Combustion chamber, gas turbine engine, combustion organization device for hydrogen-based fuel, and combustion method

Abstract

The present application provides a combustion chamber, a gas turbine engine, a combustion organization device for hydrogen-based fuel and a combustion method. The combustion organization device for hydrogen-based fuel comprises a disc-shaped body, wherein the disc-shaped body has: a pre-combustion stage comprising a pre-combustion stage fuel injection hole and an air rotation flow structure surrounding the pre-combustion stage fuel injection hole; and a main combustion stage comprising a main combustion stage fuel injection hole surrounding the air rotation flow structure. Low carbon emission and low pollution combustion are achieved.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of combustion chambers, in particular to a combustion chamber, a gas turbine engine, a combustion organization device for hydrogen-based fuel and a combustion method. BACKGROUND

[0002] The increasing environmental awareness makes the reduction of pollutant emissions in the combustion process one of the main challenges in the development of aircraft engines and gas turbines. In order to achieve lower NOx emissions while not increasing the concentration of carbon monoxide and unburned hydrocarbons in the exhaust gas, low-emission combustion forms such as lean premixed pre-vaporization and rich quenching lean combustion have been widely researched and applied in gas turbines and aircraft engines. Combustion organization forms based on sustainable fuels and other fuels such as hydrocarbon fuels are emerging in aircraft engine combustion chambers, the main purpose of which is to further reduce carbon emissions while reducing traditional pollutant emissions (such as NOx), but the exhaust emissions based on hydrocarbon fuels always contain CO2, which cannot meet the requirements of low-carbon combustion. Hydrogen combustion as one of the most environmentally friendly combustion organization methods has the problems of no combustion carbon emissions and other combustion pollution products, and is a very potential low-carbon fuel. SUMMARY

[0003] The purpose of the present application is to provide a combustion organization device for hydrogen-based fuel.

[0004] Another purpose of the present application is to provide a combustion chamber.

[0005] Still another purpose of the present application is to provide a gas turbine engine.

[0006] Still another purpose of the present application is to provide a combustion method of hydrogen-based fuel and air.

[0007] According to one aspect of the present application, a combustion organization device for hydrogen-based fuel comprises: a disc-shaped body, wherein the disc-shaped body has: a pre-combustion stage comprising a pre-combustion stage fuel injection hole and an air swirl structure surrounding the pre-combustion stage fuel injection hole; and a main combustion stage comprising a main combustion stage fuel injection hole surrounding the air swirl structure.

[0008] The technical scheme of the present application is characterized in that an air rotation structure is arranged circumferentially in the pre-combustion stage, the pre-combustion stage sprays hydrogen-based fuel and mixes with air rotation to form a pre-combustion stage flame, the upstream end of the pre-combustion stage flame, i.e. the root of the pre-combustion stage flame, is stationary and will not be affected by the rotation to change the position, and the stability is good, thereby avoiding backfire; meanwhile, the pre-combustion stage flame is affected by the rotation to be stretched and rotated in the radial direction, the diffusion degree of the pre-combustion stage flame in the radial direction and circumferential direction is increased, a space-distributed uniform heat release zone is formed, a local high temperature zone is avoided, and NOx emission is reduced. The technical scheme of the present application is characterized in that an air rotation structure is arranged circumferentially in the pre-combustion stage, the pre-combustion stage sprays hydrogen-based fuel and mixes with air rotation to form a pre-combustion stage flame, the upstream end of the pre-combustion stage flame, i.e. the root of the pre-combustion stage flame, is stationary and will not be affected by the rotation to change the position, and the stability is good, thereby avoiding backfire; meanwhile, the pre-combustion stage flame is affected by the rotation to be stretched and rotated in the radial direction, the diffusion degree of the pre-combustion stage flame in the radial direction and circumferential direction is increased, a space-distributed uniform heat release zone is formed, a local high temperature zone is avoided, and NOx emission is reduced.

[0009] In one or more embodiments of the combustion organization device, the air rotation structure comprises a pre-combustion stage air injection hole, the pre-combustion stage fuel injection hole and the main combustion stage fuel injection hole are straight holes, and the pre-combustion stage air injection hole is an inclined hole.

[0010] In one or more embodiments of the combustion organization device, the pre-combustion stage air injection hole has an inclination angle of 30°-60° with the normal direction of the disc-shaped body.

[0011] In one or more embodiments of the combustion organization device, the pre-combustion stage fuel injection hole has a diameter of 0.5mm-1mm, the pre-combustion stage air injection hole has a diameter of 0.5mm-1mm, and the main combustion stage fuel injection hole has a diameter of 0.5mm-2mm.

[0012] In one or more embodiments of the combustion organization device, the number of the pre-combustion stage fuel injection holes is 1-5; the pre-combustion stage air injection holes form a plurality of coaxial annular rings around the pre-combustion stage fuel injection hole to form a pre-combustion stage air injection annular ring belt; the number of the coaxial annular rings is 5-10; and the main combustion stage fuel injection holes form one or two coaxial annular rings around the pre-combustion stage air injection annular ring belt, and the number of the main combustion stage fuel injection holes is 30-50.

[0013] In one or more embodiments of the combustion organization device, the combustion organization device comprises a base body for connecting a fuel main pipe and fuel sub-pipes, respectively, one side of the fuel sub-pipes being connected to the base body and the other side being connected to the pre-combustion stage fuel injection holes and the main combustion stage fuel injection holes of the disc-shaped body; and an air passage is configured between the base body and the disc-shaped body for air to enter the combustion organization device.

[0014] In one or more embodiments of the combustion organization device, the disc-shaped body further comprises air cooling holes surrounding the main combustion stage fuel injection holes; the diameter of the air cooling holes is less than 0.5 mm.

[0015] In one or more embodiments of the combustion organization device, the flow area of the air cooling holes is no more than 30% of the flow area of the air swirling structure.

[0016] According to another aspect of the present application, a combustion chamber comprises a plurality of the combustion organization devices as described above, and a combustion vessel, the pre-combustion stage fuel injection holes, the air swirling structure and the main combustion stage fuel injection holes of the combustion organization devices being in direct communication with the combustion vessel, and the hydrogen-based fuel and air being able to enter the combustion vessel through the combustion organization devices for combustion.

[0017] In one or more embodiments of the combustion chamber, the combustion vessel is a ring-shaped vessel, a plurality of the combustion organization devices being circumferentially distributed and connected to the ring-shaped combustion vessel, and an air flow path of the combustion chamber comprising a first air flow path, a second air flow path and a third air flow path; the ring-shaped combustion vessel having an outer ring wall and an inner ring wall, the first air flow path providing cooling air to cooling holes of the outer ring wall, the second air flow path providing cooling air to cooling holes of the inner ring wall, and the third air flow path providing air to the combustion organization devices.

[0018] In one or more embodiments of the combustion chamber, the total area of the air cooling holes of the combustion organization devices, the total area of the pre-combustion stage air injection holes, and the total area of the cooling holes of the outer ring wall and the inner ring wall of the combustion vessel are in a ratio of 10-20%: 50-60%: 20-40%.

[0019] According to yet another aspect of the present application, a gas turbine engine comprises the combustion chamber as described above.

[0020] According to a further aspect of the present application, a hydrogen-based fuel and air combustion method includes: providing a pre-combustion stage and a main combustion stage surrounding the pre-combustion stage; in a first state, hydrogen-based fuel of the pre-combustion stage is directly injected, a pre-combustion stage flame and a swirl flow surrounding the pre-combustion stage flame form a pre-combustion stage diffusion flame, and the main combustion stage is closed; in a second state, hydrogen-based fuel of the pre-combustion stage is directly injected, a pre-combustion stage flame and a swirl flow surrounding the pre-combustion stage flame form a pre-combustion stage diffusion flame, and hydrogen-based fuel of the main combustion stage is directly injected, and a main combustion stage diffusion flame is formed by the swirl flow. BRIEF DESCRIPTION OF DRAWINGS

[0021] The above and other features, aspects and advantages of the present application will become more apparent from the following description of an embodiment thereof, taken in conjunction with the accompanying drawings, which illustrate, by way of example, the principles of the application. In the drawings, like reference numerals refer to like elements throughout. It is to be noted that the drawings are not necessarily drawn to scale and that the embodiments disclosed are to be interpreted as examples only and not in a limiting sense. In the drawings:

[0022] Figure 1 Structure diagram of a circumferential portion of a combustion chamber of an embodiment;

[0023] Figure 2A Structure diagram of a combustion organization device of an embodiment;

[0024] Figure 2B Structure diagram of another view of a combustion organization device of an embodiment;

[0025] Figure 3 Structure diagram of a disc-shaped body of an embodiment;

[0026] Figure 4 Structure diagram of yet another view of a combustion organization device of an embodiment.

[0027] Reference numerals:

[0028] 1000 - combustion chamber, 1001 - first air flow path, 1002 - second air flow path, 1003 - third air flow path, 101 - outer casing, 102 - inner casing, 103 - cap, 104 - diffuser;

[0029] 100 - combustion organization device, 200 - fuel main pipe, 300 - fuel sub-pipe;

[0030] 400 - combustion vessel, 401 - outer ring wall, 402 - inner ring wall, 403 - cooling hole;

[0031] 10 - disc-shaped body;

[0032] 1 - pre-chamber, 11 - pre-chamber fuel injection hole, 110 - air swirler structure, 12 - pre-chamber air injection hole, 120 - pre-chamber air injection hole annular band, 121 - swirler;

[0033] 2 - main combustion chamber, 21 - main combustion chamber fuel injection hole;

[0034] 20 - base body;

[0035] 3 - air cooling hole, 301 - air cooling hole annular band, 4 - air passage;

[0036] 5 - pre-chamber diffusion flame, 6 - main combustion chamber diffusion flame. DETAILED DESCRIPTION

[0037] Reference will now be made in detail to various embodiments of the application, examples of which are illustrated in the accompanying drawings and described below. While the application will be described in conjunction with the exemplary embodiments, it will be understood that the application is not limited to the exemplary embodiments. On the contrary, the application is intended to cover all alternatives, modifications, equivalents, and other embodiments that are included within the spirit and scope of the application as defined by the appended claims.

[0038] In the following description, the terms "axial", "radial", "circumferential", "upstream", "downstream", "inner", "outer" or other orientation terms indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, which are only for the convenience of describing the application and simplifying the description, and do not indicate or imply that the device or component referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation of the application. In addition, "upstream" and "downstream" are divided according to the flow direction of the air flow, for example, the air flows from "upstream" to "downstream".

[0039] Meanwhile, specific words are used in the present application to describe the embodiments of the present application. As "one embodiment" and / or "an embodiment" means a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that the "one embodiment" or "an embodiment" mentioned in different positions in the specification does not necessarily refer to the same embodiment. In addition, certain features, structures or characteristics in one or more embodiments of the present application can be properly combined.

[0040] With the increasing demand for low carbon emissions of engines, hydrogen combustion is one of the most environmentally friendly combustion organization methods at present, which needs to reasonably organize hydrogen combustion in the combustion chamber of an aero-engine and a gas turbine.

[0041] The inventors of the present application have found through in-depth research that hydrogen combustion has the characteristics of extremely fast combustion speed and high flame temperature, and that directly carrying out hydrogen combustion based on a traditional kerosene combustion aero-engine and gas turbine combustor has problems such as difficult hydrogen fuel injection arrangement, high flame temperature, easy backfire and ablation.

[0042] Based on the above considerations, the inventors have designed a combustion organization device for hydrogen-based fuel through in-depth research. The device is configured by arranging an air swirl structure circumferentially in a pre-combustion stage, mixing hydrogen-based fuel and air swirl in the pre-combustion stage to form a pre-combustion flame, and arranging a main combustion stage circumferentially in the air swirl structure. The upstream end of the pre-combustion flame, i.e. the root of the pre-combustion flame, is stationary and is not affected by the swirl to change its position, so the stability is good and backfire is avoided. At the same time, the pre-combustion flame is stretched and rotated in the radial direction under the influence of the swirl, which increases the diffusion degree of the pre-combustion flame in the radial and circumferential directions, forms a uniformly distributed heat release zone, avoids local high temperature zones, and reduces NOx emissions. The main combustion stage is arranged circumferentially in the air swirl structure, and the main combustion stage injects hydrogen-based fuel to form a main combustion flame. The radially inner side of the main combustion flame is affected by the air swirl and is stretched and rotated in the radial direction, forming a stationary main combustion diffusion flame. More hydrogen-based fuel can be burned under large engine conditions, local high temperature zones are avoided, NOx emissions are reduced, and the risk of backfire is reduced. Moreover, compared with the main combustion flame and the pre-combustion flame formed by the staged swirl combustion in the comparative scheme, the pre-combustion flame in the present scheme is burned in the radial center of the swirl zone, and the main combustion flame is burned on the radially outer side of the swirl zone. The pre-combustion stage and the main combustion stage do not affect each other, thereby avoiding the generation of local hot spots, reducing combustion pollutants NOx and low-carbon emissions. In addition, by adjusting the flame ratio of the pre-combustion stage and the main combustion stage, the needs of different working conditions of the combustion chamber can be met.

[0043] Although the combustion organization device disclosed in the embodiments of the present application is suitable for hydrogen-based fuel combustion organization, it is not limited thereto, and as long as it can be applied to the combustion organization device disclosed in the embodiments of the present application to make the fuel burn stably and reduce the risk of backfire.

[0044] Reference Figures 1 to 4 As shown in the figure, in one embodiment, the specific structure of the combustion organization device 100 for hydrogen-based fuel can be that it includes a disc-shaped body 10, and the disc-shaped body 10 has a pre-combustion stage 1 and a main combustion stage 2. The pre-combustion stage 1 includes a pre-combustion stage fuel injection hole 11 and an air swirl structure 110 surrounding the pre-combustion stage fuel injection hole 11. The main combustion stage 2 includes a main combustion stage fuel injection hole 21 surrounding the air swirl structure 110.

[0045] The meaning of "hydrogen-based fuel" here is that the volume content of hydrogen in the fuel is greater than or equal to 90%, for example, the hydrogen-based fuel can be pure hydrogen. The storage form of hydrogen-based fuel can be various, for example, it can be liquid hydrogen, compressed gaseous hydrogen, etc.

[0046] Here, the meaning of the "disc-shaped body 10" refers to a structure as a carrier of the pre-combustion stage and the main combustion stage, as shown in the figure, which is in the shape of a circular disc, but is not limited to this, and can be in other shapes, such as a square, etc. Figures 2A to 3

[0047] Here, the meaning of the "pre-combustion stage 1 and the main combustion stage 2" refers to the use of staged combustion, and the flexible adjustment of the flame ratio of the pre-combustion stage 1 and the main combustion stage 2 according to different working conditions of the combustion chamber, as shown in the figure, the pre-combustion stage diffusion flame 5 is located in the center of the swirl 121 and burns, and the main combustion stage diffusion flame 6 is located on the outer side of the swirl 121. In small working conditions, only the pre-combustion stage 1 works; in large working conditions, the pre-combustion stage 1 and the main combustion stage 2 work together. Figure 4

[0048] Here, the meaning of the "air swirl structure 110" refers to making the passing air flow into a rotating air flow to generate a backflow area downstream to promote diffusion combustion and stabilize the flame.

[0049] The beneficial effects of the present embodiment are that by arranging the air swirl structure in the circumferential direction of the pre-combustion stage, the pre-combustion stage injects hydrogen-based fuel and mixes with the air swirl to form a pre-combustion stage flame, the upstream end of the pre-combustion stage flame, i.e. the root of the pre-combustion stage flame, is stationary and will not be affected by the swirl to change its position, and has good stability, avoiding backfire. At the same time, the pre-combustion stage flame is affected by the swirl and is stretched and rotated in the radial direction, increasing the diffusion degree of the pre-combustion stage flame in the radial and circumferential directions, forming a uniformly distributed heat release area, avoiding local high temperature areas, and reducing NOx emissions. By arranging the main combustion stage in the circumferential direction of the air swirl structure, the main combustion stage injects hydrogen-based fuel to form a main combustion stage flame, the radially inner side of the main combustion stage flame is affected by the air swirl and is stretched and rotated in the radial direction, forming a stationary main combustion stage diffusion flame, which can burn more hydrogen-based fuel in large working conditions of the engine, avoid local high temperature areas, reduce NOx emissions, and reduce the risk of backfire. Moreover, compared to the main combustion stage flame and the pre-combustion stage flame formed by the staged swirl combustion in the comparative scheme, which will affect each other to generate local hot spots, the pre-combustion stage flame of the present scheme burns in the radial center of the swirl area, and the main combustion stage flame burns on the radially outer side of the swirl area, and the pre-combustion stage and the main combustion stage will not affect each other, thereby avoiding the generation of local hot spots, and playing a role in reducing combustion pollutants NOx and low carbon emissions. In addition, by adjusting the flame ratio of the pre-combustion stage and the main combustion stage, the needs of different working conditions of the combustion chamber can be met.

[0050] Reference Figures 2A to 3 ​​As shown in some embodiments, the specific structure of the disc-shaped body 10 can be that the air swirl structure 110 includes the pre-combustion stage air injection hole 12, the pre-combustion stage fuel injection hole 11 and the main combustion stage fuel injection hole 21 are straight holes, and the pre-combustion stage air injection hole 12 is an inclined hole. The beneficial effect of such an arrangement is that the inclined hole structure is simple to process and easy to form an air swirl. Unlike the features of the swirl staged combustion organization in the comparative solution, both the pre-combustion stage flame and the main combustion stage flame use direct injection of hydrogen-based fuel combustion, and air enters the combustion chamber through the inclined hole, which cools the disc-shaped body while reducing the risk of spontaneous backfire, achieving a combustion organization form with low pollution and low carbon emissions.

[0051] Reference Figures 2A to 4 As shown in some embodiments, the specific structure of the pre-combustion stage air injection hole 12 can be that the angle of inclination of the pre-combustion stage air injection hole 12 is 30°-60° with the normal direction of the disc-shaped body 10. It should be understood that, Figure 4 The pre-combustion stage air injection hole 12 does not show the angle of inclination due to the perspective of the cross-sectional line. The beneficial effect of such an arrangement is that the inclined hole forms a single swirl zone, and the flow characteristics are stable, which is convenient for organizing combustion and aerodynamic design.

[0052] Continuing to refer to Figures 2A to 4 As shown in some embodiments, the specific structure of the disc-shaped body 10 can be that the diameter of the pre-combustion stage fuel injection hole 11 is 0.5mm-2mm, the diameter of the pre-combustion stage air injection hole 12 is 0.5mm-1mm, and the diameter of the main combustion stage fuel injection hole 21 is 0.5mm-2mm. The "diameter" here is the equivalent diameter, although it is generally a circular injection hole, but it is not limited to this. The beneficial effect of such an arrangement is that appropriate amounts of fuel and air can be obtained during operation.

[0053] Continuing to refer to Figures 2A to 4 As shown in some embodiments, the specific structure of the disc-shaped body 10 can be that the number of pre-combustion stage fuel injection holes 11 is 1-5; the pre-combustion stage air injection hole 12 forms a plurality of coaxial annular A around the pre-combustion stage fuel injection hole 11, forming a pre-combustion stage air injection annular belt 120; the number of coaxial annular A is 5-10; the main combustion stage fuel injection hole 21 forms one or two coaxial annular B around the pre-combustion stage air injection annular belt 120, and the number of main combustion stage fuel injection holes 21 is 30-50. The meaning of "coaxial annular" here refers to a plurality of annular having the same axis and the same position in the axial direction. Specifically, as Figure 3In the illustrated embodiment, the annular ring of pre-combustion stage air injection holes 120 is composed of 7 coaxial annular rings in the radial direction from the inside to the outside, and the number of injection holes from the inside to the outside is 8, 12, 16, 20, 24, 28, and 32 respectively. The above fuel injection holes and air injection holes are uniformly distributed. The beneficial effect of such arrangement is that a multi-point staged direct injection array is formed, which can obtain better diffusion combustion effect, the combustion flame forms a spatially uniform heat release zone, meets the required fuel-air ratio of each working condition, improves the combustion efficiency, reduces pollution and realizes low carbon emission.

[0054] Reference Figure 2A , Figure 2B As shown in some embodiments, the specific structure of the combustion organization device 100 can be that the base body 20 is used to connect the fuel main pipe 200 and the fuel branch pipe 300 respectively, one side of the fuel branch pipe 300 is connected to the base body 20, and the other side is connected to the pre-combustion stage fuel injection hole 11 and the main combustion stage fuel injection hole 21 of the disc-shaped body 10; the air passage 4 for air entering the combustion organization device 100 is constructed between the base body 20 and the disc-shaped body 10. Specifically, as shown in Figures 2A to 4 , the fuel main pipe 200 delivers the hydrogen-based fuel c from the base body 20 to each fuel branch pipe 300, and then delivers it to the pre-combustion stage fuel injection hole 11 and the main combustion stage fuel injection hole 21. According to different working conditions, the hydrogen-based fuel is sprayed out from the pre-combustion stage fuel injection hole 11 and / or the main combustion stage fuel injection hole 21, and the air is formed into a rotational flow 121 by the air rotational flow structure 110 through the air passage 4, providing the required air for fuel combustion, and stretching the combustion flame to form a spatially uniform heat release zone, realizing low-carbon and low-pollution combustion. The beneficial effect of such arrangement is that the structure is simple and convenient for controlling the opening and closing of the injection holes.

[0055] In some embodiments, the hydrogen-based fuel in the fuel main pipe 300 is gaseous hydrogen.

[0056] Reference Figures 2A to 3 As shown in some embodiments, the specific structure of the disc-shaped body 10 can also have air cooling holes 3 surrounding the main combustion stage fuel injection hole 21; the diameter of the air cooling hole 3 is less than 0.5mm. Specifically, the air cooling holes 3 are uniformly distributed in the radial direction from the inside to the outside to form a plurality of coaxial annular rings, and the plurality of coaxial annular rings constitute an air cooling hole annular ring 301 for cooling the periphery of the disc-shaped body 10, and the air cooling hole annular ring 301 is connected to the air passage 4. Figure 3 In the illustrated embodiment, the air cooling hole annular ring 301 has four coaxial annular air cooling holes 3. The beneficial effect of such arrangement is that the diameter of the air cooling hole is less than 0.5mm, which can form a better cooling gas film on the disc-shaped body. If the diameter is larger, it will interfere with the air flow organization of the combustion, and the cooling effect will also be poorer.

[0057] Reference Figure 3As shown, in some embodiments, the specific structure of the disc-shaped body 10 can be that the flow area of the air cooling hole 3 is not more than 30% of the flow area of the air rotation structure 110. Specifically, taking the pre-combustion stage air injection hole 12 with the air rotation structure 110 as a slant hole as an example, the total area of the air cooling hole 3 is not more than 30% of the total area of the pre-combustion stage air injection hole 12. The beneficial effect of such an arrangement is to ensure that the air cooling gas does not affect the rotation flow.

[0058] Reference Figures 1 to 4 As shown, in one embodiment, the specific structure of the combustion chamber 1000 can be that it includes a plurality of combustion organization devices 100 as described above, and the pre-combustion stage fuel injection hole 11, the air rotation structure 110 and the main combustion stage fuel injection hole 21 of the combustion organization device 100 are directly communicated with the combustion container 400, and the hydrogen-based fuel and the air can enter the combustion container 400 to burn through the combustion organization device 100. The meaning of "direct communication" here refers to direct injection, i.e., the hydrogen-based fuel c and the air a are directly injected into the inside of the combustion container 400. The beneficial effect of such an arrangement is that, by adopting the hydrogen-based fuel combustion organization mode of staged flame, stable combustion flame is formed by direct injection of fuel at different positions, air rotation is formed by combining the air rotation structure, air supply during fuel combustion is realized, and the axial length of the combustion flame is shortened in space by rotation, the diffusion degree of the flame in the circumferential and radial directions is improved, and local combustion hot spots are reduced, thereby playing a role in reducing combustion pollutants NOx and low carbon emissions. Unlike the characteristics of the rotational staged combustion organization of the comparative scheme, the present scheme adopts direct injection of hydrogen-based fuel combustion in both the pre-combustion stage flame and the main combustion stage flame, and an air rotation structure is arranged between the pre-combustion stage flame and the main combustion stage flame in the radial direction, and the air enters the combustion container through the rotation structure, cools the disc-shaped body, reduces the risk of spontaneous backfire, avoids local hot spots caused by mutual influence between the pre-combustion stage and the main combustion stage, and achieves a combustion organization form with low pollution and low carbon emissions.

[0059] Reference Figure 1 As shown, in some embodiments, the specific structure of the combustion chamber 1000 can be that the combustion container 400 is an annular container, a plurality of combustion organization devices 100 are circumferentially distributed and connected with the annular combustion container 400, and the air flow path of the combustion chamber 1000 includes a first air flow path 1001, a second air flow path 1002 and a third air flow path 1003; the annular combustion container 400 has an outer ring wall 401 and an inner ring wall 402, the first air flow path 1001 provides cooling air to the cooling hole 403 of the outer ring wall 401, the second air flow path 1002 provides cooling air to the cooling hole 403 of the inner ring wall 402, and the third air flow path 1003 provides air a to the combustion organization device 100. Specifically, as shown in the figure, Figure 1As shown, the combustion chamber 1000 further comprises a diffuser 104, an outer casing 101, an inner casing 102, the upstream end of the combustion vessel 400 has a cap 103, the high pressure air a from the compressor enters the combustion chamber 1000 through the diffuser 104, under the guidance of the cap 103, the air a is divided into three streams, wherein the first air flow path 1001 flows into the outer annular cavity formed by the outer casing 101 and the outer annular wall 401, the second air flow path 1002 flows into the inner annular cavity formed by the inner casing 102 and the inner annular wall 402, enters the interior of the combustion vessel 400 through the cooling holes 403, and cools the inner and outer annular walls to prevent ablation, and the third air flow path 1003 enters the interior of the combustion vessel 400 through the combustion organization device 100 connected with the combustion vessel 400, mixes with the fuel ejected from the fuel injection hole of the fuel distribution pipe 300 through the fuel main pipe 200, and burns to form high-temperature and high-pressure combustion gas b, which flows out of the combustion chamber 1000 and enters the turbine. The beneficial effects of such arrangement are that the structure is simple, and low-pollution and low-carbon emission combustion is achieved.

[0060] Referring to Figure 1 , Figure 3 As shown, in some embodiments, the specific structure of the combustion chamber 1000 can be that the area ratio of the total area of the air cooling holes 3 of the combustion organization device 100, the total area of the pre-combustion stage air injection holes 12, and the total area of the cooling holes 403 of the outer annular wall 401 and the inner annular wall 402 of the combustion vessel 400 is 10-20%: 50-60%: 20-40%. Correspondingly, the percentage of the amount of cooling air and the amount of air participating in combustion in the entire combustion chamber is about 30-40%: 60-70%, that is, the ratio of the total area of the air cooling holes 3 of the combustion organization device 100 to the sum of the total area of the cooling holes 403 of the outer annular wall 401 and the inner annular wall 402 of the combustion vessel 400 to the total area of the pre-combustion stage air injection holes 12 is about 30-40%: 60-70%. The beneficial effects of such arrangement are that the flow rates of the cooling air and the combustion air are reasonably distributed. Preferably, in some embodiments, the area ratio of the total area of the air cooling holes 3 of the combustion organization device 100, the total area of the pre-combustion stage air injection holes 12, and the total area of the cooling holes 403 of the outer annular wall 401 and the inner annular wall 402 of the combustion vessel 400 is 15%: 55%: 30%.

[0061] Referring to Figures 1 to 4 As shown, in one embodiment, the specific structure of the gas turbine engine can comprise the combustion chamber 1000 as described above. The beneficial effects of such arrangement are that the organization combustion of hydrogen-based fuel is achieved, and low-pollution and low-carbon emission of the engine is ensured.

[0062] Continuing to refer to Figures 1 to 4 As shown, in one embodiment, the specific steps of the combustion method of the hydrogen-based fuel c and the air a can comprise:

[0063] A pre-combustion stage 1 and a main combustion stage 2 surrounding the pre-combustion stage 1 are provided. As described above, the pre-combustion stage 1 is arranged at the center of the disc-shaped body 10, and the main combustion stage 2 is arranged between the pre-combustion stage 1 and the radial direction of the pre-combustion stage 1, and the air rotation structure 110 is arranged between the pre-combustion stage 1 and the main combustion stage 2.

[0064] In the first state, the hydrogen-based fuel c of the pre-combustion stage 1 is directly injected, the pre-combustion stage flame and the rotation flow 121 surrounding the pre-combustion stage flame form a pre-combustion stage diffusion flame 5, and the main combustion stage 2 is closed. As described above, when the combustion chamber 1000 is in a low-power state, the hydrogen-based fuel c of the pre-combustion stage 1 is directly injected into the combustion container 400, the pre-combustion stage flame is located at the outlet of the pre-combustion stage fuel injection hole 11, and under the action of the inclined hole rotation flow of the pre-combustion stage air injection hole 12, the flame is further stretched in the radial direction and the circumferential direction to form a stable diffusion flame.

[0065] In the second state, the hydrogen-based fuel c of the pre-combustion stage 1 is directly injected, the pre-combustion stage flame and the rotation flow 121 surrounding the pre-combustion stage flame form a pre-combustion stage diffusion flame 5, and the hydrogen-based fuel c of the main combustion stage 2 is directly injected, and the main combustion stage diffusion flame 6 is formed under the action of the rotation flow 121. As described above, when the power of the combustion chamber is increased, the main combustion stage 2 starts to work, the hydrogen-based fuel c of the pre-combustion stage 1 is injected into the combustion container 400, and is rotated and burned on the radial outside of the rotation flow 121 to form a stable main combustion stage diffusion flame 6 which is stretched in the radial direction and the axial direction.

[0066] The hydrogen-based fuel injected by the pre-combustion stage and the hydrogen-based fuel injected by the main combustion stage have different combustion speeds and point extinction characteristics. Generally, the pre-combustion stage flame is in an equivalent state or a slightly rich combustion state, and is used for ignition and stable combustion of the combustion chamber in a low-power state. The main combustion stage flame is in a lean combustion state in principle, and is used for stable combustion of the combustion chamber in a high-power state. After the main combustion stage flame is turned on, the proportion of the hydrogen-based fuel of the pre-combustion stage and the main combustion stage can be adjusted to avoid backfire, flameout and combustion oscillation and the like, and low-pollution stable combustion with low carbon emissions is formed.

[0067] Although the present application is disclosed with the preferred embodiments as above, it is not intended to limit the present application, and any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the present application. Therefore, any modification, equivalent change and modification made to the above embodiments according to the technical essence of the present application, which does not deviate from the technical solutions of the present application, falls within the protection scope defined by the claims of the present application.

Claims

1. A combustion organization device (100) for hydrogen-based fuels, characterized by, The combustion organization device (100) comprises a base body (20) for connecting a fuel main pipe (200) and a fuel branch pipe (300) respectively, one side of the fuel branch pipe (300) is connected to the base body (20), and the other side is connected to the pre-combustion stage fuel injection hole (11) and the main combustion stage fuel injection hole (21) of the disc-shaped body (10); an air passage (4) for air entering the combustion organization device (100) is formed between the base body (20) and the disc-shaped body (10). The disc-shaped body (10) further has an air cooling hole (3) surrounding the main combustion stage fuel injection hole (21); the diameter of the air cooling hole (3) is less than 0.5 mm. The flow area of the air cooling hole (3) is not more than 30% of the flow area of the air rotation structure (110). The combustion organization device (100) comprises a base body (20) for connecting a fuel main pipe (200) and a fuel branch pipe (300) respectively, one side of the fuel branch pipe (300) is connected to the base body (20), and the other side is connected to the pre-combustion stage fuel injection hole (11) and the main combustion stage fuel injection hole (21) of the disc-shaped body (10); an air passage (4) for air entering the combustion organization device (100) is formed between the base body (20) and the disc-shaped body (10). The disc-shaped body (10) further has an air cooling hole (3) surrounding the main combustion stage fuel injection hole (21); the diameter of the air cooling hole (3) is less than 0.5 mm.

2. The combustion organization device (100) according to claim 1, characterized in that The flow area of the air cooling hole (3) is not more than 30% of the flow area of the air rotation structure (110).

3. The combustion organization device (100) according to claim 1, characterized in that The combustion organization device (100) comprises a base body (20) for connecting a fuel main pipe (200) and a fuel branch pipe (300) respectively, one side of the fuel branch pipe (300) is connected to the base body (20), and the other side is connected to the pre-combustion stage fuel injection hole (11) and the main combustion stage fuel injection hole (21) of the disc-shaped body (10); an air passage (4) for air entering the combustion organization device (100) is formed between the base body (20) and the disc-shaped body (10).

4. The combustion organization device (100) according to claim 3, characterized in that The disc-shaped body (10) further has an air cooling hole (3) surrounding the main combustion stage fuel injection hole (21); the diameter of the air cooling hole (3) is less than 0.5 mm.

5. The combustion organization device (100) according to claim 4, characterized in that The flow area of the air cooling hole (3) is not more than 30% of the flow area of the air rotation structure (110).

6. The combustion organization device (100) according to any one of claims 1 to 5, characterized in that The combustion organization device (100) comprises a base body (20) for connecting a fuel main pipe (200) and a fuel branch pipe (300) respectively, one side of the fuel branch pipe (300) is connected to the base body (20), and the other side is connected to the pre-combustion stage fuel injection hole (11) and the main combustion stage fuel injection hole (21) of the disc-shaped body (10); an air passage (4) for air entering the combustion organization device (100) is formed between the base body (20) and the disc-shaped body (10).

7. The combustion organization device (100) according to claim 6, characterized in that ​ 8. A combustion chamber (1000) characterized by, ​ 9. The combustion chamber (1000) as claimed in claim 8, characterized in that, The combustion container (400) is a ring container, a plurality of the combustion organization devices (100) are circumferentially distributed and connected with the ring combustion container (400), the air flow path of the combustion chamber (1000) includes a first air flow path (1001), a second air flow path (1002) and a third air flow path (1003); The ring combustion container (400) has an outer ring wall (401) and an inner ring wall (402), the first air flow path (1001) provides cooling air to the cooling hole of the outer ring wall (401), the second air flow path (1002) provides cooling air to the cooling hole of the inner ring wall (402), and the third air flow path (1003) provides air to the combustion organization device (100).

10. The combustion chamber (1000) as claimed in claim 9, characterized in that, The combustion organization device (100) is the combustion organization device (100) of claim 7 or 8, and the area ratio of the total area of the air cooling hole (3), the total area of the precombustion stage air injection hole (12), and the total area of the cooling hole of the outer ring wall (401) and the inner ring wall (402) is 10-20%: 50-60%: 20-40%.

11. A gas turbine engine characterized by, The combustion chamber (1000) according to any one of claims 8-10.

12. A method of combustion of a hydrogen-based fuel with air, characterized by, The combustion chamber (1000) according to any one of claims 8-10. Providing a precombustion stage (1) and a main combustion stage (2) surrounding the precombustion stage (1); In the first state, the hydrogen-based fuel of the precombustion stage (1) is directly injected, and the precombustion stage flame and the swirling flow around it form a precombustion stage diffusion flame (5), and the main combustion stage (2) is closed; In the second state, the hydrogen-based fuel of the precombustion stage (1) is directly injected, and the precombustion stage flame and the swirling flow around it form a precombustion stage diffusion flame (5), and the hydrogen-based fuel of the main combustion stage (2) is directly injected, and the swirling flow forms a main combustion stage diffusion flame (6).

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