Gas turbine and combustion chamber thereof

Abstract

The invention discloses a gas turbine and a combustion chamber thereof, and relates to the technical field of combustion chambers. The combustion chamber comprises a nozzle disc. A partition plate is further arranged in the nozzle disc. The fuel cavity is divided into a primary combustion level fuel cavity and a secondary combustion level fuel cavity by the partition plate; the fuel conveying pipe comprises a primary combustion level fuel pipe and a secondary combustion level fuel pipe; the primary combustion stage fuel pipe is communicated with the primary combustion stage fuel cavity, and the secondary combustion stage fuel pipe is communicated with the secondary combustion stage fuel cavity. Through the arrangement of the primary combustion stage fuel cavity, the secondary combustion stage fuel cavity, the primary combustion stage fuel pipe and the secondary combustion stage fuel pipe, fuel conveying can be adjusted based on the actual working condition of the gas turbine. The phenomenon that a combustion chamber is prone to flameout or unstable in combustion when the gas turbine is in a low working condition can be avoided; and the phenomenon that when the gas turbine is in a high working condition, the fuel equivalent in the mixed gas is relatively high, so that the content of combustion pollutants is increased can also be avoided.

Description

Technical Field

[0001] The present application relates to the technical field of combustion chambers, and specifically to a gas turbine and its combustion chamber. Background Technique

[0002] A gas turbine is an internal combustion power machine that uses continuously flowing gas as the working medium to drive the impeller to rotate at high speed and convert the energy of fuel into useful work. That is to say, a gas turbine is a rotary impeller type thermal engine. The existing combustion chamber of a gas turbine is as Figure 4 shown, which includes a nozzle disc 1, a flame tube 2, a fuel delivery pipe 4, an igniter 5, and a plurality of nozzles 3. The nozzle disc 1 has a fuel chamber 11 inside. The nozzles 3 can communicate with both the fuel chamber 11 and the outside of the flame tube 2. During use, fuel is injected into the fuel chamber 11 through the fuel delivery pipe 4, so that the air input from the outside of the flame tube 2 and the fuel inside the fuel chamber 11 can be premixed in the nozzles 3 to form a mixture. Further, the formed mixture can enter the flame tube 2 from the output ends of the air flow channels in the respective nozzles 3 and then participate in subsequent combustion.

[0003] 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 gas turbine requires less fuel when in a low operating condition, that is, the amount of fuel entering each nozzle is less, and during the use of the gas turbine, the amount of air entering each nozzle 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 is relatively low. If the fuel equivalence ratio of the mixture is too low, the combustion chamber is extremely likely to flame out or have unstable combustion. Summary of the Invention

[0004] The purpose of the present application is to provide a gas turbine and its combustion chamber to solve the technical problem that the combustion chamber of the existing gas turbine is prone to flameout or unstable combustion under low operating conditions.

[0005] To achieve the above purpose, the present application provides the following technical solutions: In a first aspect, the present application proposes a technical solution for a combustion chamber, which includes a nozzle disc, a flame tube, a fuel delivery pipe, an igniter, and a plurality of nozzles; each nozzle includes a pipe body, and an air flow passage is formed inside the pipe body; a plurality of fuel flow passages are further provided on the inner wall of the pipe body, and each fuel flow passage can communicate the outside of the pipe body and the air flow passage; a fuel chamber is provided inside the nozzle disc; 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 communicates with the main combustion stage fuel chamber, and the secondary combustion stage fuel pipe communicates with the secondary combustion stage fuel chamber.

[0006] 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 through the nozzle disc, and the duty fuel pipe is close to the igniter.

[0007] As a specific solution in the technical solution of the present application, the nozzle further includes ramp blocks corresponding to the fuel flow passages one by one; each ramp block is provided on the inner wall of the pipe body, and each ramp block is distributed circumferentially 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 along a first direction; the first direction is parallel to the axis line of the pipe body and points from the input end of the air flow passage to the output end; 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.

[0008] As a specific solution in the technical solution of the present application, the pipe body includes a converging pipe section and a premixing pipe section connected in sequence along the first direction; the inner diameter of the converging pipe section decreases along the first direction.

[0009] As a specific solution in the technical solution of the present application, the connection between the converging pipe section and the premixing pipe section is smoothly transitioned without a step.

[0010] As a specific solution in the technical solution of the present application, the fuel flow passages are arrayed around the axis line of the pipe body; the fuel jets ejected from the fuel flow passages can form a swirl between the ramp blocks.

[0011] As a specific solution in the technical solution of the present application, the opening at 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°.

[0012] 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°.

[0013] 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.

[0014] 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 that are sequentially arranged on the nozzle disc along a first direction; the air inlet hole and the air outlet hole are both 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.

[0015] As a specific solution in the technical solution of the present application, there are a plurality of the 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.

[0016] As a specific solution in the technical solution of the present application, a chamfer is provided at the output end of the air flow channel.

[0017] As a specific solution in the technical solution of the present application, the angle of the chamfer is 45°.

[0018] As a specific solution in the technical solution of the present application, the combustion chamber is applied to a gas turbine. When the gas turbine operates stably, the ratio of the fuel input in the main combustion stage fuel pipe and the secondary combustion stage fuel pipe is equal to the ratio of the first quantity to the second quantity; the first quantity is the number of nozzles communicated with the main combustion stage fuel chamber; the second quantity is the number of nozzles communicated with the secondary combustion stage fuel chamber.

[0019] As a specific solution in the technical solution of the present application, there are a plurality of the secondary combustion stage fuel chambers, and each secondary combustion stage fuel chamber is evenly distributed around the axis line of the nozzle disc.

[0020] In a second aspect, the present application proposes a technical solution for a gas turbine, and the gas turbine includes the combustion chamber as described in any one of the first aspects.

[0021] Compared with the prior art, the beneficial effects of the present application are: Through the settings of the main combustion stage fuel chamber, the secondary combustion stage fuel chamber, the main combustion stage fuel pipe, and the secondary combustion stage fuel pipe, the present application realizes the adjustment of the fuel delivery based on the actual working conditions of the gas turbine. It can not only avoid the phenomenon that the combustion chamber is prone to flameout or unstable combustion when the gas turbine is in a low working condition; but also avoid the phenomenon that the content of combustion pollutants increases due to a high fuel equivalence ratio in the mixture when the gas turbine is in a high working condition. Description of the Drawings

[0022] Figure 1 A three-dimensional schematic diagram of a nozzle proposed in an embodiment of the present application; Figure 2 is Figure 1 a longitudinal sectional schematic diagram of the nozzle in Figure 3 a transverse sectional schematic diagram of a nozzle proposed in an embodiment of the present application; Figure 4 a sectional schematic diagram of a combustion chamber in the prior art; Figure 5 a three-dimensional schematic diagram of a combustion chamber proposed in an embodiment of the present application; Figure 6 is Figure 5 a three-dimensional schematic diagram of the combustion chamber in another direction in Figure 7 a three-dimensional schematic diagram of a nozzle disc proposed in an embodiment of the present application; Figure 8 is Figure 7 a three-dimensional schematic diagram of the nozzle disc in another direction in Figure 9 a structural schematic diagram of a fuel chamber proposed in an embodiment of the present application; Figure 10 a structural schematic diagram of a cooling structure proposed in an embodiment of the present application; Figure 11 a longitudinal sectional schematic diagram of yet another nozzle proposed in an embodiment of the present application.

[0023] In the figure: 1. Nozzle disc; 11. Fuel chamber; 111. Partition; 112. Main combustion stage fuel chamber; 113. Secondary combustion stage fuel chamber; 2. Flame tube; 3. Nozzle; 31. Pipe body; 311. Converging pipe section; 312. Premixing pipe section; 32. Ramp block; 321. Ramp surface; 33. Fuel flow channel; 34. Air flow channel; 35. Chamfer; 4. Fuel delivery pipe; 41. Main combustion stage fuel pipe; 42. Secondary combustion stage fuel pipe; 43. Duty fuel pipe; 5. Igniter; 61. Air inlet hole; 62. Air outlet hole; 63. Cooling chamber. Detailed implementation manners

[0024] 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. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present application.

[0025] It should be noted that, in the description of this application, the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description. They do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, they cannot be understood as a limitation on this application.

[0026] Furthermore, it should be understood that for the sake of ease of description, the sizes of the various components shown in the drawings are not drawn according to actual proportions. For example, the thickness or width of certain layers may be exaggerated relative to other layers.

[0027] It should be noted that like numbers and letters represent similar items in the following figures, so once an item is defined or described in one figure, it will not need to be further discussed and described in detail in the description of the subsequent figures.

[0028] Before understanding the embodiments of the present application, it should be understood that the components or structures used to guide fluids in the 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 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.

[0029] Specifically, a gas turbine and its combustion chamber in the prior art are as follows: Figure 4 As shown, the combustion chamber includes a nozzle plate 1, a flame tube 2, a fuel delivery pipe 4, an igniter 5 and a plurality of nozzles 3. Figure 4 As shown, a nozzle disc 1 is disposed within a flame tube 2 and defines a fuel chamber 11. A fuel delivery pipe 4 is connected to the nozzle disc 1 and communicates with the fuel chamber 11. An igniter 5 is disposed within the nozzle disc 1 and extends through the nozzle disc 1. Each nozzle 3 is disposed within the nozzle disc 1 and extends axially through the flame tube 2. The interior of each nozzle 3 (hereinafter referred to as an air flow passage 34) can communicate with both the fuel chamber 11 and the exterior of the flame tube 2 (i.e., air outside the flame tube 2 can enter the interior of the nozzle 3 during use).

[0030] During use, fuel (which can be pure hydrogen, hydrogen-rich fuel, natural gas, etc.) is injected into the fuel chamber 11 through the fuel delivery pipe 4. Since the interior of each nozzle 3 can communicate with the fuel chamber 11, the fuel located in the fuel chamber 11 can enter the interior of each nozzle 3. Since each nozzle 3 penetrates the nozzle disc 1 along the axial direction of the combustion chamber 2, the air located outside the combustion chamber 2 can also enter the interior of the nozzle 3. Further, the air and fuel entering the interior of the nozzle 3 can be mixed, thereby forming a mixture. Further, the formed mixture can enter the combustion chamber 2 from the output end of each nozzle 3 and then participate in subsequent combustion.

[0031] As can be seen from the background art, when a gas turbine is in use, the amount of air entering each nozzle 3 is basically constant. In the application scenario where the gas turbine is in a high operating condition, the amount of fuel entering each nozzle 3 is large; in the application scenario where the gas turbine is in a low operating condition, the amount of fuel entering each nozzle 3 is small. If, during design, the fuel equivalence ratio of the mixture meets the combustion requirements when the gas turbine is in a low operating condition and no flameout or unstable combustion occurs, then when the gas turbine is in a high operating condition, the fuel equivalence ratio of the mixture must be too high. If the fuel equivalence ratio of the mixture is too high, the fuel is not easily burned completely, and the combustion temperature will be too high. During the combustion process, if the fuel is not burned completely or the combustion temperature is too high, both will result in an increase in the amount of pollutants generated during combustion. If, during design, the fuel equivalence ratio of the mixture meets the combustion requirements when the gas turbine is in a high operating condition, that is, the content of pollutants generated during combustion is not increased, then when the gas turbine is in a low operating condition, the fuel equivalence ratio of the mixture must be too low, that is, the combustion chamber is prone to flameout or unstable combustion.

[0032] To solve the above technical problems, an embodiment of a gas turbine and its combustion chamber is proposed in this application. The combustion chamber includes a nozzle disc 1, a combustion chamber 2, a fuel delivery pipe 4, an igniter 5, and a plurality of nozzles 3. Each nozzle 3 includes a pipe body 31. An air flow passage 34 is formed inside the pipe body 31, and a plurality of fuel flow passages 33 are further provided on the inner wall of the pipe body 31. Each fuel flow passage 33 can communicate the outside of the pipe body 31 and the air flow passage 34. A fuel chamber 11 is provided inside the nozzle disc 1, and 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 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.

[0033] During use, fuel can be respectively transported 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 transported 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 transported 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 (such as nitrogen oxides) increases due to different fuel equivalence ratios (that is, uneven mixing of the fuel-air mixture) in the fuel-air mixture formed in each nozzle 3.

[0034] In this embodiment, through the settings of the primary combustion stage fuel chamber, the secondary combustion stage fuel chamber, the primary combustion stage fuel pipe and the secondary combustion stage fuel pipe, the adjustment of fuel transportation can be realized based on the actual operating condition of the gas turbine. It can not only avoid the phenomenon that the combustion chamber is prone to flameout or unstable combustion when the gas turbine is in a low operating condition, but also avoid the phenomenon that the content of combustion pollutants increases due to a relatively high fuel equivalence ratio in the fuel-air mixture when the gas turbine is in a high operating condition.

[0035] In the embodiment of the present application, evenly transporting fuel to the primary combustion stage fuel chamber 112 and the secondary combustion stage fuel chamber 113 means transporting fuel in equal proportion to the primary combustion stage fuel chamber 112 and the secondary combustion stage fuel chamber 113 according to the number ratio of the nozzles 3 connected to the primary combustion stage fuel chamber 112 and the secondary combustion stage fuel chamber 113. For example, if there are x nozzles 3 connected to the primary combustion stage fuel chamber 112 and y nozzles 3 connected to 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 transported 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 transported 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.

[0036] In the embodiment of the present application, there is no limitation on the division 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 the non-uniformly divided primary combustion stage fuel chamber 112 and the secondary combustion stage fuel chamber 113. It should be noted that in accordance withFigure 9 The primary combustion stage fuel cavity 112 and the secondary combustion stage fuel cavity 113 divided as shown can make the temperature field in the combustion chamber tend to be uniform regardless of how the fuel amount is adjusted. Figure 9 As shown, there are two secondary fuel cavities 113, which are evenly distributed around the axis of the nozzle plate 1. Of course, in other embodiments of the present application, the number of secondary fuel cavities 113 can be set as required, for example, 3 or 4.

[0037] In order to make the fuel entering the main combustion stage fuel cavity 112 from the main combustion stage fuel pipe 41 be evenly distributed, in the embodiment of the present application, the following can be done: Figure 5 As shown, multiple branch pipes can be provided between the primary fuel pipe 41 and the nozzle plate 1; one end of each branch pipe is connected to the primary fuel pipe 41, and the other end is connected to the primary fuel cavity 112. In other words, this embodiment allows fuel to be evenly distributed throughout the primary fuel cavity 112 via multiple branch pipes. Of course, in this embodiment, branch pipes can also be used to evenly distribute fuel from the secondary fuel pipe 42 to various locations in the secondary fuel cavity 113, but this will not be discussed in detail here.

[0038] 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.

[0039] 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.

[0040] During use, fuel can be directly delivered to the interior of the combustion chamber 2 through the pilot fuel pipe 43. That is to say, in this embodiment, the fuel entering the combustion chamber 2 through the main combustion stage fuel pipe 41 and the secondary combustion stage fuel pipe 42 can form premixed combustion, while the fuel entering the combustion chamber 2 through the pilot fuel pipe 43 can form diffusion combustion. Compared with premixed combustion, diffusion combustion is more stable, and the fuel based on diffusion combustion is also easier to be ignited.

[0041] In this embodiment, the pilot fuel pipe 43 being close to the igniter 5 means that the distance between the pilot fuel pipe 43 and the igniter 5 is close enough to enable the fuel ejected from the pilot fuel pipe 43 to be easily ignited by the igniter 5. For example, in a certain model of gas turbine, the pilot 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 pilot fuel pipe 43 is less than 5 cm or less than 6 cm, etc.

[0042] In the embodiments of the present application, no restrictions are imposed on the shape and structure of the nozzle 3. For example, in an embodiment of the present application, the nozzle 3 can be as Figure 11 shown. The nozzle 3 includes a pipe body 31, and an air flow passage 34 is formed inside the pipe body 31; a plurality of fuel flow passages 33 are also provided on the pipe wall of the pipe body 31, and each fuel flow passage 33 can communicate the air flow passage 34 with the outside of the pipe body 31. In order to enable the combustion chamber proposed in this embodiment to be applicable to pure hydrogen fuel or hydrogen-rich fuel, the nozzle 3 can also be a nozzle 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 significantly 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 relatively high flow rate. The mixture with a relatively high flow rate has strong anti-backfire ability and flexible fuel adaptability. For example, the nozzle 3 can be the nozzle disclosed in the patent documents with the publication number: CN116642204A, titled: A Micro-mixing Nozzle with a Swirl Mixer and a Combustion Chamber (hereinafter referred to as Prior Art One); and, the publication number: CN116697405A, titled: A Premixed Swirl Micro-mixing Nozzle and a Combustion Chamber (hereinafter referred to as Prior Art Two).

[0043] It should be noted that in order to ensure that hydrogen and air are evenly mixed inside the nozzle, the flow channel design inside the nozzle is often more complex (for example, the nozzles disclosed in Prior Art 1 and Prior Art 2). Although nozzles with more complex flow channel designs can improve the uniformity of mixing hydrogen and air, the resulting mixture has a larger dynamic loss. Since 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. Therefore, if the dynamic loss of the mixture is large, the nozzle's anti-backfire and flexible fuel adaptability will be reduced. In addition, the more complex the nozzle design, the higher the production cost.

[0044] In order to solve the technical problem that the nozzle structure based on the existing micro-mixing combustion technology is relatively complex, 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.

[0045] 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.

[0046] 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 ejected directly 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, resulting in strong mixing of the fuel and the air, thereby improving the mixing uniformity of the fuel and the air, improving the uneven distribution of the combustion temperature, and enhancing the emission reduction effect.

[0047] For the nozzle 3 proposed in this embodiment, only through the design of multiple ramp blocks 32, the air and fuel can be effectively micro-mixed inside the nozzle 3. Its overall structure is simple, and it will not significantly reduce the power of the mixture formed by the air and fuel (such as hydrogen), and can reduce the manufacturing cost of the nozzle 3.

[0048] 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.

[0049] 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 in the first direction. For example, the ramp surface 321 can be a plane or a curved surface.

[0050] 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 more, the number of formed recirculation zones is more. If the number of formed recirculation zones is more, although the mixing of the air and fuel is more uniform, the power loss of the formed mixture is also greater. 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 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 as Figure 1 shown as 4, or can be as Figure 3 shown as 3.

[0051] As can be seen from the background art, if the speed of the mixture gas (that is, the gas formed after mixing the air and fuel) ejected from the nozzle 3 is greater, the probability of flashback of the nozzle 3 is smaller, and the adaptability of the nozzle 3 to various flexible fuels is also stronger. In order to increase the speed of the mixture gas ejected from the nozzle 3, in an embodiment of the present application, as Figure 2 shown, the pipe body 31 includes a first direction (that is, as Figure 2The direction shown in A) successively connected contraction pipe section 311 and premixing pipe section 312. 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 passage 34 increases, the velocity of the mixture formed in the air flow passage 34 will also definitely increase.

[0052] In order to avoid forming a step between the contraction pipe section 311 and the premixing pipe section 312, thereby reducing the air flow velocity in the air flow passage 34, in an embodiment of the present application, as Figure 2 shown, the inner diameter of each part of 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 passage 34 will not be reduced due to the step.

[0053] In order to further improve the mixing uniformity of air and fuel in the air flow passage 34, in an embodiment of the present application, the mixture in the air flow passage 34 can also be made to form a swirl. If the mixture in the air flow passage 34 forms a swirl, the mixing uniformity of air and fuel can be further improved, that is, the pollutant emissions can be further reduced.

[0054] In the embodiment of the present application, any reasonable method can be adopted to make the mixture in the air flow passage 34 form a swirl. For example, a swirler is provided in the air flow passage 34. If a swirler is provided in the air flow passage 34, the complexity of the nozzle will increase, and the swirler will greatly reduce the flow velocity of the formed mixture. In order not to increase the complexity of the nozzle and not greatly reduce the flow velocity of the mixture, in an embodiment of the present application, each fuel flow passage 33 can be arrayed around the axis of the pipe body 31, and the fuel jets ejected from each fuel flow passage 33 can form a swirl between each ramp block 32 (that is, such as Figure 3 the swirl D shown). In this embodiment, the mixture in the air flow passage 34 can 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.

[0055] In this embodiment, the meaning of "array" is the same as the meaning of "array" in the field of three-dimensional design. That is, an array refers to linearly replicating and arranging or circumferentially replicating and arranging a certain object (for example, the fuel flow passage 33 in the above text) in three-dimensional space according to certain rules and regulations.

[0056] In this embodiment, the shape of the fuel flow channel 33 is not limited, as long as the fuel jets ejected from the fuel flow channels 33 of each array can form a swirl. It should be clear that for the fluid (i.e., fuel), the direction of the jet 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 output end of the fuel flow channel 33 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 the fuel flow channels 33 are arrayed around the axis line of the pipe body 31, as long as the axis line direction of the output end of the fuel flow channel 33 is different from the axis line of the pipe body 31, the fuel jets will definitely form a swirl. That is to say, in this embodiment, the fuel jets ejected from the fuel flow channels 33 can form a swirl between the slope blocks 32 means that the axis line of the output end of the fuel flow channel 33 and the axis line of the pipe body 31 (i.e., the axis line of the air flow channel 34) are skew lines.

[0057] 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 uniformly, 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 slope block 32, and the direction of the fuel jet (i.e., the direction C as shown in Figure 3 ) forms an angle (i.e., the angle θ as shown in Figure 3 ) with the side surface of the slope block 32 that 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.

[0058] In this embodiment, as Figure 3 shown, hydrogen is ejected from the fuel flow channel 33 on the side surface of the slope 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 in the center of the pipe body 31 and mixes with the central air, and then enters the recirculation zone at the bottom of the slope block 32, which can effectively improve the mixing uniformity of the fuel and air.

[0059] In this embodiment, if the swirl and the mainstream in the air flow passage 34 form a head-on collision, the flow velocity of the mixed gas formed in the air flow passage 34 will be reduced. To avoid the swirl from forming a head-on collision with the mainstream in the air flow passage 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 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.

[0060] 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 passage 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 passage 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 passage 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.

[0061] It should be noted that the nozzle disk 1 is in a high-temperature usage environment for a long time. To reduce the temperature of the nozzle disk 1 during use and thus improve the service life of the nozzle disk 1, in an embodiment of the present application, the nozzle disk 1 is further provided with a plurality of cooling structures, and each cooling structure is used to cool the nozzle disk 1.

[0062] 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 for impact cooling and mixing integration; 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: A double-layer composite cooling structure for the wall surface of a gas turbine combustion chamber flame tube.

[0063] 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 plate 1 along the first direction. Both the air inlet hole 61 and the air outlet hole 62 are in communication with the cooling cavity 63. During use, the air located outside the nozzle plate 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 is then 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 plate 1.

[0064] 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 burns 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.

[0065] 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 may 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 runoff 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 must also decrease.

[0066] It should be clear that a dense nozzle 3 and air outlet hole 62 are provided in the nozzle plate 1 as shown in Figure 8 . That is, the space for arranging the air outlet hole 62 in the nozzle plate 1 is relatively narrow. If the cross-sectional area of the air outlet hole 62 is larger than the cross-sectional area of the air inlet hole 61, it is difficult to achieve that 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 overlap, it is difficult to reduce the velocity of the air flowing out from the air outlet hole 62. In order to be able to achieve that the cross-sectional area of the air outlet hole 62 is larger than the cross-sectional area of the air inlet hole 61 and also be able to achieve that the projections of the air inlet hole 61 and the air outlet hole 62 along the first direction do not overlap in a narrow space, in an embodiment of the present application, as shown in Figure 10As shown, there can be multiple air outlet holes 62, and each air outlet hole 62 is distributed around the axis line of the air inlet hole 61 (hereinafter referred to as the first axis line). And 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.

[0067] It should be clear that in application scenarios where pure hydrogen fuel and hydrogen-rich fuel are the main fuels, a relatively large injection speed of the mixture is required to avoid flashback. It should be noted that the greater the injection speed of the mixture, the easier it is to form periodic angular vortices at the end of the nozzle 3. The periodic generation and shedding of the angular vortices will be coupled with the combustion heat release, triggering thermoacoustic oscillations (the oscillation frequency is usually 100 Hz to 1000 Hz). In this embodiment, through multiple air outlet holes 62 distributed around the first axis line, since the air beam ejected from each air outlet hole 62 has a relatively low speed, these air beams can disperse the angular vortices formed by the nearby nozzles. If the angular vortices can be eliminated, the thermoacoustic oscillations generated by the combustion chamber can be reduced.

[0068] In order to further reduce the thermoacoustic oscillations generated by the combustion chamber, in the embodiment of the present application, as Figure 11 shown, a chamfer 35 is provided at the output end of the air flow channel 34. In this embodiment, the chamfer 35 can cooperate with each of the above-mentioned air outlet holes 62 to greatly weaken the formation of angular vortices. The elimination of the angular vortices makes the flow field downstream of the nozzle 3 more symmetrical, avoiding flame oscillation caused by asymmetric vortex pairs (such as Karman vortex street). The low-temperature air beam ejected from the air outlet hole 62 can actively regulate the flow field, form a stable low-speed recirculation zone, and then keep the position of the flame front fixed, avoiding flicker or blowout.

[0069] In the embodiment of the present application, there is no limitation on the way of chamfering. For example, the surface formed by the chamfer 35 can be a flat surface or an arc surface as Figure 11 shown. If the surface formed by the chamfer 35 is a flat surface, the angle of the chamfer 35 can be 45°. Of course, in other embodiments of the present application, it can be other angles.

[0070] In the embodiment of the combustion chamber proposed by the present application, through the settings of the main combustion stage fuel chamber, the secondary combustion stage fuel chamber, the main combustion stage fuel pipe, and the secondary combustion stage fuel pipe, the adjustment of the fuel delivery can be realized based on the actual working conditions of the gas turbine. It can not only avoid the phenomenon that the combustion chamber is prone to flameout or unstable combustion when the gas turbine is in a low working condition; but also avoid the phenomenon that the content of combustion pollutants increases due to a high fuel equivalence ratio in the mixture when the gas turbine is in a high working condition.

[0071] It should be clear that the embodiments of the combustor proposed in this application are merely illustrated by the application scenario of a gas turbine, and it does not mean that the combustor proposed in this application is only applicable to the application scenario of a gas turbine. That is to say, there are no restrictions on the application scenarios of the combustor proposed in this application. For example, the combustor proposed in this application can also be applied to application scenarios such as aeroengines or automotive engines, etc., and no more examples are listed here for elaboration.

[0072] After introducing the combustor proposed in the embodiments of this application, the following introduces an embodiment of a gas turbine proposed in this application. Specifically, the gas turbine includes the combustor described in any one of the above embodiments.

[0073] In the embodiment of the gas turbine proposed in this application, through the settings of the primary combustion fuel chamber, the secondary combustion fuel chamber, the primary combustion fuel pipe, and the secondary combustion fuel pipe, it is possible to adjust the fuel delivery based on the actual working conditions of the gas turbine. It can not only avoid the phenomenon that the combustor is prone to flameout or unstable combustion when the gas turbine is in a low working condition, but also avoid the phenomenon that the fuel equivalence ratio in the mixture is relatively high and the content of combustion pollutants increases when the gas turbine is in a high working condition.

[0074] Although the embodiments of this 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 this application. The scope of this application is defined by the appended claims and their equivalents.

Claims

1. A combustion chamber, comprising a nozzle disc (1), a flame tube (2), a fuel delivery pipe (4), an igniter (5) and a plurality of nozzles (3); each nozzle (3) includes a pipe body (31), and an air flow passage (34) is formed inside the pipe body (31); a plurality of fuel flow passages (33) are further arranged on the inner wall of the pipe body (31), and each fuel flow passage (33) can communicate the outside of the pipe body (31) and the air flow passage (34); a fuel chamber (11) is arranged inside the nozzle disc (1); it is characterized in that, A partition plate (111) is further provided inside the nozzle disc (1); the partition plate (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) 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).

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

3. The combustor according to claim 1, wherein, The nozzle (3) further includes ramp blocks (32) corresponding to the fuel flow channels (33) one by one; each ramp block (32) is disposed on the inner wall of the pipe body (31), and each ramp block (32) is distributed circumferentially around the pipe 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 pipe body (31) increases along a first direction; the first direction is parallel to the axis of the pipe body (31) and points from the input end to the output end of the air flow channel (34); the input end of the fuel flow channel (33) extends through the pipe body (31), and the output end of the fuel flow channel (33) extends through the corresponding ramp block (32).

4. The combustor according to claim 1, wherein The pipe body (31) includes a converging pipe section (311) and a premixing pipe section (312) connected in sequence along the first direction; the inner diameter of the converging pipe section (311) decreases along the first direction.

5. The combustor according to claim 4, characterized in that, The connection between the converging pipe section (311) and the premixing pipe section (312) has a smooth transition without a step.

6. The combustor according to claim 3, wherein The fuel flow channels (33) are arrayed around the axis of the pipe body (31); the fuel jets ejected from the fuel flow channels (33) can form a swirl between the ramp blocks (32).

7. The combustion chamber according to claim 6, characterized in that, The opening at the output end of the fuel flow channel (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°. 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°.

8. The combustion chamber according to any one of claims 1 to 7, characterized in that, 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).

9. The combustor according to claim 8, characterized in that, The cooling structure includes an air inlet hole (61), a cooling chamber (63) and an air outlet hole (62) sequentially arranged on the nozzle disc (1) along the first direction; both the air inlet hole (61) and the air outlet hole (62) communicate with the cooling chamber (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) along the first direction do not overlap. The air outlet holes (62) are multiple, 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; A chamfer (35) is provided at the output end of the air flow channel (34); The angle of the chamfer (35) is 45°; The combustion chamber is applied to a gas turbine. When the gas turbine operates stably, the ratio of the fuels input into the main combustion stage fuel pipe (41) and the secondary combustion stage fuel pipe (42) is equal to the ratio of the first quantity to the second quantity; the first quantity is the number of nozzles (3) communicated with the main combustion stage fuel chamber (112); the second quantity is the number of nozzles (3) communicated with the secondary combustion stage fuel chamber (113); There are multiple secondary combustion stage fuel chambers (113), and each secondary combustion stage fuel chamber (113) is evenly distributed around the axis line of the nozzle disc (1).

10. A gas turbine, characterized in that, Comprising a combustion chamber according to any one of claims 1 to 9.

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