Hydrogen fuel annular vortex combustor and aircraft engine

Abstract

The application relates to the technical field of combustion chamber design, and discloses a hydrogen fuel annular vortex combustion chamber and an aero-engine, which comprises a casing, a flame tube, a hydrogen pipeline and vortex vanes; the flame tube is arranged at intervals from the casing, an air flow space is formed between the flame tube and the casing, and an air inlet hole is formed in the flame tube and communicates with the air flow space; the hydrogen pipeline comprises an air inlet pipe, annular pipes and a communicating pipe, the annular pipes are arranged in communication with the communicating pipe, the air inlet pipe is arranged in communication with the annular pipes, and the injection holes are arranged towards the air inlet hole; part of the structure of the vortex vanes is arranged at intervals from the flame tube to form a vortex space, and the air inlet hole communicates with the vortex space. By arranging the annular pipes, the internal pressure balance of the hydrogen pipeline is ensured, the hydrogen fuel is mixed with air from all directions, high-uniformity mixing of the hydrogen fuel and the air is realized, the combustion efficiency of the hydrogen fuel is improved, the occurrence of local high temperature in the combustion chamber is reduced, and the emission of pollutants is reduced.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of combustion chamber design, in particular to a hydrogen fuel annular vortex combustion chamber and an aero-engine. BACKGROUND

[0002] Hydrogen fuel has great prospects as a clean and renewable energy source. The advantages and potential of applying hydrogen fuel to the field of aviation and gas turbine power are emerging. As a small aero-engine combustion chamber, the annular vortex combustion chamber is commonly used in various low-cost small aero-engines and APUs of large aero-engines. The annular vortex combustion chamber uses vortex vanes instead of vortex inducers, which greatly reduces the cost, but as a trade-off, the annular vortex combustion chamber has poor flameout performance. The highly reactive chemical properties of hydrogen fuel bring excellent point flameout performance to the hydrogen fuel aero-engine combustion chamber.

[0003] However, in the related art, the hydrogen fuel and air of the engine using hydrogen fuel as the main fuel are not uniformly mixed, which reduces the combustion efficiency and makes the energy of the fuel not fully utilized. SUMMARY

[0004] Therefore, the present application provides a hydrogen fuel annular vortex combustion chamber and an aero-engine to solve the problem of uneven mixing of hydrogen fuel and air.

[0005] In a first aspect, the present application provides a hydrogen fuel annular vortex combustion chamber, comprising: a casing; a flame tube, which is spaced apart from the casing, and an air flow space is formed between the flame tube and the casing, a plurality of air inlet holes are formed in the flame tube, the air inlet holes are spaced apart, and the air flow space is in communication with the air inlet holes; a hydrogen gas pipeline, which is arranged on one side of the flame tube close to the casing, the hydrogen gas pipeline comprises an air inlet pipe, a plurality of annular pipes and a communication pipe, the annular pipes are arranged, the annular pipes are in communication with the communication pipe, the air inlet pipe is in communication with the same annular pipe, a plurality of injection holes are formed in the communication pipe, the injection holes are arranged one by one corresponding to the air inlet holes, and the injection holes are arranged towards the air inlet holes; and a vortex vane, which is arranged on the side of the flame tube away from the hydrogen gas pipeline, part of the structure of the vortex vane is spaced apart from the flame tube to form a vortex space, and the air inlet holes are in communication with the vortex space.

[0006] Beneficial effects: By arranging a plurality of annular pipes, the hydrogen fuel is mixed with air from all directions under the premise of ensuring the internal pressure balance of the hydrogen gas pipeline, high uniformity mixing of hydrogen fuel and air is achieved, the combustion efficiency of hydrogen fuel is improved, local high temperature in the combustion chamber is reduced, and pollutant emissions are reduced.

[0007] In an alternative embodiment, the flame tube comprises an arc-shaped portion and a main body portion, the arc-shaped portion is connected with the main body portion, the air inlet hole is arranged on the arc-shaped portion, and the hydrogen pipeline is arranged on one side of the arc-shaped portion close to the casing.

[0008] In an alternative embodiment, part of the arc-shaped portion forms the communication pipe, the air inlet hole penetrates through the communication pipe, and the air inlet hole is in communication with the communication pipe through the injection hole.

[0009] In an alternative embodiment, the end of the arc-shaped portion is spaced apart from the main body portion, the end of the arc-shaped portion and the main body portion enclose a gas film cavity, the main body portion is provided with a gas film hole in communication with the gas film cavity, and the gas film hole is arranged in the circumferential direction of the hydrogen fuel ring vortex combustion chamber.

[0010] Beneficial effects: A plurality of gas film holes are arranged in the circumferential direction of the hydrogen fuel ring vortex combustion chamber, thereby forming a circumferentially continuous gas film, so that a circumferentially continuous ring vortex flow field structure is formed in the gas film cavity, and the hydrogen fuel enters the ring vortex flow field and is directly premixed and combusted after being ignited by the spark plug, so as to overcome the problem of fast flame propagation speed of hydrogen and easy backfire, thereby enabling efficient and stable combustion of hydrogen fuel.

[0011] In an alternative embodiment, a plurality of air inlet pipes are arranged, the plurality of air inlet pipes are arranged in a spaced apart manner and in communication with the same annular pipe, a plurality of vortex sheets are arranged, the plurality of vortex sheets are arranged in a spaced apart manner, and the number of the arranged air inlet pipes is an integer multiple of the number of the arranged vortex sheets.

[0012] Beneficial effects: The number of the arranged air inlet pipes is an integer multiple of the number of the arranged vortex sheets, which ensures stable pressure in the hydrogen pipeline and uniform mixing of hydrogen fuel and air.

[0013] In an alternative embodiment, the diameter of the annular pipe is D1, and 2mm≤D1≤4mm is satisfied.

[0014] Beneficial effects: By limiting the diameter of the annular pipe, the flow rate of the hydrogen fuel in the annular pipe is ensured, and the uniformity of the hydrogen fuel in the annular pipe is ensured.

[0015] In an alternative embodiment, the diameter of the communication pipe is D2, and D2<D1 is satisfied.

[0016] In an alternative embodiment, the diameter of the injection hole is D3, and 0<D3≤0.6mm is satisfied.

[0017] Beneficial effect: By limiting the diameter size of the injection hole, the hydrogen fuel uniformity in the injection hole is ensured while the speed of the hydrogen fuel ejected from the injection hole is ensured.

[0018] In an alternative embodiment, the flame tube is provided with a main combustion hole and a mixing hole, the main combustion hole and the mixing hole are arranged at intervals, the main combustion hole is in communication with the air flow space, and the mixing hole is in communication with the air flow space.

[0019] Beneficial effect: The gas after mixing of the hydrogen fuel and air enters the flame tube, burns to generate fuel gas in the flame tube, and the fuel gas further mixes with the air flowing into the main combustion hole and the mixing hole and then enters the turbine to do work.

[0020] In a second aspect, the present application also provides an aero-engine comprising the above-mentioned hydrogen fuel annular vortex combustion chamber. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the specific embodiments or prior art of the present application, the drawings needed in the specific embodiment or prior art description will be briefly introduced below. Obviously, the drawings in the following description are some embodiments of the present application, and those skilled in the art can also obtain other drawings according to these drawings without creative labor.

[0022] Figure 1 It is a front view of the hydrogen fuel annular vortex combustion chamber of the embodiment of the present application;

[0023] Figure 2 It is a rear view of the hydrogen fuel annular vortex combustion chamber of the embodiment of the present application;

[0024] Figure 3 It is a structural schematic view of the flame tube and the hydrogen gas pipeline of the embodiment of the present application;

[0025] Figure 4 It is a flow schematic view of the hydrogen fuel and air in the hydrogen fuel annular vortex combustion chamber of the embodiment of the present application.

[0026] Explanation of reference signs:

[0027] 10, casing; 20, flame tube; 21, air flow space; 22, air inlet hole; 23, arc-shaped part; 24, main body part; 241, film hole; 25, main combustion hole; 26, mixing hole; 30, hydrogen gas pipeline; 31, air inlet pipe; 32, annular pipe; 33, communication pipe; 331, injection hole; 40, vortex sheet; 41, vortex space. DETAILED DESCRIPTION

[0028] In order to make the purposes, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are some but not all of the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative efforts belong to the protection scope of the present application.

[0029] The embodiments of the present application are described below with reference to the drawings. Figures 1 to 4

[0030] According to the embodiments of the present application, in a first aspect, a hydrogen fuel annular vortex combustion chamber is provided, comprising: a casing 10, a flame tube 20, a hydrogen pipeline 30 and a vortex sheet 40. The flame tube 20 is arranged spaced apart from the casing 10, and an air flow space 21 is formed between the flame tube 20 and the casing 10. The flame tube 20 is provided with air inlet holes 22, and the air inlet holes 22 are arranged spaced apart from each other. The air flow space 21 is in communication with the air inlet holes 22. The hydrogen pipeline 30 is arranged on one side of the flame tube 20 close to the casing 10. The hydrogen pipeline 30 comprises an air inlet pipe 31, annular pipes 32 and a communication pipe 33. The annular pipes 32 are arranged spaced apart from each other. Each of the annular pipes 32 is in communication with the communication pipe 33. The air inlet pipe 31 is in communication with the same annular pipe 32. The communication pipe 33 is provided with injection holes 331. The injection holes 331 are arranged spaced apart from each other. Each of the injection holes 331 corresponds to one of the air inlet holes 22. The injection holes 331 are arranged towards the air inlet holes 22. The vortex sheet 40 is arranged on one side of the flame tube 20 away from the hydrogen pipeline 30. Part of the structure of the vortex sheet 40 is arranged spaced apart from the flame tube 20 to form a vortex space 41. The air inlet holes 22 are in communication with the vortex space 41.

[0031] By arranging the annular pipes 32, the hydrogen fuel is mixed with air from all directions under the premise of ensuring the internal pressure balance of the hydrogen pipeline 30. The high uniformity mixing of the hydrogen fuel and air is achieved. The combustion efficiency of the hydrogen fuel is improved. The occurrence of local high temperature in the combustion chamber is reduced. The emission of pollutants is reduced.

[0032] It should be noted that the hydrogen fuel annular vortex combustion chamber in the present embodiment is an annular structure, Figure 1 and Figure 2 The structure in the present embodiment is one-eighth of a full annular structure. The structure model shown in Figure 1 and Figure 2 is circumferentially arrayed to obtain the original model of the present embodiment.

[0033] Specifically, in the present embodiment, the annular pipes 32 are two, and the annular pipes 32 are annular pipelines along the circumference of 360° of the hydrogen fuel annular vortex combustion chamber.

[0034] ​It should be noted that the number of annular pipes 32 can be adjusted by those skilled in the art according to actual needs.

[0035] Further, the annular pipes 32 can move in the axial direction or the radial direction of the hydrogen fuel annular vortex combustion chamber.

[0036] Specifically, the flow of hydrogen fuel and air in the hydrogen fuel annular vortex combustion chamber is shown in Figure 4 , Figure 4 The solid line in the figure is the air flow schematic line, and the dashed line is the hydrogen fuel flow schematic line.

[0037] Specifically, the flow of hydrogen fuel and air in the hydrogen fuel annular vortex combustion chamber is shown in Figure 3 , the hydrogen fuel enters the annular pipe 32 on the upper side of the figure through the intake pipe 31, and the hydrogen fuel flows into the communication pipe 33 through the intake pipe 31, part of the hydrogen fuel flows to the intake hole 22 through the injection hole 331, and then flows to the vortex space 41 through the intake hole 22; The hydrogen fuel and air entering the vortex space 41 are uniformly mixed and form a vortex through the vortex sheet 40; The hydrogen fuel not flowing out of the injection hole 331 in the communication pipe 33 enters the annular pipe 32 on the lower side of the figure, automatically balances the pressure inside the hydrogen gas pipeline 30, and further ensures the high uniformity of hydrogen gas mixing in all directions.

[0038] In one embodiment, as shown in Figure 3 , the flame tube 20 includes an arc-shaped portion 23 and a main body portion 24, the arc-shaped portion 23 is connected with the main body portion 24, the intake hole 22 is arranged on the arc-shaped portion 23, and the hydrogen gas pipeline 30 is arranged on one side of the arc-shaped portion 23 close to the casing 10.

[0039] In one embodiment, as shown in Figure 3 , part of the arc-shaped portion 23 forms a communication pipe 33, the intake hole 22 penetrates the communication pipe 33, and the intake hole 22 communicates with the communication pipe 33 through the injection hole 331.

[0040] Specifically, part of the arc-shaped portion 23 is a hollow cavity to form the communication pipe 33, the intake hole 22 penetrates the communication pipe 33, and the hole wall of the intake hole 22 separates the intake hole 22 from the communication pipe 33; The injection hole 331 is arranged on the hole wall of the intake hole 22 to communicate with the intake hole 22, so as to realize the mixing of hydrogen fuel and air.

[0041] It should be noted that in other embodiments not shown, the communication pipe 33 and the arc-shaped portion 23 can also be separately arranged, but the injection hole 331 needs to be arranged towards the intake hole 22.

[0042] In one embodiment, as shown in Figure 1As shown, the end of the arc-shaped part 23 is spaced apart from the main body part 24, and the gas film cavity is formed between the end of the arc-shaped part 23 and the main body part 24. The main body part 24 is provided with a gas film hole 241 in communication with the gas film cavity. The gas film hole 241 is arranged along the circumference of the hydrogen fuel ring vortex combustion chamber.

[0043] It should be noted that the hydrogen fuel ring vortex combustion chamber is provided with a plurality of gas film holes 241 along the circumference, thereby forming a circumferentially continuous gas film, so that a circumferentially continuous ring vortex flow field structure is formed in the gas film cavity, so that the hydrogen fuel enters the ring vortex flow field and is directly premixed and organized combustion after being ignited by the spark plug, thereby overcoming the problem of fast hydrogen flame propagation speed and easy backfire, and thereby enabling efficient and stable combustion of hydrogen fuel.

[0044] In one embodiment, as shown in Figure 2 The intake pipe 31 is provided with a plurality of intake pipes 31, and the plurality of intake pipes 31 are spaced apart and arranged in communication with the same annular pipe 32. The vortex sheet 40 is provided with a plurality of vortex sheets 40, and the plurality of vortex sheets 40 are spaced apart. The number of intake pipes 31 is an integer multiple of the number of vortex sheets 40.

[0045] It should be noted that the number of intake pipes 31 is an integer multiple of the number of vortex sheets 40, which ensures the stability of the pressure in the hydrogen pipe 30, and thereby ensures the uniform mixing of hydrogen fuel and air.

[0046] In one embodiment, the diameter of the annular pipe 32 is D1, which satisfies 2mm≤D1≤4mm.

[0047] It should be noted that by limiting the diameter of the annular pipe 32, the flow rate of the hydrogen fuel in the annular pipe 32 is ensured, and the uniformity of the hydrogen fuel in the annular pipe 32 is ensured.

[0048] It should be noted that when D1<2mm, the flow rate of the hydrogen fuel in the annular pipe 32 is fast, but the uniformity of the hydrogen fuel in the annular pipe 32 is poor, which does not meet the requirements; when D1>4mm, the uniformity of the hydrogen fuel in the annular pipe 32 is good, but the flow rate of the hydrogen fuel in the annular pipe 32 is slow, which does not meet the requirements.

[0049] In one embodiment, the diameter of the communication pipe 33 is D2, which satisfies D2<D1.

[0050] In one embodiment, the diameter of the injection hole 331 is D3, which satisfies 0<D3≤0.6mm.

[0051] It should be noted that by limiting the diameter of the injection hole 331, the speed of the hydrogen fuel injected from the injection hole 331 is ensured, and the uniformity of the hydrogen fuel in the injection hole 331 is ensured.

[0052] It should be noted that when D3>0.6mm, the hydrogen fuel in the injection hole 331 is uniform, but the speed of the hydrogen fuel sprayed from the injection hole 331 is slow, which does not meet the requirements.

[0053] In one embodiment, as shown in FIG. 1, the flame tube 20 is provided with a main combustion hole 25 and a mixing hole 26, the main combustion hole 25 is spaced apart from the mixing hole 26, the main combustion hole 25 is in communication with the air flow space 21, and the mixing hole 26 is in communication with the air flow space 21. Figure 1

[0054] It should be noted that the gas after mixing of the hydrogen fuel and the air enters the flame tube 20, burns in the flame tube 20 to generate combustion gas, and the combustion gas further mixes with the air flowing into the main combustion hole 25 and the mixing hole 26 to enter the turbine to do work.

[0055] According to the embodiments of the present application, the second aspect further provides an aero-engine comprising the above-mentioned hydrogen fuel annular combustion chamber.

[0056] Although the embodiments of the present application are described in conjunction with the drawings, various modifications and changes can be made by those skilled in the art without departing from the spirit and scope of the present application, and such modifications and changes fall within the scope defined by the present application.​

Claims

1. A hydrogen fuel annular vortex combustor characterized by, Comprise: A machine case (10); A flame tube (20) is spaced apart from the machine case (10), an air flow space (21) is formed between the flame tube (20) and the machine case (10), the flame tube (20) is provided with air inlet holes (22), the air inlet holes (22) are spaced apart, the air flow space (21) is communicated with the air inlet holes (22); A hydrogen pipeline (30) is arranged on one side of the flame tube (20) close to the machine case (10), the hydrogen pipeline (30) comprises an air inlet pipe (31), an annular pipe (32) and a communication pipe (33), the annular pipe (32) is provided with a plurality of annular pipes (32), the annular pipe (32) is communicated with the communication pipe (33), the air inlet pipe (31) is communicated with the same annular pipe (32), the communication pipe (33) is provided with a plurality of injection holes (331), the injection holes (331) are communicated with the air inlet holes (22) one by one, and the injection holes (331) are arranged towards the air inlet holes (22); A vortex sheet (40) is arranged on the side of the flame tube (20) away from the hydrogen pipeline (30), part of the structure of the vortex sheet (40) is spaced apart from the flame tube (20) to form a vortex space (41), and the air inlet holes (22) are communicated with the vortex space (41); The flame tube (20) comprises an arc-shaped part (23) and a main body part (24), the arc-shaped part (23) is connected with the main body part (24), the air inlet holes (22) are arranged on the arc-shaped part (23), and the hydrogen pipeline (30) is arranged on one side of the arc-shaped part (23) close to the machine case (10); Part of the arc-shaped part (23) forms the communication pipe (33), the air inlet holes (22) penetrate through the communication pipe (33), and the air inlet holes (22) are communicated with the communication pipe (33) through the injection holes (331).

2. The hydrogen fuel annular vortex combustor of claim 1, wherein, The end of the arc-shaped part (23) is spaced apart from the main body part (24), the arc-shaped part (23) and the main body part (24) form an air film cavity, the main body part (24) is provided with air film holes (241), the air film holes (241) are communicated with the air film cavity, and the air film holes (241) are arranged along the circumference of the hydrogen fuel ring vortex combustion chamber.

3. The hydrogen fuel annular vortex combustor according to any one of claims 1-2, wherein, The air inlet pipe (31) is provided with a plurality of air inlet pipes (31), the air inlet pipes (31) are spaced apart and communicated with the same annular pipe (32), the vortex sheet (40) is provided with a plurality of vortex sheets (40), the vortex sheets (40) are spaced apart, and the number of the air inlet pipes (31) is an integer multiple of the number of the vortex sheets (40).

4. The hydrogen fuel annular vortex combustor according to any one of claims 1-2, wherein, The diameter of the annular pipe (32) is D1, and 2mm≤D1≤4mm is satisfied.

5. The hydrogen fuel annular vortex combustor of claim 4, wherein, The diameter of the communication pipe (33) is D2, and D2 6. The hydrogen fuel annular vortex combustor according to any one of claims 1-2, wherein, The diameter of the injection hole (331) is D3, satisfying 0 < D3 ≤ 0.6 mm.

7. The hydrogen fuel annular vortex combustor according to any one of claims 1-2, wherein, The flame tube (20) is provided with a main combustion hole (25) and a mixing hole (26), the main combustion hole (25) and the mixing hole (26) are arranged at intervals, the main combustion hole (25) communicates with the air flow space (21), and the mixing hole (26) communicates with the air flow space (21).

8. An aeroengine characterised in that, A hydrogen fuel annular vortex combustor according to any one of claims 1 to 7.

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