Gas turbine and combustion system thereof

Abstract

The utility model discloses a gas turbine and a combustion system thereof, and relates to the technical field of gas turbines. The combustion system comprises a gas compressor, a high-low pressure turbine and a power turbine. One end of the first pipeline is communicated with the output end of the gas compressor, and the other end of the first pipeline is communicated with the input end of the high-low pressure turbine; the main combustion chamber is arranged on the first pipeline; one end of the second pipeline is communicated with the output end of the high-low pressure turbine, and the other end of the second pipeline is communicated with the input end of the power turbine; and the auxiliary combustion chamber is arranged on the second pipeline. Through the arrangement of the auxiliary combustion chamber, the amount of fuel entering the main combustion chamber can be reduced, and then power consumption of the fuel in the main combustion chamber due to pressurization is reduced. And meanwhile, the fuel entering the auxiliary combustion chamber does not need higher conveying pressure, so that the energy consumption of the whole fuel pressurization system can be reduced.

Description

Technical Field

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

[0002] Gas turbines used for power generation generally use natural gas or fuel oil as their design fuel. If a gas turbine that uses natural gas or fuel oil (i.e., high calorific value fuel) as fuel is changed to burn medium- and low-calorific value fuel gas (such as hydrogen or methane), the thermal parameters and operating point of the gas turbine will change. For example, if medium- and low-calorific value fuel is used and the same power turbine inlet temperature as natural gas is required, the supply of medium- and low-calorific value fuel gas is greater than the supply of natural gas. In order to supply more medium- and low-calorific value fuel gas, it is necessary to increase the fuel supply pressure of the system, which results in a significant increase in the energy consumption of the fuel boosting system. This is also a major reason why the integrated gasification combined cycle (IGCC) power generation system is not economical. Utility Model Content

[0003] The purpose of the present application is to provide a gas turbine and a combustion system thereof to solve the technical problem of increased fuel supply energy consumption after a gas turbine using high calorific value fuel is switched to medium or low calorific value fuel gas.

[0004] To achieve the above objectives, this application provides the following technical solutions:

[0005] In a first aspect, the present application proposes a technical solution of a combustion system, the combustion system comprising:

[0006] Compressor, high and low pressure turbines and power turbines;

[0007] A first pipeline, one end of which is connected to the output end of the compressor, and the other end of which is connected to the input end of the high-pressure and low-pressure turbines;

[0008] A main combustion chamber, arranged in the first pipeline;

[0009] A second pipeline, one end of which is connected to the output end of the high-pressure and low-pressure turbines, and the other end of which is connected to the input end of the power turbine;

[0010] The auxiliary combustion chamber is arranged in the second pipeline.

[0011] As a specific solution in the technical solution of the present application, a third pipeline is also arranged between the compressor and the high- and low-pressure turbines, one end of the third pipeline is connected to the output end of the compressor, and the other end of the third pipeline is connected to the input end of the high- and low-pressure turbines.

[0012] As a specific solution in the technical solution of the present application, a first air intake regulating device is also provided in the first pipeline, and the first air intake regulating device is used to control the gas flow in the first pipeline.

[0013] As a specific solution in the technical solution of the present application, a fourth pipeline is also arranged between the high and low pressure turbines and the power turbine, one end of the fourth pipeline is connected to the output end of the high and low pressure turbines, and the other end of the fourth pipeline is connected to the input end of the power turbine.

[0014] As a specific solution in the technical solution of the present application, a second air intake regulating device is further provided in the second pipeline, and the second air intake regulating device is used to control the gas flow in the second pipeline.

[0015] As a specific solution in the technical solution of the present application, the compressor, high-pressure and low-pressure turbines and the power turbine are coaxial; or, any two of the compressor, high-pressure and low-pressure turbines and the power turbine are coaxial; or, the axes of the compressor, high-pressure and low-pressure turbines and the power turbine are independent of each other.

[0016] As a specific solution in the technical solution of the present application, it also includes a first fuel boosting device, which is used to provide fuel to the main combustion chamber and the auxiliary combustion chamber.

[0017] As a specific solution in the technical solution of the present application, it also includes a second fuel boosting device and a third fuel boosting device; the second fuel boosting device is used to provide fuel to the main combustion chamber; the third fuel boosting device is used to provide fuel to the auxiliary combustion chamber.

[0018] As a specific solution in the technical solution of the present application, a first water vapor inlet is provided on the fuel supply pipeline of the main combustion chamber; and / or a second water vapor inlet is provided on the fuel supply pipeline of the auxiliary combustion chamber.

[0019] In a second aspect, the present application proposes a technical solution for a gas turbine, which includes a combustion system as described in any one of the first aspects.

[0020] Compared with the prior art, the beneficial effects of this application are:

[0021] The present application can reduce the amount of fuel entering the main combustion chamber by setting up the auxiliary combustion chamber, thereby reducing the power consumption of the main combustion chamber fuel due to supercharging. At the same time, the fuel entering the auxiliary combustion chamber does not need a high delivery pressure, thus reducing the energy consumption of the entire fuel supercharging system. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1A structural schematic diagram of a combustion system proposed in an embodiment of the present application;

[0023] Figure 2 This is a schematic diagram of the structure of another combustion system proposed in an embodiment of the present application.

[0024] In the figure: 1. compressor; 11. first pipeline; 12. third pipeline; 2. high and low pressure turbines; 21. second pipeline; 22. fourth pipeline; 3. power turbine; 4. main combustion chamber; 41. first air intake regulating device; 5. auxiliary combustion chamber; 51. second air intake regulating device; 6. first fuel boosting device; 61. third air intake regulating device; 62. fourth air intake regulating device; 7. second fuel boosting device; 8. third fuel boosting device. DETAILED DESCRIPTION

[0025] 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.

[0026] 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.

[0027] 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.

[0028] It should be noted that similar 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.

[0029] It should be clear that in order to solve the technical problem of increased fuel supply energy consumption after the gas turbine using high calorific value fuel in the background technology is changed to medium and low calorific value fuel gas, the present application proposes an embodiment of a combustion system, which includes a compressor 1, a high and low pressure turbine 2, a power turbine 3, a first pipeline 11, a second pipeline 21, a main combustion chamber 4 and a secondary combustion chamber 5. Among them, if Figure 1 and Figure 2 As shown, one end of the first pipeline 11 is connected to the output end of the compressor 1, and the other end of the first pipeline 11 is connected to the input end of the high-pressure and low-pressure turbines 2. One end of the second pipeline 21 is connected to the output end of the high-pressure and low-pressure turbines 2, and the other end of the second pipeline 21 is connected to the input end of the power turbine 3. The main combustion chamber 4 is arranged in the first pipeline 11; the auxiliary combustion chamber 5 is arranged in the second pipeline 21.

[0030] When using, Figure 1 and Figure 2 As shown, a part of the fuel (which can be a medium-low calorific value fuel or a high calorific value fuel) is injected into the main combustion chamber 4 to participate in the combustion, and another part of the fuel (which can be a medium-low calorific value fuel or a high calorific value fuel) is injected into the auxiliary combustion chamber 5 to participate in the combustion. Different from the prior art, through the setting of the auxiliary combustion chamber 5, it is not necessary for all the fuel to enter the main combustion chamber 4 to participate in the combustion. In other words, it is possible to reduce the amount of fuel entering the main combustion chamber 4, thereby reducing the power consumption of the fuel in the main combustion chamber 4 due to supercharging. At the same time, the fuel entering the auxiliary combustion chamber 5 does not require a high delivery pressure, so the energy consumption of the entire fuel supercharging system can be reduced.

[0031] Depend on Figure 1 and Figure 2 It can be seen that, since the auxiliary combustion chamber 5 is located before the power turbine 3, the auxiliary combustion chamber 5 can greatly increase the inlet temperature of the power turbine 3, thereby improving the output power and efficiency of the whole machine. In other words, in the application scenario where the combustion system switches from high calorific value fuel to medium and low calorific value fuel gas, the inlet temperature of the power turbine 3 can also meet the design requirements without significantly increasing the fuel supply pressure.

[0032] It should be clear that due to the reduction of fuel entering the main combustion chamber 4, the inlet temperature of the main combustion chamber 4 and the high and low pressure turbines 2 is relatively reduced. Compared with the method of increasing the supply pressure of the fuel in the main combustion chamber 4 and then increasing the inlet temperature of the power turbine 3, the embodiment of the combustion system proposed in the embodiment of the present application can extend the service life of each component in the main combustion chamber 4 and the high and low pressure turbines 2. Due to the decrease in operating temperature, the moving blades and stator blades in the main combustion chamber 4 and the high and low pressure turbines 2 can also adopt relatively simple manufacturing processes and structures or select materials with relatively low temperature resistance, so as to reduce the manufacturing cost of the equipment.

[0033] During the combustion process in the main combustion chamber 4, the amount of compressed air required in the main combustion chamber 4 depends on the amount of fuel in the main combustion chamber 4. Generally, the amount of compressed air generated by the compressor 1 is greater than the amount of compressed air required during the combustion in the main combustion chamber 4. In order to utilize all the compressed air in the compressor 1, in one embodiment of the present application, Figure 1 and Figure 2As shown, a third pipeline 12 is further provided between the compressor 1 and the high- and low-pressure turbines 2 , one end of the third pipeline 12 is connected to the output end of the compressor 1 , and the other end of the third pipeline 12 is connected to the input end of the high- and low-pressure turbines 2 .

[0034] When using, Figure 1 and Figure 2 As shown, part of the compressed air generated by the compressor 1 enters the main combustion chamber 4 through the first pipeline 11 to participate in combustion, and the other part enters the high-pressure and low-pressure turbines 2 through the third pipeline 12. The compressed air entering the high-pressure and low-pressure turbines 2 can not only reduce the outlet temperature of the main combustion chamber 4, but also drive the high-pressure and low-pressure turbines 2 to perform work.

[0035] In the embodiment of the present application, the ratio of compressed air entering the main combustion chamber 4 and the third pipeline 12 can be controlled based on the structure of the first pipeline 11 and the third pipeline 12. It is easy to understand that the pressure of the compressed air in the first pipeline 11 and the third pipeline 12 is consistent. That is to say, in this embodiment, the ratio of compressed air entering the main combustion chamber 4 and the third pipeline 12 can be controlled by designing the flow path cross-sectional area of ​​the first pipeline 11 and the third pipeline 12.

[0036] In order to be able to adjust the compressed air entering the main combustion chamber 4 in real time according to the actual combustion situation, in one embodiment of the present application, Figure 1 and Figure 2 As shown, a first air intake regulating device 41 is further provided in the first pipeline 11 , and the first air intake regulating device 41 is used to control the gas flow entering the main combustion chamber 4 .

[0037] It is easy to understand that the amount of compressed air generated by the general compressor 1 during stable operation is fixed, and the amount of compressed air generated by the compressor 1 is equal to the sum of the compressed air entering the main combustion chamber 4 and the third pipeline 12. Therefore, when the compressor 1 is in stable operation, if the amount of compressed air entering the main combustion chamber 4 increases, the amount of compressed air entering the third pipeline 12 decreases; if the amount of compressed air entering the main combustion chamber 4 decreases, the amount of compressed air entering the third pipeline 12 increases. In other words, by setting the first air intake regulating device 41, it is possible to achieve real-time adjustment of the amount of compressed air entering the main combustion chamber 4 and the third pipeline 12 based on the actual combustion conditions of the main combustion chamber 4. By controlling the amount of compressed air entering the main combustion chamber 4 and the third pipeline 12, the temperature of the main combustion chamber 4 and the inlet of the high and low pressure turbine 2 is controlled.

[0038] In the embodiment of the present application, the first air intake regulating device 41 may be any device capable of controlling the flow of a fluid. For example, the first air intake regulating device 41 may be a flow control valve or an opening control valve. It should be noted that the second air intake regulating device 51, the third air intake regulating device 61, and the fourth air intake regulating device 62 described below are also the same, and will not be described in detail later.

[0039] Depend on Figure 1 and Figure 2 It can be seen that the high-temperature combustion gas formed by the combustion in the main combustion chamber 4 and the compressed air in the third pipeline 12 are mixed to form a high-temperature mixed gas, which enters the high-pressure and low-pressure turbines 2 through the first pipeline 11 and drives the high-pressure and low-pressure turbines 2 to perform work. The exhaust gas of the high-pressure and low-pressure turbines 2 enters the auxiliary combustion chamber 5 through the second pipeline 21, and mixes with the fuel in the auxiliary combustion chamber 5 to participate in combustion again. In order to ensure that the fuel in the auxiliary combustion chamber 5 can be burned normally and adjust the inlet temperature of the power turbine 3, as shown in FIG. Figure 1 and Figure 2 As shown, a fourth pipeline 22 is also arranged between the high- and low-pressure turbines 2 and the power turbine 3 , one end of the fourth pipeline 22 is connected to the output end of the high- and low-pressure turbines 2 , and the other end of the fourth pipeline 22 is connected to the input end of the power turbine 3 .

[0040] When in use, part of the high-temperature mixed gas inside the high-pressure and low-pressure turbines 2 first enters the auxiliary combustion chamber 5 through the second pipeline 21 and then flows into the power turbine 3, and the other part of the high-temperature mixed gas directly enters the power turbine 3 through the fourth pipeline 22. The high-temperature mixed gas entering the power turbine 3 can drive the power turbine 3 to perform work.

[0041] In order to control the amount of high-temperature mixed gas entering the auxiliary combustion chamber 5 based on the combustion condition of the auxiliary combustion chamber 5, in one embodiment of the present application, Figure 1 and Figure 2 As shown, a second air intake regulating device 51 is further provided in the second pipeline 21 , and the second air intake regulating device 51 is used to control the gas flow in the second pipeline 21 .

[0042] In the embodiment of the present application, the compressor 1, the high-pressure and low-pressure turbines 2 and the power turbine 3 can be coaxial, and then work can be performed externally. It is also possible that any two of the compressor 1, the high-pressure and low-pressure turbines 2 and the power turbine 3 are coaxial, and then work can be performed externally. It is also possible that the axes of the compressor 1, the high-pressure and low-pressure turbines 2 and the power turbine 3 are independent of each other, that is, the three are not coaxial, and then work can be performed externally separately.

[0043] In the embodiment of the present application, any device can be used to supply fuel to the main combustion chamber 4 and the auxiliary combustion chamber 5. For example, in one embodiment of the present application, Figure 1As shown, the combustion system further includes a first fuel boosting device 6. The first fuel boosting device 6 is used to simultaneously supply fuel to the main combustion chamber 4 and the secondary combustion chamber 5. When in use, the first fuel boosting device 6 can deliver fuel to both the main combustion chamber 4 and the secondary combustion chamber 5. In order to be able to control the amount of fuel in the main combustion chamber 4 and the secondary combustion chamber 5, as shown in FIG. Figure 1 As shown, a third air intake regulating device 61 is provided between the first fuel boosting device 6 and the main combustion chamber 4, and a fourth air intake regulating device 62 is provided between the first fuel boosting device 6 and the secondary combustion chamber 5. The third air intake regulating device 61 is used to control the amount of fuel entering the main combustion chamber 4, and the fourth air intake regulating device 62 is used to control the amount of fuel entering the secondary combustion chamber 5. It should be understood that since the fuel supply pressures required by the main combustion chamber 4 and the secondary combustion chamber 5 are different, in this embodiment, the first fuel boosting device 6 can be a device with two different fuel pressure supply output ends. For example, the first fuel boosting device 6 can be a dual-output motor pump or a dual-output hydraulic pump. In another embodiment of the present application, Figure 2 As shown, the combustion system also includes a second fuel boosting device 7 and a third fuel boosting device 8; the second fuel boosting device 7 is used to provide fuel to the main combustion chamber 4; the third fuel boosting device 8 is used to provide fuel to the auxiliary combustion chamber 5.

[0044] It should be clear that the combustion speed of medium and low calorific value fuel gas is faster than that of high calorific value fuel. If the combustion speed of the fuel is too fast, it is easy to burn the combustion chamber. In order to protect the main combustion chamber 4, in one embodiment of the present application, a first water vapor inlet (not shown in the figure) can be set on the fuel supply pipeline of the main combustion chamber 4 so that water vapor is mixed with fuel and enters the combustion chamber for combustion. When in use, water vapor is injected into the fuel supply pipeline of the main combustion chamber 4 through the first water vapor inlet to prevent the main combustion chamber 4 from being burned. It is easy to understand that in another embodiment of the present application, a second water vapor inlet can also be set in the fuel supply pipeline of the auxiliary combustion chamber 5. When in use, water vapor is injected into the auxiliary combustion chamber 5 through the second water vapor inlet. A third water vapor inlet can also be set on the main combustion chamber 4 to absorb the heat generated during the combustion of the fuel and increase the output power of the high and low pressure turbines 2.

[0045] It should be clear that in the embodiment of the combustion system proposed in the present application, the amount of fuel entering the main combustion chamber can be reduced by setting the auxiliary combustion chamber, thereby reducing the power consumption of the main combustion chamber fuel due to supercharging. At the same time, the fuel entering the auxiliary combustion chamber does not need a high delivery pressure, so the energy consumption of the entire fuel supercharging system can be reduced. After experimental verification, compared with the prior art, the embodiment of the present application reduces the fuel supply energy consumption by at least 50%. Through the setting of the auxiliary combustion chamber, the inlet temperature of the power turbine can also be greatly increased, thereby increasing the overall output power of the system. At the same time, water vapor also works in the high and low pressure turbines and the power turbine. After experimental verification, compared with the prior art, the embodiment of the present application can increase the output power by about 15%. Through the setting of the auxiliary combustion chamber, the service life of each component in the main combustion chamber and the high and low pressure turbines can be effectively improved. After experimental verification, compared with the prior art, the embodiment of the present application can increase the life of the moving blades and stator blades in the high and low pressure turbines by about 20%.

[0046] After introducing the embodiment of the combustion system proposed in the present application, an embodiment of a gas turbine proposed in the present application is introduced below. The gas turbine includes the combustion system proposed in any one of the above embodiments.

[0047] Since the gas turbine in the embodiment of the present application includes the combustion system proposed above, the gas turbine can reduce the amount of fuel entering the main combustion chamber through the provision of the auxiliary combustion chamber, thereby reducing the supply pressure of the fuel in the main combustion chamber. Since the fuel entering the auxiliary combustion chamber does not require a high delivery pressure, the energy consumption of the entire fuel boosting system can be reduced. Through the provision of the auxiliary combustion chamber, the inlet temperature of the power turbine can also be greatly increased, thereby increasing the overall output power of the system. Through the provision of the auxiliary combustion chamber, the service life of each component in the main combustion chamber and the high and low pressure turbines can be effectively increased.

[0048] 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 combustion system, characterized in that: include: A compressor (1), a high-pressure and low-pressure turbine (2) and a power turbine (3); A first pipeline (11), one end of which is connected to the output end of the compressor (1), and the other end of which is connected to the input end of the high-pressure and low-pressure turbines (2); A main combustion chamber (4) is arranged in the first pipeline (11); A second pipeline (21), one end of which is connected to the output end of the high- and low-pressure turbines (2), and the other end of which is connected to the input end of the power turbine (3); The auxiliary combustion chamber (5) is arranged in the second pipeline (21).

2. The combustion system according to claim 1, characterized in that: A third pipeline (12) is also provided between the compressor (1) and the high- and low-pressure turbines (2); one end of the third pipeline (12) is connected to the output end of the compressor (1), and the other end of the third pipeline (12) is connected to the input end of the high- and low-pressure turbines (2).

3. The combustion system according to claim 2, characterized in that: A first air intake regulating device (41) is also provided in the first pipeline (11), and the first air intake regulating device (41) is used to control the gas flow in the first pipeline (11).

4. The combustion system according to claim 1, characterized in that: A fourth pipeline (22) is also provided between the high- and low-pressure turbines (2) and the power turbine (3); one end of the fourth pipeline (22) is connected to the output end of the high- and low-pressure turbines (2), and the other end of the fourth pipeline (22) is connected to the input end of the power turbine (3).

5. The combustion system according to claim 4, characterized in that: A second air intake regulating device (51) is also provided in the second pipeline (21), and the second air intake regulating device (51) is used to control the gas flow in the second pipeline (21).

6. The combustion system according to any one of claims 1 to 5, characterized in that: The compressor (1), the high-pressure and low-pressure turbines (2) and the power turbine (3) are coaxial; or any two of the compressor (1), the high-pressure and low-pressure turbines (2) and the power turbine (3) are coaxial; or the axes of the compressor (1), the high-pressure and low-pressure turbines (2) and the power turbine (3) are independent of each other.

7. The combustion system according to any one of claims 1 to 5, characterized in that: It also includes a first fuel pressure boosting device (6), which is used to provide fuel to the main combustion chamber (4) and the auxiliary combustion chamber (5).

8. The combustion system according to any one of claims 1 to 5, characterized in that: It also includes a second fuel boosting device (7) and a third fuel boosting device (8); the second fuel boosting device (7) is used to supply fuel to the main combustion chamber (4); and the third fuel boosting device (8) is used to supply fuel to the secondary combustion chamber (5).

9. The combustion system according to any one of claims 1 to 5, characterized in that: A first water vapor inlet is provided on the fuel supply pipeline of the main combustion chamber (4); and / or a second water vapor inlet is provided on the fuel supply pipeline of the auxiliary combustion chamber (5).

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

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