Gas turbine and nozzle thereof

Abstract

The invention discloses a gas turbine and a nozzle thereof, and relates to the technical field of gas nozzles. The nozzle comprises a base; a premixing flow channel is formed in the spray pipe; the inner diameter of the premixing runner is gradually reduced from the head end to the tail end; the elastic piece is arranged between the base and the spray pipe; during use, elastic potential energy is stored in the elastic piece, and the elastic potential energy enables the spray pipe to have the trend of getting close to the base in the first direction. The fuel flow channel and the air flow channel are arranged on the base; the tail end of the fuel flow channel and the tail end of the air flow channel communicate with the premixing flow channel. The effective length of the premixing flow channel can be adjusted through the elastic piece based on the actual working condition of the gas turbine, then mixed gas with different mixing uniformity degrees is obtained, the gas turbine can be made to be easy to start and not prone to flameout under the low working condition, and it can be kept that pollutants generated by the gas turbine under the high working condition are few.

Description

Technical Field

[0001] The present application relates to the technical field of gas nozzles, and in particular to a gas turbine and a nozzle thereof. Background Art

[0002] With the increase of environmental awareness, the demand for low-emission gas turbines is also increasing. In the existing technology, lean-burn premixed combustion technology is often used to reduce the emission of pollutants when the gas turbine is working. Premixed combustion technology refers to the technology of pre-mixing fuel and air relatively evenly to form a mixed gas, and then injecting the mixed gas into the combustion chamber for combustion. Lean-burn premixed combustion technology refers to the technology of making the combustion equivalent in the mixed gas relatively low, so that the mixed gas can be fully burned, and the combustion temperature is low, thereby reducing the emission of pollutants such as carbon monoxide or nitrogen oxides.

[0003] It should be noted that the operating condition of the gas turbine is positively correlated with the amount of fuel input into the combustion chamber. The more fuel is input into the combustion chamber, the higher the operating condition of the gas turbine; the less fuel is input into the combustion chamber, the lower the operating condition of the gas turbine. In other words, the amount of fuel input when the gas turbine is started or in a low operating condition is less. In other words, the combustion equivalence ratio of the mixture is lower when the gas turbine is started or in a low operating condition. The lower combustion equivalence ratio makes it difficult for the gas turbine to ignite and start, or it is easy to flameout at a low operating condition. Summary of the invention

[0004] The purpose of the present application is to provide a gas turbine and a nozzle thereof to solve the technical problems that nozzles based on lean premixed combustion technology are difficult to ignite and easily flame out under low operating conditions.

[0005] To achieve the above objectives, this application provides the following technical solutions:

[0006] In a first aspect, the present application proposes a technical solution of a nozzle, the nozzle comprising:

[0007] Base;

[0008] The nozzle is slidably connected with the base in a first direction; the first direction is parallel to the axis of the nozzle; a premixing channel is formed inside the nozzle; the inner diameter of the premixing channel decreases from the head end to the end end;

[0009] an elastic member disposed between the base and the nozzle; when in use, the elastic member stores elastic potential energy, and the elastic potential energy causes the nozzle to have a tendency to approach the base along the first direction;

[0010] A fuel flow channel and an air flow channel are arranged on the base; the ends of the fuel flow channel and the air flow channel are both connected to the premixing flow channel.

[0011] As a specific solution in the technical solution of the present application, a plug is provided at the end of the fuel flow channel; the plug is provided with multiple fuel nozzles, each of which is connected to the fuel flow channel; when in use, the fuel beam ejected from the fuel nozzle intersects with the air beam ejected from the air flow channel 5.

[0012] As a specific solution in the technical solution of this application, the air flow channel includes:

[0013] Air intake;

[0014] an annular flow channel, the annular flow channel being connected to the air inlet;

[0015] A plurality of air spray holes are evenly distributed around the axis of the premixing flow channel, and each air spray hole is connected to the annular flow channel.

[0016] As a specific solution in the technical solution of the present application, each air nozzle hole is a swirl hole; and a swirler is provided at the end of the premixing channel.

[0017] As a specific solution in the technical solution of the present application, the nozzle is also provided with a plurality of cooling holes, each cooling hole runs from the head end of the nozzle to the end of the nozzle, and each cooling hole is connected to the air flow channel.

[0018] As a specific solution in the technical solution of the present application, a control structure is also arranged between the base and the nozzle; the control structure is used to adjust the flow area of ​​the air flow channel based on the pressure in the premixing flow channel, so that the flow area of ​​the air flow channel changes in a positive correlation with the pressure in the premixing flow channel.

[0019] As a specific solution in the technical solution of the present application, the control structure includes an air groove formed on the base; the nozzle is adapted to the air groove; the air flow channel includes:

[0020] an air inlet hole, connected to the air slot;

[0021] At least one control hole; each control hole is arranged on the side wall of the air slot, and each control hole is connected to the air slot; when in use, the nozzle covers a portion of each control hole;

[0022] A plurality of air spray holes are evenly distributed around the axis of the premixing channel, and each air spray hole is connected to the control hole.

[0023] As a specific solution in the technical solution of the present application, each control hole is a long strip-shaped hole, and the length direction of each control hole is parallel to the first direction.

[0024] As a specific solution in the technical solution of this application, the control structure includes:

[0025] At least one trumpet nozzle hole is provided on the base; one end of each trumpet nozzle hole is connected to the air flow channel, and the other end of each trumpet nozzle hole is connected to the premixing flow channel;

[0026] A conical block corresponding to each horn spray hole is arranged on the spray pipe and is adapted to the corresponding horn spray hole.

[0027] In a second aspect, the present application proposes a technical solution for a gas turbine, which includes a nozzle as described in any one of the first aspects.

[0028] Compared with the prior art, the beneficial effects of this application are:

[0029] The present application can adjust the effective length of the premixing flow channel based on the actual operating conditions of the gas turbine through elastic parts, thereby obtaining mixed gases with different mixing uniformities, which not only makes the gas turbine easy to start and not easy to stall under low operating conditions, but also keeps the pollutants generated when the gas turbine is under high operating conditions relatively small. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 A three-dimensional schematic diagram of a nozzle proposed in an embodiment of the present application;

[0031] Figure 2 A cross-sectional schematic diagram of a nozzle proposed in an embodiment of the present application;

[0032] Figure 3 A cross-sectional schematic diagram of another nozzle proposed in an embodiment of the present application;

[0033] Figure 4 for Figure 3 A magnified view of part A;

[0034] Figure 5 A cross-sectional schematic diagram of another nozzle proposed in an embodiment of the present application;

[0035] Figure 6 A three-dimensional schematic diagram of a base proposed in an embodiment of the present application;

[0036] Figure 7 A cross-sectional schematic diagram of another nozzle proposed in an embodiment of the present application;

[0037] Figure 8 for Figure 7 Magnified view of part D.

[0038] In the figure: 1. base; 11. air groove; 12. trumpet nozzle; 2. nozzle; 21. premixing flow channel; 22. cooling hole; 23. conical block; 3. elastic part; 4. fuel flow channel; 41. plugging; 42. fuel nozzle; 5. air flow channel; 51. air inlet hole; 52. annular flow channel; 53. air nozzle; 54. control hole; 6. swirler. DETAILED DESCRIPTION

[0039] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0040] It should be noted that, in the description of the present application, the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description. They do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore should not be understood as a limitation on the present application.

[0041] 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.

[0042] It should be noted that like reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined or described in one drawing, it will not require further detailed discussion and description in the description of the subsequent drawings.

[0043] Before understanding the technical solution of the present application, it should be clear that the uniformity of the premixing of fuel and air in a gas turbine based on lean premixed combustion technology mainly depends on the design of the premixing channel in the nozzle. In general, the longer the length of the premixing channel in the nozzle, the longer the mixing time, the better the premixing uniformity of the fuel and air, that is, the more complete the subsequent fuel combustion, the less pollutants generated. For example, the patent documents with publication number: CN104390235A, title: Premixed swirl service nozzle; and publication number: CN103148514A, title: A two-stage radial lean premixed low-emission gas nozzle both disclose similar nozzles with premixing channels.

[0044] It should be noted that during the use of the gas turbine, the amount of air input into the combustion chamber remains basically unchanged. As known from the background technology, the gas turbine controls its operating conditions by controlling the amount of fuel input into the combustion chamber. That is to say, if the gas turbine is in lean premixed combustion under full operating conditions, that is, the combustion equivalent of the mixed gas ejected from the nozzle is relatively low, then the combustion equivalent ratio of the mixed gas ejected from the nozzle is even lower when the gas turbine is in low operating conditions or when starting up. The low combustion equivalent ratio makes it difficult to start, or it is difficult to ensure that the gas turbine does not shut down under low operating conditions. In order to ensure the utilization efficiency of the gas turbine, it is generally necessary to ensure that the gas turbine is operating in a high operating condition or full operating condition for a long time. If the combustion equivalent of the nozzle is relatively high under low operating conditions through design, the combustion equivalent ratio of the gas turbine under high operating conditions or full operating conditions is higher, and the pollutants generated by the gas turbine during long-term use are more, which means that the design significance of the lean premixed combustion nozzle is lost.

[0045] In order to solve the above-mentioned technical problems, the present application proposes an embodiment of a nozzle, which includes a base 1, a nozzle 2, an elastic member 3, and a fuel flow channel 4 and an air flow channel 5 arranged on the base 1. Figure 1 and Figure 2 As shown, the nozzle 2 forms a sliding connection with the base 1 along a first direction, and the first direction is parallel to the axis of the nozzle 2. A premixing channel 21 is formed inside the nozzle 2. The elastic member 3 is arranged between the base 1 and the nozzle 2. When in use, the elastic member 3 stores elastic potential energy, and the elastic potential energy makes the nozzle 2 have a tendency to approach the base 1 along the first direction. The fuel flow channel 4 and the air flow channel 5 are arranged on the base 1, and the ends of the fuel flow channel 4 and the air flow channel 5 are both connected to the premixing flow channel 21.

[0046] It should be noted that in the present application, the components or structures used to guide the fluid in the nozzle (for example, the nozzle 2, the premixing flow channel 21, the fuel flow channel 4, and the air flow channel 5, etc.) are defined as the head end and the tail end, wherein the head end refers to the end where the fluid (for example, fuel, air, or mixed gas, etc.) flows into the component or structure, and the tail end refers to the end where the fluid flows out of the component or structure. That is to say, in the nozzle proposed in the embodiment of the present application, the flow direction of the fluid is always from the head end of a component or structure to the tail end when in use.

[0047] It should be clear that in this embodiment, if Figure 2As shown, the fuel beam flowing out of the fuel flow channel 4 and the air beam flowing out of the air flow channel 5 can be mixed inside the premixing flow channel 21 to form a mixed gas, and the formed mixed gas is finally sprayed into the combustion chamber (not shown in the figure) from the end of the premixing flow channel 21 for combustion. The purpose of designing the premixing flow channel 21 is to allow the air beam and the fuel beam to be premixed evenly in the premixing flow channel 21 before flowing into the combustion chamber for combustion, so that the combustion is more complete and the combustion temperature is lower, thereby reducing the amount of pollutants generated. The effective length of the premixing flow channel 21 (that is, Figure 2 The length L) shown in FIG. 1 refers to the length of the premixing flow channel 21 through which the fuel and air flow in and out of the premixing flow channel 21. It is easy to understand that if the effective length of the premixing flow channel 21 is longer, the mixing uniformity of the mixed gas is better; if the effective length of the premixing flow channel 21 is shorter, the mixing uniformity of the mixed gas is worse.

[0048] It should be noted that, in the embodiment of the present application, the elastic member 3 stores elastic potential energy, and the elastic potential energy makes the nozzle 2 have a tendency to approach the base 1 along the first direction. That is to say, in the embodiment of the present application, the elastic member 3 has a tendency to shorten the effective length of the premixing flow channel 21. As can be seen from the foregoing, if the gas turbine is upgraded from a low operating condition to a high operating condition, the amount of fuel will definitely increase, that is, the pressure of the mixed gas formed by the mixture of fuel and air will increase, and further, the mixed gas with increased pressure can overcome the elastic force of the elastic member 3 to push the nozzle 2 to move away from the base 1 along the first direction. If the nozzle 2 moves away from the base 1 along the first direction, the effective length of the premixing flow channel 21 increases, that is, the mixing uniformity of the mixed gas will be better. If the gas turbine is reduced from a high operating condition to a low operating condition, the amount of fuel will definitely decrease, that is, the pressure of the mixed gas formed by the mixture of fuel and air will decrease, and further, under the elastic force of the elastic member 3, the nozzle 2 moves along the first direction toward the base 1. If the nozzle 2 moves along the first direction toward the direction close to the base 1, the effective length of the premixing channel 21 is shortened, that is, the mixing uniformity of the mixed gas will deteriorate. For a mixed gas with poor mixing uniformity, the local gas inside can maintain a high combustion equivalence ratio, so that the gas turbine is not easy to flameout. In addition, when the gas turbine is started, the effective length of the premixing channel 21 is the shortest, and the combustion equivalence ratio of part of the gas in the mixed gas formed by it can be maintained at the highest, so that the mixed gas is easy to ignite, that is, the gas turbine is easy to start. In other words, the nozzle embodiment proposed in the present application can adjust the effective length of the premixing channel based on the actual operating conditions of the gas turbine through an elastic member, thereby obtaining a mixed gas with different mixing uniformities, which can not only make the gas turbine easy to start and not easy to flameout under low operating conditions, but also keep the pollutants generated by the gas turbine under high operating conditions less.

[0049] In the embodiment of the present application, there is no restriction on the shape and structure of the premixing channel 21. For example, the shape and structure of the premixing channel 21 may be similar to the premixing channel disclosed in the patent document with publication number: CN104390235A, title: Premixing swirl service nozzle; and publication number: CN103148514A, title: A two-stage radial lean-burn premixing low-emission gas nozzle. In order to avoid the nozzle from flashback, in one embodiment of the present application, such as Figure 2 As shown, the inner diameter of the premixing channel 21 decreases from its head end to its end. It is easy to understand that if the inner diameter of the premixing channel 21 decreases from its head end to its end, the speed of the mixed gas will increase during the flow of the premixing channel 21, and the mixed gas with increased speed can effectively avoid the occurrence of backfire.

[0050] In order to improve the mixing uniformity of the air beam ejected from the air flow channel 5 and the fuel beam ejected from the fuel flow channel 4, in one embodiment of the present application, Figure 3 and Figure 4 As shown, a plug 41 is provided at the end of the fuel flow channel 4. The plug 41 is provided with a plurality of fuel injection holes 42, each of which is connected to the fuel flow channel 4. When in use, the fuel beam injected from the fuel injection hole 42 intersects with the air beam injected from the air flow channel 5. Specifically, the flow direction of the air beam injected from the air flow channel 5 is as follows: Figure 4 As shown in the direction C in FIG. 1 , the flow direction of the partial fuel beam ejected from the fuel injection hole 42 is as follows: Figure 4 As shown in the direction B in the figure. Since the fuel beam in direction B and the air beam in direction C can intersect and mix, the mixing performance of the fuel beam and the air beam can be improved, that is, the obtained mixed gas can be mixed more evenly. If the mixed gas can be mixed evenly, the amount of pollutants generated during combustion can be reduced.

[0051] In order to further improve the mixing uniformity of the air beam ejected from the air flow channel 5 and the fuel beam ejected from the fuel flow channel 4, in one embodiment of the present application, Figure 2 As shown, the air flow channel 5 may include an air inlet 51, an annular flow channel 52 and a plurality of air spray holes 53. Specifically, the annular flow channel 52 is connected to the air inlet 51. The air spray holes 53 are evenly distributed around the axis of the premixing flow channel 21, and each air spray hole 53 is connected to the annular flow channel 52. Figure 2 As shown, the axis center line of the annular flow channel 52 coincides with the axis center line of the nozzle 2 .

[0052] When in use, the air outside the nozzle first enters the air inlet 51; further, the air in the air inlet 51 enters the annular flow channel 52; further, the air in the annular flow channel 52 enters each air nozzle hole 53. Since each air nozzle hole 53 is evenly distributed around the axis of the premixing flow channel 21, the air entering the premixing flow channel 21 from the outside of the nozzle can be evenly dispersed to all parts of the premixing flow channel 21, that is, the mixing uniformity of the subsequent air beam and fuel beam is improved.

[0053] In order to further improve the mixing uniformity of the air beam ejected from the air flow channel 5 and the fuel beam ejected from the fuel flow channel 4, in one embodiment of the present application, each air injection hole 53 may be a swirl hole. It is easy to understand that if each air injection hole 53 is a swirl hole, the air entering the premixing flow channel 21 can form a swirl, and the swirl air is conducive to improving the mixing uniformity of the air beam and the fuel beam.

[0054] In order to ensure that the mixed gas flowing out of the premixing channel 21 can still be mixed and burned in the combustion chamber to improve the mixing uniformity of the mixed gas and thus reduce the amount of pollutants, in one embodiment of the present application, a swirler 6 is provided at the end of the premixing channel 21. It should be clear that the mixed gas passing through the swirler 6 can form a swirl, which is conducive to further mixing the fuel and air in the mixed gas. In an embodiment of the present application, the rotation direction of the air swirl formed by each air nozzle 53 and the mixed gas swirl formed by the swirler 6 can be opposite. For example, if the air swirl rotates clockwise, the mixed gas swirl can rotate counterclockwise; if the air swirl rotates counterclockwise, the mixed gas swirl can rotate clockwise. If the rotation directions of the air swirl and the mixed gas swirl are opposite, it is more conducive to mixing the fuel and air evenly.

[0055] In the embodiment of the present application, the elastic member 3 may be any elastic component, for example, the elastic member 3 may be an elastic metal sheet or a spring.

[0056] It should be understood that the nozzle 2 is close to the combustion chamber, that is, the nozzle 2 is in a high-temperature use environment. In order to increase the service life of the nozzle 2, in one embodiment of the present application, Figure 5 and Figure 7 As shown, the nozzle 2 may also be provided with a plurality of cooling holes 22 , each cooling hole 22 runs from the head end of the nozzle 2 to the tail end of the nozzle 2 , and each cooling hole 22 is connected to the air flow channel 5 .

[0057] During use, since each cooling hole 22 is connected to the air flow channel 5, the air in the air flow channel 5 can enter the nozzle 2 from the head end of the nozzle 2 and then be ejected from the tail end of the nozzle 2. The air flowing through the nozzle 2 can reduce the temperature of the nozzle 2, thereby increasing the service life of the nozzle 2.

[0058] It should be clear that the combustion equivalence ratio refers to the ratio of the amount of air required for complete combustion of the fuel to the actual amount of air supplied. In this embodiment, when the combustion equivalence ratio is greater than 1, it means that the actual amount of air contained in the mixture is less than the required theoretical amount of air, that is, the amount of air is insufficient; when the combustion equivalence ratio is less than 1, it means that the actual amount of air in the mixture exceeds the required theoretical amount of air, that is, the amount of air is excessive. In order to further improve the combustion equivalence ratio of the mixture at low operating conditions or when the gas turbine is started to avoid flameout or difficulty in starting the gas turbine, in an embodiment of the present application, a control structure can also be provided between the base 1 and the nozzle 2. The control structure is used to adjust the flow area of ​​the air flow channel 5 based on the pressure in the premixing flow channel 21, so that the flow area of ​​the air flow channel 5 changes in a positive correlation with the pressure in the premixing flow channel 21.

[0059] It should be noted that the positive correlation between the flow area of ​​the air flow channel 5 and the pressure in the premixing flow channel 21 means that if the pressure in the premixing flow channel 21 increases, the flow area of ​​the air flow channel 5 also increases; if the pressure in the premixing flow channel 21 decreases, the flow area of ​​the air flow channel 5 also decreases. It is easy to understand that if the flow area of ​​the air flow channel 5 decreases, the amount of air entering the premixing flow channel 21 through the air flow channel 5 will definitely decrease; in the application scenario where the gas turbine is in a low operating condition or when starting, if the amount of air entering the premixing flow channel 21 decreases, the combustion equivalence ratio of the mixed gas will definitely increase, which is conducive to starting the gas turbine or the gas turbine is not easy to shut down.

[0060] In the embodiments of the present application, any suitable structure may be used as the control structure. For example, the control structure may be at least as shown in the following two embodiments.

[0061] Embodiment 1 of the control structure

[0062] In this embodiment, if Figure 5 As shown, the control structure includes an air groove 11 formed in the base 1, and the nozzle 2 is adapted to the air groove 11. Specifically, the nozzle 2 is adapted to the air groove 11, which means that after the nozzle 2 is inserted into the air groove 11 during use, the nozzle 2 can move freely along the first direction, and the air in the air groove 11 will not leak a large amount from the gap between the nozzle 2 and the air groove 11. For example, the air leakage amount can be less than or equal to 20% of the total amount of air in the air groove 11.

[0063] In this embodiment, if Figure 5As shown, the air flow channel 5 includes an air inlet hole 51, at least one control hole 54 and a plurality of air spray holes 53. The air inlet hole 51 is connected to the air slot 11. Each control hole 54 is arranged on the side wall of the air slot 11, and each control hole 54 is connected to the air slot 11. The nozzle 2 covers a part of each control hole 54. Each air spray hole 53 is evenly distributed around the axis of the premixing flow channel 21, and each air spray hole 53 is connected to the control hole 54.

[0064] When in use, the air outside the nozzle first enters the air groove 11 through the air inlet hole 51; further, the air in the air groove 11 enters the control hole 54; further, the air in the control hole 54 can enter the air nozzle hole 53; finally, the air forms an air beam from the air nozzle hole 53 and enters the premixing channel 21.

[0065] It should be clear that in this embodiment, if Figure 5 As shown, since the nozzle 2 covers a portion of each control hole 54, the flow area of ​​the air flow channel 5 depends on the size of the portion of each control hole 54 covered by the nozzle 2. If the nozzle 2 covers a larger portion of the control hole 54, the flow area of ​​the air flow channel 5 is smaller; if the nozzle 2 covers a smaller portion of the control hole 54, the flow area of ​​the air flow channel 5 is larger. Figure 5 It can be seen that if the gas turbine is upgraded from a low operating condition to a high operating condition, the nozzle 2 moves along the first direction away from the base 1, that is, the portion of the nozzle 2 covering the control hole 54 becomes smaller, and the flow area of ​​the air flow channel 5 becomes larger. In other words, the amount of air entering the premixing flow channel 21 increases, and the combustion equivalence ratio of the mixed gas decreases. If the gas turbine is reduced from a high operating condition to a low operating condition, the nozzle 2 moves along the first direction toward the base 1, that is, the portion of the nozzle 2 covering the control hole 54 becomes larger, and the flow area of ​​the air flow channel 5 becomes smaller. In other words, the amount of air entering the premixing flow channel 21 decreases, and the combustion equivalence ratio of the mixed gas increases.

[0066] In order to improve the sensitivity of the flow area control of the air flow channel 5, in one embodiment of the present application, Figure 6 As shown, each control hole 54 is a long strip hole, and the length direction of each control hole 54 is parallel to the first direction. Since the control holes 54 are long strips and extend along the first direction, even if the working condition of the gas turbine changes slightly, that is, the nozzle 2 moves slightly along the first direction, the embodiment of the present application can sensitively adjust the flow area of ​​the air flow channel 5 based on the change of the working condition.

[0067] Embodiment 2 of the control structure

[0068] In this embodiment, if Figure 7As shown in the figure (elastic member 3 is not shown in the figure), the control structure includes at least one trumpet nozzle hole 12 arranged on the base 1, and a conical block 23 corresponding to each trumpet nozzle hole 12. In the embodiment, one end of each trumpet nozzle hole 12 is connected to the air flow channel 5, and the other end of each trumpet nozzle hole 12 is connected to the premixing flow channel 21. Each conical block 23 is arranged on the nozzle 2, and the conical block 23 is adapted to the corresponding trumpet nozzle hole 12. In this embodiment, the conical block 23 is adapted to the corresponding trumpet nozzle hole 12 when used. Figure 8 As shown, a gap d is formed between the conical block 23 and the corresponding trumpet nozzle 12, that is, the air in the air flow channel 5 can enter the premixing flow channel 21 through the gap d. In other words, in this embodiment, if the gap d is smaller, the flow area of ​​the air flow channel 5 is also smaller; if the gap d is larger, the flow area of ​​the air flow channel 5 is also larger. Figure 8 It can be seen that if the gas turbine is upgraded from a low operating condition to a high operating condition, the nozzle 2 moves along the first direction away from the base 1, that is, the gap d becomes larger, and the flow area of ​​the air flow channel 5 becomes larger. In other words, the amount of air entering the premixing flow channel 21 increases, and the combustion equivalence ratio of the mixed gas decreases. If the gas turbine is reduced from a high operating condition to a low operating condition, the nozzle 2 moves along the first direction toward the base 1, that is, the gap d becomes smaller, and the flow area of ​​the air flow channel 5 becomes smaller. In other words, the amount of air entering the premixing flow channel 21 decreases, and the combustion equivalence ratio of the mixed gas increases.

[0069] It should be clear that, through the setting of the control structure of this embodiment, such as Figure 8 As shown, after the air flows out from the gap d, its flow path is as follows Figure 8 As shown in the path E shown, the air can be dispersed in a trumpet shape. In other words, the air flowing out of the control structure is more conducive to mixing and dispersion with the fuel in the premixing channel 21.

[0070] It should be clear that the nozzle embodiment proposed in the present application can adjust the effective length of the premixing flow channel based on the actual operating conditions of the gas turbine through elastic parts, thereby obtaining a mixture with different mixing uniformities, which not only makes the gas turbine easy to start and not easy to stall under low operating conditions, but also can keep the pollutants generated when the gas turbine is under high operating conditions relatively small.

[0071] After introducing the nozzle proposed in the embodiment of the present application, a gas turbine proposed in the present application is introduced below. The gas turbine includes the nozzle described in any one of the above embodiments.

[0072] It should be clear that the nozzle of the gas turbine embodiment proposed in the present application can adjust the effective length of the premixing flow channel through elastic parts based on the actual operating conditions of the gas turbine, thereby obtaining a mixture with different mixing uniformities. This not only makes the gas turbine easy to start and not easy to stall under low operating conditions, but also keeps the pollutants generated when the gas turbine is under high operating conditions relatively low.

[0073] Although the embodiments of the present application have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present application, and that the scope of the present application is defined by the appended claims and their equivalents.

Claims

1. A nozzle, characterized in that: include: Base (1); A nozzle (2) is slidably connected to the base (1) along a first direction; The first direction is parallel to the axis of the nozzle (2); a premixing channel (21) is formed inside the nozzle (2); the inner diameter of the premixing channel (21) decreases from its head end to its tail end; an elastic member (3) disposed between the base (1) and the nozzle (2); when in use, the elastic member (3) stores elastic potential energy, and the elastic potential energy causes the nozzle (2) to have a tendency to approach the base (1) along the first direction; A fuel flow channel (4) and an air flow channel (5) are arranged on the base (1); the ends of the fuel flow channel (4) and the air flow channel (5) are both connected to the premixing flow channel (21).

2. The nozzle according to claim 1, characterized in that A plug (41) is provided at the end of the fuel flow channel (4); the plug (41) is provided with a plurality of fuel injection holes (42), each of which is connected to the fuel flow channel (4); when in use, the fuel beam injected from the fuel injection hole (42) intersects with the air beam injected from the air flow channel 5.

3. The nozzle according to claim 1, characterized in that The air flow channel (5) comprises: Air inlet (51); an annular flow channel (52), the annular flow channel (52) being in communication with the air inlet hole (51); A plurality of air spray holes (53), each of the air spray holes (53) is evenly distributed around the axis of the premixing channel (21), and each of the air spray holes (53) is connected to the annular channel (52).

4. The nozzle according to claim 3, characterized in that Each air spray hole (53) is a swirl hole; and a swirler (6) is provided at the end of the premixing channel (21).

5. The nozzle according to claim 1 or 2, characterized in that: The nozzle (2) is also provided with a plurality of cooling holes (22), each cooling hole (22) extending from the head end of the nozzle (2) to the tail end of the nozzle (2), and each cooling hole (22) is connected to the air flow channel (5).

6. The nozzle according to claim 5, characterized in that A control structure is also provided between the base (1) and the nozzle (2); the control structure is used to adjust the flow area of ​​the air flow channel (5) based on the pressure in the premixing flow channel (21), so that the flow area of ​​the air flow channel (5) changes in a positive correlation with the pressure in the premixing flow channel (21).

7. The nozzle according to claim 6, characterized in that The control structure comprises an air groove (11) formed on the base (1); the nozzle (2) is adapted to the air groove (11); and the air flow channel (5) comprises: An air inlet (51) communicated with the air groove (11); at least one control hole (54); each control hole (54) is arranged on a side wall of the air groove (11), and each control hole (54) is connected to the air groove (11); when in use, the nozzle (2) covers a portion of each control hole (54); A plurality of air spray holes (53), each of the air spray holes (53) is evenly distributed around the axis of the premixing channel (21), and each of the air spray holes (53) is connected to a control hole (54).

8. The nozzle according to claim 7, characterized in that Each control hole (54) is a long strip-shaped hole, and the length direction of each control hole (54) is parallel to the first direction.

9. The nozzle according to claim 6, characterized in that The control structure includes: At least one trumpet nozzle hole (12) is disposed on the base (1); one end of each trumpet nozzle hole (12) is connected to the air flow channel (5), and the other end of each trumpet nozzle hole (12) is connected to the premixing flow channel (21); A conical block (23) corresponding one to each trumpet spray hole (12), the conical block (23) being arranged on the spray pipe (2), and the conical block (23) being adapted to the corresponding trumpet spray hole (12).

10. A gas turbine, characterized in that: Comprising a nozzle as claimed in any one of claims 1 to 9.

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