Nozzle rotational flow assembly, combustion chamber structure and aero-engine

Abstract

The invention relates to the technical field of aircrafts, and discloses a nozzle rotational flow assembly, a combustion chamber structure and an aero-engine. The nozzle rotational flow assembly comprises a spray pipe and a rotational flow piece. A first through hole and a second through hole are formed between a spray pipe and a rotational flow piece and communicate with a first rotational flow channel and a diffusion cavity correspondingly, the first rotational flow channel achieves premixing of fuel gas and combustion-supporting gas, so that uniform and stable premixed combustion flames are formed in the peripheral area of a combustion cavity, the combustion efficiency is improved, and ignition delay is reduced; fuel gas is introduced into the diffusion cavity through the second through hole, and the fuel gas and combustion-supporting gas entering from the second rotational flow channel are combusted at the position close to the central axis of the combustion cavity. Through the design of the first through holes, the local high temperature of the flame core area is reduced, the generation amount of nitric oxide is reduced from the source, and the environmental protection performance of the hydrogen fuel combustion system is improved. The decoupling design of the premixing channel and the diffusion channel is realized through simple through hole layout, and the manufacturing difficulty and cost are reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a nozzle swirl component, a combustion chamber structure and an aircraft engine. Background Art

[0002] With the global aviation industry's growing demand for green, low-carbon power systems, hydrogen fuel, with its primary combustion product being water and near-zero carbon emissions, is becoming a key fuel option for next-generation aircraft engines. However, hydrogen fuel exhibits significant differences in combustion characteristics from traditional jet fuel, particularly in terms of combustion propagation speed. The propagation speed of a hydrogen fuel flame is approximately 10 times that of jet fuel, posing a series of technical challenges in organizing combustion.

[0003] To mitigate flashback and combustion chamber head erosion caused by the high flame propagation velocity of hydrogen fuel, existing technologies typically employ a higher hydrogen fuel injection velocity coupled with a diffusion combustion mode. This improves flame stability and reduces the risk of flashback caused by turbulent combustion. Diffusion combustion also helps reduce the occurrence of oscillating combustion, thereby improving the reliability and durability of the combustion system.

[0004] However, diffusion combustion suffers from insufficient mixing of hydrogen fuel and air, particularly in the main combustion zone, which can easily form localized high-temperature hotspots and trigger the generation of large amounts of NOx (nitrogen oxides). Significant increases in NOx emissions will adversely impact the airworthiness certification of hydrogen-fueled aircraft engines. Summary of the Invention

[0005] In view of this, the present invention provides a nozzle swirl assembly, a combustion chamber structure and an aircraft engine to solve the problems in the prior art of poor environmental protection of the combustion chamber, high nitrogen oxide generation rate, and easy formation of local high temperature.

[0006] In order to solve the above technical problems, the technical solutions of the present invention are as follows:

[0007] In the first aspect, the present invention provides a nozzle swirl assembly, comprising: a nozzle and a swirl member; the nozzle is provided with an air inlet passage, one end of the nozzle is connected to the supply end of the fuel gas so that the fuel gas passes into the air inlet passage; the swirl member is provided with a diffusion chamber connected to the combustion chamber, the swirl member is provided with a first swirl passage and a second swirl passage connected to the diffusion chamber, the first swirl passage and the second swirl passage are used to pass the combustion-supporting gas, the other end of the nozzle is provided with a first through hole and a second through hole connected to the air inlet passage; the first through hole is connected to the first swirl passage, so that the fuel gas flows through the air inlet passage and then passes through the air inlet passage. The fuel gas is ejected from the first through hole and is premixed with the combustion-supporting gas in the first swirl channel to form a first stream of fuel gas. The first stream of fuel gas flows through the diffusion chamber into the combustion chamber and is premixed and burned in a direction away from the central axis of the combustion chamber. The second through hole is connected to the diffusion chamber. After flowing through the air intake channel, the fuel gas enters the diffusion chamber from the second through hole to form a second stream of fuel gas. The combustion-supporting gas flows through the second swirl channel into the diffusion chamber to form a third stream of fuel gas. The second and third streams of fuel gas enter the combustion chamber through the diffusion chamber and are diffused and burned in a direction close to the central axis of the combustion chamber.

[0008] It has the following advantages:

[0009] The present invention provides a nozzle swirl assembly. A first through-hole and a second through-hole are provided between the nozzle and the swirl element, respectively communicating with a first swirl channel and a diffusion chamber. This allows fuel gas and combustion-supporting gas to mix to form a first stream of gas and a second stream of gas, respectively. The swirl element also has a second swirl channel communicating with the diffusion chamber to form a third stream of gas. Premixed combustion and diffusion combustion occur in the inner and outer regions of the combustion chamber, respectively, along the central axis. This achieves zoned coupling of premixed and diffusion combustion. The first swirl channel premixes the fuel gas and combustion-supporting gas, forming a uniform and stable premixed combustion flame in the outer region of the combustion chamber, improving combustion efficiency and reducing ignition delay. The second through-hole introduces the fuel gas into the diffusion chamber, where it combusts together with the combustion-supporting gas entering through the second swirl channel near the central axis of the combustion chamber. The design of the first through-hole reduces the local high temperature in the core region of the flame, reducing nitrogen oxide generation at the source and improving the environmental performance of the hydrogen fuel combustion system. This application achieves a decoupled design of the premixing and diffusion channels through a simple through-hole layout, reducing manufacturing difficulty and cost, and enhancing the structural engineering feasibility and adjustable flexibility.

[0010] According to an embodiment of the first aspect of the present invention, a plurality of the first through holes and a plurality of the second through holes are provided, wherein the plurality of the first through holes are opened on the side wall of the nozzle and are evenly spaced along the circumference, and the plurality of the second through holes are opened on the end surface of the other end of the nozzle and are evenly spaced along the circumference.

[0011] According to the first aspect of the present invention, the first through hole is inclined from the air inlet direction to the air outlet direction along the inner wall of the air inlet passage toward the outer wall of the nozzle;

[0012] Along the air inlet direction toward the air outlet direction, the second through hole is inclined from the inner side of the central axis toward the outer side of the central axis.

[0013] According to an embodiment of the first aspect of the present invention, the air intake channel includes a first flow segment and a second flow segment that are connected to each other, the inner diameters of the first flow segment are equal, the inner diameter of the second flow segment gradually increases from the air intake direction toward the air outlet direction to form a bell-mouth shape, the first through hole is connected to the first flow segment, and the second through hole is connected to the second flow segment and is arranged close to the outer edge of the nozzle.

[0014] According to an embodiment of the first aspect of the present invention, the swirl member is provided with a connecting hole along the central axis from its first end, the diffusion chamber is opened along the central axis and passes through the second end of the swirl member, the connecting hole is communicated with the diffusion chamber, the nozzle is passed through the connecting hole so that the other end of the nozzle extends into the diffusion chamber, and the second through hole is communicated with the diffusion chamber.

[0015] According to an embodiment of the first aspect of the present invention, the swirl member includes a first swirl impeller and a second swirl impeller, the first swirl impeller is arranged at the inlet end of the first swirl channel, and the second swirl impeller is arranged at the inlet end of the second swirl channel, and the axes of the first swirl impeller and the second swirl impeller are consistent with the central axis of the swirl member.

[0016] According to an embodiment of the first aspect of the present invention, the first swirl impeller and the second swirl impeller have the same direction of rotation.

[0017] According to an embodiment of the first aspect of the present invention, the first swirl channel includes an air intake section and a premixing section, the first swirl impeller is arranged in the air intake section, the first through hole is connected to the front end of the premixing section, the rear end of the premixing section is connected to the diffusion chamber, and the premixing section has a Laval nozzle-like structure.

[0018] In the second aspect, the present invention also provides a combustion chamber structure, including a casing and the nozzle swirl assembly; the casing includes an outer casing body and an inner casing body, the rear end of the outer casing body is connected to the rear end of the inner casing body, and a cooling channel is formed between the outer casing body and the inner casing body, the inner casing body is provided with a combustion chamber, the nozzle swirl assembly is provided at the front end of the inner casing body, the nozzle is passed through the side wall of the outer casing body to extend to connect with the supply end of the fuel gas, and the front end of the outer casing body is provided with an air inlet for combustion-supporting gas; the side wall of the inner casing body is radially provided with cooling holes.

[0019] In a third aspect, the present invention further provides an aircraft engine comprising the combustion chamber structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0021] Figure 1 A schematic structural diagram of a combustion chamber structure provided in an embodiment of the second aspect of the present invention;

[0022] Figure 2 A cross-sectional structural diagram of a combustion chamber structure provided in an embodiment of the second aspect of the present invention;

[0023] Figure 3 A schematic structural diagram of a swirl component provided in an embodiment of the first aspect of the present invention;

[0024] Figure 4 This is a structural cross-sectional view of the nozzle swirl assembly provided in the embodiment of the first aspect of the present invention.

[0025] Description of reference numerals:

[0026] 1. Nozzle; 11. Inlet channel; 12. First through hole; 13. Second through hole; 111. First flow section; 112. Second flow section; 2. Swirl element; 21. First swirl channel; 22. Second swirl channel; 23. First swirl impeller; 24. Second swirl impeller; 25. Diffuser; 26. Connecting hole; 211. Inlet section; 212. Premixing section; 3. Casing; 31. Outer casing; 32. Inner casing; 33. Cooling channel; 34. Combustion chamber. DETAILED DESCRIPTION

[0027] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without making creative efforts shall fall within the scope of protection of the present invention.

[0028] In the description of the present invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate and simplify the description of the present invention. They are not intended to indicate or imply that the devices or components referred to must have, be constructed, or operate in a specific orientation, and therefore should not be construed as limitations on the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0029] 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 understood in a broad sense. For example, they may refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; 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 the specific circumstances.

[0030] In addition, the technical features involved in different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0031] Reference Figure 1 、 Figure 2 、 Figure 3 and Figure 4As shown, in the first aspect, the present invention provides a nozzle swirl assembly, comprising: a nozzle 1 and a swirl member 2; the nozzle 1 is provided with an air inlet channel 11, one end of the nozzle 1 is connected to the supply end of the fuel gas so that the fuel gas enters the air inlet channel; the swirl member 2 is provided with a diffusion chamber 25 connected to the combustion chamber 34, the swirl member 2 is provided with a first swirl channel 21 and a second swirl channel 22 connected to the diffusion chamber 25, the first swirl channel 21 and the second swirl channel 22 are used to pass the combustion-supporting gas, the other end of the nozzle 1 is provided with a first through hole 12 and a second through hole 13 connected to the air inlet channel 11; the first through hole 12 is connected to the first swirl channel 21, so that the fuel gas flows into the nozzle 1; After passing through the air intake channel 11, it is ejected from the first through hole 12 and premixed with the combustion-supporting gas in the first swirl channel 21 to form a first stream of gas. The first stream of gas flows through the diffusion chamber 25 into the combustion chamber 34 and is premixed and burned in a direction away from the central axis of the combustion chamber 34; the second through hole 13 is connected to the diffusion chamber 25, and the fuel gas flows through the air intake channel 11 and enters the diffusion chamber 25 from the second through hole 13 to form a second stream of gas. The combustion-supporting gas flows through the second swirl channel 22 and enters the diffusion chamber 25 to form a third stream of gas; the second stream of gas and the third stream of gas enter the combustion chamber 34 through the diffusion chamber 25 and are diffused and burned in a direction close to the central axis of the combustion chamber 34.

[0032] Specifically, the present invention provides a nozzle swirl assembly. A first through-hole 12 and a second through-hole 13 are provided between the nozzle 1 and the swirl element 2, respectively communicating with a first swirl channel 21 and a diffusion chamber 25. This allows fuel gas and combustion-supporting gas to mix to form a first stream of gas and a second stream of gas, respectively. The swirl element 2 also includes a second swirl channel 22 communicating with the diffusion chamber 25 to form a third stream of gas. Premixed combustion and diffusion combustion occur within and outside the central axis of the combustion chamber 34, respectively, thereby achieving zoned coupling of premixed and diffusion combustion. The first swirl channel 21 premixes the fuel gas and combustion-supporting gas, forming a uniform and stable premixed combustion flame in the outer region of the combustion chamber 34, improving combustion efficiency and reducing ignition delay. The second through-hole 13 introduces the fuel gas into the diffusion chamber 25, where it is burned together with the combustion-supporting gas entering from the second swirl channel 22 near the central axis of the combustion chamber 34. The design of the first through-hole reduces the local high temperature in the core region of the flame, reducing nitrogen oxide generation at the source and improving the environmental performance of the hydrogen fuel combustion system. The present application realizes the decoupling design of the premixing channel and the diffusion channel through a simple through-hole layout, reduces the manufacturing difficulty and cost, and enhances the engineering feasibility and adjustment flexibility of the structure.

[0033] It is understandable that compared with the traditional central staged combustion structure, the present invention does not require a complex internal staged gas distribution structure of the nozzle. Through a simple through-hole layout, the decoupling design of the premixing channel and the diffusion channel is realized, which reduces the manufacturing difficulty and cost, enhances the engineering feasibility and adjustment flexibility of the structure, and thus reduces production costs. The nozzle swirl assembly is highly scalable in structure and can adjust the flow ratio of each gas according to different working conditions to meet the requirements of stable operation of hydrogen-fueled aircraft engines in multiple working conditions from low-load ignition to high-load and high-temperature combustion. By optimizing the combustion organization form, the emission level and flame morphology are effectively controlled, and the comprehensive requirements of hydrogen-fueled aircraft engines for low emissions, high efficiency, and controllable combustion are met, providing technical support for their airworthiness certification, and having good prospects for application and promotion.

[0034] It should be noted that the fuel gas is hydrogen fuel and the combustion-supporting gas is air.

[0035] Reference Figure 3 and Figure 4 As shown, in the embodiment of the first aspect of the present invention, a plurality of first through holes 12 and a plurality of second through holes 13 are provided, a plurality of first through holes 12 are opened on the side wall of the nozzle 1 and are evenly spaced along the circumference, and a plurality of second through holes 13 are opened on the end face of the other end of the nozzle 1 and are evenly spaced along the circumference.

[0036] Specifically, in order to improve the uniformity of gas distribution and enable efficient mixing of the fuel gas and the combustion-supporting gas, a plurality of first through holes 12 and second through holes 13 are provided. The first through holes 12 are opened on the side wall of the nozzle 1 and are evenly spaced along the outer circumference. After the fuel gas enters the air inlet channel 11 of the nozzle 1 from the fuel gas supply end, it is split at the first through hole 12 and enters the first swirl channel 21 through the first through hole 12. It is premixed with the combustion-supporting gas in the first swirl channel 21 to form a first stream of gas. A first adjusting member is provided inside the nozzle 1. The first adjusting member can slide along the inner wall of the nozzle 1 to cover the first through hole 12, thereby adjusting the opening size of the first through hole 12. By adjusting the opening of the first through hole 12, the proportion of premixed combustion can be adjusted.

[0037] Similarly, the second through hole 13 is provided on the end surface of the other end of the nozzle 1 and is evenly spaced along the circumferential direction. A second adjusting member is provided on the inner side of the end surface of the other end of the nozzle 1. The second adjusting member can be rotated along the axis to adjust the opening of the second through hole 13 to control the amount of fuel gas passing through the second through hole 13. By adjusting the opening of the second through hole 13, the proportion of diffusion combustion can be adjusted, thereby ensuring the high controllability of combustion.

[0038] In the embodiment of the first aspect of the present invention, the first through hole 12 is inclined from the air intake direction toward the air outlet direction along the inner wall of the air intake channel 11 toward the outer wall of the nozzle 1;

[0039] From the air inlet direction to the air outlet direction, the second through hole 13 is inclined from the inner side of the central axis to the outer side of the central axis.

[0040] Specifically, by angling both the first and second through-holes 12, 13, the radial velocity component of the fuel gas is increased, thereby improving the penetration depth of the air entering the swirl element 2. For the first through-hole 12, if the combustion-supporting gas flows back into the inlet passage 11 of the nozzle 1, it will hinder the intake of the fuel gas, resulting in unstable fuel gas supply and causing flashback or oscillating combustion. The first through-hole 12 is tilted along the inner wall of the inlet passage 11 toward the outer wall of the nozzle 1, from the inlet direction to the outlet direction. This requires the airflow in the first swirl passage 21 to form an obtuse angle with the original direction in order to flow into the hydrogen fuel nozzle, i.e., reverse flow occurs. In the present invention, air flows forward when unobstructed, so the tilted arrangement of the first through-hole 12 prevents reverse flow of air into the inlet passage 11. Furthermore, for the fuel gas, the direction of injection into the first swirl passage 21 along the first through-hole 12 is forward flow, making it easier for the fuel gas to be split and mixed with the combustion-supporting gas in the first swirl passage 21.

[0041] Similarly, in order to make the fuel gas burn together with the combustion-supporting gas toward the outside of the diffusion chamber 25, the second through hole 13 is inclined from the inside of the central axis toward the outside of the central axis along the air intake direction toward the air outlet direction; by tilting the first through hole 12 and the second through hole 13, on the one hand, the rectification effect is improved, so that the combustion-supporting gas and the fuel gas are turned before premixing, avoiding the combustion-supporting gas from hindering the injection of the fuel gas; on the other hand, the air intake volume is increased, so as to better organize the premixed combustion and diffusion combustion to be carried out at a relatively lean fuel-air ratio, control the maximum temperature of the main combustion zone, and reduce NOx emissions; at the same time, the swirl element 2 can better match the nozzle 1, provide a suitable premixing section 212 for ensuring the premixing effect of the fuel gas and the combustion-supporting gas, and ensure that the circumferential angle of the second through hole 13 is the same as the two-stage rotation direction of the swirl element 2 to enhance the mixing of the fuel gas and the combustion-supporting gas before diffusion combustion.

[0042] The present invention can regulate the relative proportion of premixed combustion and diffusion combustion by actively adjusting multiple parameters such as the inclined hole angle, inclined hole position, inclined hole opening area (including number and opening diameter) of the first through hole 12 and the second through hole 13, the relative position and relative size of the first through hole 12 and the second through hole 13 and the first swirl channel 21 and the second swirl channel 22 of the swirl member 2, so as to meet the requirements of comprehensive performance under different working environments. In this process, the various parameters are relatively independent and there will be no problem of mutual interference or large performance changes caused by small changes. The high working stability of the combustion chamber is maintained, and the hydrogen fuel aircraft engine achieves a balance between stability, low emissions and acceptable costs.

[0043] In the first embodiment of the present invention, the air intake channel 11 includes a first flow segment 111 and a second flow segment 112 that are connected to each other. The inner diameters of the first flow segment 111 are equal, and the inner diameter of the second flow segment 112 gradually increases from the air intake direction toward the air outlet direction to form a bell-mouth shape. The first through hole 12 is connected to the first flow segment 111, and the second through hole 13 is connected to the second flow segment 112 and is arranged near the outer edge of the nozzle 1.

[0044] Specifically, to increase the amount of air intake at the end of the nozzle 1 and better organize both premixed combustion and diffusion combustion at a leaner fuel-air ratio, the intake passage 11 is configured as a first flow section 111 and a second flow section 112. The first flow section 111 has a uniform inner diameter, and a first through-hole 12 is formed on the sidewall of the first flow section 111. The fuel gas is divided within the first flow section 111, with one portion being injected into the first swirl passage 21 through the first through-hole 12 and the other portion being distributed into the second flow passage. The second flow passage has an inner diameter that gradually increases from the intake direction toward the exhaust direction, forming a bell-shaped shape. This increases the pressure differential of the fuel gas ejected, allowing the fuel gas to pass through the second through-hole 13 at high speed into the diffusion chamber 25. The outer edge orientation of the second through-hole 13 allows for diffusion combustion of the second stream of fuel gas formed by the fuel gas and the third stream of fuel gas formed by the combustion-supporting gas within the second swirl passage 22.

[0045] In the first embodiment of the present invention, the swirl element 2 has a connecting hole 26 extending from its first end along the central axis, and the diffusion chamber 25 is opened along the central axis and passes through the second end of the swirl element 2. The connecting hole 26 is connected to the diffusion chamber 25. The nozzle 1 is passed through the connecting hole 26 so that the other end of the nozzle 1 extends into the diffusion chamber 25. The second through hole 13 is connected to the diffusion chamber 25.

[0046] Specifically, nozzle 1 is inserted through connection hole 26, allowing the other end of nozzle 1 to extend into communication with diffuser chamber 25. Fuel gas enters diffuser chamber 25 directly through second through-hole 13, ensuring sufficient fuel gas intake. Connection hole 26 provides a mounting base for nozzle 1, ensuring stable fit between nozzle 1 and swirl element 2. By adjusting the relative position of nozzle 1 and swirl element 2, the premixing channel and diffuser channel can be adjusted, reducing manufacturing complexity and production costs.

[0047] In the embodiment of the first aspect of the present invention, the swirl member 2 includes a first swirl impeller 23 and a second swirl impeller 24. The first swirl impeller 23 is arranged at the inlet end of the first swirl channel 21, and the second swirl impeller 24 is arranged at the inlet end of the second swirl channel 22. The axes of the first swirl impeller 23 and the second swirl impeller 24 are consistent with the central axis of the swirl member 2.

[0048] In the first embodiment of the present invention, the first swirl impeller 23 and the second swirl impeller 24 have the same rotation direction.

[0049] Specifically, the swirl element 2 in the present invention is a radial swirl element 2, that is, the axes of the first swirl impeller 23 and the second swirl impeller 24 are consistent with the central axis of the swirl element 2, and the combustion-supporting gas enters from the peripheral wall of the swirl element 2. The first swirl impeller 23 and the second swirl impeller 24 have the same direction of rotation, so that the intake direction of the first swirl channel 21 and the second swirl channel 22 remains consistent, thereby forming a two-stage radial swirl element 2.

[0050] In the first embodiment of the present invention, the first swirl channel 21 includes an air intake section 211 and a premixing section 212, the first swirl impeller 23 is arranged in the air intake section 211, the first through hole 12 is connected to the front end of the premixing section 212, the rear end of the premixing section 212 is connected to the diffusion chamber 25, and the premixing section 212 has a Laval nozzle-like structure.

[0051] In the first embodiment of the present invention, the inner diameter of the diffusion chamber 25 gradually increases from the side close to the nozzle 1 to the side close to the combustion chamber 34, and is designed in a trumpet-shaped manner, thereby improving the mixing state of the first gas, the second gas and the third gas when they enter the combustion chamber, thereby improving the combustion efficiency.

[0052] Reference Figure 1 and Figure 2 As shown, in the second aspect of the invention, the present invention also provides a combustion chamber structure, including a casing 3 and a nozzle swirl assembly; the casing 3 includes an outer casing body 31 and an inner casing body 32, the rear end of the outer casing body 31 is connected to the rear end of the inner casing body 32, and a cooling channel 33 is formed between the outer casing body 31 and the inner casing body 32, the inner casing body 32 is provided with a combustion chamber 34, the nozzle swirl assembly is arranged at the front end of the inner casing body 32, the nozzle 1 is penetrated through the side wall of the outer casing body 31 to extend to communicate with the supply end of the fuel gas, and the front end of the outer casing body 31 is provided with an air inlet for the combustion-supporting gas; the side wall of the inner casing body 32 is radially provided with cooling holes.

[0053] Specifically, the casing 3 is provided with a main combustion hole for adjusting the position of the main combustion zone, and the cooling hole is provided for controlling the wall temperature of the casing 3 .

[0054] In a third aspect of the invention, the present invention further provides an aircraft engine, including a combustion chamber structure.

[0055] Although the embodiments of the present invention have been described with reference to the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the present invention. Such modifications and variations are all within the scope defined by the appended claims.

Claims

1. A nozzle swirl assembly, characterized in that: include: A nozzle (1) is provided with an air inlet passage (11), one end of the nozzle (1) being in communication with a fuel gas supply end so that the fuel gas flows into the air inlet passage; A swirl member (2), the swirl member (2) is provided with a diffusion chamber (25) communicating with the combustion chamber (34), the swirl member (2) is provided with a first swirl channel (21) and a second swirl channel (22) communicating with the diffusion chamber (25), the first swirl channel (21) and the second swirl channel (22) being used to introduce combustion-supporting gas, and the other end of the nozzle (1) is provided with a first through hole (12) and a second through hole (13) communicating with the air inlet channel (11); The first through hole (12) is in communication with the first swirl channel (21), so that the fuel gas flows through the air inlet channel (11) and is ejected from the first through hole (12), and is premixed with the combustion-supporting gas in the first swirl channel (21) to form a first stream of fuel gas, which flows through the diffusion chamber (25) into the combustion chamber (34) and is premixed and burned in a direction away from the central axis of the combustion chamber (34); The second through hole (13) is in communication with the diffusion chamber (25); the fuel gas flows through the air inlet channel (11) and then enters the diffusion chamber (25) from the second through hole (13) to form a second stream of fuel gas; the combustion-supporting gas flows through the second swirl channel (22) and then enters the diffusion chamber (25) to form a third stream of fuel gas; the second stream of fuel gas and the third stream of fuel gas enter the combustion chamber (34) through the diffusion chamber (25) and are diffused and burned in a direction close to the central axis of the combustion chamber (34).

2. The nozzle swirl assembly according to claim 1, characterized in that: A plurality of the first through holes (12) and a plurality of the second through holes (13) are provided. The plurality of the first through holes (12) are opened on the side wall of the nozzle (1) and are evenly spaced along the circumference. The plurality of the second through holes (13) are opened on the end surface of the other end of the nozzle (1) and are evenly spaced along the circumference.

3. The nozzle swirl assembly according to claim 2, characterized in that: Along the inner wall of the air inlet channel (11) toward the outer wall of the nozzle (1), the first through hole (12) is inclined from the air inlet direction toward the air outlet direction; Along the air inlet direction toward the air outlet direction, the second through hole (13) is inclined from the inner side of the central axis toward the outer side of the central axis.

4. The nozzle swirl assembly according to claim 1, characterized in that: The air inlet channel (11) comprises a first flow section (111) and a second flow section (112) which are connected to each other. The inner diameters of the first flow section (111) are equal, and the inner diameter of the second flow section (112) gradually increases from the air inlet direction toward the air outlet direction to form a bell-mouth shape. The first through hole (12) is connected to the first flow section (111), and the second through hole (13) is connected to the second flow section (112) and is arranged close to the outer edge of the nozzle (1).

5. The nozzle swirl assembly according to claim 1, characterized in that: The swirl member (2) is provided with a connecting hole (26) along the central axis direction from the first end thereof, the diffusion chamber (25) is provided along the central axis direction thereof and passes through the second end of the swirl member (2), the connecting hole (26) is communicated with the diffusion chamber (25), the nozzle (1) is passed through the connecting hole (26) so that the other end of the nozzle (1) extends into the diffusion chamber (25), and the second through hole (13) is communicated with the diffusion chamber (25).

6. The nozzle swirl assembly according to claim 5, characterized in that: The swirl member (2) comprises a first swirl impeller (23) and a second swirl impeller (24), wherein the first swirl impeller (23) is arranged at the inlet end of the first swirl channel (21), and the second swirl impeller (24) is arranged at the inlet end of the second swirl channel (22), and the axes of the first swirl impeller (23) and the second swirl impeller (24) are consistent with the central axis of the swirl member (2).

7. The nozzle swirl assembly according to claim 6, characterized in that: The first swirl impeller (23) and the second swirl impeller (24) have the same direction of rotation.

8. The nozzle swirl assembly according to claim 6, characterized in that: The first swirl channel (21) comprises an air intake section (211) and a premixing section (212); the first swirl impeller (23) is provided in the air intake section (211); the first through hole (12) is in communication with the front end of the premixing section (212); the rear end of the premixing section (212) is in communication with the diffusion chamber (25); and the premixing section (212) is in a Laval nozzle-like structure.

9. A combustion chamber structure, characterized in that: It comprises a casing (3) and a nozzle swirl assembly according to any one of claims 1 to 8; The casing (3) comprises an outer casing (31) and an inner casing (32), the rear end of the outer casing (31) is connected to the rear end of the inner casing (32), a cooling channel (33) is formed between the outer casing (31) and the inner casing (32), the inner casing (32) is provided with a combustion chamber (34), the nozzle swirl assembly is provided at the front end of the inner casing (32), the nozzle (1) is provided through the side wall of the outer casing (31) to extend to communicate with the supply end of the fuel gas, and the front end of the outer casing (31) is provided with an air inlet for the combustion-supporting gas; The side wall of the inner box body (32) is provided with cooling holes in the radial direction.

10. An aircraft engine, characterized in that: Comprising the combustion chamber structure according to claim 9.

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