Hydrogen fuel annular vortex combustor assembly and aircraft engine

Abstract

The present application relates to the technical field of engine, and provides a hydrogen fuel annular vortex combustion chamber assembly and an aero-engine. The hydrogen fuel annular vortex combustion chamber assembly comprises a casing, an air introduction cavity, an annular vortex combustion chamber, an air inlet, a gas outlet, a mixing hole, a plurality of first cooling holes and a plurality of hydrogen gas introduction holes; the hydrogen gas introduction hole can also be referred to as a hydrogen gas inclined hole; the gas outlet, the first cooling hole and the plurality of hydrogen gas introduction holes are connected with the annular vortex combustion chamber; the air inlet is connected with the first cooling hole through the air introduction cavity; the hydrogen fuel annular vortex combustion chamber assembly is used for forming a spanwise vortex of airflow air in the annular vortex combustion chamber, which enters the annular vortex combustion chamber through the air inlet, the air introduction cavity and the first cooling hole in sequence, and is used for forming a circumferential vortex of hydrogen gas in the flame tube, which enters the annular vortex combustion chamber through the plurality of hydrogen gas introduction holes. The present application can realize stable flame combustion, ensure the sufficiency of combustion, improve the combustion efficiency, reduce pollutants such as nitrogen oxides, and widen the stable working boundary.

Description

Technical Field

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

[0002] The hydrogen fuel toroidal vortex combustor assembly is a critical component commonly found in aircraft engines. It mixes and combusts 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 toroidal vortex combustor assembly play a vital role in the engine's efficiency, reliability, and environmental friendliness.

[0003] Hydrogen is crucial for applications in fields such as aircraft engines, aerospace propulsion systems, and ground-based gas turbines. It can achieve zero carbon emissions, helping to mitigate global warming and protect the environment.

[0004] However, hydrogen has a lower density and less inertia compared to conventional fuels, resulting in a slower diffusion rate in the flow field. This makes it difficult for hydrogen to mix with air in the hydrogen fuel vortex combustor assembly (vortex combustor), leading to incomplete combustion and affecting combustion efficiency. Summary of the Invention

[0005] This invention provides a hydrogen fuel annular vortex combustor assembly and an aero-engine to solve the technical problem in the prior art where incomplete combustion and reduced combustion efficiency are caused by uneven mixing of hydrogen and air in the annular vortex combustor.

[0006] This invention provides a hydrogen fuel annular vortex combustor assembly, which includes an air inlet chamber, an annular vortex combustor, an air inlet, a gas outlet, multiple first cooling holes, and multiple hydrogen inlet holes. The gas outlet, the first cooling holes, and the multiple hydrogen inlet holes are connected to the annular vortex combustor. The air inlet is connected to the first cooling holes through the air inlet chamber. The hydrogen fuel annular vortex combustor assembly is used to form a spanwise vortex in the annular vortex combustor when the incoming air enters the annular vortex combustor sequentially through the air inlet, the air inlet chamber, and the first cooling holes. Furthermore, it is used to form a circumferential vortex in the region where the spanwise vortex is located when the hydrogen enters the annular vortex combustor through the multiple hydrogen inlet holes.

[0007] According to one embodiment of the present invention, a hydrogen fuel vortex combustor assembly includes: a casing having an annular cavity; an air inlet disposed at the end of the casing along its axial direction and communicating with the annular cavity; a combustion component located within the annular cavity and connected to the cavity wall of the annular cavity, wherein the outer surface of the combustion component and the inner surface of the casing are spaced apart to form an air inlet cavity surrounding the combustion component; an annular vortex combustor, a gas outlet, a first cooling hole, and a hydrogen inlet hole disposed on the combustion component; a plurality of hydrogen pipes arranged at intervals along the circumference of the casing and penetrating the outer peripheral wall of the casing along the radial direction of the casing, the ends of the plurality of hydrogen pipes being connected to the outer peripheral wall of the combustion component and communicating with each hydrogen inlet hole; wherein the extending direction of the hydrogen inlet hole is arranged at an angle to the radial direction of the casing.

[0008] According to one embodiment of the present invention, the combustion component includes: a flame tube located within an annular cavity and connected to the cavity wall of the annular cavity; a vortex combustion chamber, a gas outlet, a first cooling hole, and a hydrogen inlet hole disposed in the flame tube; and a hydrogen box sleeved on the outer peripheral wall of the flame tube, the hydrogen box having a hydrogen accommodating cavity, a plurality of first through holes, and a plurality of second through holes; the plurality of first through holes are located on the inner peripheral wall of the hydrogen box and are spaced apart along its circumference; the plurality of second through holes are located on the outer peripheral wall of the hydrogen box and are spaced apart along its circumference; the plurality of first through holes and the plurality of second through holes... The second through hole connects to the hydrogen containment chamber; multiple first through holes are connected one-to-one to multiple hydrogen inlet holes; the ends of multiple hydrogen pipes are connected one-to-one to multiple second through holes; a slot assembly is located in the annular vortex combustion chamber and connected to the chamber wall of the annular vortex combustion chamber, and at least one slot is formed between the outer peripheral wall of the slot assembly and the inner peripheral wall of the flame tube; the first cooling hole connects to the slot so that the incoming air can enter the slot in sequence through the air inlet, the air inlet chamber and the first cooling hole, and form a spanwise vortex in the annular vortex combustion chamber through the slot.

[0009] According to one embodiment of the present invention, the flame tube includes a first tube wall, an end plate, and a second tube wall; the first tube wall is connected to the second tube wall through the end plate, and the first tube wall, the end plate, and the second tube wall surround to form an annular vortex combustion chamber; the connecting end of the first tube wall has an outer wall surface cooling hole group; the outer wall surface cooling hole group has a plurality of first cooling holes, which are arranged at intervals along the circumference of the first tube wall, and the first tube wall surrounds the second tube wall; the connecting end of the second tube wall has an inner wall surface cooling hole group, which has a plurality of first cooling holes, which are arranged at intervals along the circumference of the second tube wall; an air inlet is located between the end of the casing and the free end of the first tube wall; a gas outlet is located between the free end of the first tube wall and the free end of the second tube wall; and a hydrogen inlet is located in the first tube wall.

[0010] According to one embodiment of the present invention, there are two slots, namely a first slot and a second slot; the slot assembly includes a first slot tongue and a second slot tongue; the first slot tongue extends axially along the casing and is connected to an end plate at its end, the first slot tongue surrounds the second slot tongue, and a first slot is formed between the outer peripheral wall of the first slot tongue, the end plate and the first cylindrical wall; the second slot tongue extends axially along the casing and surrounds the second cylindrical wall, and is connected to an end plate at its end, and a second slot is formed between the outer peripheral wall of the second slot tongue, the end plate and the second cylindrical wall.

[0011] According to one embodiment of the invention, the casing has a first end and a second end disposed opposite to each other in its axial direction; an air inlet and a gas outlet are located at the first end; the flame tube has a third end and a fourth end in the direction from the first end to the second end; and a slot assembly is located at the fourth end.

[0012] According to one embodiment of the present invention, the first cylinder wall has a plurality of second cooling holes and a plurality of mixing holes; the plurality of second cooling holes are arranged at intervals along the circumference of the first cylinder wall and are located at the third end; the plurality of mixing holes are located between the first end and the hydrogen box and are arranged at intervals along the circumference of the first cylinder wall.

[0013] According to one embodiment of the present invention, the free end of the second cylindrical wall is inclined from a first direction to a second direction; the first direction is the direction from the second end to the first end; the second direction is the radial outward direction of the casing.

[0014] According to one embodiment of the present invention, the included angle is 28 degrees to 62 degrees.

[0015] The present invention also provides an aircraft engine, comprising: the hydrogen fuel annular vortex combustor assembly of the above embodiments.

[0016] The features and advantages of the hydrogen fuel annular vortex combustor assembly and aero-engine of the present invention are as follows:

[0017] The incoming air enters the annular vortex combustion chamber sequentially through the air inlet, air introduction cavity, and first cooling hole, forming a spanwise vortex within the chamber. Meanwhile, hydrogen (fuel) enters the annular vortex combustion chamber through multiple hydrogen introduction holes, forming a circumferential vortex in the region of the spanwise vortex. This circumferential vortex, within the flame tube, allows for thorough mixing of hydrogen and incoming air in this region, creating an annular vortex flame stabilization zone. This zone maintains a hydrogen-to-air ratio of 0.01 to 0.016, achieving stable flame combustion, ensuring complete combustion, improving combustion efficiency, reducing pollutants such as nitrogen oxides, and broadening the stable operating boundary. Furthermore, since the incoming air passes through the first cooling hole, its temperature is lower than the gas temperature within the combustion chamber. Therefore, as the incoming air flows through the first cooling hole, it cools the walls of the annular vortex combustion chamber surrounding the cooling hole. Attached Figure Description

[0018] 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.

[0019] Figure 1 This is a perspective view of the hydrogen fuel annular vortex combustion chamber assembly of the present invention.

[0020] Figure 2 This is an exploded view of the hydrogen fuel annular vortex combustion chamber assembly of the present invention.

[0021] Figure 3 This is a side view of the hydrogen fuel annular vortex combustion chamber assembly of the present invention.

[0022] Figure 4 yes Figure 3 A cross-sectional view along the AA direction.

[0023] Figure label:

[0024] 100, Casing; 1001, Annular cavity; 1002, Air inlet; 1003, First end; 1004, Second end; 200, Combustion component; 210, Flame tube; 211, First tube wall; 2111, Hydrogen inlet; 2112, Second cooling hole; 2113, Mixing hole; 212, End plate; 213, Second tube wall; 214, Circular vortex combustion chamber; 215, First cooling hole; 216, Gas outlet; 220, Hydrogen box; 230, Slot assembly; 231, First slot tongue; 2310, First slot; 232, Second slot tongue; 2320, Second slot; 300, Hydrogen pipe; O, Axial direction of the casing. Detailed Implementation

[0025] 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.

[0026] In the description of this embodiment, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this embodiment and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this embodiment.

[0027] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this embodiment, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0028] In this embodiment, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," "link," and "fix" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; 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; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this embodiment based on the specific circumstances.

[0029] 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.

[0030] Figures 1 to 4 The invention illustrates a hydrogen fuel annular vortex combustor assembly and an aero-engine. As shown in the figures, the hydrogen fuel annular vortex combustor assembly of the present invention includes an air inlet chamber, an annular vortex combustor 214, an air inlet 1002, a gas outlet 216, multiple first cooling holes 215, and multiple hydrogen inlet holes 2111. The gas outlet 216, the first cooling holes 215, and the multiple hydrogen inlet holes 2111 are connected to the annular vortex combustor 214. The air inlet 1002 is connected to the first cooling holes 215 through the air inlet chamber. The hydrogen fuel annular vortex combustor assembly is used to form a spanwise vortex in the annular vortex combustor 214 by the incoming air that sequentially enters the annular vortex combustor 214 through the air inlet 1002, the air inlet chamber, and the first cooling holes 215. Furthermore, the hydrogen that enters the annular vortex combustor 214 through the multiple hydrogen inlet holes 2111 forms a circumferential vortex in the region where the spanwise vortex is located.

[0031] In practice, incoming air enters the annular vortex combustion chamber 214 sequentially through air inlet 1002, air inlet cavity, and first cooling hole 215, forming a spanwise vortex within the annular vortex combustion chamber 214. Meanwhile, hydrogen (fuel) enters the annular vortex combustion chamber 214 through multiple hydrogen inlet holes 2111, forming a circumferential vortex in the region of the spanwise vortex, i.e., a circumferential vortex within the flame tube 210. Under the influence of the spanwise and circumferential vortices, hydrogen and incoming air can fully mix in this region (flame tube 210), forming an annular vortex flame stabilization zone. The hydrogen-to-air ratio in the annular vortex flame stabilization zone can range from 0.01 to 0.016, achieving stable flame combustion, ensuring complete combustion, improving combustion efficiency, reducing pollutants such as nitrogen oxides, and broadening the stable operating boundary. In addition, since the incoming air passes through the first cooling hole 215, the temperature of the incoming air is lower than that of the gas in the combustion chamber. Therefore, when the incoming air flows through the first cooling hole 215, it can cool the chamber wall of the annular vortex combustion chamber 214 around the first cooling hole 215.

[0032] In this embodiment, a spanwise vortex can be defined as a vortex whose direction is perpendicular to a predominant flow direction in a flow field; a circumferential vortex can be defined as a vortex whose direction is parallel to a predominant flow direction in a flow field.

[0033] According to one embodiment of the present invention, a hydrogen fuel annular vortex combustor assembly includes a casing 100, a combustion component 200, and a plurality of hydrogen pipes 300. The casing 100 has an annular cavity 1001; an air inlet 1002 is located at the end of the casing 100 along its axial direction O and communicates with the annular cavity 1001; the combustion component 200 is located inside the annular cavity 1001 and connected to the cavity wall of the annular cavity 1001, and there is a gap between the outer surface of the combustion component 200 and the inner surface of the casing 100 to form a space surrounding the combustion component. An air inlet chamber 200; a vortex combustion chamber 214, a gas outlet 216, a first cooling hole 215, and a hydrogen inlet hole 2111 are provided in the combustion component 200; a plurality of hydrogen pipes 300 are arranged at intervals along the circumference of the casing 100 and penetrate the outer peripheral wall of the casing 100 along the radial direction of the casing 100, and the ends of the plurality of hydrogen pipes 300 are connected to the outer peripheral wall of the combustion component 200 and connected to each hydrogen inlet hole 2111; wherein, the extending direction of the hydrogen inlet hole 2111 is set at an angle to the radial direction of the casing 100.

[0034] In practice, after passing through multiple hydrogen pipes 300, hydrogen flows into the annular vortex combustion chamber 214 through multiple hydrogen inlet holes 2111. Since the extension direction of the hydrogen inlet hole 2111 (or hydrogen oblique hole) is set at an angle to the radial direction of the casing 100, the hydrogen can form a circumferential vortex in the region where the spanwise vortex is located.

[0035] In this embodiment, the casing 100 is used to connect the compressor, turbine and afterburner of the aircraft engine; the included angle can be 28 degrees to 62 degrees, for example, the included angle can be 28 degrees, 30 degrees or 60 degrees.

[0036] According to one embodiment of the present invention, the combustion component 200 includes a flame tube 210, a hydrogen box 220, and a slot assembly 230; the flame tube 210 is located inside an annular cavity 1001 and connected to the cavity wall of the annular cavity 1001; an annular vortex combustion chamber 214, a gas outlet 216, a first cooling hole 215, and a hydrogen inlet hole 2111 are disposed in the flame tube 210; the hydrogen box 220 is sleeved on the outer peripheral wall of the flame tube 210, and the hydrogen box 220 has a hydrogen accommodating cavity, a plurality of first through holes, and a plurality of second through holes; the plurality of first through holes are located on the inner peripheral wall of the hydrogen box 220 and are spaced apart along its circumference; the plurality of second through holes are located on the outer peripheral wall of the hydrogen box 220 and are spaced apart along its circumference. The components are arranged at intervals; multiple first through holes and multiple second through holes can connect to the hydrogen containment cavity; multiple first through holes are connected one-to-one to multiple hydrogen inlet holes 2111; the ends of multiple hydrogen pipes 300 are connected one-to-one to multiple second through holes; a slot assembly 230 is located in the annular vortex combustion chamber 214 and is connected to the chamber wall of the annular vortex combustion chamber 214, and at least one slot is formed between the outer peripheral wall of the slot assembly 230 and the inner peripheral wall of the flame tube 210; a first cooling hole 215 connects to the slot so that the incoming air can enter the slot sequentially through the air inlet 1002, the air inlet cavity and the first cooling hole 215, and form a spanwise vortex in the annular vortex combustion chamber 214 through the slot.

[0037] In specific implementation, hydrogen gas enters the hydrogen receiving cavity after passing through multiple hydrogen pipes 300. After entering the hydrogen receiving cavity, it flows into the annular vortex combustion chamber 214 through multiple hydrogen inlet holes 2111 via the first through hole. The slots of the slot assembly 230 not only guide the direction of the incoming air flow, causing the incoming air flow to form a spanwise vortex in the annular vortex combustion chamber 214, thereby making the air and hydrogen mix more evenly, but also increase the contact area between the air and the chamber wall of the annular vortex combustion chamber 214 by guiding the direction of the incoming air flow, thereby expanding the cooling range, that is, being able to cool a larger area of ​​the annular vortex combustion chamber 214 chamber wall.

[0038] It should be noted that the connection part (or connection surface) between the hydrogen box 220 and the flame tube 210 can be thickened to ensure the direction of the velocity of the hydrogen coming out of the hydrogen inlet hole 2111. That is, if the connection part between the hydrogen box 220 and the flame tube 210 is too thin, the depth of the hydrogen inlet hole 2111 will be insufficient, resulting in different velocities of the hydrogen coming out of the hydrogen inlet hole 2111, thus making it difficult to enter the spanwise vortex center.

[0039] According to one embodiment of the present invention, the flame tube 210 includes a first tube wall 211, an end plate 212, and a second tube wall 213; the first tube wall 211 is connected to the second tube wall 213 through the end plate 212, and the first tube wall 211, the end plate 212, and the second tube wall 213 surround to form an annular vortex combustion chamber 214, and the connecting end of the first tube wall 211 has an outer wall surface cooling hole group; the outer wall surface cooling hole group has a plurality of first cooling holes 215, and the plurality of first cooling holes 215 are arranged at intervals along the circumference of the first tube wall 211. The cylinder wall 211 surrounds the second cylinder wall 213; the connecting end of the second cylinder wall 213 has an inner wall surface cooling hole group, the inner wall surface cooling hole group has a plurality of first cooling holes 215, the plurality of first cooling holes 215 are arranged at intervals along the circumference of the second cylinder wall 213; the air inlet 1002 is located between the end of the casing 100 and the free end of the first cylinder wall 211; the gas outlet 216 is located between the free end of the first cylinder wall 211 and the free end of the second cylinder wall 213; the hydrogen inlet hole 2111 is located in the first cylinder wall 211.

[0040] In specific implementation, after the incoming air enters through the first cooling hole 215 of the outer wall cooling hole group, it can cool the connecting end of the first cylinder wall 211 (outer chamber wall of the annular vortex combustion chamber 214). In addition, after the incoming air enters through the first cooling hole 215 of the inner wall cooling hole group, it can cool the connecting end of the second cylinder wall 213 (inner chamber wall of the annular vortex combustion chamber 214).

[0041] In this embodiment, there are two slots, namely a first slot 2310 and a second slot 2320. The slot assembly 230 includes a first slot tongue 231 and a second slot tongue 232. The first slot tongue 231 extends along the axial direction O of the housing 100, and its end is connected to the end plate 212. The first slot tongue 231 surrounds the second slot tongue 232, and the first slot 231 is formed between the outer peripheral wall of the first slot tongue 231, the end plate 212, and the first cylindrical wall 211. The second slot tongue 232 extends along the axial direction O of the housing 100 and surrounds the second cylindrical wall 213. Its end is connected to the end plate 212, and the second slot 232 is formed between the outer peripheral wall of the second slot tongue 232, the end plate 212, and the second cylindrical wall 213. The casing 100 has a first end 1003 and a second end 1004 disposed opposite to each other along its axial direction O; an air inlet 1002 and a gas outlet 216 are located at the first end 1003; the flame tube 210 has a third end and a fourth end along the direction from the first end 1003 to the second end 1004; and a slot assembly 230 is located at the fourth end.

[0042] According to one embodiment of the present invention, the first cylindrical wall 211 has a plurality of second cooling holes 2112 and a plurality of mixing holes 2113; the plurality of second cooling holes 2112 are arranged at intervals along the circumference of the first cylindrical wall 211 and are located at the third end; the plurality of mixing holes 2113 are located between the first end 1003 and the hydrogen box 220 and are arranged at intervals along the circumference of the first cylindrical wall 211.

[0043] In specific implementation, the incoming air can enter the air inlet cavity through the air inlet 1002. After entering the air inlet cavity, part of the incoming air enters the annular vortex combustion chamber 214 through the second cooling hole 2112. Since the second cooling hole 2112 is located at the gas outlet 216, the temperature of the incoming air is lower than the temperature of the gas. Therefore, the incoming air can reduce the temperature of the chamber wall (first cylinder wall 211) of the annular vortex combustion chamber 214 at the gas outlet 216. Another part of the incoming air can be injected radially along the casing 100 after passing through multiple mixing holes 2113, so as to adjust the internal temperature distribution of the annular vortex combustion chamber 214 radially along the casing 100 and reduce hot spots. In addition, part of the air entering through the mixing holes 2113 is used to form a spanwise vortex in the main combustion zone (the area where the spanwise vortex is located) and help mix.

[0044] In this embodiment, the hot spot refers to the ratio of the maximum temperature of the gas outlet 216 exceeding the average value to the temperature rise of the annular vortex combustion chamber 214, and the lower the ratio, the better.

[0045] According to one embodiment of the present invention, the free end of the second cylindrical wall 213 is inclined from a first direction to a second direction; the first direction is the direction from the second end 1004 to the first end 1003; the second direction is the radially outward direction of the casing 100, that is, the end of the flame tube 210 is configured as a tapered structure.

[0046] In practical implementation, the above-mentioned structural design can prevent the generation of vortices at the gas outlet 216, reduce the residence time of the gas, and prevent the walls of the annular vortex combustion chamber 214 at the outlet from being burned. In other words, the space at the gas outlet 216 is smaller, so there is no space for the vortex to form.

[0047] In summary, the technical solution of this invention is a ring vortex flame-stabilized combustion. For the ring vortex combustion chamber 214, by eliminating the conventional oblique holes on the head end face used to form the circumferential vortex, the air content in the main combustion zone is ensured to be approximately 60%, and the hydrogen-to-air ratio is within the range of 0.01 to 0.016, thus reducing nitrogen oxide emissions. Multiple cooling holes (first cooling hole 215 and second cooling hole 2112) are provided in the main combustion zone, and slotted tongues (first slotted tongue 231 and second slotted tongue 232) are used to guide the direction of the incoming airflow, solving the cooling problem while forming a spanwise vortex. A ring of hydrogen boxes 220 is installed on the outer wall of the flame tube 210, and hydrogen is delivered into the hydrogen boxes 220 using six hydrogen pipes 300. 70 to 90 oblique hydrogen holes are opened on the thickened wall surface where the hydrogen boxes 220 connect to the outer wall of the flame tube 210, allowing the hydrogen to achieve an oblique injection velocity of 800 m / s. The circumferential vortex is formed by the high-speed injection of hydrogen gas through these obliquely directed nozzles. These oblique nozzles can directly inject hydrogen gas into the center of the inner circumferential vortex of the flame tube 210 while forming the circumferential vortex, promoting flame stability and stable combustion. The inner wall of the flame tube 210 contracts at the outlet to prevent the formation of vortices near the outlet, which could create a dead zone and cause excessively high temperatures that could burn out the wall of the flame tube 210, thus ensuring experimental safety.

[0048] The present invention also provides an aero-engine including the hydrogen fuel annular vortex combustor assembly of the above embodiments. The specific structure, working principle, and beneficial effects of the hydrogen fuel annular vortex combustor assembly are the same as those of the above embodiments, and will not be repeated here.

[0049] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "method," "specific method," or "some methods," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or method is included in at least one embodiment or method of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or method. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or methods. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or methods described in this specification, as well as the features of different embodiments or methods.

[0050] 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 assembly, characterized in that, The hydrogen fuel annular vortex combustor assembly has an air inlet chamber, an annular vortex combustor (214), an air inlet (1002), a gas outlet (216), a plurality of first cooling holes (215) and a plurality of hydrogen inlet holes (2111). The gas outlet (216), the first cooling hole (215) and the plurality of hydrogen inlet holes (2111) can be connected to the annular vortex combustion chamber (214). The air inlet (1002) is connected to the first cooling hole (215) through the air introduction cavity; The hydrogen fuel annular vortex combustor assembly is used to cause incoming air that enters the annular vortex combustor (214) sequentially through the air inlet (1002), the air inlet cavity and the first cooling hole (215) to form a spanwise vortex in the annular vortex combustor (214), and to cause hydrogen that enters the annular vortex combustor (214) through the plurality of hydrogen inlet holes (2111) to form a circumferential vortex in the region where the spanwise vortex is located; The hydrogen fuel annular vortex combustor assembly includes: The casing (100) has an annular cavity (1001); the air inlet (1002) is located at the end of the casing (100) along its axial (O) direction and can communicate with the annular cavity (1001). A combustion component (200) is located inside the annular cavity (1001) and connected to the cavity wall of the annular cavity (1001). The outer surface of the combustion component (200) and the inner surface of the casing (100) are spaced apart to form an air inlet cavity surrounding the combustion component (200). The annular vortex combustion chamber (214), the gas outlet (216), the first cooling hole (215), and the hydrogen inlet hole (2111) are provided in the combustion component (200). Multiple hydrogen pipes (300) are arranged at intervals along the circumference of the casing (100) and penetrate the outer peripheral wall of the casing (100) radially. The ends of the multiple hydrogen pipes (300) are connected to the outer peripheral wall of the combustion component (200) and communicate with each of the hydrogen inlet holes (2111). The hydrogen inlet hole (2111) extends at an angle to the radial direction of the casing (100); The combustion component (200) includes: The flame tube (210) is located inside the annular cavity (1001) and connected to the cavity wall of the annular cavity (1001); the vortex combustion chamber (214), the gas outlet (216), the first cooling hole (215) and the hydrogen inlet hole (2111) are provided in the flame tube (210). A hydrogen box (220) is fitted onto the outer peripheral wall of the flame tube (210). The hydrogen box (220) has a hydrogen accommodating cavity, a plurality of first through holes, and a plurality of second through holes. The plurality of first through holes are located on the inner peripheral wall of the hydrogen box (220) and are spaced apart along its circumference. The plurality of second through holes are located on the outer peripheral wall of the hydrogen box (220) and are spaced apart along its circumference. The plurality of first through holes and the plurality of second through holes can communicate with the hydrogen accommodating cavity. The plurality of first through holes are connected one-to-one with the plurality of hydrogen inlet holes (2111). The ends of the plurality of hydrogen pipes (300) are connected one-to-one with the plurality of second through holes. The slot assembly (230) is located inside the annular vortex combustion chamber (214) and connected to the chamber wall of the annular vortex combustion chamber (214). At least one slot is formed between the outer peripheral wall of the slot assembly (230) and the inner peripheral wall of the flame tube (210). The first cooling hole (215) communicates with the slot so that the incoming air can enter the slot in sequence through the air inlet (1002), the air inlet cavity and the first cooling hole (215), and form the spanwise vortex in the annular vortex combustion chamber (214) through the slot.

2. The hydrogen fuel annular vortex combustor assembly according to claim 1, characterized in that, The flame tube (210) includes a first tube wall (211), an end plate (212), and a second tube wall (213). The first cylindrical wall (211) is connected to the second cylindrical wall (213) through the end plate (212). The first cylindrical wall (211), the end plate (212) and the second cylindrical wall (213) surround the annular vortex combustion chamber (214). The connecting end of the first cylindrical wall (211) has an outer wall surface cooling hole group. The outer wall surface cooling hole group has a plurality of first cooling holes (215). The plurality of first cooling holes (215) are arranged at intervals along the circumference of the first cylindrical wall (211). The first cylindrical wall (211) surrounds the second cylindrical wall (213). The connecting end of the second cylinder wall (213) has an inner wall surface cooling hole group, the inner wall surface cooling hole group has a plurality of first cooling holes (215), and the plurality of first cooling holes (215) are arranged at intervals along the circumference of the second cylinder wall (213); The air inlet (1002) is located between the end of the casing (100) and the free end of the first cylindrical wall (211); The gas outlet (216) is located between the free end of the first cylinder wall (211) and the free end of the second cylinder wall (213); The hydrogen inlet (2111) is located on the first cylinder wall (211).

3. The hydrogen fuel annular vortex combustor assembly according to claim 2, characterized in that, There are two grooves, namely the first groove (2310) and the second groove (2320). The slot assembly (230) includes a first slot tongue (231) and a second slot tongue (232); The first slotted tongue (231) extends along the axial direction (O) of the casing (100), and the end of the first slotted tongue (231) is connected to the end plate (212). The first slotted tongue (231) surrounds the second slotted tongue (232), and the first slot (2310) is formed between the outer peripheral wall of the first slotted tongue (231), the end plate (212), and the first cylindrical wall (211). The second slotted tongue (232) extends along the axial direction (O) of the casing (100) and surrounds the second cylindrical wall (213), and the end of the second slotted tongue (232) is connected to the end plate (212). The second slot (2320) is formed between the outer peripheral wall of the second slotted tongue (232), the end plate (212) and the second cylindrical wall (213).

4. The hydrogen fuel annular vortex combustor assembly according to claim 2, characterized in that, The casing (100) has a first end (1003) and a second end (1004) disposed opposite to each other along its axial (O) direction. The air inlet (1002) and the gas outlet (216) are located at the first end (1003). The flame tube (210) has a third end and a fourth end along the direction from the first end (1003) to the second end (1004); The groove assembly (230) is located at the fourth end.

5. The hydrogen fuel annular vortex combustor assembly according to claim 4, characterized in that, The first cylinder wall (211) has a plurality of second cooling holes (2112) and a plurality of mixing holes (2113). A plurality of second cooling holes (2112) are arranged at circumferential intervals along the first cylinder wall (211) and located at the third end; Multiple mixing holes (2113) are located between the first end (1003) and the hydrogen box (220) and are arranged at intervals along the circumferential direction of the first cylinder wall (211).

6. The hydrogen fuel annular vortex combustor assembly according to claim 4, characterized in that, The free end of the second cylindrical wall (213) is inclined from the first direction to the second direction; The first direction is the direction from the second end (1004) to the first end (1003); The second direction is the radial outward direction of the casing (100).

7. The hydrogen fuel annular vortex combustor assembly of any one of claims 1 to 6, wherein, The included angle is between 28 degrees and 62 degrees.

8. An aeroengine characterised in that, include: The hydrogen fuel annular vortex combustor assembly as described in any one of claims 1 to 7.

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