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

Abstract

This invention provides a combustion chamber, a gas turbine engine, a combustion organization device for hydrogen-based fuels, and a combustion method. The combustion organization device for hydrogen-based fuels includes: a pre-combustion stage, comprising a pre-combustion stage annular wall, pre-combustion stage fuel nozzles, and a first swirler; the axial position of the pre-combustion stage fuel nozzles is located upstream of the outlet of the first annular chamber; the pre-combustion stage is surrounded by a main combustion stage, the main combustion stage comprising a main combustion stage annular wall, main combustion stage fuel nozzles, and a second swirler, the main combustion stage annular wall and the pre-combustion stage annular wall forming a second annular chamber, the main combustion stage fuel nozzles being direct injection, and their axial position being the same as the axial position of the outlet of the second annular chamber. This achieves low-carbon, low-pollution emission combustion.

Description

Technical Field

[0001] This invention relates to the field of combustion chambers, and more particularly to combustion chambers, gas turbine engines, combustion organization devices for hydrogen-based fuels, and combustion methods. Background Technology

[0002] Increased environmental awareness has made reducing pollutant emissions during combustion one of the major challenges in the development of aero-engines and gas turbines. To achieve lower NOx emissions without increasing the concentration of carbon monoxide and unburned hydrocarbons in the exhaust, low-emission combustion methods such as lean fuel premixing and pre-evaporation, and rich fuel quenching and lean fuel combustion have been widely researched and applied in gas turbines and aero-engines. With the advent of carbon neutrality goals, combustion organization methods based on sustainable fuels and other fuels, such as hydrocarbon fuels, have emerged in aero-engine combustors. Their main purpose is to further reduce carbon emissions while reducing traditional pollutant emissions (such as NOx). However, hydrocarbon fuel-based exhaust emissions always contain CO2, failing to meet the requirements of low-carbon combustion. Hydrogen combustion, as one of the most environmentally friendly combustion organization methods currently available, avoids the problem of combustion-free carbon emissions and other combustion pollution products, making it a highly promising low-carbon fuel. Summary of the Invention

[0003] The purpose of this invention is to provide a combustion organization device for hydrogen-based fuels.

[0004] Another object of the present invention is to provide a combustion chamber.

[0005] Another object of the present invention is to provide a gas turbine engine.

[0006] Another object of the present invention is to provide a method for combustion of hydrogen-based fuel with air.

[0007] According to one aspect of the present invention, a combustion organization device for hydrogen-based fuel includes: a pre-combustion stage, comprising a pre-combustion stage annular wall, a pre-combustion stage fuel nozzle, and a first swirler; the pre-combustion stage annular wall provides a first annular chamber, the pre-combustion stage fuel nozzle and the first swirler are located inside the first annular chamber, the first swirler surrounds at least a portion of the pre-combustion stage fuel nozzle, and the axial position of the pre-combustion stage fuel nozzle is located upstream of the outlet of the first annular chamber; a main combustion stage, the pre-combustion stage being surrounded by the main combustion stage, the main combustion stage including a main combustion stage annular wall, a main combustion stage fuel nozzle, and a second swirler, the main combustion stage annular wall and the pre-combustion stage annular wall forming a second annular chamber, the second swirler being located inside the second annular chamber, the main combustion stage fuel nozzle surrounding at least a portion of the main combustion stage annular wall, and the main combustion stage fuel nozzle being a direct injection, its axial position being the same as the axial position of the outlet of the second annular chamber.

[0008] The technical solution of this application achieves stable combustion of the pre-combustion stage flame by setting a pre-combustion stage nozzle upstream of the outlet of the first annular chamber, allowing hydrogen-based fuel to mix with the air swirling through the first cyclone separator to form a partially premixed combustion pre-combustion stage flame, thus suppressing the formation of thermal NOx. By setting a main combustion stage nozzle at the same axial position at the outlet of the second annular chamber, hydrogen-based fuel is directly injected and undergoes high-speed shear mixing and combustion with the air swirling through the second cyclone separator to form a non-premixed flame, reducing the risk of backfire. The main combustion stage is injected through multiple tiny nozzles, resulting in a relatively uniform circumferential distribution of the combustion flame and high flame stability characteristics. This avoids the formation of local hot spots and effectively suppresses the formation of thermal NOx, thus giving the pre-combustion stage flame and the main combustion stage flame different combustion rates and ignition / quenching characteristics. Typically, the pre-combustion stage flame is used for ignition and stable combustion under low thrust conditions, while the main combustion stage flame is used for stable combustion under high thrust conditions. After the main combustion stage flame is activated, the ratio of hydrogen-based fuel in the pre-combustion stage and the main combustion stage can be adjusted to avoid backfire, flameout, and combustion oscillation, thus achieving stable combustion with low carbon emissions and low pollution. Furthermore, this solution does not involve a completely new combustion organization device design; instead, it improves upon the structure of a traditional kerosene combustion organization device to achieve safe and stable combustion of hydrogen-based fuel, resulting in low pollution and low carbon emissions, and reducing the cost and risk of redesign.

[0009] In one or more embodiments of the combustion organization device, the pre-combustion stage annular wall includes a tapering section and an expanding section connected downstream of the tapering section, a throat is formed at the junction of the tapering section and the expanding section, the axial position of the pre-combustion stage fuel injection orifice is located downstream of the throat, and the first swirler is located upstream of the tapering section.

[0010] In one or more embodiments of the combustion organization device, the axial position of the pre-combustion stage fuel injection orifice is located 5mm-20mm downstream of the throat.

[0011] In one or more embodiments of the combustion organization device, the expansion section has air cooling holes.

[0012] In one or more embodiments of the combustion organization device, the pre-combustion stage fuel nozzles include straight injection nozzles and oblique injection nozzles; the number of pre-combustion stage fuel nozzles is 6-12, and the diameter of the nozzles is 0.5mm-1mm.

[0013] In one or more embodiments of the combustion organization device, the main combustion stage fuel injection holes are evenly distributed circumferentially around the annular wall of the main combustion stage, and the number of the main combustion stage fuel injection holes is 12-20, with a diameter of 0.5mm-1mm.

[0014] In one or more embodiments of the combustion organization device, the number of swirls in the second swirler is adjustable from the number of swirls in the first swirler.

[0015] In one or more embodiments of the combustion organization device, the pre-combustion stage fuel nozzle is connected to a first hydrogen-based fuel line, and the main combustion stage fuel nozzle is connected to a second hydrogen-based fuel line.

[0016] According to another aspect of the present invention, a combustion chamber includes: a combustion organization device as described above; a combustion container; wherein the combustion organization device is located at the upstream end of the combustion container and connected thereto, a first hydrogen-based fuel can be directly injected into the combustion container from the main combustion stage fuel injection orifice, a first air can be directly injected into the combustion container from the second annular chamber, and a second hydrogen-based fuel can be premixed with the second air to form a mixed fluid that flows out from the first annular chamber into the combustion container.

[0017] In one or more embodiments of the combustion chamber, the combustion container is an annular container, and a plurality of the combustion organization devices are distributed circumferentially and connected to the annular combustion container; a portion of the combustion organization devices have pre-combustion stage fuel injection holes that are straight injection holes, and another portion of the combustion organization devices have pre-combustion stage fuel injection holes that are oblique injection holes.

[0018] In one or more embodiments of the combustion chamber, the wall of the combustion vessel has cooling channels through which third air enters the combustion chamber.

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

[0020] According to another aspect of the present invention, a method for organizing the combustion of hydrogen-based fuel and air includes: in the main combustion stage, a first hydrogen-based fuel and a first air are directly injected into the combustion vessel from the main combustion stage fuel nozzle and a second annular chamber, respectively; in the pre-combustion stage, a second hydrogen-based fuel and a second air are premixed to form a mixed fluid, which is then output to the combustion vessel. Attached Figure Description

[0021] The above and other features, properties, and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments, in which the same reference numerals always denote the same features. It should be noted that these drawings are merely illustrative and are not drawn to scale, and should not be construed as limiting the scope of protection actually claimed by the present invention, wherein:

[0022] Figure 1 This is a schematic diagram of the circumferential portion of a combustion chamber according to one embodiment;

[0023] Figure 2A This is a schematic diagram of the structure of a combustion organization device according to an embodiment;

[0024] Figure 2B This is a schematic diagram of the combustion organization device according to another embodiment;

[0025] Figure 3A This is a schematic diagram of the combustion organization device from another perspective of one embodiment;

[0026] Figure 3B According to one embodiment Figure 3A A schematic diagram of the AA section;

[0027] Figure 4A A schematic diagram of the combustion organization device from another perspective of another embodiment;

[0028] Figure 4B According to one embodiment Figure 4A A schematic diagram of the AA section.

[0029] Figure label:

[0030] 1000 - Combustion chamber, 1001 - First air flow path, 1002 - Second air flow path, 1003 - Third air flow path, 101a - Outer casing, 102a - Inner casing, 103 - Diffuser;

[0031] 100 - Combustion organization device;

[0032] 1-Pre-combustion stage;

[0033] 11-Pre-combustion stage annular wall, 110-throat, 111-constriction section, 112-expansion section, 1120-air cooling hole;

[0034] 101 - First annular chamber; 1011 - Outlet of the first annular chamber;

[0035] 102 - Second annular chamber; 1021 - Outlet of the second annular chamber;

[0036] 12-Pre-combustion fuel nozzle, 121-Linear injection nozzle, 122-Oblique injection nozzle;

[0037] 13-First hydrocyclone;

[0038] 2-Main combustion stage, 21-Main combustion stage annular wall, 22-Main combustion stage fuel injection hole, 23-Second cyclone separator;

[0039] 31 - First hydrogen-based fuel line; 32 - Second hydrogen-based fuel line;

[0040] 200 - Combustion vessel, 201 - Wall, 202 - Cooling passage. Detailed Implementation

[0041] Reference will now be made in detail to various embodiments of the invention, examples of which are shown in the accompanying drawings and described below. Although the invention will be described in conjunction with exemplary embodiments, it should be understood that this specification is not intended to limit the invention to those exemplary embodiments. Rather, the invention is intended to cover not only these exemplary embodiments, but also various alternatives, modifications, equivalents, and other embodiments that may be included within the spirit and scope of the invention as defined by the appended claims.

[0042] In the following description, the orientation or positional relationship indicated by terms such as "axial," "radial," "circumferential," "upstream," "downstream," "inner," "outer," or other directional terms is based on the orientation or positional relationship shown in the accompanying drawings and is only for the convenience of describing the invention and simplifying the description, and is not intended to indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. In addition, "upstream" and "downstream" are based on the direction of airflow, for example, air flows from "upstream" to "downstream."

[0043] Furthermore, this application uses specific terms to describe its embodiments. For example, "an embodiment" and / or "one embodiment" refers to a particular feature, structure, or characteristic associated with at least one embodiment of this application. Therefore, it should be emphasized and noted that "an embodiment" or "one embodiment" mentioned twice or more in different locations in this specification do not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of this application can be appropriately combined.

[0044] With increasing demands for low carbon emissions from engines, hydrogen combustion is one of the most environmentally friendly combustion organization methods currently available, and it is necessary to rationally organize the combustion of hydrogen in the combustion chambers of aero engines and gas turbines.

[0045] The inventors of this application, through in-depth research, discovered that hydrogen combustion is characterized by extremely fast combustion speed and high flame temperature. Directly using conventional kerosene-fired burners in aircraft engines and gas turbines for hydrogen combustion presents problems such as difficulties in hydrogen fuel injection arrangement, high flame temperature, and susceptibility to backfire and ablation. Furthermore, developing a completely new combustion chamber would not only be costly but also carry significant risks.

[0046] Based on the above considerations, the inventors, through in-depth research, designed a combustion organization device for hydrogen-based fuels. By setting a pre-combustion stage nozzle upstream of the outlet of the first annular chamber, the hydrogen-based fuel is mixed with the air swirling through the first cyclone separator to form a partially premixed combustion pre-combustion stage flame, achieving stable combustion and suppressing the formation of thermal NOx. By setting a main combustion stage nozzle at the same axial position at the outlet of the second annular chamber, the hydrogen-based fuel is directly injected and undergoes high-speed shear mixing with the air swirling through the second cyclone separator to form a non-premixed flame, reducing the risk of backfire. The main combustion stage is injected through multiple tiny nozzles, resulting in a relatively uniform circumferential distribution of the combustion flame and high flame stability characteristics. This avoids the formation of local hot spots and effectively suppresses the formation of thermal NOx, thus giving the pre-combustion stage flame and the main combustion stage flame different combustion rates and ignition / quenching characteristics. Typically, the pre-combustion stage flame is used for ignition and stable combustion under low thrust conditions, while the main combustion stage flame is used for stable combustion under high thrust conditions. After the main combustion stage flame is activated, the ratio of hydrogen-based fuel in the pre-combustion stage and the main combustion stage can be adjusted to avoid backfire, flameout, and combustion oscillation, thus achieving stable combustion with low carbon emissions and low pollution. Furthermore, this solution does not involve a completely new combustion organization device design; instead, it improves upon the structure of a traditional kerosene combustion organization device to achieve safe and stable combustion of hydrogen-based fuel, resulting in low pollution and low carbon emissions, and reducing the cost and risk of redesign.

[0047] Although the combustion organization device disclosed in the embodiments of this application is applicable to the combustion organization of hydrogen-based fuels, it is not limited thereto. The combustion organization device disclosed in the embodiments of this application can be used as long as it is used to ensure stable combustion of fuel and reduce the risk of backfire.

[0048] refer to Figures 1 to 4B As shown, in one embodiment, the combustion organization device 100 for hydrogen-based fuels may specifically include a pre-combustion stage 1 and a main combustion stage 2.

[0049] The pre-combustion stage 1 includes a pre-combustion stage annular wall 11, a pre-combustion stage fuel nozzle 12, and a first swirler 13; the pre-combustion stage annular wall 11 provides a first annular chamber 101, the pre-combustion stage fuel nozzle 12 and the first swirler 13 are located inside the first annular chamber 101, the first swirler 13 surrounds at least a portion of the pre-combustion stage fuel nozzle 12, and the axial position of the pre-combustion stage fuel nozzle 12 is located upstream of the outlet 1011 of the first annular chamber 101.

[0050] The pre-combustion stage 1 is surrounded by the main combustion stage 2. The main combustion stage 2 includes a main combustion stage annular wall 21, a main combustion stage fuel injection hole 22, and a second swirler 23. The main combustion stage annular wall 21 and the pre-combustion stage annular wall 11 form a second annular chamber 102. The second swirler 23 is located inside the second annular chamber 102. The main combustion stage fuel injection hole 22 surrounds at least part of the main combustion stage annular wall 21, and the main combustion stage fuel injection hole 22 is a direct injection. Its axial position is the same as the axial position of the outlet 1021 of the second annular chamber 102.

[0051] Here, "hydrogen-based fuel" means that the hydrogen content in the fuel is greater than or equal to 90% by volume. For example, hydrogen-based fuel can be pure hydrogen gas. Hydrogen-based fuel can be stored in various forms, such as liquid hydrogen, compressed gaseous hydrogen, etc.

[0052] The term "pre-combustion stage 1, main combustion stage 2" here refers to the use of staged combustion, where the flame ratio of pre-combustion stage 1 and main combustion stage 2 is flexibly adjusted according to different combustion chamber operating conditions and emission requirements. Figure 2A As shown, the main combustion stage 2 surrounds the radial outer periphery of the pre-combustion stage 1. Under low operating conditions, only the pre-combustion stage 1 operates; under high operating conditions, the pre-combustion stage 1 and the main combustion stage 2 operate together.

[0053] The meaning of "first swirler 13 and second swirler 23" here is to transform the passing airflow into a rotating airflow, accelerate the mixing of fuel and air, promote diffusion combustion, and stabilize the flame.

[0054] The “first annular chamber 101 and second annular chamber 102” here constitute the flow channel for air to pass through, so as to mix air with fuel for combustion.

[0055] The phrase "the main combustion stage fuel nozzle 22 is directly injected" here means that the main combustion stage fuel is injected in the axial direction and is not premixed with the air passing through the second vortex 23. The main combustion stage fuel is directly injected into the combustion chamber and mixed with the air to form a non-premixed flame.

[0056] The beneficial effects of this embodiment are as follows: By setting a pre-combustion stage nozzle upstream of the outlet of the first annular chamber, hydrogen-based fuel is mixed with the air swirling through the first cyclone separator to form a partially premixed combustion pre-combustion stage flame, achieving stable combustion of the pre-combustion stage flame and suppressing the formation of thermal NOx (thermal NOx refers to nitrogen oxides generated by the oxidation of N2 in combustion air at high temperatures); by setting a main combustion stage nozzle at the same axial position at the outlet of the second annular chamber, hydrogen-based fuel is directly injected and mixed with the high-speed shearing combustion of the air swirling through the second cyclone separator to form a non-premixed flame, reducing the risk of backfire. The main combustion stage is injected through multiple tiny nozzles, resulting in a relatively uniform circumferential distribution of the combustion flame and high flame stability characteristics. It also avoids the formation of local hot spots, effectively suppressing the formation of thermal NOx. Thus, the pre-combustion stage flame and the main combustion stage flame have different combustion rates and ignition / quenching characteristics. Typically, the pre-combustion stage flame is used for ignition and stable combustion under low thrust conditions, while the main combustion stage flame is used for stable combustion under high thrust conditions. After the main combustion stage flame is activated, the ratio of hydrogen-based fuel in the pre-combustion stage and the main combustion stage can be adjusted to avoid backfire, flameout, and combustion oscillation, thus achieving stable combustion with low carbon emissions and low pollution. Furthermore, this solution does not involve a completely new combustion organization device design; instead, it improves upon the structure of a traditional kerosene combustion organization device to achieve safe and stable combustion of hydrogen-based fuel, resulting in low pollution and low carbon emissions, and reducing the cost and risk of redesign.

[0057] refer to Figure 3A As shown, in some embodiments, the specific structure of the pre-combustion stage 1 may be that the pre-combustion stage annular wall 11 includes a tapering section 111 and an expansion section 112 connected downstream of the tapering section 111, a throat 110 is formed at the connection between the tapering section 111 and the expansion section 112, the axial position of the pre-combustion stage fuel injection hole 12 is located downstream of the throat 110, and the first swirler 13 is located upstream of the tapering section 111.

[0058] The term "converging segment 111" here refers to a structure whose radial dimension gradually decreases from upstream to downstream. In contrast, "expanding segment 112" refers to a structure whose radial dimension gradually increases from upstream to downstream. The connection between the converging segment 11 and the expanding segment 112 is the point where the radial dimension is smallest, which is the throat 110.

[0059] The beneficial effect of this design is that the converging section reduces the airflow area and increases the air velocity. Air passes through the first swirler, becoming a swirling flow, and reaches its maximum velocity at the throat. Upon entering the expansion section, it accelerates, carrying away and mixing with the fuel ejected from the pre-combustion stage nozzles, thus reducing the risk of backfire. The expansion section gives the mixed airflow a certain expansion angle, allowing for thorough and uniform combustion and reducing pollutant emissions.

[0060] refer to Figure 3A , Figure 3B As shown, in some embodiments, the specific structure of the pre-combustion stage 1 can be such that the axial position of the pre-combustion stage fuel nozzle 12 is located 5mm-20mm downstream of the throat 110. The advantage of this arrangement is that it allows the fuel to be accelerated and carried away by the airflow, preventing backfire, while simultaneously achieving a better premixing effect.

[0061] refer to Figure 2A , Figure 2B As shown, in some embodiments, the expansion section 112 may have an air cooling hole 1120. This design helps prevent the high combustion temperature of hydrogen from eroding the expansion section wall. Preferably, the diameter of the air cooling hole 1120 is less than 0.5 mm, forming a better cooling gas film and preventing excessively large hole diameters from affecting the air swirling flow field and the amount of air participating in combustion, which would be detrimental to stable combustion.

[0062] refer to Figures 2A to 4B As shown, in some embodiments, the specific structure of the pre-combustion stage fuel nozzle 12 may include a straight injection nozzle 121 and an oblique injection nozzle 122; the number of pre-combustion stage fuel nozzles 12 is 6-12, and the diameter is 0.5mm-1mm. Here, "straight injection nozzle 121" means that the axis of the nozzle is parallel to the axis of the pre-combustion stage annular wall 11, such as... Figure 2A , Figure 3A , Figure 3B As shown. The meaning of "oblique injection nozzle 122" refers to the fact that the axis of the nozzle is inclined to the axis of the pre-combustion stage annular wall 11, as... Figure 2B , Figure 4A , Figure 4B As shown. For example, the multiple pre-combustion stage fuel nozzles 12 can be partially straight injection nozzles 121 and partially oblique injection nozzles 122. When the pre-combustion stage fuel flow rate is small, an oblique injection scheme can be adopted, for example, the oblique injection nozzles 122 supply fuel while the straight injection nozzles 121 do not supply fuel. This gives the pre-combustion stage flame a certain initial velocity in the radial direction, thus enabling it to fully ignite the main combustion stage mixture. When the pre-combustion stage fuel flow rate is large, a straight injection scheme can be adopted, for example, the straight injection nozzles 121 supply fuel while the straight injection nozzles 121 do not supply fuel. The pre-combustion stage flame can ignite the main combustion stage flame through its own diffusion effect without penetrating the central recirculation zone formed by the main combustion stage mixture, thus avoiding flame tube wall erosion. The beneficial effect of this configuration is that the number and diameter of the fuel nozzles can achieve a suitable pre-combustion stage fuel injection quantity and a better mixing effect with air.

[0063] Continue to refer to Figures 2A to 4BAs shown, in some embodiments, the specific structure of the main combustion stage fuel injection orifice 22 can be that the main combustion stage fuel injection orifice 22 is evenly distributed circumferentially around the annular wall 21 of the main combustion stage, with 12-20 orifice 22 and a diameter of 0.5mm-2mm. The advantage of this arrangement is that the number and diameter of the fuel injection orifice can achieve a suitable main combustion stage fuel injection quantity and better shear mixing with air, which is beneficial for cooperating with the pre-combustion stage to meet different operating conditions and emission requirements.

[0064] refer to Figure 3A , Figure 4A As shown, in some embodiments, the combustion organization device 100 may have an adjustable swirl number between the second swirler 23 and the first swirler 13. Specifically, the swirl numbers of the second swirler 23 and the first swirler 13 can be matched according to the combustion chamber design. For example, the swirl number of the first swirler 13 may remain constant between 0.5 and 1.2, while the swirl number of the second swirler 23 is adjusted based on combustion chamber tests. For instance, if oscillating combustion occurs in the combustion chamber during testing, the swirl number of the second-stage swirler 23 can be adjusted to 0.5 to 0.8. The beneficial effect of this setting is that it results in a longer main combustion stage flame formed by the combustion of hydrogen-based fuel, which is not significantly different in length from the pre-combustion stage flame, thus facilitating stable combustion. For example, if high NOx emissions occur in the combustion chamber during the test, the swirl number of the second-stage swirler 23 can be adjusted to 0.8 to 1.2. The beneficial effect of this setting is that the main combustion stage flame formed by the combustion of hydrogen-based fuel in the main combustion stage is shorter, which can effectively reduce NOx emissions.

[0065] refer to Figures 1 to 2B As shown, in some embodiments, the pre-combustion stage fuel nozzle 12 is connected to the first hydrogen-based fuel line 31, and the main combustion stage fuel nozzle 22 is connected to the second hydrogen-based fuel line 32. The advantage of this arrangement is that it facilitates control over the fuel supply to the pre-combustion stage fuel nozzle and the main combustion stage fuel nozzle.

[0066] In some embodiments, the hydrogen-based fuel in the first hydrogen-based fuel line 31 and the second hydrogen-based fuel line 32 is gaseous hydrogen.

[0067] refer to Figure 1As shown, in one embodiment, the combustion chamber 1000 may specifically include: the combustion organization device 100 and the combustion container 200 as described above. The combustion organization device 100 is located upstream of and connected to the combustion container 200. A first hydrogen-based fuel can be directly injected into the combustion container 200 from the main combustion stage fuel nozzle 22, and a first air a1 can be directly injected into the combustion container 200 from the second annular chamber 102. The second hydrogen-based fuel can be premixed with the second air a2 to form a mixed fluid that flows out from the first annular chamber 101 into the combustion container 200. The beneficial effect of this configuration is that by adopting a staged flame hydrogen-based fuel combustion organization method, the pre-combustion stage forms a premixed flame, and the main combustion stage forms a non-premixed flame, resulting in different combustion speeds and ignition / quenching characteristics between the pre-combustion stage flame and the main combustion stage flame. By adjusting the ratio of the pre-combustion stage flame to the main combustion stage flame, different operating conditions and emission requirements can be met, achieving low-carbon and low-pollution combustion. Furthermore, existing combustion chamber structures can be used, reducing the cost and risk of redesign.

[0068] Continue to refer to Figure 1 As shown, in some embodiments, the combustion container 200 may be an annular container with multiple combustion organization devices 100 distributed circumferentially and connected to it. A portion of the pre-combustion stage fuel nozzles 12 of the combustion organization devices 100 are straight-line injection nozzles 121, while the other portion are oblique-line injection nozzles 122. The advantage of this configuration is that it allows for selection based on different needs. When the pre-combustion stage fuel flow rate is low, an oblique injection scheme can be used, giving the pre-combustion stage flame a certain initial radial velocity, thus fully igniting the main combustion stage mixture. When the pre-combustion stage fuel flow rate is high, a straight-line injection scheme can be used, allowing the pre-combustion stage flame to ignite the main combustion stage flame through its own diffusion effect without penetrating the central recirculation zone formed by the main combustion stage mixture, thus avoiding flame tube wall erosion.

[0069] Continue to refer to Figure 1 As shown, in some embodiments, the combustion container 200 may have a wall 201 with a cooling channel 202, through which the third air a3 enters the combustion chamber 200. This arrangement has the advantage of preventing the high combustion temperature of hydrogen-based fuels from ablating the walls of the combustion container. Specifically, as... Figure 1 , Figure 3AAs shown, the combustion chamber 100 also includes a diffuser 103, an outer casing 101a, and an inner casing 102a. High-pressure air a from the compressor enters the combustion chamber 1000 through the diffuser 103. The air a is divided into a first air a1, a second air a2, and a third air a3. The third air a3 flows into the annular cavity formed by the outer casing 101a, the inner casing 102a, and the wall 201 of the combustion vessel. It enters the interior of the combustion vessel 200 through the cooling channel 202 to cool the wall 201 of the combustion vessel 200 and prevent erosion. The second air a2 is mixed with fuel injected through the first annular chamber 101 of the pre-combustion stage 1 of the combustion organization device 100 and delivered to the pre-combustion stage fuel nozzle 12 via the first hydrogen-based fuel pipeline 31. The mixed airflow enters the combustion chamber 200 for combustion, forming a pre-combustion stage flame. The first air a1 enters the combustion chamber 200 directly from the second annular chamber 102 of the main combustion stage 2 of the combustion organization device 100, and mixes with fuel injected directly into the combustion chamber 200 through the second hydrogen-based fuel pipeline 32 via the main combustion stage fuel nozzle 22, forming a main combustion stage flame. By flexibly adjusting the ratio of the pre-combustion stage flame and the main combustion stage flame, different engine operating conditions and emission requirements can be met. The resulting high-temperature, high-pressure combustion gas b flows out of the combustion chamber 1000 and enters the turbine.

[0070] refer to Figures 1 to 4B As shown, in one embodiment, the specific structure of the gas turbine engine may include the combustion chamber 1000 as described above. The advantage of this configuration is that it enables organized combustion of hydrogen-based fuels, ensuring low pollution and low carbon emissions from the engine, and reducing the cost and risk of designing a completely new combustion chamber.

[0071] Continue to refer to Figures 1 to 4B As shown, in one embodiment, the specific steps of the combustion organization method for hydrogen-based fuel and air may include:

[0072] In the main combustion stage 2, the first hydrogen-based fuel and the first air a1 are directly injected into the combustion vessel 200 from the main combustion stage fuel injection port 22 and the second annular chamber 102, respectively. Continuing from the above, as... Figure 3A As shown, the main combustion stage annular wall 21 and the pre-combustion stage annular wall 11 form the second annular chamber 102. The second swirler 23 is located inside the second annular chamber 102. The axial position of the main combustion stage fuel nozzle 22 is the same as the axial position of the outlet 1021 of the second annular chamber 102. The first air a1 enters the combustion vessel 200 directly through the second swirler 23 and mixes and burns with the first hydrogen-based fuel that is transported to the main combustion stage fuel nozzle 22 through the second hydrogen-based fuel pipeline 32 and directly injected into the combustion vessel 200, forming a non-premixed flame in the main combustion stage.

[0073] In pre-combustion stage 1, the second hydrogen-based fuel and the second air a2 are premixed to form a mixed fluid, which is then output to the combustion vessel 200. As described above, as... Figure 3A As shown, the pre-combustion stage annular wall 11 provides a first annular chamber 101. The pre-combustion stage fuel nozzle 12 and the first swirler 13 are located inside the first annular chamber 101. The axial position of the pre-combustion stage fuel nozzle 12 is located upstream of the outlet 1011 of the first annular chamber 101. The second air a2 passes through the first swirler 13 and mixes with the fuel injected through the first hydrogen-based fuel pipeline 31 to the pre-combustion stage fuel nozzle 12. The mixed airflow enters the combustion container 200 for combustion, forming a pre-combustion stage premixed flame.

[0074] The beneficial effect of this setup is that the pre-combustion stage flame and the main combustion stage flame have different combustion speeds and ignition / quenching characteristics. The pre-combustion stage flame is used for ignition and stable combustion under low thrust conditions, while the main combustion stage flame is used for stable combustion under high thrust conditions. After the main combustion stage flame is activated, the ratio of hydrogen-based fuel in the pre-combustion stage and the main combustion stage can be adjusted to avoid backfire, flameout, and combustion oscillations, thus achieving low-carbon, low-pollution, and stable combustion.

[0075] While the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the invention. Any variations and modifications can be made by those skilled in the art without departing from the spirit and scope of the invention. Therefore, any modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention, without departing from the scope of the invention, fall within the protection scope defined by the claims of the present invention.

Claims

1. A combustion organization device (100) for hydrogen-based fuels, characterized by, Comprising: a pre-combustion stage (1) comprising a pre-combustion stage annular wall (11), a pre-combustion stage fuel injection hole (12) and a first swirler (13); the pre-combustion stage annular wall (11) provides a first annular chamber (101), the pre-combustion stage fuel injection hole (12) and the first swirler (13) are located inside the first annular chamber (101), the first swirler (13) surrounds at least part of the pre-combustion stage fuel injection hole (12), the axial position of the pre-combustion stage fuel injection hole (12) is upstream of the outlet (1011) of the first annular chamber; a main combustion stage (2) surrounding the pre-combustion stage (1), the main combustion stage (2) comprises a main combustion stage annular wall (21), a main combustion stage fuel injection hole (22) and a second swirler (23), the main combustion stage annular wall (21) and the pre-combustion stage annular wall (11) constitute a second annular chamber (102), the second swirler (23) is located inside the second annular chamber (102), the main combustion stage fuel injection hole (22) surrounds at least part of the main combustion stage annular wall (21), and the main combustion stage fuel injection hole (22) is direct injection, and the axial position of the main combustion stage fuel injection hole (22) is the same as the axial position of the outlet (1021) of the second annular chamber; the pre-combustion stage annular wall (11) comprises a converging section (111) and a diverging section (112) connected downstream of the converging section (111), a throat (110) is formed at the connection of the converging section (111) and the diverging section (112), the axial position of the pre-combustion stage fuel injection hole (12) is downstream of the throat (110), and the first swirler (13) is located upstream of the converging section (111); the axial position of the pre-combustion stage fuel injection hole (12) is 5-20mm downstream of the throat (110); the main combustion stage fuel injection hole (22) is uniformly distributed in the circumferential direction around the main combustion stage annular wall (21), the number of the main combustion stage fuel injection hole (22) is 12-20, and the hole diameter is 0.5-2mm.

2. The combustion organization device (100) according to claim 1, characterized in that the diverging section (112) has air cooling holes (1120).

3. The combustion organization device (100) according to claim 1, characterized in that the pre-combustion stage fuel injection hole (12) comprises straight-line injection holes (121) and oblique-line injection holes (122), the number of the pre-combustion stage fuel injection hole (12) is 6-12, and the hole diameter is 0.5-1mm.

4. The combustion organization device (100) according to claim 1, characterized in that the swirl number of the second swirler (23) is adjustable.

5. The combustion organization device (100) according to claim 1, characterized in that the pre-combustion stage fuel injection hole (12) is connected to a first hydrogen-based fuel pipeline (31), and the main combustion stage fuel injection hole (22) is connected to a second hydrogen-based fuel pipeline (32).

6. A combustion chamber (1000) characterized by, Comprising: the combustion organization device (100) according to any one of claims 1-5; a combustion vessel (200); The combustion organization device (100) is connected to the upstream end of the combustion container (200), first hydrogen-based fuel can be directly injected into the combustion container (200) from the main combustion stage fuel injection hole (22), first air can be directly injected into the combustion container (200) from the second annular chamber (102), and second hydrogen-based fuel can be mixed with second air to form a mixed fluid and then output from the first annular chamber (101) into the combustion container (200).

7. The combustion chamber (1000) as claimed in claim 6, characterized in that, The combustion container (200) is a ring-shaped container, and a plurality of combustion organization devices (100) are circumferentially distributed and connected to the ring-shaped combustion container (200); the pre-combustion stage fuel injection hole (12) of a part of the combustion organization devices (100) is a straight-line injection hole (121), and the pre-combustion stage fuel injection hole (12) of another part of the combustion organization devices (100) is an inclined-line injection hole (122).

8. The combustion chamber (1000) as claimed in claim 6, characterized in that, The wall surface of the combustion container (200) has a cooling channel, and third air enters the combustion container (200) through the wall surface.

9. A gas turbine engine characterized by, The combustion chamber (1000) according to any one of claims 6-8 is included.

10. A method of combustion organization of a hydrogen-based fuel and air, characterized by, The combustion organization method uses the combustion organization device (100) according to any one of claims 1-5. In the main combustion stage, first hydrogen-based fuel and first air are directly injected into the combustion container from the main combustion stage fuel injection hole and the second annular chamber, respectively; In the pre-combustion stage, second hydrogen-based fuel is mixed with second air to form a mixed fluid, and then output to the combustion container.

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