Hydrogen fuel annular vortex combustor structure and aircraft engine

Abstract

The application relates to the technical field of engines, and provides a hydrogen fuel annular vortex combustion chamber structure and an aero-engine, wherein the hydrogen fuel annular vortex combustion chamber structure comprises a casing, a flame tube and a plurality of nozzle assemblies; the flame tube is nested in the casing and is bent to form an annular combustion chamber; the plurality of nozzle assemblies are arranged in an annular array along the circumferential direction of the annular combustion chamber; the nozzle assemblies penetrate through the outer wall of the casing and the outer wall of the flame tube and are communicated with the annular combustion chamber; the nozzle assemblies are used for spraying fuel into the annular combustion chamber; the spraying direction of the nozzle assemblies is inclined away from the annular combustion chamber and is arranged at an angle with the axial direction and the radial direction of the annular combustion chamber. The application realizes the increase of the contact distance and time of hydrogen and air, the increase of the mixing ratio, the increase of the combustion efficiency and the emission level.

Description

Technical Field

[0001] This invention relates to the field of engine technology, and in particular to a hydrogen fuel ring vortex combustor structure and an aero-engine. Background Technology

[0002] Gas turbine engines are a type of power machinery widely used in many industrial fields such as aviation, shipbuilding, and power generation, playing a vital role in the development of the national economy. Compared with other engines, micro gas turbine engines have many advantages, exhibiting significant advantages in fuel consumption, noise, emissions, and vibration. They can be used not only in traditional distributed power generation but also in various power generation methods such as grid-connected power generation. They are applicable not only in urban areas but also in remote regions due to their portability and reliable operation. Besides transportation applications such as land and sea border defense, micro gas turbine engines have applications in new energy vehicles, electromechanical processing, and metal materials, thus attracting considerable attention.

[0003] The hydrogen fuel-powered vortex combustor is a key component commonly found in aircraft engines. It mixes and burns fuel and air to produce high-temperature, high-pressure gas that drives a turbine to propel the aircraft or other maneuvering devices. The design and performance of the hydrogen fuel-powered vortex combustor play a crucial role in the engine's efficiency, reliability, and environmental friendliness.

[0004] In related technical fields, hydrogen fuel is not easily mixed with air in the vortex combustion chamber, resulting in incomplete combustion and affecting combustion efficiency and emission levels. Summary of the Invention

[0005] This invention provides a hydrogen fuel ring vortex combustor structure and an aero-engine to solve the technical defects in the prior art where hydrogen fuel is not easy to mix with air in the ring vortex combustor, resulting in incomplete combustion and affecting combustion efficiency and emission levels. It achieves the goal of increasing the contact distance and time between hydrogen and air, increasing the mixing ratio, and thus improving combustion efficiency and emission levels.

[0006] This invention provides a hydrogen fuel ring vortex combustion chamber structure, comprising: Casing; A flame tube, which is nested in the housing, is bent to form an annular combustion chamber; A plurality of nozzle assemblies are arranged in a circular array along the circumferential direction of the annular combustion chamber. The nozzle assemblies penetrate the outer wall of the casing and the outer wall of the flame tube and communicate with the annular combustion chamber. The nozzle assemblies are used to inject fuel into the annular combustion chamber. The nozzle assembly is inclined away from the annular combustion chamber and is angular to both the axial and radial directions of the annular combustion chamber.

[0007] According to a hydrogen fuel annular vortex combustor structure provided by the present invention, the injection direction of the nozzle assembly is deflected toward the downstream direction of the annular combustor, and the angle between the injection direction of the nozzle assembly and the radial direction of the annular combustor is α, wherein α is greater than or equal to 10° and less than or equal to 30°.

[0008] According to a hydrogen fuel annular vortex combustion chamber structure provided by the present invention, the injection direction of the nozzle is inclined toward the downstream direction of the annular combustion chamber, and the angle between the injection direction of the nozzle assembly and the axial direction of the annular combustion chamber is β, wherein β is greater than or equal to 10° and less than or equal to 30°.

[0009] According to a hydrogen fuel vortex combustion chamber structure provided by the present invention, the nozzle assembly has an incident surface, and a plurality of evenly distributed nozzle holes are formed on the incident surface, wherein a spray cone angle γ is formed between the plurality of nozzle holes, wherein γ is greater than or equal to 65° and less than or equal to 75°.

[0010] According to a hydrogen fuel annular vortex combustion chamber structure provided by the present invention, the plurality of nozzle assemblies include at least two ignition nozzles, and the hydrogen fuel annular vortex combustion chamber structure further includes at least two ignition nozzles. The at least two ignition nozzles are arranged axially symmetrically in the annular combustion chamber, the ignition nozzles are arranged adjacent to each other, and the ignition nozzles are inclined toward the direction of the ignition nozzles.

[0011] According to the present invention, a hydrogen fuel annular vortex combustor structure includes a first hydrogen supply line and a second hydrogen supply line. The first hydrogen supply line is connected to the ignition nozzle, and the second hydrogen supply line is connected to the remaining nozzle assemblies. When the annular combustor is ignited, the ignition nozzle is supplied with hydrogen through the first hydrogen supply line, which is suitable for igniting the annular combustor. Subsequently, the remaining nozzle assemblies are supplied with hydrogen through the second hydrogen supply line, which is suitable for flame propagation in the annular combustor.

[0012] According to a hydrogen fuel annular vortex combustion chamber structure provided by the present invention, the nozzle assembly includes a nozzle and a cap, the cap being fitted over the outside of the nozzle and spaced apart from the outer periphery of the nozzle, and the cap having an inlet near the end extending into the annular combustion chamber, with a portion of the nozzle exposed inside the annular combustion chamber through the inlet.

[0013] According to a hydrogen fuel ring vortex combustion chamber structure provided by the present invention, an air passage cavity is formed between the inner wall surface of the cap and the outer wall surface of the nozzle. The wall surface of the cap located between the outer wall of the casing and the outer wall of the flame tube is provided with a plurality of air inlets, and the plurality of air inlets are connected to the injection port through the air passage cavity.

[0014] According to a hydrogen fuel annular vortex combustion chamber structure provided by the present invention, the number of nozzle assemblies is greater than or equal to 12 and less than or equal to 16.

[0015] This application also provides an aero-engine, which includes the aforementioned hydrogen fuel annular vortex combustor structure. The hydrogen fuel annular vortex combustor structure includes a casing, a flame tube, and a plurality of nozzle assemblies. The flame tube is nested in the casing and is bent to form an annular combustor. The plurality of nozzle assemblies are arranged in a circular array along the circumferential direction of the annular combustor. The nozzle assemblies penetrate the outer wall of the casing and the outer wall of the flame tube and communicate with the annular combustor. The nozzle assemblies are used to inject fuel into the annular combustor. The injection direction of the nozzle assemblies is inclined away from the annular combustor and is angular to both the axial and radial directions of the annular combustor.

[0016] This application increases the contact distance and time between the hydrogen ejected from the nozzle assembly and the air inside the annular combustion chamber by setting the nozzle assembly and the injection direction of the nozzle assembly away from the annular combustion chamber and at an angle to both the axial and radial directions of the annular combustion chamber. This makes the hydrogen and air mix more evenly, improves the mixing ratio, and can effectively reduce the oil-air ratio at the head of the annular combustion chamber, thereby reducing the area of ​​the high-temperature zone, reducing NOx emissions, and thus improving combustion efficiency and emission levels. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in this invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of an embodiment of the hydrogen fuel annular vortex combustion chamber structure provided by the present invention; Figure 2 yes Figure 1 Side view of the structure of a hydrogen fuel ring vortex combustor; Figure 3 yes Figure 2 Sectional view at point AA; Figure 4 yes Figure 2 Sectional view at point BB; Figure 5 yes Figure 1 A schematic diagram of the structure of one embodiment of the nozzle assembly; Figure 6 yes Figure 5 Another perspective view of the nozzle assembly; Figure 7 yes Figure 6 Sectional view at point CC.

[0019] Figure label: 10. Hydrogen fuel annular vortex combustion chamber structure; 100. Casing; 110. Outer wall of the casing; 120. Side wall of the casing; 130. Inner wall of the casing; 140. U-shaped bottom wall of the casing; 150. Intake chamber; 160. Air inlet; 200, Flame tube; 210, Annular combustion chamber; 220, Outer wall of flame tube; 230, End wall of flame tube; 240, Inner wall of flame tube; 250, Gas outlet; 300, Nozzle assembly; 310, Nozzle; 311, Entrance surface; 311a, Nozzle orifice; 320, Cap; 321, Inlet port; 322, Air inlet; 330, Air passage; 340, Ignition nozzle; 400. Ignition nozzle. Detailed Implementation

[0020] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0021] In the description of the embodiments of the present invention, it should be noted that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the embodiments of the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the embodiments of the present invention. In addition, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0022] In the description of the embodiments of the present invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "connected" and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of the present invention based on the specific circumstances.

[0023] This invention proposes a hydrogen fuel ring vortex combustion chamber structure and an aero-engine.

[0024] In embodiments of the present invention, such as Figures 1 to 4 As shown, the hydrogen fuel annular vortex combustor structure 10 includes a casing 100, a flame tube 200, and several nozzle assemblies 300. The flame tube 200 is nested in the casing 100 and is bent to form an annular combustion chamber 210. Several nozzle assemblies 300 are arranged in a circular array along the circumference of the annular combustion chamber 210. The nozzle assemblies 300 penetrate the outer wall of the casing 100 and the outer wall of the flame tube 200 and communicate with the annular combustion chamber 210. The nozzle assemblies 300 are used to inject fuel into the annular combustion chamber 210. The injection direction of the nozzle assemblies 300 is inclined away from the annular combustion chamber 210 and is angular to both the axial and radial directions of the annular combustion chamber 210.

[0025] The casing 100 is the outer shell of the combustion chamber, serving to protect internal components, maintain structural integrity, and withstand the pressure and temperature generated during combustion. Additionally, the casing 100 may integrate a cooling system or other auxiliary equipment to ensure stable operation of the combustion chamber even under extreme conditions.

[0026] The flame tube 200 is the main combustion zone of the annular combustion chamber 210, which is where fuel and air mix and burn. The annular design of the flame tube 200 allows fuel to burn over a wider area, resulting in more uniform fuel-air mixing and more complete combustion, thus improving combustion efficiency. More uniform combustion reduces the formation of unburned fuel and harmful substances, helping to lower emission levels. The design of the flame tube 200 also helps to form a stable flame, improving combustion stability.

[0027] By bending the flame tube 200, a continuous annular combustion chamber 210 can be formed. This allows the flame to be evenly distributed throughout the annular area, avoiding flame concentration and localized overheating, and further improving the uniformity and stability of combustion.

[0028] The nozzle assembly 300 is responsible for injecting fuel (i.e., hydrogen) into the annular combustion chamber 210, where it mixes with air for combustion. The design and performance of the nozzle assembly 300 directly affect the mixing effect of fuel and air, thereby affecting combustion efficiency and emission levels.

[0029] Multiple nozzle assemblies 300 are arranged in a ring array along the circumference of the annular combustion chamber 210, which ensures uniform fuel distribution throughout the entire annular combustion chamber 210. This helps to form a uniform flame and temperature field, improving combustion stability and efficiency.

[0030] The nozzle assembly 300 needs to penetrate the outer walls of the casing 100 and the flame tube 200 to directly inject fuel into the annular combustion chamber 210. This ensures a direct and efficient fuel supply and avoids fuel loss and leakage during transport.

[0031] The nozzle assembly 300 is designed to be inclined away from the annular combustion chamber 210, which helps to increase the contact area and time between fuel and air. When fuel is injected into the annular combustion chamber 210 at a certain angle, it can mix better with air to form a more uniform air-fuel mixture, thereby improving combustion efficiency.

[0032] The injection direction of the nozzle assembly 300 is angled to both the axial and radial directions of the annular combustion chamber 210, giving the fuel a certain rotational momentum as it enters the annular combustion chamber 210. This helps the fuel to disperse and mix better within the annular combustion chamber 210, further improving combustion efficiency. Simultaneously, it can also reduce the air-fuel ratio at the combustion chamber head and decrease the area of ​​the high-temperature zone, thereby reducing emissions of harmful substances such as NOx.

[0033] This application increases the contact distance and time between the hydrogen ejected by the nozzle assembly 300 and the air inside the annular combustion chamber 210 by setting the nozzle assembly 300 and the injection direction of the nozzle assembly 300 away from the annular combustion chamber 210, and setting it at an angle to both the axial and radial directions of the annular combustion chamber 210. This makes the hydrogen and air mix more evenly, improves the mixing ratio, and can effectively reduce the oil-air ratio at the head of the annular combustion chamber 210, thereby reducing the area of ​​the high-temperature zone, reducing NOx emissions, and thus improving combustion efficiency and emission levels.

[0034] Reference Figure 5 According to the present invention, a hydrogen fuel annular vortex combustion chamber structure 10 is provided, wherein the injection direction of the nozzle assembly 300 is deflected toward the downstream direction of the annular combustion chamber 210, and the angle between the injection direction of the nozzle assembly 300 and the radial direction of the annular combustion chamber 210 is α, wherein α is greater than or equal to 10° and less than or equal to 30°.

[0035] Understandably, when the injection direction of the nozzle assembly 300 is deflected downstream of the annular combustion chamber 210, the injected fuel forms a specific injection trajectory. This trajectory interacts with the airflow within the combustion chamber, contributing to better fuel-air mixing.

[0036] By setting the included angle α between 10° and 30°, it can be ensured that the fuel injection trajectory does not deviate too much from the airflow direction, nor is it too perpendicular to the radial direction of the annular combustion chamber 210. This ensures that the fuel and air are fully mixed, while preventing the fuel from directly impacting the combustion chamber wall, thus avoiding waste or poor combustion.

[0037] The shape and stability of the flame have a significant impact on combustion efficiency and emissions performance. By adjusting the injection direction and angle α of the nozzle assembly 300, the distribution and shape of the flame within the combustion chamber can be controlled.

[0038] When the included angle α is set appropriately, the flame can form a stable and uniform distribution in the combustion chamber, avoiding the flame from being too concentrated or too dispersed. This can improve combustion efficiency and reduce emissions.

[0039] If the fuel injection direction deviates too much from the airflow direction, or if the injection is too perpendicular, the fuel may not be fully mixed with the air before being expelled directly from the combustion chamber, resulting in fuel waste. Incomplete combustion also increases the generation and emission of harmful substances. By optimizing the injection direction and angle α, it is possible to ensure thorough mixing of fuel and air, improve combustion efficiency, and reduce fuel waste and harmful emissions.

[0040] Under different operating conditions and combustion requirements, it may be necessary to adjust the fuel-air mixing ratio and flame shape. By adjusting the injection direction and angle α of the nozzle assembly 300, different combustion requirements can be flexibly adapted.

[0041] For example, under high-load conditions, it may be necessary to increase the fuel supply and raise the combustion temperature; while under low-load conditions, it is necessary to reduce the fuel supply and control the combustion temperature. By adjusting the injection direction and angle α, precise control of the combustion process can be achieved.

[0042] Optionally, the angle α between the injection direction of the nozzle assembly 300 and the radial direction of the annular combustion chamber 210 can be any angle among 10°, 11°, 12°, 13°, 14°, 15°, 16°, 17°, 18°, 19°, 20°, 21°, 22°, 23°, 24°, 25°, 26°, 27°, 28°, 29° or 30°, and can be set according to design requirements.

[0043] Reference Figure 7 According to the present invention, a hydrogen fuel annular vortex combustion chamber structure 10 is provided, wherein the injection direction of the nozzle 310 is inclined toward the downstream direction of the annular combustion chamber 210, and the angle between the injection direction of the nozzle assembly 300 and the axial direction of the annular combustion chamber 210 is β, wherein β is greater than or equal to 10° and less than or equal to 30°.

[0044] Understandably, the injection direction of nozzle 310 is inclined towards the downstream direction of the annular combustion chamber 210, meaning that after entering the combustion chamber, the fuel will be injected in the direction of gas flow within the combustion chamber. This helps the fuel to mix better with the hot air or premixed gas already present in the combustion chamber, thereby improving combustion efficiency.

[0045] The included angle β is the angle between the injection direction of the nozzle assembly 300 and the axial direction of the annular combustion chamber 210. When β is too small, the fuel injection direction is almost parallel to the axial direction of the combustion chamber, which may lead to uneven fuel distribution within the combustion chamber and affect combustion efficiency. When β is too large, the fuel injection direction is almost parallel to the radial direction of the combustion chamber, which may cause fuel to directly impact the combustion chamber wall, resulting in fuel waste and unstable combustion.

[0046] By optimizing the injection direction and angle β of nozzle 310, combustion efficiency can be improved, and emissions of unburned fuel and harmful substances can be reduced. This is because better fuel-air mixing increases the rate and completeness of the combustion reaction, thereby reducing the formation of unburned fuel and harmful substances. By adjusting the angle β, different combustion requirements and operating conditions can be accommodated.

[0047] Optionally, the angle β between the injection direction of the nozzle assembly 300 and the axial direction of the annular combustion chamber 210 can be any angle among 10°, 11°, 12°, 13°, 14°, 15°, 16°, 17°, 18°, 19°, 20°, 21°, 22°, 23°, 24°, 25°, 26°, 27°, 28°, 29° or 30°, and can be set according to design requirements.

[0048] Reference Figure 7 According to the present invention, a hydrogen fuel vortex combustion chamber structure 10 is provided, wherein the nozzle assembly 300 has an incident surface 311, and a plurality of evenly distributed nozzle holes 311a are provided on the incident surface 311, and a spray cone angle γ is formed between the plurality of nozzle holes 311a, wherein γ is greater than or equal to 65° and less than or equal to 75°.

[0049] Understandably, when the injection cone angle γ is within this range, the fuel flow can form a relatively uniform distribution within the combustion chamber. This helps to ensure thorough mixing of fuel and air, thereby improving combustion efficiency. If γ is too small, the fuel flow may become too concentrated, leading to uneven combustion; if γ is too large, the fuel flow may become too dispersed, reducing the mixing effect with air.

[0050] An appropriate injection cone angle γ can promote thorough mixing of fuel and air, thereby improving combustion efficiency. When fuel and air are mixed evenly, the combustion reaction can be more complete and rapid, reducing the emission of unburned fuel and harmful substances.

[0051] Within this angular range, the fuel injection is also relatively stable. A stable fuel flow helps maintain the stability and controllability of the flame in the combustion chamber, preventing flame extinction or unstable combustion.

[0052] Optionally, the spray cone angle γ formed between the multiple nozzles 311a can be any angle among 56°, 66°, 67°, 68°, 69°, 70°, 71°, 72°, 73°, 74° or 75°, and can be set according to design requirements.

[0053] Reference Figures 2 to 4 According to a hydrogen fuel annular vortex combustion chamber structure 10 provided by the present invention, a plurality of nozzle 310 assemblies 300 include at least two ignition nozzles 340, and the hydrogen fuel annular vortex combustion chamber structure 10 further includes at least two ignition nozzles 400. The at least two ignition nozzles 400 are arranged axially symmetrically within the annular combustion chamber 210. The ignition nozzles 340 are arranged adjacent to each other and are inclined toward the ignition nozzles 400. The hydrogen fuel annular vortex combustion chamber structure 10 has a first hydrogen supply line and a second hydrogen supply line. The first hydrogen supply line is connected to the ignition nozzles 340, and the second hydrogen supply line is connected to the remaining nozzle 310 assemblies 300. When the annular combustion chamber 210 is ignited, the ignition nozzles 340 are supplied with hydrogen through the first hydrogen supply line, which is suitable for igniting the annular combustion chamber 210. Then, the remaining nozzle 310 assemblies 300 are supplied with hydrogen through the second hydrogen supply line, which is suitable for flame propagation of the annular combustion chamber 210. This improves the ignition and combustion efficiency of the hydrogen fuel annular vortex combustion chamber structure 10.

[0054] Reference Figures 5 to 7 According to the present invention, a hydrogen fuel annular vortex combustion chamber structure 10 is provided, wherein the nozzle assembly 300 includes a nozzle 310 and a cap 320. The cap 320 is fitted over the outside of the nozzle 310 and the outer periphery of the cap 320 and the nozzle 310 are spaced apart from each other. The end of the cap 320 near the end of the annular combustion chamber 210 is provided with an inlet 321, and part of the nozzle 310 is exposed in the annular combustion chamber 210 through the inlet 321.

[0055] Understandably, nozzle 310 is the main component for fuel injection, responsible for injecting fuel into the combustion chamber at a certain pressure and velocity. The design of nozzle 310 directly affects the fuel injection pattern and the mixing effect of fuel and air.

[0056] The cap 320 covers the outside of the nozzle 310 and is spaced apart from the outer periphery of the nozzle 310. This provides an additional injection environment for the fuel while optimizing the fuel-air mixture. The cap 320 has an inlet 321 near the end that extends into the annular combustion chamber 210, which allows part of the nozzle 310 to be exposed inside the annular combustion chamber 210.

[0057] The gap between the cap 320 and the nozzle 310 can form a cavity, which can serve as a region for the initial mixing of fuel and air. When fuel is injected from the nozzle 310, it will first be initially mixed with the air in this region before entering the combustion chamber.

[0058] The design of the cap 320 increases the contact area between fuel and air, thereby enhancing the mixing effect. At the same time, the injection port 321 of the cap 320 can further guide the fuel flow, allowing it to be better dispersed in the combustion chamber.

[0059] Reference Figures 5 to 7 According to the hydrogen fuel vortex combustion chamber structure 10 provided by the present invention, an air passage cavity 330 is formed between the inner wall surface of the cap 320 and the outer wall surface of the nozzle 310. The wall surface of the cap 320 located between the outer wall of the casing 100 and the outer wall of the flame tube 200 is provided with a plurality of air inlets 322. The plurality of air inlets 322 are connected to the injection port 321 through the air passage cavity 330.

[0060] Understandably, the cap 320 has several air inlets 322 on the wall between the outer wall of the casing 100 and the outer wall of the flame tube 200. These air inlets 322 allow some air from the casing 100 to enter the air passage 330. When this air passes through the air passage 330 and is ejected from the injection port 321, it carries away some of the heat from the surface of the nozzle 310, thereby effectively reducing the temperature of the nozzle 310. This helps prevent the nozzle 310 from being damaged by overheating, improving the reliability and durability of the combustion chamber.

[0061] The air entering the air passage 330 is used not only to cool the nozzle 310, but also to premix with the hydrogen injected from the nozzle 310. This allows the hydrogen and air to begin mixing before being injected into the annular combustion chamber 210, thereby improving the uniformity and efficiency of the mixing. Uniform mixing contributes to a more stable and efficient combustion process.

[0062] Due to the presence of the air passage 330 and the air inlet 322, the hydrogen-air mixture gains additional propulsion when ejected from the injection port 321. This increases the injection distance of the mixture, thereby extending the mixing distance of the hydrogen and air within the combustion chamber. A longer mixing distance means that the hydrogen and air have more time and opportunity to mix thoroughly, further improving the uniformity of the mixture and combustion efficiency.

[0063] Through the aforementioned premixing and increased mixing distance mechanisms, the hydrogen fuel annular vortex combustor structure 10 can significantly improve the hydrogen-air mixture ratio. A higher mixture ratio means that more hydrogen can undergo combustion reactions with air, thereby improving the thermal efficiency and energy output of the combustor.

[0064] Reference Figures 1 to 4According to the present invention, a hydrogen fuel annular vortex combustion chamber structure 10 is provided, wherein the flame tube 200 includes an outer wall 220, an end wall 230, and an inner wall 240 connected in sequence. The outer wall 220, the end wall 230, and the inner wall 240 enclose and form an annular combustion chamber 210. The outer wall 220 and the inner wall 240 are provided with a gas outlet 250 at a distance from the end wall 230.

[0065] Understandably, the flame tube 200 consists of an outer wall 220, an end wall 230, and an inner wall 240, which together enclose and form an annular combustion chamber 210. This ensures that the combustion process takes place in a closed and controlled environment, thereby improving the stability and efficiency of combustion.

[0066] Specifically, the outer wall 220 and the inner wall 240 of the flame tube are spaced apart at the ends away from the end wall 230 of the flame tube, forming gas outlets 250. The gas outlets 250 allow the combustion gases to be smoothly discharged from the combustion chamber and enter the subsequent turbine or other power unit to generate thrust or power.

[0067] Furthermore, since you mentioned a hydrogen fuel vortex combustor, this type of combustor may have some special design features to accommodate the combustion characteristics of hydrogen fuel. For example, the materials and structure of the flame tube 200 may need to be optimized to withstand the high temperature and high pressure environment generated by hydrogen fuel combustion; at the same time, it is also necessary to consider how to effectively mix hydrogen and air to ensure the stability and efficiency of the combustion process.

[0068] Reference Figures 1 to 4 According to the present invention, a hydrogen fuel annular vortex combustion chamber structure 10 is provided, wherein the casing 100 includes an outer casing wall 110, a side casing wall 120, an inner casing wall 130, and a U-shaped bottom casing wall 140, which together enclose an air intake chamber 150 surrounding the outer periphery of the flame tube 200; the outer casing wall 220 is connected to the U-shaped bottom casing wall 140, the inner casing wall 240 is connected to the inner casing wall 130, the outer casing wall 110 and the U-shaped bottom casing wall 140 together form an air inlet 160, the air outlet 160 communicates with the air intake chamber 150, and the outer casing wall 220 and the inner casing wall 240 are provided with a main combustion hole, a mixing hole, and a cooling hole that communicate with the annular combustion chamber 210 and the air intake passage.

[0069] Understandably, the casing 100 consists of an outer casing wall 110, a side casing wall 120, an inner casing wall 130, and a U-shaped bottom casing wall 140, which together enclose an intake chamber 150. The outer wall of the flame tube 200 is connected to the U-shaped bottom casing wall of the casing 100, while the inner wall of the flame tube 200 is connected to the inner wall of the casing 100. The air inlet 160 is located between the outer casing wall 110 and the U-shaped bottom casing wall 140, and communicates with the intake chamber 150 to supply air to the combustion chamber.

[0070] The main combustion orifice is used to introduce air into the annular combustion chamber 210, where it mixes with and burns the hydrogen fuel. The mixing orifice is used to further mix the air and fuel during combustion, ensuring more uniform and efficient combustion. The cooling orifice is used to cool the flame tube 200, preventing damage due to high temperatures. These orifices may introduce cool air into the walls of the flame tube 200, removing heat through heat exchange.

[0071] Of course, in other embodiments, the cooling holes located inside the annular combustion chamber 210 can also be provided with slotted tongues, so that some air flows in through the cooling holes, is guided by the slotted tongues, and forms an air film cooling inside the flame tube 200.

[0072] Reference Figure 4 According to the present invention, a hydrogen fuel annular vortex combustion chamber structure 10 is provided, wherein the number of nozzle assemblies 300 is greater than or equal to 12 and less than or equal to 16.

[0073] It is understood that the number of nozzle assemblies 300 can be set according to the size of the hydrogen fuel annular vortex combustion chamber structure 10 or the required thrust. In this application, the number of nozzle assemblies 300 is preferably greater than or equal to 12 and less than or equal to 16. Of course, other embodiments can also be set as needed, such as 10 or 20.

[0074] Optionally, the number of nozzle assemblies 300 can be 12, 13, 14, 15 or 16, etc., which can be set according to actual needs.

[0075] The present invention also proposes an aero-engine, which includes the above-described hydrogen fuel annular vortex combustor structure 10. The specific structure of the hydrogen fuel annular vortex combustor structure 10 is as described in the above embodiments. Since the present aero-engine adopts all the technical solutions of all embodiments of the above-described hydrogen fuel annular vortex combustor structure 10, it has at least all the beneficial effects brought about by the technical solutions of the above embodiments, which will not be described in detail here.

[0076] In embodiments of the present invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0077] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0078] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A hydrogen fuel annular vortex combustion chamber structure, characterized in that, include: Casing; A flame tube, which is nested in the housing, is bent to form an annular combustion chamber; A plurality of nozzle assemblies are arranged in a circular array along the circumferential direction of the annular combustion chamber. The nozzle assemblies penetrate the outer wall of the casing and the outer wall of the flame tube and communicate with the annular combustion chamber. The nozzle assemblies are used to inject fuel into the annular combustion chamber. The nozzle assembly is inclined away from the annular combustion chamber in the injection direction, and is set at an angle to both the axial and radial directions of the annular combustion chamber. The nozzle assembly includes a nozzle and a cap. The cap is fitted over the outside of the nozzle and is spaced apart from the outer periphery of the nozzle. The cap has an inlet near the end that extends into the annular combustion chamber. A portion of the nozzle is exposed inside the annular combustion chamber through the inlet. An air passage cavity is formed between the inner wall surface of the cap and the outer wall surface of the nozzle. The wall surface of the cap located between the outer wall of the casing and the outer wall of the flame tube is provided with a plurality of air inlets. The plurality of air inlets are connected to the injection port through the air passage cavity.

2. The hydrogen fuel annular vortex combustion chamber structure according to claim 1, characterized in that, The injection direction of the nozzle assembly is deflected towards the downstream direction of the annular combustion chamber, and the angle between the injection direction of the nozzle assembly and the radial direction of the annular combustion chamber is α, wherein α is greater than or equal to 10° and less than or equal to 30°.

3. The hydrogen fuel annular vortex combustion chamber structure according to claim 1, characterized in that, The nozzle's injection direction is inclined towards the downstream direction of the annular combustion chamber, and the angle between the injection direction of the nozzle assembly and the axial direction of the annular combustion chamber is β, wherein β is greater than or equal to 10° and less than or equal to 30°.

4. The hydrogen fuel annular vortex combustion chamber structure according to claim 1, characterized in that, The nozzle assembly has an incident surface with a plurality of evenly distributed nozzle holes, and a spray cone angle γ is formed between the plurality of nozzle holes, wherein γ is greater than or equal to 65° and less than or equal to 75°.

5. The hydrogen fuel annular vortex combustion chamber structure according to claim 1, characterized in that, The nozzle assembly includes at least two ignition nozzles, and the hydrogen fuel annular vortex combustion chamber structure further includes at least two ignition nozzles. The at least two ignition nozzles are arranged axially symmetrically in the annular combustion chamber. The ignition nozzles are arranged adjacent to each other and are inclined toward the direction of the ignition nozzles.

6. The hydrogen fuel annular vortex combustion chamber structure according to claim 5, characterized in that, The hydrogen fuel annular vortex combustion chamber structure further includes a first hydrogen supply line and a second hydrogen supply line. The first hydrogen supply line is connected to the ignition nozzle, and the second hydrogen supply line is connected to the remaining nozzle assemblies. When the annular combustion chamber is ignited, the ignition nozzle is supplied with hydrogen through the first hydrogen supply line, which is suitable for igniting the annular combustion chamber. Then, the remaining nozzle assemblies are supplied with hydrogen through the second hydrogen supply line, which is suitable for flame propagation in the annular combustion chamber.

7. The hydrogen fuel annular vortex combustion chamber structure according to any one of claims 1-6, characterized in that, The number of nozzle assemblies is greater than or equal to 12 and less than or equal to 16.

8. An aircraft engine, characterized in that, include: The hydrogen fuel annular vortex combustion chamber structure as described in any one of claims 1 to 7.

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