Combustion chamber and nozzle thereof

Abstract

The invention discloses a combustion chamber and a nozzle thereof, and relates to the technical field of nozzles. The nozzle includes: a tube body; an air flow channel is formed in the pipe body; a plurality of slope blocks; the slope blocks are arranged on the inner wall of the pipe body and distributed in the circumferential direction of the pipe body. Each slope block is provided with a slope surface, and the distance between each slope surface and the inner wall of the pipe body is gradually increased in the first direction; the fuel flow channel is arranged on the slope block; the input ends of the fuel flow channels extend and penetrate through the pipe body, and the output ends of the fuel flow channels extend and penetrate through the corresponding slope blocks. According to the nozzle, air and fuel can be effectively micro-mixed in the nozzle only through the design of the slope blocks, the overall structure is simple, the power of mixed gas formed by the air and the fuel cannot be greatly reduced, and the manufacturing cost of the nozzle can be reduced.

Description

Technical Field

[0001] This application relates to the technical field of nozzles, and specifically to a combustion chamber and its nozzle. Background Art

[0002] Gas turbines are one of the important equipment in the field of energy and power. Traditional gas turbines mainly use natural gas as fuel. However, under the increasing environmental protection requirements, in the future low-carbon clean energy ecosystem, flexible combustion of fuel bodies mainly composed of hydrogen and mixed with other fuels (such as carbon monoxide or methane, etc.) is the main way for gas turbines to achieve low-carbon or even zero-carbon power generation. However, the combustion characteristics of hydrogen fuel are significantly different from those of traditional hydrocarbon fuels. Hydrogen has a wider combustion limit, a faster flame propagation speed, and a higher adiabatic flame temperature. To solve the above technical problems, those skilled in the art have designed nozzles based on micro-mixing combustion technology. Micro-mixing combustion technology is to achieve ultra-low emissions by reducing the mixing scale of fuel (such as pure hydrogen fuel or hydrogen-rich fuel) and air without basically reducing the gas flow rate. Since the power loss of the mixture formed by mixing fuel and oxidant is small, the mixture can maintain a high flow rate. The mixture with a high flow rate has strong anti-backfire ability and flexible fuel adaptability. For existing nozzles based on micro-mixing combustion technology, in order to ensure the uniform mixing of hydrogen and air, their internal flow channel designs are relatively complex. For example, in the patent documents with publication number: CN116642204A, titled: A micro-mixing nozzle with a swirl mixer and a combustion chamber; and, publication number: CN116697405A, titled: A pre-mixed swirl micro-mixing nozzle and a combustion chamber, similar nozzles are disclosed. Although the nozzle with a relatively complex flow channel design can improve the uniform mixing of hydrogen and air, the power loss of the mixture formed by it is large, resulting in a decrease in the anti-backfire and flexible fuel adaptability of the nozzle, and the more complex the nozzle design, the higher the manufacturing cost. Summary of the Invention

[0003] The purpose of this application is to provide a combustion chamber and its nozzle to solve the technical problem that the structure of existing nozzles based on micro-mixing combustion technology is relatively complex.

[0004] To achieve the above purpose, this application provides the following technical solutions: In the first aspect, this application proposes a technical solution for a nozzle, and the nozzle includes: A pipe body; an air flow channel is formed inside the pipe body; Multiple ramp blocks; each ramp block is disposed on the inner wall of the pipe body, and the ramp blocks are circumferentially distributed around the pipe body; each ramp block has a ramp surface, and the distance between the ramp surface and the inner wall of the pipe body increases in a first direction; the first direction is parallel to the axis of the pipe body and points from the input end to the output end of the air flow passage; A fuel flow passage provided in the ramp block; the input end of the fuel flow passage extends through the pipe body, and the output end of the fuel flow passage extends through the corresponding ramp block.

[0005] As a specific solution in the technical solution of the present application, the pipe body includes a contraction pipe section and a premixing pipe section connected in sequence in the first direction; the inner diameter of the contraction pipe section decreases in the first direction.

[0006] As a specific solution in the technical solution of the present application, the ramp surface is a plane or a curved surface.

[0007] As a specific solution in the technical solution of the present application, the fuel flow passages are arrayed around the axis of the pipe body; the fuel jets ejected from the fuel flow passages can form a swirl between the ramp blocks.

[0008] As a specific solution in the technical solution of the present application, the opening of the output end of the fuel flow passage is located on the side surface of the ramp block; the angle between the direction of the fuel jet and the side surface is greater than or equal to 45° and less than or equal to 75°.

[0009] As a specific solution in the technical solution of the present application, the spatial angle between the direction of the fuel jet and the first direction is greater than or equal to 30° and less than or equal to 60°.

[0010] In a second aspect, the present application proposes a technical solution for a combustion chamber. The combustion chamber includes the nozzle as described in any one of the first aspects.

[0011] As a specific solution in the technical solution of the present application, it includes: A flame tube; A nozzle disc disposed in the flame tube; the nozzle disc has a fuel chamber; Multiple nozzles; each nozzle is disposed on the nozzle disc, and each nozzle axially penetrates the nozzle disc along the axis of the flame tube; the input end of the fuel flow passage in each nozzle is communicated with the fuel chamber; 1]A fuel delivery pipe disposed on the nozzle disc, and the fuel delivery pipe is communicated with the fuel chamber; An igniter; the igniter penetrates the nozzle disc.

[0012] As a specific solution in the technical solution of the present application, a partition is further provided inside the nozzle disc; the partition divides the fuel chamber into a main combustion stage fuel chamber and a secondary combustion stage fuel chamber; the fuel delivery pipe includes a main combustion stage fuel pipe and a secondary combustion stage fuel pipe; the main combustion stage fuel pipe is communicated with the main combustion stage fuel chamber, and the secondary combustion stage fuel pipe is communicated with the secondary combustion stage fuel chamber.

[0013] As a specific solution in the technical solution of the present application, the fuel delivery pipe further includes a duty fuel pipe; the duty fuel pipe penetrates the nozzle disc, and the duty fuel pipe is close to the igniter.

[0014] As a specific solution in the technical solution of the present application, the nozzle disc is further provided with a plurality of cooling structures, and each cooling structure is used to cool the nozzle disc.

[0015] As a specific solution in the technical solution of the present application, the cooling structure includes an air inlet hole, a cooling cavity and an air outlet hole which are sequentially arranged on the nozzle disc along a first direction; both the air inlet hole and the air outlet hole are communicated with the cooling cavity; the axis lines of the air inlet hole and the air outlet hole are both parallel to the first direction, and the projections of the air inlet hole and the air outlet hole along the first direction do not overlap.

[0016] As a specific solution in the technical solution of the present application, there are a plurality of air outlet holes, and each air outlet hole is distributed around the axis line of the air inlet hole; the sum of the cross-sectional areas of each air outlet hole is greater than the cross-sectional area of the air inlet hole, and the cross-section is perpendicular to the first direction.

[0017] Compared with the prior art, the beneficial effects of the present application are: Through the design of only a plurality of ramp blocks in the present application, air and fuel can be effectively micro-mixed inside the nozzle. Its overall structure is simple, and it will not significantly reduce the power of the mixture formed by air and fuel, and can reduce the manufacturing cost of the nozzle. Description of the Drawings

[0018] Figure 1 Is a three-dimensional schematic diagram of a nozzle proposed by an embodiment of the present application; Figure 2 Is Figure 1 The longitudinal sectional view of the nozzle in Figure 3 Is a cross-sectional schematic diagram of a nozzle proposed by an embodiment of the present application; Figure 4 Is a sectional view schematic diagram of a combustion chamber proposed by an embodiment of the present application; Figure 5 Is a three-dimensional schematic diagram of a combustion chamber proposed by an embodiment of the present application; Figure 6For Figure 5 Schematic three-dimensional view of the middle combustion chamber in another direction; Figure 7 Schematic three-dimensional view of a nozzle disc proposed in an embodiment of the present application; Figure 8 For Figure 7 Schematic three-dimensional view of the nozzle disc in another direction; Figure 9 Schematic structural view of a fuel chamber proposed in an embodiment of the present application; Figure 10 Schematic structural view of a cooling structure proposed in an embodiment of the present application.

[0019] In the figure: 1. Nozzle disc; 11. Fuel chamber; 111. Partition; 112. Main combustion stage fuel chamber; 113. Sub-combustion stage fuel chamber; 2. Flame tube; 3. Nozzle; 31. Tube body; 311. Converging tube section; 312. Premixing tube section; 32. Ramp block; 321. Ramp surface; 33. Fuel flow channel; 34. Air flow channel; 4. Fuel delivery pipe; 41. Main combustion stage fuel pipe; 42. Sub-combustion stage fuel pipe; 43. Duty fuel pipe; 5. Igniter; 61. Air inlet hole; 62. Air outlet hole; 63. Cooling chamber. Detailed implementation manners

[0020] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present application without creative efforts shall fall within the protection scope of the present application.

[0021] It should be noted that in the description of the present application, the orientation or positional relationship indicated by the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the accompanying drawings. It is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be construed as a limitation to the present application.

[0022] In addition, it should be understood that, for the convenience of description, the sizes of the various components shown in the accompanying drawings are not drawn in actual proportional relationships. For example, the thickness or width of some layers may be exaggerated relative to other layers.

[0023] It should be noted that similar reference numerals and letters denote similar items in the following accompanying drawings. Therefore, once an item is defined or described in one accompanying drawing, it will not be necessary to further specifically discuss and describe it in the description of subsequent accompanying drawings.

[0024] Before understanding the embodiments of the present application, it should be understood that the components or structures used to guide fluids in a nozzle or combustion chamber (e.g., the fuel flow channel 33, the air flow channel 34, the main combustion stage fuel pipe 41, and the duty class fuel pipe 43, etc.) all have an input end and an output end, wherein the input end refers to the end where the fluid (e.g., fuel, air, or a mixture, etc.) flows into the component or structure, and the output end refers to the end where the fluid flows out of the component or structure. In other words, in the nozzle or combustion chamber proposed in the embodiments of the present application, the flow direction of the fluid during use is always from the input end of a component or structure to the output end.

[0025] In order to solve the technical problem of the relatively complex structure of the existing nozzle based on the micro-mixing combustion technology mentioned in the background art, this application proposes an embodiment of a nozzle. The nozzle 3 includes a tube body 31, a plurality of slope blocks 32, and a fuel flow channel 33 provided on the slope blocks 32. Figure 1 As shown, each ramp block 32 is provided on the inner wall of the pipe body 31, and each ramp block 32 is distributed around the circumference of the pipe body 31. Figure 2 As shown, each slope block 32 has a slope surface 321, and the slope surface 321 is along the first direction (ie, as shown in FIG. Figure 2 The distance from the inner wall of the tube body 31 increases in the direction A) shown. The first direction is parallel to the axis of the tube body 31 and points from the input end of the air flow channel 34 to the output end. The air flow channel 34 is formed inside the tube body 31. The input end of the fuel flow channel 33 extends through the tube body 31, and the output end of the fuel flow channel 33 extends through the corresponding ramp block 32.

[0026] When in use, the air outside the tube body 31 enters the interior of the air flow channel 34 from the input end of the air flow channel 34; after the air encounters the slope block 32, the slope surface 321 and the slope block 32 will disturb the flow direction of the air, so that the air flowing through the slope block 32 forms a slope behind the slope block 32. Figure 2 The recirculation zone B shown. Furthermore, fuel located outside the tube body 31 (hereinafter referred to as the fuel cavity 11) enters the fuel flow channel 33 from its input end. Because the output end of the fuel flow channel 33 extends through the corresponding ramp block 32, the fuel flowing out of the output end of the fuel flow channel 33 will inevitably flow through the recirculation zone B. If the fuel flows near the recirculation zone B, it will be drawn into the recirculation zone B. Furthermore, the air and fuel in the recirculation zone B can be strongly mixed. It should be understood that the more uniform the mixing of air and fuel, the fewer pollutants (e.g., nitrogen oxides) produced by subsequent combustion.

[0027] In this embodiment, if Figure 2As shown, after the air flows through the ramp block 32, shedding vortices are generated at the edge of the ramp block 32, and then a recirculation zone is formed at the bottom of the ramp block 32. When hydrogen is directly ejected along the axial direction of the pipe body 31 from the bottom of the ramp block 32, it just enters the recirculation zone at the bottom of the ramp block 32. The recirculation zone entrains the fuel located at the center of the vortex, causing the fuel and air to be strongly mixed, thereby improving the mixing uniformity of the fuel and air, improving the uneven distribution of the combustion temperature, and enhancing the emission reduction effect.

[0028] For the nozzle proposed in this embodiment, only through the design of multiple ramp blocks, the air and fuel can be effectively micro-mixed inside the nozzle. Its overall structure is simple, and it will not significantly reduce the power of the mixture formed by the air and fuel, and can reduce the manufacturing cost of the nozzle.

[0029] In the embodiment of the present application, there are no excessive restrictions on the shape and structure of the ramp block 32, as long as the ramp block 32 can cause a recirculation zone B to be formed behind the ramp block 32 for the air flowing in the first direction. For example, the ramp block 32 can be a triangular block, or can be a Figure 1 trapezoidal block as shown.

[0030] In the embodiment of the present application, there are no excessive restrictions on the ramp surface 321, as long as the distance between the ramp surface 321 and the inner wall of the pipe body 31 increases along the first direction. For example, the ramp surface 321 can be a plane or a curved surface.

[0031] In the embodiment of the present application, there is no restriction on the number of ramp blocks 32, as long as the recirculation zones formed by each ramp block 32 meet the mixing requirements of the air and fuel. It is easy to understand that if the number of ramp blocks 32 is larger, the number of formed recirculation zones is larger. If the number of formed recirculation zones is larger, although the mixing of the air and fuel is more uniform, the power loss of the formed mixture is also larger. Based on this, in order to avoid a large power loss of the formed mixture due to a large number of ramp blocks 32, and also to avoid uneven mixing of the air and fuel due to a small number of ramp blocks 32, in a specific embodiment of the present application, the number of ramp blocks 32 can be Figure 1 4 as shown, or can be 3 as shown in Figure 3 .

[0032] As can be seen from the background art, if the speed of the mixture gas ejected from the nozzle (that is, the gas formed after the air and fuel are mixed) is higher, the probability of the nozzle generating flashback is smaller, and the adaptability of the nozzle to various flexible fuels is also stronger. In order to increase the speed of the mixture gas ejected from the nozzle, in an embodiment of the present application, as shown in Figure 2 , the pipe body 31 includes along the first direction (that is, as shown in Figure 2The direction shown in A) A contraction pipe section 311 and a premixing pipe section 312 connected in sequence. The inner diameter of the contraction pipe section 311 decreases along the first direction. Since the inner diameter of the contraction pipe section 311 decreases along the first direction, the air velocity flowing through the contraction pipe section 311 will increase. If the air velocity in the air flow channel 34 increases, the velocity of the mixture gas formed in the air flow channel 34 will also definitely increase.

[0033] In order to avoid forming a step between the contraction pipe section 311 and the premixing pipe section 312, and further reduce the air flow velocity in the air flow channel 34, in an embodiment of the present application, as Figure 2 shown, the inner diameter of each part in the premixing pipe section 312 is equal, and the minimum inner diameter of the contraction pipe section 311 is equal to the inner diameter of the premixing pipe section 312. Since the minimum inner diameter of the contraction pipe section 311 is equal to the inner diameter of the premixing pipe section 312, the connection between the contraction pipe section 311 and the premixing pipe section 312 has a smooth transition without a step, that is, the air flow velocity in the air flow channel 34 will not be reduced due to the step.

[0034] In order to further improve the mixing uniformity of air and fuel in the air flow channel 34, in an embodiment of the present application, the mixture gas in the air flow channel 34 can also be made to form a swirl. If the mixture gas in the air flow channel 34 forms a swirl, the mixing uniformity of air and fuel can be further improved, that is, the emission of pollutants can be further reduced.

[0035] In the embodiment of the present application, any reasonable method can be adopted to make the mixture gas in the air flow channel 34 form a swirl. For example, a swirler is arranged in the air flow channel 34. If a swirler is arranged in the air flow channel 34, the complexity of the nozzle will increase, and the swirler will greatly reduce the flow velocity of the formed mixture gas. In order not to increase the complexity of the nozzle and not greatly reduce the flow velocity of the mixture gas, in an embodiment of the present application, each fuel flow channel 33 can be arrayed around the axis line of the pipe body 31, and the fuel jets ejected from each fuel flow channel 33 can form a swirl between each ramp block 32 (that is, such as Figure 3 the swirl D shown).

[0036] In this embodiment, the meaning of "array" is the same as that in the field of three-dimensional design. That is, an array refers to linearly replicating and arranging or circumferentially replicating and arranging an object (for example, the fuel flow channel 33 in the above text) in three-dimensional space according to certain rules and regulations.

[0037] In this embodiment, it is possible to make the mixture gas in the air flow channel 34 form a swirl without setting a swirler. That is to say, this embodiment will neither increase the complexity of the nozzle nor greatly reduce the flow velocity of the mixture gas.

[0038] In this embodiment, the shape of the fuel flow channel 33 is not limited as long as the fuel jets ejected from each array can form a swirl. It should be clear that for the fluid (i.e., fuel), the jet direction formed by it must be parallel to the axis line of the flow channel output end. For example, as Figure 2 shown, if the axis line of the fuel flow channel 33 output end is parallel to the first direction (i.e., the direction A as shown in Figure 2 ), then the direction of the fuel jet ejected from the fuel flow channel 33 is also parallel to the first direction. It should be noted that since each fuel flow channel 33 is arrayed around the axis line of the pipe body 31, as long as the axis line direction of the fuel flow channel 33 output end is different from the axis line of the pipe body 31, each fuel jet will surely form a swirl. That is to say, in this embodiment, the fuel jets ejected from each fuel flow channel 33 can form a swirl between each ramp block 32 means that the axis line of the fuel flow channel 33 output end and the axis line of the pipe body 31 are skew lines.

[0039] In this embodiment, the size of the swirl formed by each fuel jet is closely related to the jet direction formed by each fuel jet. If the formed swirl is small, it is difficult to make the air and fuel mix evenly, that is, there are more pollutants generated during subsequent combustion; if the formed swirl is large, the power loss of forming the mixture is large, that is, flashback is likely to occur during subsequent combustion. In order to avoid the swirl formed by each fuel jet being too large or too small, in an embodiment of the present application, as Figure 3 shown, the opening at the output end of the fuel flow channel 33 is located on the side surface of the ramp block 32, and the angle between the direction of the fuel jet (i.e., the direction C as shown in Figure 3 ) and the side surface of the ramp block 32 (i.e., the angle θ as shown in Figure 3 ) is greater than or equal to 45° and less than or equal to 75°. Specifically, in this embodiment, the angle θ can be any degree among 45°, 50°, 55°, 60°, 65°, 70° and 75°, or any degree between two adjacent degrees above.

[0040] In this embodiment, as Figure 3 shown, hydrogen is ejected from the fuel flow channel 33 on the side surface of the ramp block 32, the ejection angle θ is greater than or equal to 45° and less than or equal to 75°, forming a certain angle with the air flow direction. The fuel forms a small swirl at the center of the pipe body 31 and mixes with the central air, and then enters the recirculation zone at the bottom of the ramp block 32, which can effectively improve the mixing uniformity of the fuel and air.

[0041] In this embodiment, if the swirl and the mainstream in the air flow channel 34 form a head-on collision, the flow velocity of the mixed gas formed in the air flow channel 34 will be reduced. To avoid the swirl from forming a head-on collision with the mainstream in the air flow channel 34, in an embodiment of the present application, the spatial angle between the direction of the fuel jet and the first direction can be greater than or equal to 30° and less than or equal to 60°. Specifically, the above-mentioned spatial angle can be any one of the degrees of 30°, 35°, 40°, 45°, 50°, 55° and 60°, or any degree between the above adjacent two degrees.

[0042] In the embodiments of the present application, there are no excessive restrictions on the sizes of the various components in the nozzle 3, as long as the sizes of the various components can satisfy the uniform mixing of air and fuel. For example, in a specific embodiment of the present application, the diameter of the air flow channel 34 (i.e., the diameter d as shown in Figure 2 can be greater than or equal to 5 mm and less than or equal to 7 mm; the height of the ramp block 32 (i.e., the height H as shown in Figure 2 can be greater than or equal to 1.5 mm and less than or equal to 2.0 mm; the distance between the end of the ramp block 32 and the output end of the air flow channel 34 (i.e., the distance S as shown in Figure 2 can be greater than or equal to 1 mm and less than or equal to 3 mm; the length of the contraction pipe section 311 in the first direction can be greater than or equal to 2 mm and less than or equal to 4 mm; the diameter of the fuel flow channel 33 can be greater than or equal to 0.4 mm and less than or equal to 0.8 mm, etc. Of course, in other embodiments of the present application, the above sizes can be designed according to requirements.

[0043] For the nozzle proposed in the embodiments of the present application, just through the design of multiple ramp blocks, the air and fuel can form effective micro-mixing inside the nozzle. Its overall structure is simple, not only will it not significantly reduce the power of the mixed gas formed by the air and fuel, but also it can reduce the manufacturing cost of the nozzle.

[0044] After introducing the nozzle proposed in the embodiments of the present application, the following introduces an embodiment of a combustion chamber proposed by the present application. This combustion chamber includes the nozzle 3 proposed in any one of the above embodiments.

[0045] For the combustion chamber proposed in the embodiments of the present application, the nozzle it has can make the air and fuel form effective micro-mixing inside the nozzle just through the design of multiple ramp blocks. Its overall structure is simple, not only will it not significantly reduce the power of the mixed gas formed by the air and fuel, but also it can reduce the manufacturing cost of the nozzle.

[0046] In a specific embodiment of the present application, the combustion chamber may include a nozzle disc 1, a flame tube 2, a fuel delivery pipe 4, an igniter 5 and multiple nozzles 3. As shown in Figure 4As shown in the figure, the nozzle disc 1 is arranged inside the combustion chamber 2, and the nozzle disc 1 has a fuel chamber 11. The fuel delivery pipe 4 is arranged on the nozzle disc 1, and the fuel delivery pipe 4 communicates with the fuel chamber 11. The igniter 5 is arranged on the nozzle disc 1, and the igniter 5 penetrates through the nozzle disc 1. Each nozzle 3 is arranged on the nozzle disc 1, and each nozzle 3 penetrates through the nozzle disc 1 along the axial direction of the combustion chamber 2. The input end of the fuel flow passage 33 in each nozzle 3 communicates with the fuel chamber 11.

[0047] During use, fuel (which can be pure hydrogen or hydrogen-rich fuel) is injected into the fuel chamber 11 through the fuel delivery pipe 4. Since the input end of the fuel flow passage 33 in each nozzle 3 communicates with the fuel chamber 11, the fuel located in the fuel chamber 11 can enter the air flow passages 34 of each nozzle 3 through the fuel flow passage 33. Since each nozzle 3 penetrates through the nozzle disc 1 along the axial direction of the combustion chamber 2, the air located outside the combustion chamber 2 can enter the air flow passage 34 from the input end of the air flow passage 34 in the nozzle 3. Further, the air and fuel entering the air flow passage 34 can be mixed as described above, and then a mixture is formed. Further, the formed mixture can enter the combustion chamber 2 from the output end of the air flow passage 34 in each nozzle 3, and then participate in subsequent combustion.

[0048] It should be noted that the operating condition of the gas turbine is positively correlated with the amount of fuel injected into the combustion chamber. That is to say, if the amount of fuel injected into the combustion chamber is more, the operating condition of the gas turbine is higher; if the amount of fuel injected into the combustion chamber is less, the operating condition of the gas turbine is lower. It should be clear that since the amount of fuel required when the gas turbine is in a low operating condition is less, that is, the amount of fuel entering each nozzle 3 is less, and during the use of the gas turbine, the amount of air entering each nozzle 3 is basically unchanged. Therefore, when the gas turbine is in a low operating condition, the fuel equivalence ratio of the mixture formed by each nozzle 3 is lower. If the fuel equivalence ratio of the mixture is too low, the combustion chamber is extremely likely to flame out or the combustion is unstable.

[0049] In order to avoid the phenomenon of flameout or unstable combustion in the combustion chamber when the gas turbine is in a low operating condition, in an embodiment of the present application, a partition 111 is further arranged inside the nozzle disc 1. The partition 111 divides the fuel chamber 11 into a main combustion stage fuel chamber 112 and a secondary combustion stage fuel chamber 113. As Figure 5 and Figure 6 shown, the fuel delivery pipe 4 includes a main combustion stage fuel pipe 41 and a secondary combustion stage fuel pipe 42. The main combustion stage fuel pipe 41 communicates with the main combustion stage fuel chamber 112, and the secondary combustion stage fuel pipe 42 communicates with the secondary combustion stage fuel chamber 113.

[0050] During use, fuel can be respectively delivered to the primary combustion stage fuel chamber 112 and the secondary combustion stage fuel chamber 113 through the primary combustion stage fuel pipe 41 and the secondary combustion stage fuel pipe 42. If the gas turbine is in a low operating condition, most of the fuel can be delivered to the secondary combustion stage fuel chamber 113 through the secondary combustion stage fuel pipe 42, so that the fuel-air mixture generated by the nozzle 3 in the secondary combustion stage fuel chamber 113 has a relatively high fuel equivalence ratio, thereby avoiding the phenomenon that the flame in the combustion chamber is extinguished or the combustion is unstable due to the too low fuel equivalence ratio in the fuel-air mixture. If the gas turbine is in a high operating condition, fuel can be evenly delivered to the primary combustion stage fuel chamber 112 and the secondary combustion stage fuel chamber 113 through the primary combustion stage fuel pipe 41 and the secondary combustion stage fuel pipe 42, thereby avoiding the phenomenon that the content of pollutants (i.e., nitrogen oxides) increases due to different fuel equivalence ratios (i.e., uneven mixing of the fuel-air mixture) in the fuel-air mixtures formed in each nozzle 3.

[0051] In the embodiment of the present application, evenly delivering fuel to the primary combustion stage fuel chamber 112 and the secondary combustion stage fuel chamber 113 means delivering fuel to the primary combustion stage fuel chamber 112 and the secondary combustion stage fuel chamber 113 in proportion according to the number ratio of the nozzles 3 communicating with the primary combustion stage fuel chamber 112 and the secondary combustion stage fuel chamber 113. For example, if there are x nozzles 3 communicating with the primary combustion stage fuel chamber 112 and y nozzles 3 communicating with the secondary combustion stage fuel chamber 113; where x is greater than or equal to y, and both x and y are positive integers greater than or equal to 1; then when the gas turbine is in a high operating condition, x÷(x + y)×100% of the fuel can be delivered to the primary combustion stage fuel chamber 112 through the primary combustion stage fuel pipe 41; and y÷(x + y)×100% of the fuel can be delivered to the secondary combustion stage fuel chamber 113 through the secondary combustion stage fuel pipe 42. Of course, in other embodiments of the present application, other reasonable methods can also be used to distribute fuel to the primary combustion stage fuel chamber 112 and the secondary combustion stage fuel chamber 113.

[0052] In the embodiment of the present application, there is no limitation on the splitting method of the primary combustion stage fuel chamber 112 and the secondary combustion stage fuel chamber 113. For example: the fuel chamber 11 can be evenly divided into the primary combustion stage fuel chamber 112 and the secondary combustion stage fuel chamber 113; or as Figure 9 shown, the fuel chamber 11 can be divided into an unevenly divided primary combustion stage fuel chamber 112 and secondary combustion stage fuel chamber 113. It should be noted that no matter how the fuel quantity is adjusted for the primary combustion stage fuel chamber 112 and the secondary combustion stage fuel chamber 113 divided as shown in Figure 9 shown, the temperature field in the combustion chamber can be made to tend to be uniform.

[0053] It should be noted that most gas turbines use lean premixed combustion technology. Lean premixed combustion involves premixing fuel and air to form a mixture where the stoichiometric ratio of the fuel in the resulting mixture is lower than the stoichiometric ratio required for combustion. The advantage of lean premixed combustion is that the air content in the mixture is relatively high, allowing the fuel to burn fully while also keeping the combustion temperature low. If the fuel burns fully and the combustion temperature is low, the pollutants produced by combustion (such as nitrogen oxides) can be minimized. It should be noted that if a gas turbine uses lean premixed combustion technology, the low stoichiometric ratio of the fuel in the mixture makes it difficult to ignite, which in turn makes it difficult to start the gas turbine.

[0054] In order to make the combustion chamber proposed in the embodiment of the present application applicable to the gas turbine based on the lean premixed combustion technology, in one embodiment of the present application, as shown in FIG. Figure 5 and Figure 6 As shown, the fuel delivery pipe 4 further includes a duty class fuel pipe 43. The duty class fuel pipe 43 passes through the nozzle plate 1, and the duty class fuel pipe 43 is close to the igniter 5.

[0055] During operation, fuel can be delivered directly to the interior of the flame tube 2 via the duty-stage fuel pipe 43. That is, in this embodiment, the fuel entering the flame tube 2 via the primary-stage fuel pipe 41 and the secondary-stage fuel pipe 42 can form premixed combustion, while the fuel entering the flame tube 2 via the duty-stage fuel pipe 43 can form diffusion combustion. Compared to premixed combustion, diffusion combustion is more stable and easier to ignite.

[0056] In this embodiment, the duty class fuel pipe 43 being close to the igniter 5 means that the distance between the duty class fuel pipe 43 and the igniter 5 is close enough so that the fuel ejected from the duty class fuel pipe 43 can be easily ignited by the igniter 5. For example, in a certain type of gas turbine, the duty class fuel pipe 43 being close to the igniter 5 means that the distance between the axis of the igniter 5 and the axis of the duty class fuel pipe 43 is less than 5 centimeters or less than 6 centimeters.

[0057] It should be noted that the nozzle disc 1 is used in a high-temperature environment for a long time. In order to reduce the temperature of the nozzle disc 1 during use and thereby increase the service life of the nozzle disc 1, in one embodiment of the present application, the nozzle disc 1 is also provided with multiple cooling structures, each cooling structure being used to cool the nozzle disc 1.

[0058] In this embodiment, the cooling structure can be any suitable structure that can cool the nozzle disk 1. For example, the cooling structure can be the cooling wall surface structure disclosed in the patent application document with the publication number: CN117570471A and the name: Combustion chamber flame tube cooling wall surface structure and flame tube with integrated impingement cooling and mixing; or it can be the wall surface double-layer composite cooling structure disclosed in the patent application document with the publication number: CN116357999A and the name: Double-layer composite cooling structure for the wall surface of a gas turbine combustion chamber flame tube.

[0059] In a specific embodiment of the present application, the cooling structure may include an air inlet hole 61, a cooling cavity 63, and an air outlet hole 62 that are sequentially arranged on the nozzle disk 1 along the first direction. Both the air inlet hole 61 and the air outlet hole 62 are connected to the cooling cavity 63. During use, the air outside the nozzle disk 1 will enter the cooling cavity 63 through the air inlet hole 61 as shown in Figure 7 and the air in the cooling cavity 63 will then be ejected from the air outlet hole 62 as shown in Figure 8 . Since the temperature of the air is much lower than the temperature of the flame during combustion, the air flowing in the cooling structure can reduce the temperature of the nozzle disk 1.

[0060] In this embodiment, the higher the velocity of the air ejected from the air outlet hole 62, the more likely it is that the mixture ejected from the nozzle 3 will burn unstably, that is, flame detachment occurs. In order to reduce the velocity of the air ejected from the air outlet hole 62 and thus avoid the occurrence of flame detachment, in an embodiment of the present application, the axis lines of both the air inlet hole 61 and the air outlet hole 62 are parallel to the first direction, and the projections of the air inlet hole 61 and the air outlet hole 62 along the first direction do not overlap. If the projections of the air inlet hole 61 and the air outlet hole 62 along the first direction do not overlap, the air entering the cooling cavity 63 from the air inlet hole 61 will surely impact on the inner wall of the cooling cavity 63. If the air entering the cooling cavity 63 impacts on the inner wall of the cooling cavity 63, the kinetic energy of the air will be consumed, that is, the velocity of the air flowing out from the air outlet hole 62 will be reduced.

[0061] In order to further reduce the velocity of the air flowing out from the air outlet hole 62, in an embodiment of the present application, the cross-sectional area of the air outlet hole 62 can be larger than the cross-sectional area of the air inlet hole 61, and the cross-section is perpendicular to the first direction. Based on the principle of flow conservation, it can be known that if the flow area becomes larger, the flow velocity must decrease. That is to say, if the cross-sectional area of the air outlet hole 62 is larger than the cross-sectional area of the air inlet hole 61, the velocity of the air flowing through the air outlet hole 62 will also surely decrease.

[0062] It should be clear that in as ​In the nozzle plate 1 shown, dense nozzles 3 and air outlet holes 62 are provided. That is, the space in the nozzle plate 1 where the air outlet holes 62 are provided is relatively narrow. If the cross-sectional area of the air outlet holes 62 is larger than that of the air inlet holes 61, it is difficult to achieve that the projections of the air inlet holes 61 and the air outlet holes 62 in the first direction do not overlap. If the projections of the air inlet holes 61 and the air outlet holes 62 in the first direction overlap, it is difficult to reduce the velocity of the air flowing out of the air outlet holes 62. In order to be able to achieve that the cross-sectional area of the air outlet holes 62 is larger than that of the air inlet holes 61 in a narrow space and also be able to achieve that the projections of the air inlet holes 61 and the air outlet holes 62 in the first direction do not overlap, in an embodiment of the present application, as ​ shown, there can be multiple air outlet holes 62, and each of the air outlet holes 62 is distributed around the axis line of the air inlet hole 61. And the sum of the cross-sectional areas of each of the air outlet holes 62 is larger than the cross-sectional area of the air inlet hole 61, and the cross-section is perpendicular to the first direction.

[0063] For the combustion chamber proposed in the embodiment of the present application, the nozzle it has can enable the air and fuel to form effective micro-mixing inside the nozzle only through the design of multiple ramp blocks. Its overall structure is simple. It will not significantly reduce the power of the mixture formed by the air and fuel, and can reduce the manufacturing cost of the nozzle.

[0064] It should be clear that the embodiments of the present application only illustrate the embodiments of the nozzle and the combustion chamber proposed in the present application through the application scenario of a gas turbine, and it does not mean that the nozzle and the combustion chamber proposed in the present application are only applicable to the application scenario of a gas turbine. That is to say, there is no restriction on the application scenarios of the nozzle and the combustion chamber proposed in the present application. For example, the nozzle and the combustion chamber proposed in the present application can also be applied to application scenarios such as aero-engines or automotive engines, etc., and no more examples are listed here for elaboration.

[0065] Although the embodiments of the present application have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principle and spirit of the present application. The scope of the present application is defined by the appended claims and their equivalents.

Claims

1. A nozzle (3), characterized in that, Comprising: A tube body (31); an air flow passage (34) is formed inside the tube body (31); A plurality of ramp blocks (32); each ramp block (32) is disposed on the inner wall of the tube body (31), and each ramp block (32) is circumferentially distributed around the tube body (31); each ramp block (32) has a ramp surface (321), and the distance between the ramp surface (321) and the inner wall of the tube body (31) increases along a first direction; the first direction is parallel to the axis of the tube body (31) and points from the input end to the output end of the air flow passage (34); A fuel flow passage (33) disposed on the ramp block (32); the input end of the fuel flow passage (33) extends through the tube body (31), and the output end of the fuel flow passage (33) extends through the corresponding ramp block (32).

2. The nozzle (3) according to claim 1, characterized in that, The tube body (31) includes a converging tube section (311) and a premixing tube section (312) connected in sequence along the first direction; the inner diameter of the converging tube section (311) decreases along the first direction.

3. The nozzle (3) according to claim 1, characterized in that, The ramp surface (321) is a plane or a curved surface.

4. The nozzle (3) according to any one of claims 1 to 3, characterized in that, Each fuel flow passage (33) is arrayed around the axis of the tube body (31); the fuel jets ejected from each fuel flow passage (33) can form a swirl between each ramp block (32).

5. The nozzle (3) according to claim 4, characterized in that, The opening at the output end of the fuel flow passage (33) is located on the side surface of the ramp block (32); the angle between the direction of the fuel jet and the side surface is greater than or equal to 45° and less than or equal to 75°.

6. The nozzle (3) according to claim 5, characterized in that, The spatial angle between the direction of the fuel jet and the first direction is greater than or equal to 30° and less than or equal to 60°.

7. A combustion chamber, characterized in that, Comprising a nozzle (3) as described in any one of claims 1 to 6.

8. The combustor according to claim 7, characterized in that, Comprising: A combustion chamber liner (2); A nozzle disc (1), disposed inside the combustion chamber liner (2); A fuel chamber (11) is provided in the nozzle disc (1); A plurality of nozzles (3); each nozzle (3) is disposed on the nozzle disc (1), and each nozzle (3) axially penetrates the nozzle disc (1) along the combustion chamber liner (2); the input end of the fuel flow passage (33) in each nozzle (3) is communicated with the fuel chamber (11); A fuel delivery pipe (4), disposed on the nozzle disc (1), and the fuel delivery pipe (4) is communicated with the fuel chamber (11); An igniter (5); the igniter (5) penetrates the nozzle disc (1).

9. The combustion chamber according to claim 8, characterized in that, A partition (111) is further provided inside the nozzle disc (1); the partition (111) divides the fuel chamber (11) into a main combustion stage fuel chamber (112) and a secondary combustion stage fuel chamber (113); the fuel delivery pipe (4) includes a main combustion stage fuel pipe (41) and a secondary combustion stage fuel pipe (42); the main combustion stage fuel pipe (41) is communicated with the main combustion stage fuel chamber (112), and the secondary combustion stage fuel pipe (42) is communicated with the secondary combustion stage fuel chamber (113).

10. The combustor according to claim 9, characterized in that, The fuel delivery pipe (4) further includes a duty fuel pipe (43); the duty fuel pipe (43) penetrates the nozzle disc (1), and the duty fuel pipe (43) is close to the igniter (5).

11. The combustor according to claim 8, wherein The nozzle disc (1) is further provided with a plurality of cooling structures, and each cooling structure is used to cool the nozzle disc (1).

12. The combustion chamber according to claim 11, characterized in that, The cooling structure includes an air inlet hole (61), a cooling cavity (63) and an air outlet hole (62) which are sequentially arranged on the nozzle disc (1) along a first direction; the air inlet hole (61) and the air outlet hole (62) are both communicated with the cooling cavity (63); the axis lines of the air inlet hole (61) and the air outlet hole (62) are both parallel to the first direction, and the projections of the air inlet hole (61) and the air outlet hole (62) in the first direction do not overlap.

13. The combustion chamber according to claim 12, characterized in that, There are a plurality of the air outlet holes (62), and each air outlet hole (62) is distributed around the axis line of the air inlet hole (61); the sum of the cross-sectional areas of each air outlet hole (62) is greater than the cross-sectional area of the air inlet hole (61), and the cross-section is perpendicular to the first direction.

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