Combustor, gas turbine engine, mixer for hydrogen-based fuel, and mixing method

Abstract

The application relates to a combustor, a gas turbine engine, a mixer for hydrogen-based fuel and a mixing method. The mixer for hydrogen-based fuel comprises a first annular wall surface forming a first annular chamber, the end of the first annular wall surface being an air outlet end; a second annular wall surface located in the radial space defined by the first annular wall surface; the end of the second annular wall surface being a closed end surface, and the side wall of the second annular wall surface being provided with fuel injection holes, the injection direction of the fuel injection holes being radially outward; wherein the end of the second annular wall surface and the axial position of the fuel injection holes are located downstream of the end of the first annular wall surface, and the radial space between the inner wall of the first annular wall surface and the outer wall of the second annular wall surface forms an air passage.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of combustion chambers, in particular to a combustor, a gas turbine engine, a mixer for hydrogen-based fuel and a mixing 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 NO x 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. With the proposal of the carbon neutral target, 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 NO x ). However, 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 mixer for hydrogen-based fuel.

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

[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 mixing method of hydrogen-based fuel and air.

[0007] According to one aspect of the present application, a mixer for hydrogen-based fuel comprises: a first annular wall surface forming a first annular chamber, the end of the first annular wall surface being an air outlet end; a second annular wall surface located in the radial space defined by the first annular wall surface; the end of the second annular wall surface being a closed end surface, the side wall of the second annular wall surface having a fuel injection hole, the injection direction of the fuel injection hole being radially outward; wherein the end of the second annular wall surface and the axial position of the fuel injection hole are located downstream of the end of the first annular wall surface, and the radial space between the inner wall of the first annular wall surface and the outer wall of the second annular wall surface forms an air passage.

[0008] The technical scheme of the present application is different from the comparative scheme in that the liquid fuel needs to be radially injected into the air of the axial jet through the fuel injection hole to accelerate the hydrogen-based fuel and the air to mix rapidly, so that the mixture is fully and rapidly combusted; at the same time, the end of the second annular wall surface is a closed end surface, a shear layer is generated, and a backflow area is formed at the closed end surface, so that the combustion flame is stable. The risk of backfire and ablation of the combustion chamber is reduced, and a safe, stable, low-pollution and low-carbon emission combustion organization form is realized.

[0009] In one or more embodiments of the mixer, the downstream section of the air channel has a tapered structure.

[0010] In one or more embodiments of the mixer, the angle of the tapered structure is 30°-60°.

[0011] In one or more embodiments of the mixer, the fuel injection holes are uniformly distributed in the circumferential direction, the number is 8-20, and the diameter of the fuel injection holes is 0.3mm-2mm.

[0012] In one or more embodiments of the mixer, the axial position of the fuel injection hole is located 5mm-10mm downstream of the end of the first annular wall surface.

[0013] In one or more embodiments of the mixer, the axial position of the end of the second annular wall surface is located 10mm-20mm downstream of the end of the first annular wall surface.

[0014] In one or more embodiments of the mixer, the first annular wall surface is a housing, including a cylindrical surface and a tapered surface of the downstream section of the first annular wall surface, which is tapered relative to the radial dimension of the cylindrical surface; the second annular wall surface is a solid cylinder, and a fuel channel is arranged in the solid cylinder to communicate with the fuel injection hole.

[0015] In one or more embodiments of the mixer, the end of the second annular wall surface is a flat surface.

[0016] According to another aspect of the present application, a burner includes a plurality of mixers as described above.

[0017] In one or more embodiments of the burner, the plurality of mixers form a plurality of coaxial annular rings relative to the axis of the annular cavity, and the plurality of first coaxial annular rings can be selectively combined.

[0018] In one or more embodiments of the combustor, the plurality of mixers form a plurality of combustor groups in a circumferential distribution of the annular cavity, each combustor group comprising the plurality of mixers forming a plurality of second coaxial annulars relative to an axis of the combustor group, the plurality of combustor groups and the plurality of second coaxial annulars being selectively combinable.

[0019] A gas turbine engine according to yet another aspect of the present application comprises a combustor as described above.

[0020] A hydrogen-based fuel and air mixing method according to yet another aspect of the present application comprises: providing a hydrogen-based fuel injection hole at a radially inner side of an air passage; the injection direction of the fuel injection hole of the hydrogen-based fuel is set to be radially outward injection; the axial position of the fuel injection hole is set to be located downstream of the air outlet end of the air passage; a closed end surface is provided at a position extending downstream of the axial position of the fuel injection hole. 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 the embodiments, taken in conjunction with the accompanying drawings, which show at least one example of a preferred embodiment of the present application. It is to be understood that the drawings are designed solely for the purpose of illustration and does not purport to show every possible embodiment of the present application, and that the description is not to be considered as limiting the scope of the application. In the drawings:

[0022] Figure 1 Structure diagram of a mixer according to an embodiment;

[0023] Figure 2 Structure diagram of a cross section A-A of a combustor according to an embodiment; Figure 1

[0024] Structure diagram of a combustor according to an embodiment; Figure 3

[0025] Structure diagram of a combustor according to an embodiment; Figure 4A

[0026] Structure diagram of a combustor according to another embodiment. Figure 4B Reference Signs:

[0027] 100 - mixer, 200 - combustor;

[0028] 1 - first annular wall surface, 10 - first annular cavity, 11 - cylindrical surface, 12 - conical surface, 101 - end portion, 102 - inner wall;

[0029]

[0030] ​2 - second annular wall, 201 - end, 202 - outer wall, 203 - side wall, 21 - fuel injection hole, 22 - fuel passage, 20 - fuel pipe;

[0031] 3 - air passage;

[0032] 4 - annular cavity, 41, 42, 43, 44 - coaxial annular, 410, 420, 430, 440, 450, 460, 470, 480 - combustor group. DETAILED DESCRIPTION

[0033] Reference will now be made in detail to various embodiments of the present application, examples of which are illustrated in the accompanying drawings and described below. While the present application will be described in conjunction with the exemplary embodiments, it should be understood that the present application is not limited to those exemplary embodiments. On the contrary, the present application is intended to cover various alternatives, modifications, equivalents and other embodiments, which can be included within the spirit and scope of the present application as defined by the appended claims.

[0034] In the following description, the terms "left", "right", "radial", "axial", "circumferential", "inner", "outer", "upstream", "downstream" or other orientation terms indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, only for the convenience of describing the present 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 on the present application.

[0035] At the same time, 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 "an embodiment" or "one 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.

[0036] 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.

[0037] 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 direct hydrogen combustion based on the traditional kerosene combustion of an aero-engine and a gas turbine combustor has problems such as difficult hydrogen fuel injection arrangement, high flame temperature, easy backfire and ablation. Therefore, a brand new hydrogen fuel nozzle assembly needs to be developed to adapt to the characteristics of hydrogen combustion.

[0038] Based on the above considerations, the inventors have made an in-depth study and designed a mixer for hydrogen-based fuel. Unlike the liquid fuel which needs to be organized by cyclone combustion, the hydrogen-based fuel is radially injected into the axial jet through the fuel injection hole, which accelerates the rapid mixing of hydrogen-based fuel and air, so that the mixing is fully and quickly combusted. At the same time, the end of the second annular wall surface is closed, which generates a shear layer and forms a backflow area at the closed end surface, so that the combustion flame is stable. The risk of backfire and ablation in the combustion chamber is reduced, and a safe and stable combustion organization form with low pollution and low carbon emission is realized.

[0039] In addition, different arrangements and arrangements can be adopted for different mixers to adapt to different combustion chamber forms and meet different working condition requirements.

[0040] Although the mixer disclosed in the embodiments of the present application is suitable for hydrogen-based fuel combustion organization, it is not limited thereto, and the mixer disclosed in the embodiments of the present application can be applied to stable combustion of fuel and reduction of backfire risk.

[0041] Reference Figure 1 Combination Figure 2 As shown in the figure, in one embodiment, the specific structure of the mixer 100 for hydrogen-based fuel b can be that it comprises a first annular wall surface 1 and a second annular wall surface 2. The first annular wall surface 1 constitutes a first annular chamber 10, and the end 101 of the first annular wall surface 1 is an air outlet end. The second annular wall surface 2 is located in the radial space defined by the first annular wall surface 1; the end 201 of the second annular wall surface 2 is a closed end surface, and the side wall 203 of the second annular wall surface 2 has a fuel injection hole 21, and the injection direction of the fuel injection hole 21 is radially outward. Wherein, the axial position of the end 201 of the second annular wall surface 2 and the fuel injection hole 21 is located downstream of the end 101 of the first annular wall surface 1, and the radial space between the inner wall 102 of the first annular wall surface 1 and the outer wall 202 of the second annular wall surface 2 constitutes an air passage 3.

[0042] 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.

[0043] The meaning of "closed end surface" here is that the downstream end of the side wall 203 extends radially inward to close the end 201 of the second annular wall surface 2. Compared with the downstream end of the first annular chamber 10 formed by the first annular wall surface 1 which is open for air a to pass through, the end 201 of the second annular wall surface 2 and the side wall 203 constitute a bluff body, which can generate a shear layer at the connection between the end 201 and the side wall 203, so as to stabilize the combustion flame, and can form a backflow area at the end 201 to strengthen the flame stabilization effect.

[0044] The beneficial effect of the embodiment is that, unlike the liquid fuel of the comparative scheme which needs the characteristics of swirl combustion organization, the hydrogen-based fuel is radially injected into the air of the axial jet through the fuel injection hole, the hydrogen-based fuel is accelerated to mix with the air quickly, and the mixing is sufficient and fast combustion; at the same time, by setting the end of the second annular wall surface as a closed end surface, a shear layer is generated and a backflow zone is formed at the closed end surface, so that the combustion flame is stable. Reduce the risk of backfire and ablation of the combustion chamber, realize safe and stable combustion organization form with low pollution and low carbon emission.

[0045] Reference Figure 2 As shown in some embodiments, the specific structure of the air channel 3 can be that the downstream section of the air channel 3 has a tapered structure 31.

[0046] The "air channel 3" here is for the rapid passage of air a, and its extension direction is axial.

[0047] The "tapered structure 31" here means a structure whose radial dimension gradually decreases from upstream to downstream.

[0048] The "downstream section" here means that compared with the "downstream end", the radial minimum dimension of the tapered structure 31 can be located at the downstream end of the air channel 3, or it can also be a structure that first tapers and then is straight, that is, the radial minimum dimension is located on the downstream side of the air channel 3, and then extends to the downstream end with the radial minimum dimension.

[0049] The beneficial effect of such a setting is that by setting the tapered structure to reduce the flow area of the air, the air flow rate is increased to carry away the hydrogen-based fuel sprayed from the fuel injection hole and mix, thereby preventing spontaneous combustion and backfire and improving combustion stability.

[0050] Continue to refer to Figure 2 As shown in some embodiments, the specific structure of the tapered structure 31 can be that the angle θ of the tapered structure 31 is 30°-60°. The beneficial effect of such a setting is that the optimal air flow rate can be obtained, so that the air flow rate through the tapered structure is moderately increased, preventing the air flow rate from being increased too much, causing the flame to separate from the mixer, the fuel and air cannot be mixed and ignited, and the flame-out phenomenon occurs; or preventing the air flow rate from being too low, which cannot mix and carry away the hydrogen-based fuel, causing the fuel to return to the mixer and the backfire phenomenon occurs.

[0051] Reference Figure 1As shown, in some embodiments, the specific structure of the fuel injection hole 21 can be that the fuel injection hole 21 is circumferentially uniformly distributed in a plurality of 8-20, and the diameter of the fuel injection hole 21 is 0.3-2 mm. The "diameter" here is the equivalent diameter, and is not limited to the fuel injection hole 21 being a circular injection hole. The beneficial effect of such arrangement is that by uniformly distributing a plurality of fuel injection holes in the circumferential direction, rapid and stable combustion of hydrogen-based fuel multi-point injection is achieved; the diameter design of the fuel injection hole can make the injection hole spray a suitable amount of hydrogen-based fuel, and the problem of overheating and burning caused by excessive fuel amount will not occur, nor will the problem of insufficient fuel amount and ineffective combustion.

[0052] Reference Figure 1 In combination Figure 2 As shown, in some embodiments, the specific structure of the fuel injection hole 21 can be that the axial position of the fuel injection hole 21 is located 5-10 mm downstream of the end portion 101 of the first annular wall surface 1. The beneficial effect of such arrangement is that it can ensure good mixing of hydrogen-based fuel and air, and effectively prevent backfire from occurring.

[0053] Reference Figure 1 In combination Figure 2 As shown, in some embodiments, the specific structure of the end portion 201 of the second annular wall surface 2 can be that the axial position of the end portion 201 of the second annular wall surface 2 is located 10-20 mm downstream of the end portion 101 of the first annular wall surface 1. The beneficial effect of such arrangement is that the optimal distance between the fuel injection hole and the end portion of the second annular wall surface can be obtained, and if the fuel injection hole is too close to the end portion, it is easy to burn due to high temperature; if it is too far, backfire is easy to occur, and the flame returns to the fuel injection hole.

[0054] Reference Figure 1 In combination Figure 2 As shown, in some embodiments, the specific structure of the mixer 100 for hydrogen-based fuel can be that the first annular wall surface 1 is a shell, including a cylindrical surface 11 and a conical surface 12 downstream of the first annular wall surface 1, which has a radial dimension tapering relative to the cylindrical surface 11; the second annular wall surface 2 is a solid cylinder, and a fuel passage 22 is arranged in the solid cylinder to communicate with the fuel injection hole 21. The meaning of "downstream section" here is as described above, and the radial minimum dimension of the conical surface 12 can be located at the downstream end of the air passage 3, or can also be a structure that tapers first and then is straight, i.e. the radial minimum dimension is located on the downstream side of the air passage 3, and then extends to the downstream end with the radial minimum dimension. The downstream end of the "solid cylinder" here is the end portion 201 of the second annular wall surface 2, which constitutes a closed end surface. The beneficial effect of such arrangement is that the structure is simple and easy to process and manufacture.

[0055] Reference Figure 2As shown, in some embodiments, the specific structure of the second annular wall surface 2 can be that the end 201 of the second annular wall surface 2 is a flat surface. The beneficial effect of such an arrangement is to promote air recirculation at the end and strengthen flame stability.

[0056] Reference is made to Figures 3 to 4B As shown, in one embodiment, the specific structure of the combustor 200 can be that it comprises a plurality of mixers 100 as described above. Specifically, in the case of the combustor 200 as shown in Figure 3 As shown in the embodiment of a part of the combustor 200, four mixers 100 are arranged in a group in the radial direction, with the fuel passages 22 of each mixer 200 being connected by a fuel pipe 20 Figure 2 As shown, the beneficial effect of such an arrangement is that, by flexible arrangement of the mixers, different combustion chamber forms can be met, ensuring stable and safe combustion of hydrogen-based fuel, reducing the risk of combustion chamber backfire and ablation, and achieving a safe and stable combustion organization form with low pollution and low carbon emissions.

[0057] Reference is made to Figure 4A As shown, in some embodiments, the specific structure of the combustor 200 can be that a plurality of mixers 100 form a plurality of coaxial annular rings 41, 42, 43, 44 relative to the axis O1 of the annular cavity 4, and a plurality of first coaxial annular rings 41, 42, 43, 44 can be selectively combined.

[0058] Here, the meaning of "annular cavity 4" refers to the cavity structure of the annular combustion chamber, and the axis O1 of the annular cavity 4 is the axis O1 of the annular combustion chamber.

[0059] Here, the meaning of "coaxial annular ring" refers to a plurality of annular rings having the same axis and the same position in the axial direction.

[0060] Here, the meaning of "selectively combined" is that different specifications of mixers are formed by different designs of the number, size, height from the end surface 201, and angle θ of the taper structure 31 of the fuel injection hole 21, and different specifications of mixers are arranged to meet the combustion characteristic requirements of different working conditions. Specifically, the mixer 100 with more fuel injection holes 21, larger diameter, and larger diameter of the first annular chamber 10 is a large-specification mixer; the mixer 100 with fewer fuel injection holes 21, smaller diameter, and smaller diameter of the first annular chamber 10 is a small-specification mixer. When only large-specification mixers are working, it is suitable for small working conditions in the combustion chamber; when only small-specification mixers are working, it is suitable for small working conditions in the combustion chamber; when large-specification and small-specification mixers are working simultaneously, it is suitable for large working conditions in the combustion chamber. For example Figure 4AIn the shown embodiment, the same large-size mixers are arranged in the coaxial annular 42, 43, the same small-size mixers are arranged in the coaxial annular 41, 44; in large working conditions, the mixers located in the coaxial annular 41, 42, 43, 44 work simultaneously; in medium and small working conditions, only the mixers located in the coaxial annular 42, 43 work; in small working conditions, only the mixers located in the coaxial annular 41, 44 work. It can be understood that different arrangement forms of different-size mixers 100 can be used to form different combustion organization modes according to different combustion characteristics requirements.

[0061] The beneficial effect of such an arrangement is that different combustion organization modes with different combustion characteristics can be formed by arranging and combining different-size mixers to meet different working conditions of the combustion chamber.

[0062] Reference Figure 4B As shown, in some embodiments, the specific structure of the combustor 200 can be that a plurality of mixers 100 form a plurality of combustor groups 410, 420, 430, 440, 450, 460, 470, 480 distributed in the circumferential direction of the annular cavity 4, each combustor group includes a plurality of mixers 100 forming a plurality of second coaxial annular 411, 412, 413 relative to the axis O2 of the combustor group, and the plurality of combustor groups and the plurality of second coaxial annular can be selectively combined. This embodiment is another arrangement mode to adapt to different combustion chamber forms. As described above, different-size mixers can also be arranged in this embodiment to meet different working conditions of the combustion chamber. For example, the combustor groups 410, 430, 450, 470 can use large-size mixers, and the combustor groups 420, 440, 460, 480 can use small-size mixers; or the combustor groups 410, 420, 430, 440, 450, 460, 470, 480 can be of the same form, the second coaxial annular 411, 413 can use large-size mixers, and the second coaxial annular 412 can use small-size mixers.

[0063] It can be understood that other combination and arrangement modes of the plurality of mixers 100 can be used according to the form and working condition requirements of the combustion chamber, and are not limited to Figure 4A 、 Figure 4B The combustor 200 shown.

[0064] Reference Figures 1 to 4B As shown, in one embodiment, the specific structure of the gas turbine engine can include the combustor 200 as described above. The beneficial effect of such an arrangement is that different combustion chamber forms can be adapted to meet different working condition requirements, and the hydrogen-based fuel can be stably and safely combusted to reduce the risk of backfire and ablation of the combustion chamber, and to achieve a safe and stable combustion organization mode with low pollution and low carbon emission.

[0065] Continuing to refer to Figures 1 to 4BAs shown, in one embodiment, the specific steps of the hydrogen-based fuel and air mixing method can be, including:

[0066] The hydrogen-based fuel injection hole 21 is arranged radially inside the air passage 3. As described above, the radial space between the inner wall 102 of the first annular wall surface 1 and the outer wall 202 of the second annular wall surface 2 constitutes the air passage 3, and the side wall 203 of the second annular wall surface 2 has the fuel injection hole 21. The second annular wall surface 2 is a solid cylinder, and the fuel passage 22 is arranged in the solid cylinder to communicate with the fuel injection hole 21, and the hydrogen-based fuel b enters the nozzle 10 through the fuel passage 22. Figure 1 、 Figure 2 As shown, the radial space between the inner wall 102 of the first annular wall surface 1 and the outer wall 202 of the second annular wall surface 2 constitutes the air passage 3, and the side wall 203 of the second annular wall surface 2 has the fuel injection hole 21. The second annular wall surface 2 is a solid cylinder, and the fuel passage 22 is arranged in the solid cylinder to communicate with the fuel injection hole 21, and the hydrogen-based fuel b enters the nozzle 10 through the fuel passage 22.

[0067] The injection direction of the hydrogen-based fuel injection hole 21 is arranged to be radially outward. As described above, the radial space between the inner wall 102 of the first annular wall surface 1 and the outer wall 202 of the second annular wall surface 2 constitutes the air passage 3, and the side wall 203 of the second annular wall surface 2 has the fuel injection hole 21. The second annular wall surface 2 is a solid cylinder, and the fuel passage 22 is arranged in the solid cylinder to communicate with the fuel injection hole 21, and the hydrogen-based fuel b enters the nozzle 10 through the fuel passage 22. Figure 1 、 Figure 2 As shown, the radial space between the inner wall 102 of the first annular wall surface 1 and the outer wall 202 of the second annular wall surface 2 constitutes the air passage 3, and the side wall 203 of the second annular wall surface 2 has the fuel injection hole 21. The second annular wall surface 2 is a solid cylinder, and the fuel passage 22 is arranged in the solid cylinder to communicate with the fuel injection hole 21, and the hydrogen-based fuel b enters the nozzle 10 through the fuel passage 22.

[0068] The axial position of the fuel injection hole 21 is arranged to be downstream of the air outlet end of the air passage 3. As described above, the radial space between the inner wall 102 of the first annular wall surface 1 and the outer wall 202 of the second annular wall surface 2 constitutes the air passage 3, and the side wall 203 of the second annular wall surface 2 has the fuel injection hole 21. The second annular wall surface 2 is a solid cylinder, and the fuel passage 22 is arranged in the solid cylinder to communicate with the fuel injection hole 21, and the hydrogen-based fuel b enters the nozzle 10 through the fuel passage 22. Figure 1 、 Figure 2 As shown, the axial position of the fuel injection hole 21 is 5-10 mm downstream of the end 101 of the first annular wall surface 1, which can ensure good mixing of hydrogen-based fuel and air, and can effectively prevent backfire.

[0069] The closed end surface is arranged at the position where the axial position of the fuel injection hole 21 extends downstream. As described above, the radial space between the inner wall 102 of the first annular wall surface 1 and the outer wall 202 of the second annular wall surface 2 constitutes the air passage 3, and the side wall 203 of the second annular wall surface 2 has the fuel injection hole 21. The second annular wall surface 2 is a solid cylinder, and the fuel passage 22 is arranged in the solid cylinder to communicate with the fuel injection hole 21, and the hydrogen-based fuel b enters the nozzle 10 through the fuel passage 22. Figure 1 、 Figure 2 As shown, the axial position of the end 201 of the second annular wall surface 2 is 10-20 mm downstream of the end 101 of the first annular wall surface 1, which generates a shear layer and forms a backflow area at the closed end surface, stabilizes the combustion flame at the end 201, ensures that the distance between the injection hole and the end is appropriate, and prevents burnout or backfire. The global equivalence ratio of hydrogen combustion flame is 0.3-0.6.

[0070] The beneficial effects of such arrangement are that, unlike the liquid fuel which needs to be organized by swirl combustion in the comparative scheme, hydrogen is directly injected into the accelerated air jet for combustion, reducing the risk of combustion chamber backfire and ablation, and realizing a safe and stable, low-pollution and low-carbon emission combustion organization form.

[0071] In summary, the beneficial effects of the above embodiments of the burner, gas turbine engine, mixer for hydrogen-based fuel, and mixing method include but are not limited to one or a combination of the following:

[0072] 1. Unlike the characteristics of the liquid fuel needing swirl combustion organization of the comparative scheme, hydrogen-based fuel is radially injected into the air axial jet through the setting of the fuel injection hole, the hydrogen-based fuel and the air are accelerated to mix quickly, the mixing is full and fast, and the combustion is stable; meanwhile, the end of the second annular wall surface is set as a closed end surface, a shear layer is generated, and a backflow area is formed on the closed end surface, so that the combustion flame is stable. The backfire and ablation risk of the combustion chamber is reduced, and a safe and stable, low-pollution and low-carbon emission combustion organization form is realized.

[0073] 2. Through the flexible arrangement of the mixer, different combustion chamber forms can be met, stable and safe combustion of the hydrogen-based fuel is ensured, the backfire and ablation risk of the combustion chamber is reduced, and a safe and stable, low-pollution and low-carbon emission combustion organization form is realized.

[0074] 3. Different combustion chamber forms can be adapted to meet different working condition requirements, the hydrogen-based fuel can be stably and safely combusted, the backfire and ablation risk of the combustion chamber is reduced, and a safe and stable, low-pollution and low-carbon emission combustion organization form is realized.

[0075] 4. Unlike the characteristics of the liquid fuel needing swirl combustion organization of the comparative scheme, hydrogen is directly injected into the accelerated air jet for combustion, the backfire and ablation risk of the combustion chamber is reduced, and a safe and stable, low-pollution and low-carbon emission combustion organization form is realized.

[0076] 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, without departing from the technical solutions of the present application, fall within the protection scope defined by the claims of the present application.

Claims

1. A mixer (100) for hydrogen-based fuels, characterized in that, include: The first annular wall (1) forms the first annular chamber (10), and the end (101) of the first annular wall (1) is the air outlet. The second annular wall (2) is located within the radial space defined by the first annular wall (1); the end (201) of the second annular wall (2) is a closed end face, and the side wall of the second annular wall (2) has a fuel injection hole (21), the injection direction of the fuel injection hole (21) is radially outward; Wherein, the end (201) of the second annular wall (2) and the axial position of the fuel injection hole (21) are located downstream of the end (101) of the first annular wall (1), and the radial space between the inner wall of the first annular wall (1) and the outer wall of the second annular wall (2) forms an air passage (3).

2. The mixer (100) as claimed in claim 1, characterized in that, The downstream section of the air passage (3) has a tapered structure (31).

3. The mixer (100) as claimed in claim 2, characterized in that, The angle of the tapered structure (31) is 30°-60°.

4. The mixer (100) as claimed in claim 1, characterized in that, The fuel injection holes (21) are evenly distributed in a circumferential manner, with a quantity of 8-20, and the diameter of the fuel injection holes (21) is 0.3mm-2mm.

5. The mixer (100) as claimed in claim 1, characterized in that, The axial position of the fuel injection hole (21) is located 5mm-10mm downstream of the end (101) of the first annular wall (1).

6. The mixer (100) as claimed in claim 5, characterized in that, The axial position of the end (201) of the second annular wall (2) is located 10mm-20mm downstream of the end (101) of the first annular wall (1).

7. The mixer (100) as claimed in claim 1, characterized in that, The first annular wall (1) is a shell, including a cylindrical surface (11) and a downstream section of the first annular wall (1) having a tapered surface (12) that tapers in radial dimension relative to the cylindrical surface (11); the second annular wall (2) is a solid column, in which a fuel channel (22) is provided to connect the fuel injection hole (21).

8. The mixer (100) as claimed in claim 1, characterized in that, The end (201) of the second annular wall (2) is a plane.

9. A burner (200), characterized in that, Includes multiple mixers (100) as described in any one of claims 1-8.

10. The burner (200) as claimed in claim 9, characterized in that, The plurality of mixers (100) form a plurality of first coaxial rings (41, 42, 43, 44) relative to the axis (O1) of the annular cavity (4), and the plurality of first coaxial rings (41, 42, 43, 44) can be selectively combined.

11. The burner (200) as claimed in claim 9, characterized in that, The plurality of mixers (100) constitute a plurality of burner groups (410, 420, 430, 440, 450, 460, 470, 480) circumferentially distributed in the annular cavity (4), each burner group including the plurality of mixers (100) constituting a plurality of second coaxial rings (411, 412, 413) relative to the axis (O2) of the burner group, the plurality of burner groups and the plurality of second coaxial rings may be selectively combined.

12. A gas turbine engine, characterized in that, Includes the burner (200) as described in any one of claims 9-11.

13. A method for mixing hydrogen-based fuel with air, characterized in that, include: Hydrogen-based fuel injection holes (21) are provided on the radial inner side of the air passage (3); The injection direction of the fuel nozzle (21) for hydrogen-based fuel is set to radially outward; The axial position of the fuel injection hole (21) is set to be downstream of the air outlet end of the air passage (3); The closed end face is positioned downstream of the axial position of the fuel injection hole (21).

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