ignition nozzle (1) and the general nozzle (2) is equivalent, and the auxiliary oil circuit equivalent ratio of the ignition nozzle (1) and the general nozzle (2) is equivalent. The ignition nozzle (1) is provided with a first-stage pre-filming swirler (10), and a first secondary fuel passage (11) is provided on the outside of the first-stage pre-filming swirler (10). The first secondary fuel passage (11) is connected to the secondary fuel line branch pipe (4) through the secondary fuel inlet (7) of the ignition nozzle. The first secondary fuel passage (11) is provided with a first oblique hole (12) on the circumferential side near the first-stage pre-filming swirler (10). A first secondary swirler (15) is provided on the outside of the first secondary fuel passage (11). A first primary fuel passage (18) is provided on the outside of the first secondary swirler (15). The first primary fuel passage (18) is connected to the main fuel line branch pipe (6) through the main fuel inlet (8) of the ignition nozzle. A plurality of first fuel injection ports (19) are connected circumferentially downstream of the first primary fuel passage (18). The first secondary fuel passage (11) has a first annular electrode (16) on its secondary fuel nozzle surface, and a second annular electrode (17) is provided at the secondary swirl passage where the first secondary swirler (15) is installed. The first annular electrode (16) and the second annular electrode (17) constitute the ignition structure. The general nozzle (2) is provided with a second primary fuel passage (21) and a second secondary fuel passage (20). The downstream of the second primary fuel passage (21) is connected to a plurality of second fuel injection ports (23). The inlet of the second secondary fuel passage (20) is connected to the second primary fuel passage (21). The second primary fuel passage (21) is connected to the main fuel line branch pipe (6) through the primary fuel inlet (9) of the general nozzle. The general nozzle (2) is also provided with a second primary pre-filming swirler and a second secondary swirler. The second primary pre-filming swirler is located inside the second secondary fuel passage (20), and the second secondary swirler is located outside the second secondary fuel passage (20). The second secondary fuel passage (20) is provided with a second oblique cut hole (22) on the side of the second secondary fuel passage (20) near the second primary pre-filming swirler.

2. The oil supply device according to claim 1, characterized in that, Downstream of the first-stage swirling channel (13) where the first-stage pre-filming swirling device (10) is installed, a contraction-expansion structure (14) is provided. The contraction-expansion structure (14) is located on the side wall of the first-stage swirling channel (13). The profile of the contraction-expansion structure (14) first contracts and then expands along the gas flow direction.

3. The oil supply device according to claim 2, characterized in that, The first oblique cut hole (12) has an axial angle and a circumferential angle. The axial angle is the angle between the component of the axis of the first oblique cut hole (12) on the normal plane at the position of the first oblique cut hole (12) on the inner wall surface of the first-stage vortex channel (13) and the inner wall surface of the first-stage vortex channel (13). The circumferential angle is the angle between the component of the axis of the first oblique cut hole (12) on the tangential plane at the position of the first oblique cut hole (12) on the inner wall surface of the first-stage vortex channel (13) and the normal plane at the position of the first oblique cut hole (12) on the inner wall surface of the first-stage vortex channel (13).

4. The oil supply device according to claim 3, characterized in that, The circumferential angle of the first oblique cut hole (12) is opposite to the installation angle of the first primary pre-filming hydrocyclone (10).

5. The oil supply device according to claim 1, characterized in that, The blade installation angle of the first secondary hydrocyclone (15) is opposite to that of the first primary pre-film hydrocyclone (10), and / or the blade installation angle of the second secondary hydrocyclone is opposite to that of the second primary pre-film hydrocyclone.

6. The oil supply device according to claim 1, characterized in that, The first oblique cut hole (12) is uniformly arranged on the side wall of the first secondary fuel passage (11), and / or the second oblique cut hole (22) is uniformly arranged on the side wall of the second secondary fuel passage (20).

7. The oil supply device according to claim 1, characterized in that, The ignition nozzle (1) and the auxiliary oil line main pipe (3) are located on the same side, and both the ignition nozzle (1) and the general nozzle (2) are semi-circular.

8. The oil supply device according to claim 1, characterized in that, The ignition nozzle (1) and the general nozzle (2) are arranged in an alternating manner.

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