Hydrogen fuel ring turbine combustor and aero-engine

Abstract

The invention relates to the technical field of combustion chamber design, and discloses a hydrogen fuel ring vortex combustion chamber and an aero-engine, the hydrogen fuel ring vortex combustion chamber comprises a casing, a flame tube, a hydrogen pipeline and a vortex sheet; the flame tube and the cartridge receiver are arranged at an interval, an air flowing space is formed between the flame tube and the cartridge receiver, and air inlet holes communicated with the air flowing space are formed in the flame tube; the hydrogen pipeline comprises a gas inlet pipe, annular pipes and a communicating pipe, the multiple annular pipes communicate with the communicating pipe, the gas inlet pipe communicates with the annular pipes, and the spraying holes face the gas inlet holes; partial structures of the vortex pieces and the flame tube are arranged at intervals to form vortex spaces, and the air inlet holes communicate with the vortex spaces. The annular pipes are arranged, so that the pressure balance in the hydrogen pipeline is guaranteed, hydrogen fuel is mixed with air in all directions, high-uniformity mixing of the hydrogen fuel and the air is achieved, the combustion efficiency of the hydrogen fuel is improved, local high temperature in the combustion chamber is reduced, and emission of pollutants is reduced.

Description

Technical Field

[0001] The invention relates to the technical field of combustion chamber design, and in particular to a hydrogen fuel annular vortex combustion chamber and an aeroengine. Background Art

[0002] Hydrogen fuel is a promising clean and renewable energy source. The advantages and potential of applying hydrogen fuel to aviation and gas engine power are emerging. As a small aircraft engine combustion chamber, the vortex combustion chamber is commonly used in various low-cost small aircraft engines and APUs of large aircraft engines. The vortex combustion chamber uses vortex sheets instead of vortex generators, which greatly reduces costs. However, as a price, the flameout performance of the vortex combustion chamber is poor. The extremely active chemical properties of hydrogen fuel bring excellent ignition and flameout performance to the hydrogen fuel aircraft engine combustion chamber.

[0003] However, in the related art, in engines using hydrogen fuel as the main fuel, the hydrogen fuel is not mixed evenly with the air, which reduces the combustion efficiency and makes it impossible to fully utilize the energy of the fuel. Summary of the invention

[0004] In view of this, the present invention provides a hydrogen fuel vortex combustion chamber and an aircraft engine to solve the problem of uneven mixing of hydrogen fuel and air.

[0005] In a first aspect, the present invention provides a hydrogen fuel annular vortex combustion chamber, comprising: a casing; a flame tube, the flame tube is spaced apart from the casing, an air flow space is formed between the flame tube and the casing, an air intake hole is provided on the flame tube, a plurality of the air intake holes are spaced apart, and the air flow space is connected to the air intake hole; a hydrogen pipeline, the hydrogen pipeline is provided on a side of the flame tube close to the casing, the hydrogen pipeline comprises an air intake pipe, an annular pipe and a connecting pipe, a plurality of the annular pipes are provided, a plurality of the annular pipes are connected to the connecting pipe, the air intake pipe is connected to the same annular pipe, a spray hole is provided on the connecting pipe, a plurality of the spray holes are provided, a plurality of the spray holes are arranged in a one-to-one correspondence with a plurality of the air intake holes, and the spray hole is arranged toward the air intake hole; a vortex sheet, the vortex sheet is provided on a side of the flame tube away from the hydrogen pipeline, a partial structure of the vortex sheet is spaced apart from the flame tube to form a vortex space, and the air intake hole is connected to the vortex space.

[0006] Beneficial effects: By setting up a number of annular tubes, under the premise of ensuring the pressure balance inside the hydrogen pipeline, hydrogen fuel is mixed with air from all directions, achieving a high uniformity of mixing of hydrogen fuel and air, improving the combustion efficiency of hydrogen fuel, reducing the occurrence of local high temperature in the combustion chamber, and reducing pollutant emissions.

[0007] In an optional embodiment, the flame tube includes an arc portion and a main body portion, the arc portion is connected to the main body portion, the air inlet is opened on the arc portion, and the hydrogen pipeline is arranged on a side of the arc portion close to the casing.

[0008] In an optional embodiment, part of the arc-shaped portion forms the connecting pipe, the air inlet hole passes through the connecting pipe, and the air inlet hole is connected with the connecting pipe through the spray hole.

[0009] In an optional embodiment, the end of the arc portion is spaced apart from the main body portion, and an air film cavity is formed between the end of the arc portion and the main body portion. An air film hole is opened on the main body portion, and the air film hole is connected to the air film cavity. A plurality of air film holes are arranged along the circumference of the hydrogen fuel vortex combustion chamber.

[0010] Beneficial effects: A number of air film holes are arranged along the circumference of the hydrogen fuel annular vortex combustion chamber to form a circumferentially continuous air film, so that a circumferentially continuous annular vortex flow field structure is formed in the air film cavity, so that the hydrogen fuel enters the annular vortex flow field and is directly premixed and organized for combustion after ignition by the spark plug, so as to overcome the problem of fast propagation speed of hydrogen flame and easy backfire, thereby enabling the hydrogen fuel to burn efficiently and stably.

[0011] In an optional embodiment, a plurality of the intake pipes are provided, the plurality of the intake pipes are spaced apart and connected to the same annular pipe, a plurality of the vortex sheets are provided, the plurality of the vortex sheets are spaced apart, and the number of the intake pipes is an integer multiple of the number of the vortex sheets.

[0012] Beneficial effect: The number of intake pipes is an integer multiple of the number of vortex sheets, which ensures that the pressure in the hydrogen pipeline is stable, thereby ensuring uniform mixing of hydrogen fuel and air.

[0013] In an optional implementation, the diameter of the annular tube is D1, satisfying 2mm≤D1≤4mm.

[0014] Beneficial effect: By limiting the diameter size of the annular tube, the flow rate of the hydrogen fuel in the annular tube is guaranteed while the uniformity of the hydrogen fuel in the annular tube is guaranteed.

[0015] In an optional implementation, the diameter of the connecting pipe is D2, satisfying D2<D1.

[0016] In an optional implementation, the diameter of the spray hole is D3, satisfying 0<D3≤0.6mm.

[0017] Beneficial effect: By limiting the diameter of the nozzle hole, the speed at which the hydrogen fuel is sprayed out of the nozzle hole is ensured while ensuring the uniformity of the hydrogen fuel in the nozzle hole.

[0018] In an optional embodiment, a main combustion hole and a mixing hole are opened on the flame tube, the main combustion hole and the mixing hole are arranged at intervals, the main combustion hole is connected to the air flow space, and the mixing hole is connected to the air flow space.

[0019] Beneficial effect: The gas after the hydrogen fuel and air are mixed enters the flame tube, burns in the flame tube to produce combustion gas, and the combustion gas is further mixed with the air flowing in from the main combustion hole and the mixing hole and then enters the turbine to perform work.

[0020] In a second aspect, the present invention further provides an aircraft engine comprising the above-mentioned hydrogen fuel vortex combustion chamber. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0022] Figure 1 It is a positive triaxial diagram of the hydrogen fuel annular vortex combustion chamber according to an embodiment of the present invention;

[0023] Figure 2 It is a rear view of the hydrogen fuel vortex combustion chamber according to an embodiment of the present invention;

[0024] Figure 3 This is a schematic structural diagram of a flame tube and a hydrogen pipeline according to an embodiment of the present invention;

[0025] Figure 4 Schematic diagram of the flow of hydrogen fuel and air in a hydrogen fuel vortex combustion chamber according to an embodiment of the present invention.

[0026] Description of reference numerals:

[0027] 10. Casing; 20. Flame tube; 21. Air flow space; 22. Air inlet; 23. Arc-shaped portion; 24. Main body; 241. Air film hole; 25. Main combustion hole; 26. Mixing hole; 30. Hydrogen pipeline; 31. Air inlet pipe; 32. Annular pipe; 33. Connecting pipe; 331. Spray hole; 40. Vortex sheet; 41. Vortex space. DETAILED DESCRIPTION

[0028] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.

[0029] Combine the following Figures 1 to 4 , describing an embodiment of the present invention.

[0030] According to an embodiment of the present invention, 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 spaced apart from the casing 10, an air flow space 21 is formed between the flame tube 20 and the casing 10, an air inlet hole 22 is provided on the flame tube 20, a plurality of air inlet holes 22 are spaced apart, and the air flow space 21 is connected to the air inlet hole 22; the hydrogen pipeline 30 is arranged on a side of the flame tube 20 close to the casing 10, the hydrogen pipeline 30 comprises an air inlet pipe 31, an annular pipe 32 and a connecting pipe 33, a plurality of annular pipes 32 are arranged, and the plurality of annular pipes 32 are connected to the connecting pipe 33. 3 is connected, the air inlet pipe 31 is connected with the same annular pipe 32, a spray hole 331 is opened on the connecting pipe 33, a plurality of spray holes 331 are provided, the plurality of spray holes 331 are arranged in a one-to-one correspondence with the plurality of air inlet holes 22, and the spray holes 331 are arranged toward the air inlet holes 22; the swirl sheet 40 is arranged at a side of the flame tube 20 away from the hydrogen pipeline 30, a part of the structure of the swirl sheet 40 is spaced apart from the flame tube 20 to form a swirl space 41, and the air inlet hole 22 is connected with the swirl space 41.

[0031] The hydrogen fuel annular vortex combustion chamber of the present embodiment is applied, by setting up a plurality of annular tubes 32, under the premise of ensuring the internal pressure balance of the hydrogen pipeline 30, the hydrogen fuel is mixed with the air from all directions, thereby achieving a high uniformity mixing of the hydrogen fuel and the air, improving the combustion efficiency of the hydrogen fuel, reducing the occurrence of local high temperature in the combustion chamber, and reducing the emission of pollutants.

[0032] It should be noted that the hydrogen fuel annular vortex combustion chamber of this embodiment is an annular structure. Figure 1 and Figure 2 The structure in the figure is one eighth of the full ring structure. Figure 1 and Figure 2 The original model of this embodiment can be obtained by circumferentially arranging the structural model shown.

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

[0034] It should be noted that those skilled in the art can adjust the number of the annular tubes 32 according to actual needs.

[0035] It is further explained that the annular tube 32 can move in the axial direction or radial direction of the hydrogen fuel annular vortex combustion chamber.

[0036] For details, please refer to Figure 4 , Figure 4 Schematic diagram of the flow of hydrogen fuel and air in a hydrogen fuel vortex combustion chamber is shown in the figure, where the solid line is the schematic line for air flow and the dotted line is the schematic line for hydrogen fuel flow.

[0037] For details, please refer to Figure 3 The hydrogen fuel enters the annular tube 32 on the upper side of the figure from the intake pipe 31, and then flows into the connecting pipe 33 through the intake pipe 31. Part of the hydrogen fuel flows to the intake hole 22 through the nozzle 331, and then flows to the vortex space 41 from the intake hole 22. After entering the vortex space 41, the hydrogen fuel and the air are evenly mixed, and a vortex is formed through the vortex sheet 40. The hydrogen fuel that does not flow out of the nozzle 331 in the connecting pipe 33 enters the annular tube 32 on the lower side of the figure, automatically balancing the pressure inside the hydrogen pipeline 30, thereby ensuring high uniformity of hydrogen mixing in all directions.

[0038] In one embodiment, Figure 3 As shown, the flame tube 20 includes an arc portion 23 and a main body 24 , the arc portion 23 is connected to the main body 24 , the air inlet 22 is opened on the arc portion 23 , and the hydrogen pipeline 30 is arranged on a side of the arc portion 23 close to the casing 10 .

[0039] In one embodiment, Figure 3 As shown, part of the arc-shaped portion 23 forms a connecting pipe 33 , the air inlet hole 22 passes through the connecting pipe 33 , and the air inlet hole 22 is connected to the connecting pipe 33 through the spray hole 331 .

[0040] Specifically, part of the arc-shaped portion 23 has a cavity inside to form a connecting tube 33, the air inlet hole 22 penetrates the connecting tube 33, and the hole wall of the air inlet hole 22 separates the air inlet hole 22 from the connecting tube 33; the spray hole 331 is opened on the hole wall of the air inlet hole 22, so as to achieve the mixing of hydrogen fuel and air through the air inlet hole 22 and the connecting hole.

[0041] It should be noted that in other embodiments not shown, the connecting pipe 33 and the arc-shaped portion 23 may also be provided separately, but it is necessary to ensure that the spray hole 331 is provided toward the air inlet 22 .

[0042] In one embodiment, Figure 1As shown, the end of the arc portion 23 is spaced apart from the main body 24, and an air film cavity is formed between the end of the arc portion 23 and the main body 24. An air film hole 241 is opened on the main body 24, and the air film hole 241 is connected to the air film cavity. There are several air film holes 241 arranged along the circumference of the hydrogen fuel annular vortex combustion chamber.

[0043] It is worth noting that a number of air film holes 241 are arranged along the circumference of the hydrogen fuel annular vortex combustion chamber to form a circumferentially continuous air film, so that a circumferentially continuous annular vortex flow field structure is formed in the air film cavity, so that the hydrogen fuel enters the annular vortex flow field and is directly premixed and organized for combustion after ignition by the spark plug, so as to overcome the problem of fast propagation speed of hydrogen flame and easy backfire, thereby enabling the hydrogen fuel to burn efficiently and stably.

[0044] In one embodiment, Figure 2 As shown, a plurality of intake pipes 31 are provided, and the plurality of intake pipes 31 are arranged at intervals and connected to the same annular pipe 32; a plurality of swirl sheets 40 are provided, and the plurality of swirl sheets 40 are arranged at intervals, and the number of intake pipes 31 is an integer multiple of the number of swirl sheets 40.

[0045] It is worth noting that the number of the air intake pipes 31 is an integer multiple of the number of the vortex sheets 40 , so as to ensure the pressure in the hydrogen pipeline 30 is stable, thereby ensuring the uniform mixing of hydrogen fuel and air.

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

[0047] It is worth noting that by limiting the diameter size of the annular tube 32 , the uniformity of the hydrogen fuel in the annular tube 32 is ensured while ensuring the flow rate of the hydrogen fuel in the annular tube 32 .

[0048] It should be noted that when D1 is less than 2 mm, the flow rate of the hydrogen fuel in the annular tube 32 is faster, but the uniformity of the hydrogen fuel in the annular tube 32 is poor and does not meet the requirements; when D1 is greater than 4 mm, the uniformity of the hydrogen fuel in the annular tube 32 is good, but the flow rate of the hydrogen fuel in the annular tube 32 is slower and does not meet the requirements.

[0049] In one embodiment, the diameter of the connecting pipe 33 is D2, satisfying D2<D1.

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

[0051] It is worth noting that by limiting the diameter size of the spray hole 331 , the uniformity of the hydrogen fuel in the spray hole 331 is ensured while the speed at which the hydrogen fuel is sprayed out of the spray hole 331 is ensured.

[0052] It should be noted that when D3>0.6 mm, the uniformity of the hydrogen fuel in the spray hole 331 is good, but the speed at which the hydrogen fuel is sprayed out of the spray hole 331 is slow and does not meet the requirements.

[0053] In one embodiment, Figure 1 As shown, a main combustion hole 25 and a mixing hole 26 are provided on the flame tube 20 . The main combustion hole 25 and the mixing hole 26 are arranged at intervals. The main combustion hole 25 is connected to the air flow space 21 , and the mixing hole 26 is connected to the air flow space 21 .

[0054] It is worth noting that the gas after the hydrogen fuel and air are mixed enters the flame tube 20, burns in the flame tube 20 to generate combustion gas, and the combustion gas is further mixed with the air flowing into the main combustion hole 25 and the mixing hole 26 and then enters the turbine to perform work.

[0055] According to an embodiment of the present invention, in a second aspect, there is also provided an aircraft engine comprising the above-mentioned hydrogen fuel annular vortex combustion chamber.

[0056] Although the embodiments of the present invention have been described in conjunction with the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the present invention. Such modifications and variations are all within the scope defined by the present invention.

Claims

1. A hydrogen fuel vortex combustion chamber, characterized in that: include: Receiver (10); A flame tube (20), the flame tube (20) and the casing (10) are arranged at intervals, an air flow space (21) is formed between the flame tube (20) and the casing (10), an air inlet hole (22) is opened on the flame tube (20), a plurality of the air inlet holes (22) are arranged at intervals, and the air flow space (21) is communicated with the air inlet holes (22); A hydrogen pipeline (30), the hydrogen pipeline (30) being arranged on a side of the flame tube (20) close to the casing (10), the hydrogen pipeline (30) comprising an intake pipe (31), an annular pipe (32) and a connecting pipe (33), a plurality of the annular pipes (32) being arranged, the plurality of the annular pipes (32) being connected to the connecting pipe (33), the intake pipe (31) being connected to the same annular pipe (32), the connecting pipe (33) being provided with a spray hole (331), a plurality of the spray holes (331) being arranged, the plurality of the spray holes (331) being arranged in a one-to-one correspondence with the plurality of the intake holes (22), and the spray hole (331) being arranged toward the intake hole (22); A swirl sheet (40), wherein the swirl sheet (40) is arranged on a side of the flame tube (20) away from the hydrogen pipeline (30), a part of the structure of the swirl sheet (40) is spaced apart from the flame tube (20) to form a swirl space (41), and the air inlet (22) is connected to the swirl space (41).

2. The hydrogen fuel vortex combustion chamber according to claim 1, characterized in that: The flame tube (20) comprises an arc-shaped portion (23) and a main body (24), the arc-shaped portion (23) being connected to the main body (24), the air inlet hole (22) being provided on the arc-shaped portion (23), and the hydrogen pipeline (30) being provided on a side of the arc-shaped portion (23) close to the casing (10).

3. The hydrogen fuel vortex combustion chamber according to claim 2, characterized in that: Part of the arc-shaped portion (23) forms the connecting pipe (33), the air inlet hole (22) passes through the connecting pipe (33), and the air inlet hole (22) is connected to the connecting pipe (33) through the spray hole (331).

4. The hydrogen fuel vortex combustion chamber according to claim 2, characterized in that: The end of the arc-shaped portion (23) is spaced apart from the main body (24), and an air film cavity is formed between the end of the arc-shaped portion (23) and the main body (24). An air film hole (241) is provided on the main body (24), and the air film hole (241) is connected to the air film cavity. A plurality of air film holes (241) are arranged along the circumference of the hydrogen fuel annular vortex combustion chamber.

5. The hydrogen fuel vortex combustion chamber according to any one of claims 1 to 4, characterized in that: A plurality of the air intake pipes (31) are provided, and the plurality of the air intake pipes (31) are arranged at intervals and are connected to the same annular pipe (32); a plurality of the swirl sheets (40) are provided, and the plurality of the swirl sheets (40) are arranged at intervals; the number of the air intake pipes (31) provided is an integer multiple of the number of the swirl sheets (40) provided.

6. The hydrogen fuel vortex combustion chamber according to any one of claims 1 to 4, characterized in that: The diameter of the annular tube (32) is D1, which satisfies 2mm≤D1≤4mm.

7. The hydrogen fuel vortex combustion chamber according to claim 6, characterized in that: The diameter of the connecting pipe (33) is D2, satisfying D2<D1.

8. The hydrogen fuel vortex combustion chamber according to any one of claims 1 to 4, characterized in that: The diameter of the spray hole (331) is D3, satisfying 0<D3≤0.6mm.

9. The hydrogen fuel vortex combustion chamber according to any one of claims 1 to 4, characterized in that: 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 an interval, the main combustion hole (25) is connected to the air flow space (21), and the mixing hole (26) is connected to the air flow space (21).

10. An aircraft engine, characterized in that: A hydrogen fuel vortex combustion chamber comprising the hydrogen fuel vortex combustion chamber as described in any one of claims 1 to 9.

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