A gas turbine fuel supply system and method thereof

Abstract

The application discloses a gas turbine fuel supply system and a method thereof, and relates to the technical field of gas turbines. The gas turbine fuel supply system comprises a main fuel pipeline, a plurality of fuel annular pipes, a plurality of sub-fuel pipelines corresponding to the fuel annular pipes one by one, a first end of each sub-fuel pipeline being in communication with the main fuel pipeline, a second end of each sub-fuel pipeline being in communication with a corresponding fuel annular pipe, a first control assembly for at least controlling the on-off of the main fuel pipeline, and a second control assembly corresponding to the sub-fuel pipelines one by one for at least controlling the fuel flow of a corresponding sub-fuel pipeline. The application realizes the control of the amount of fuel delivered by the second control assembly into the combustion chamber through the sub-fuel pipelines corresponding to the fuel annular pipes one by one and the second control assembly corresponding to the sub-fuel pipelines one by one.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of gas turbines, in particular to a gas turbine fuel supply system and method thereof. BACKGROUND

[0002] With the continuous enhancement of public environmental awareness, the market's requirements for gas turbine pollutant emissions are increasingly high, that is, the emissions of flue gas NOx and CO in the energy combustion process are increasingly strict. In the present situation of high dependence on fossil energy for large-scale power generation and power driving, reducing the generation of pollutants in the fuel combustion process has become a top priority. In order to meet the low emission of pollutants, low emission combustion technology is one of the technical problems that gas turbines must overcome. The relatively mature low emission combustion technology at present is the staged combustion technology using lean oil premixing. It should be noted that staged combustion refers to the supply of air and fuel required for combustion to different parts of the combustion process to control the combustion temperature and reduce pollutant emissions.

[0003] It should be noted that the gas turbine needs to supply fuel into the combustion chamber through the nozzle. In the prior art, in order to realize staged combustion, a plurality of flow channels are arranged in the nozzle. The flow channels correspond one by one to the regions in the combustion chamber where fuel needs to be supplied. The main fuel pipeline of the gas turbine is directly connected with the nozzle, and the main fuel pipeline can deliver fuel to the corresponding regions of the combustion chamber through the flow channels in the nozzle. It is easy to understand that under the condition of the same fluid pressure, the fluid delivery amount is in direct proportion to the flow path of the flow channel, that is, by controlling the flow path of each flow channel in the nozzle, the corresponding content of fuel can be delivered to different regions of the combustion chamber. It can be seen that in this way, the fuel supplied to the combustion chamber has a basically consistent fuel ratio in different regions of the combustion chamber within the full operating range of the gas turbine. If the fuel in the combustion chamber can only be maintained at a certain ratio, then during the process of improving the operating conditions of the gas turbine, either fuel shortage will occur, resulting in backfire and oscillating combustion, or too much fuel will occur, resulting in insufficient combustion, too high combustion temperature, and increased emissions of pollutants. SUMMARY

[0004] The purpose of the present application is to provide a gas turbine fuel supply system and method thereof to solve the technical problem that the fuel ratio in different regions of the combustion chamber cannot be adjusted in the prior art.

[0005] To achieve the above-mentioned purpose, the present application provides the following technical solutions:

[0006] In a first aspect, the technical scheme of the present application provides a gas turbine fuel supply system, which comprises: a main fuel pipeline; a plurality of fuel annular pipes; a plurality of sub-fuel pipelines corresponding to the fuel annular pipes one by one, a first end of each sub-fuel pipeline being in communication with the main fuel pipeline, and a second end of each sub-fuel pipeline being in communication with a corresponding fuel annular pipe; a first control assembly used at least for controlling the opening and closing of the main fuel pipeline; and a second control assembly corresponding to the sub-fuel pipelines one by one and used at least for controlling the fuel flow of a corresponding sub-fuel pipeline.

[0007] As a specific scheme in the technical scheme of the present application, the technical scheme further comprises a diffusion assembly used for diffusing gas in the main fuel pipeline, wherein the diffusion assembly comprises: a diffusion pipeline, a first end of the diffusion pipeline being in communication with the main fuel pipeline; a first stop valve and a first quick cut-off valve arranged in the diffusion pipeline and used for controlling the opening and closing of the diffusion pipeline; and the first stop valve and the first quick cut-off valve are arranged in a first direction in sequence, and the first direction is from a second end of the diffusion pipeline to the first end of the diffusion pipeline.

[0008] As a specific scheme in the technical scheme of the present application, the technical scheme further comprises a purge assembly used for purging gas in the gas turbine fuel supply system, wherein the purge assembly comprises: a purge pipeline in communication with the main fuel pipeline; and a second stop valve arranged in the purge pipeline and used for controlling the opening and closing of the purge pipeline.

[0009] As a specific scheme in the technical scheme of the present application, the first control assembly comprises a second quick cut-off valve arranged in the main fuel pipeline.

[0010] As a specific scheme in the technical scheme of the present application, the first control assembly further comprises a third stop valve arranged in the main fuel pipeline, and the third stop valve and the second quick cut-off valve are arranged in a second direction in sequence, and the second direction is parallel to the fuel flow direction in the main fuel pipeline.

[0011] As a specific scheme in the technical scheme of the present application, the first control assembly further comprises a first pressure sensor and a temperature sensor arranged in the main fuel pipeline, the first pressure sensor and the temperature sensor are located between the third stop valve and the second quick cut-off valve, and the first pressure sensor and the temperature sensor are electrically connected with the second quick cut-off valve respectively.

[0012] As a specific scheme in the technical scheme of the present application, the second control assembly comprises an adjusting valve arranged in the sub-fuel pipeline.

[0013] As a specific solution of the technical scheme in the application, the second control assembly further comprises a quick cut-off valve arranged in the fuel distribution pipeline, and the quick cut-off valve and the regulating valve are sequentially arranged along a third direction, and the third direction is from the first end of the fuel distribution pipeline to the second end.

[0014] As a specific solution of the technical scheme in the application, the second control assembly further comprises two pressure sensors arranged in the fuel distribution pipeline, one of the pressure sensors is arranged between the quick cut-off valve and the regulating valve, and the pressure sensor is electrically connected with the quick cut-off valve; and the other pressure sensor is arranged between the regulating valve and the fuel annular pipeline, and the pressure sensor is electrically connected with the regulating valve.

[0015] In a second aspect, the technical scheme of the application provides a gas turbine fuel supply method, and the method comprises:

[0016] obtaining first data and a target working state of the gas turbine;

[0017] obtaining a current working state of the gas turbine based on the first data;

[0018] controlling the fuel supply amount of each region in the combustion chamber based on the current working state and the target working state of the gas turbine, so that the gas turbine reaches the target working state.

[0019] Compared with the prior art, the technical scheme of the application has the following beneficial effects:

[0020] Through the arrangement of the plurality of fuel distribution pipelines corresponding to the fuel annular pipeline and the second control assembly corresponding to the fuel distribution pipeline, the amount of fuel delivered by the fuel distribution pipeline to the combustion chamber can be controlled through the second control assembly. That is, the application can adjust the amount of fuel burned in each stage of the combustion chamber based on the working state of the gas turbine, so that the stability of the combustion can be ensured and the flame temperature can be reduced to achieve low emission of pollutants in different working conditions of the gas turbine. BRIEF DESCRIPTION OF DRAWINGS

[0021] Figure 1 FIG. 1 is a structural schematic diagram of a gas turbine fuel supply system according to an embodiment of the application;

[0022] Figure 2 FIG. 2 is a flowchart of a gas turbine fuel supply method according to an embodiment of the application;

[0023] Figure 3 FIG. 3 is a flowchart of the gas turbine from the shutdown state to the warm-up state according to an embodiment of the application;

[0024] Figure 4Flow chart for the gas turbine to be raised from the warm state to the low working condition state according to the embodiment of the present application;

[0025] Figure 5 Flow chart for the gas turbine to be raised from the low working condition state to the high working condition state according to the embodiment of the present application.

[0026] In the figure: 2, main fuel pipeline; 21, third stop valve; 22, first pressure sensor; 23, temperature sensor; 24, second quick cut-off valve; 3, blow-off pipeline; 31, first stop valve; 32, first quick cut-off valve; 4, purge pipeline; 41, second stop valve; 5, first sub-fuel pipeline; 51, third quick cut-off valve; 52, second pressure sensor; 53, first regulating valve; 54, third pressure sensor; 6, second sub-fuel pipeline; 61, fourth quick cut-off valve; 62, fourth pressure sensor; 63, second regulating valve; 64, fifth pressure sensor; 7, third sub-fuel pipeline; 71, fifth quick cut-off valve; 72, sixth pressure sensor; 73, third regulating valve; 74, seventh pressure sensor; 81, first fuel annular pipe; 82, second fuel annular pipe; 83, third fuel annular pipe. DETAILED DESCRIPTION

[0027] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0028] It should be noted that, in the description of the present application, the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0029] In addition, it should be understood that, for the convenience of description, the sizes of various components shown in the drawings are not drawn in accordance with the actual proportional relationship, for example, the thickness or width of certain layers can be exaggerated relative to other layers.

[0030] It should be noted that similar reference numbers and letters represent similar items in the following drawings, and therefore, once an item is defined or described in one drawing, it will not need to be further specifically discussed and described in the description of subsequent drawings.

[0031] To solve the technical problems in the background art, as shown in the background Figure 1 The present application proposes an embodiment of a gas turbine fuel supply system, specifically, the gas turbine fuel supply system comprises: a plurality of fuel annular pipes, a main fuel pipeline 2, a plurality of sub-fuel pipelines corresponding to the fuel annular pipes one by one, a first control assembly, and a second control assembly corresponding to the sub-fuel pipelines one by one. Wherein, the first end of each sub-fuel pipeline is in communication with the main fuel pipeline 2, and the second end of each sub-fuel pipeline is in communication with the corresponding fuel annular pipe. The first control assembly is at least used for controlling the on-off of the main fuel pipeline 2. The second control assembly corresponding to the sub-fuel pipeline is at least used for controlling the fuel flow of the corresponding sub-fuel pipeline.

[0032] Specifically, the fuel annular pipe mainly presents an annular pipe structure, which is used to connect a plurality of nozzles so that each nozzle can be distributed in a ring shape in the combustion chamber. Since the fuel annular pipe is a mature prior art, it will not be described in detail in the embodiments of the present application. It should be clear that in the prior art gas turbine, only one fuel annular pipe is generally provided, and in the embodiments of the present application, the number of fuel annular pipes needs to be determined based on the flow channel type of staged combustion. That is, in the embodiments of the present application, at least two fuel annular pipes need to be provided.

[0033] Specifically, since there are various types of staged combustion gas turbines, it is difficult for the present application to enumerate all types of staged combustion gas turbines. Hereinafter, the application scenarios of the gas turbine having a pre-combustion stage flow channel, a diffusion stage flow channel and a main combustion stage flow channel will be taken as an example to describe the embodiments of the present application. As known from the foregoing, if the gas turbine has a pre-combustion stage flow channel, a diffusion stage flow channel and a main combustion stage flow channel, as shown in Figure 1 The gas turbine fuel supply system needs to include a first fuel annular pipe 81 corresponding to the pre-combustion stage flow channel, a second fuel annular pipe 82 corresponding to the diffusion stage flow channel, and a third fuel annular pipe 83 corresponding to the main combustion stage flow channel.

[0034] It is easy to understand that in the embodiments of the present application, the pre-combustion stage flow channel, the diffusion stage flow channel and the main combustion stage flow channel can be respectively formed in one nozzle. When installing, the first fuel annular pipe 81 can be connected with the pre-combustion stage flow channel in the nozzle, the second fuel annular pipe 82 can be connected with the diffusion stage flow channel in the nozzle, and the third fuel annular pipe 83 can be connected with the main combustion stage flow channel in the nozzle. In other embodiments of the present application, three nozzles can be provided, which are respectively a pre-combustion stage nozzle, a diffusion stage nozzle and a main combustion stage nozzle, that is, the pre-combustion stage flow channel is formed in the pre-combustion stage nozzle, the diffusion stage flow channel is formed in the diffusion stage nozzle, and the main combustion stage flow channel is formed in the main combustion stage nozzle. When installing, the first fuel annular pipe 81 can be connected with the pre-combustion stage nozzle, the second fuel annular pipe 82 can be connected with the diffusion stage nozzle, and the third fuel annular pipe 83 can be connected with the main combustion stage nozzle.

[0035] It needs to be clear that through the multiple fuel distribution pipes corresponding to the fuel annular pipes and the second control assembly corresponding to the fuel distribution pipes, the embodiments of the present application can control the amount of fuel delivered by the fuel distribution pipes to the combustion chamber through the second control assembly. That is, the embodiments of the present application can adjust the amount of fuel for combustion at each stage in the combustion chamber based on the working state of the gas turbine, so that the gas turbine can ensure the stability of combustion and reduce the flame temperature in different working conditions, and realize low emission of pollutants.

[0036] In order to ensure the safety of the gas turbine after shutdown, in the embodiments of the present application, the fuel supply system of the gas turbine can further include a diffusion assembly for venting the gas in the main fuel pipe 2. It is easy to understand that in one embodiment of the present application, as shown in Figure 1 , the diffusion assembly can include a diffusion pipe 3, and the first end of the diffusion pipe 3 is connected with the main fuel pipe 2. That is, after the gas turbine is shut down, the combustible gas in the main fuel pipe 2 can be discharged through the diffusion pipe 3 to reduce the safety hazard. In order to be able to control the on-off of the diffusion pipe 3, in one embodiment of the present application, as shown in Figure 1 , the diffusion assembly can further include a first quick cut-off valve 32 arranged in the diffusion pipe 3, and the first quick cut-off valve 32 is used to control the on-off of the diffusion pipe 3. In order to avoid the first quick cut-off valve 32 from failing to cut off the diffusion pipe 3 and causing a safety accident, in another embodiment of the present application, as shown in Figure 1As shown, the dispersing assembly can further include a first stop valve 31 arranged in the dispersing pipeline 3, and the first stop valve 31 is also used to control the opening and closing of the dispersing pipeline 3. Moreover, the first stop valve 31 and the first quick cut-off valve 32 are arranged in a first direction in sequence, and the first direction is from the second end of the dispersing pipeline 3 to the first end of the dispersing pipeline 3. If the first quick cut-off valve 32 fails, the first stop valve 31 can be used to cut off the dispersing pipeline 3.

[0037] It should be noted that, in the above-mentioned embodiments, the dispersing assembly is mainly based on the fact that the gas pressure in the main fuel pipeline 2 is greater than the gas pressure in the dispersing pipeline 3, so that the gas in the main fuel pipeline 2 can be discharged along the dispersing pipeline 3. In other embodiments of the present application, in order to reduce the gas pressure in the dispersing pipeline 3, the dispersing assembly can further include a pump, which is used to suck the gas in the dispersing pipeline 3, so as to reduce the gas pressure in the dispersing pipeline 3.

[0038] In order to ensure the safety of the gas turbine before starting or after stopping, in the embodiments of the present application, the gas turbine fuel supply system can further include a purging assembly for purging the gas in the gas turbine fuel supply system. In the embodiments of the present application, as shown in the drawings, Figure 1 The purging assembly includes a purging pipeline 4. As known from the foregoing, since the main fuel pipeline 2 can be connected with all other pipelines in the gas turbine fuel supply system, in order to realize that the purging pipeline 4 can purge all pipelines in the gas turbine fuel supply system proposed in the embodiments of the present application, as shown in the drawings, Figure 1 The purging pipeline 4 can be connected with the main fuel pipeline 2.

[0039] Specifically, before the gas turbine starts or after the gas turbine stops, the gas in the main fuel pipeline 2, the dispersing pipeline 3 and each branch fuel pipeline can be replaced by a protective gas through the purging pipeline 4, so as to ensure the safety of the gas turbine fuel supply system. In the embodiments of the present application, the type of the protective gas is not limited, which can be nitrogen or inert gas.

[0040] In order to be able to control the opening and closing of the purging pipeline 4, in an embodiment of the present application, as shown in the drawings, Figure 1 The purging assembly can further include a second stop valve 41 arranged in the purging pipeline 4, and the second stop valve 41 is used to control the opening and closing of the purging pipeline 4. It is easy to understand that, in order to be able to control the opening and closing of the purging pipeline 4 more safely, a quick cut-off valve can also be arranged on the purging pipeline 4.

[0041] As can be seen from the above, the first control assembly is mainly used for controlling the opening and closing of the main fuel pipeline 2. It is easy to understand that the first control assembly can be any valve or switch capable of controlling the opening and closing of the pipeline. In an embodiment of the present application, as shown in Figure 1 the first control assembly can include a second quick cut-off valve 24 arranged in the main fuel pipeline 2.

[0042] In an embodiment of the present application, the second quick cut-off valve 24 can be controlled in any control mode, for example: manual control, electric control or pneumatic control, etc. In order to quickly cut off the main fuel pipeline 2 when the gas turbine works abnormally, in an embodiment of the present application, the second quick cut-off valve 24 is electrically controlled, and the first control assembly can further include a first pressure sensor 22 and a temperature sensor 23 arranged in the main fuel pipeline 2. The first pressure sensor 22 and the temperature sensor 23 are electrically connected to the second quick cut-off valve 24, respectively. The first pressure sensor 22 is used to monitor the fuel pressure in the main fuel pipeline 2, and the temperature sensor 23 is used to monitor the fuel temperature in the main fuel pipeline 2. If the fuel pressure or temperature in the main fuel pipeline 2 is abnormal, the main fuel pipeline 2 is cut off through the second quick cut-off valve 24.

[0043] In order to ensure the effectiveness of cutting off the main fuel pipeline 2, in an embodiment of the present application, as shown in Figure 1 the first control assembly can further include a third stop valve 21 arranged in the main fuel pipeline 2, the third stop valve 21 and the second quick cut-off valve 24 are arranged in the second direction in sequence, and the second direction is parallel to the fuel flow direction in the main fuel pipeline 2. The first pressure sensor 22 and the temperature sensor 23 are located between the third stop valve 21 and the second quick cut-off valve 24. By arranging the third stop valve 21, if the second quick cut-off valve 24 fails, the main fuel pipeline 2 can still be cut off through the third stop valve 21 to improve the fault tolerance rate of cutting off the main fuel pipeline 2.

[0044] As can be seen from the above, the second control assembly is mainly used for controlling the fuel flow of the corresponding sub-fuel pipeline. It is easy to understand that in an embodiment of the present application, the second control assembly can be any valve or switch capable of controlling the flow of the pipeline. In an embodiment of the present application, the second control assembly includes a regulating valve arranged in the sub-fuel pipeline. As shown in Figure 1 in a specific embodiment of the present application, the sub-fuel pipeline includes a first sub-fuel pipeline 5, a second sub-fuel pipeline 6 and a third sub-fuel pipeline 7; and the second control assembly includes a first regulating valve 53 arranged in the first sub-fuel pipeline 5, a second regulating valve 63 arranged in the second sub-fuel pipeline 6 and a third regulating valve 73 arranged in the third sub-fuel pipeline 7.

[0045] In order to quickly control the on-off of each sub-fuel pipeline, in an embodiment of the present application, the second control assembly can further include a quick cut-off valve arranged in the sub-fuel pipeline. That is, in the embodiment of the present application, the on-off of the sub-fuel pipeline can be quickly controlled through the quick cut-off valve. In the embodiment of the present application, the quick cut-off valve and the regulating valve are sequentially arranged along a third direction, and the third direction is from the first end to the second end of the sub-fuel pipeline. That is, the quick cut-off valve on the sub-fuel pipeline is closer to the main fuel pipeline 2, and if the fuel supply in the main fuel pipeline 2 is abnormal, the quick cut-off valve can quickly cut off the sub-fuel pipeline. As shown in Figure 1 In a specific embodiment of the present application, a third quick cut-off valve 51 is arranged in the first sub-fuel pipeline 5, a fourth quick cut-off valve 61 is arranged in the second sub-fuel pipeline 6, and a fifth quick cut-off valve 71 is arranged in the third sub-fuel pipeline 7.

[0046] In order to further ensure the safety of each sub-fuel pipeline and accurately control the fuel flow in each sub-fuel pipeline, in the embodiment of the present application, the second control assembly further includes two pressure sensors arranged in the sub-fuel pipeline. One of the pressure sensors is arranged between the quick cut-off valve and the regulating valve, and the pressure sensor is electrically connected with the quick cut-off valve. Specifically, the pressure sensor is used to measure the fuel pressure of the sub-fuel pipeline, and if the fuel pressure is abnormal, the sub-fuel pipeline is cut off through the quick cut-off valve to ensure the safety of the sub-fuel pipeline. The other pressure sensor is arranged between the regulating valve and the fuel annular pipe, and the pressure sensor is electrically connected with the regulating valve. That is, in the embodiment of the present application, a pressure sensor is arranged before and after the regulating valve in each sub-fuel pipeline, and the regulating valve can accurately control the fuel flow in the sub-fuel pipeline based on the data of the two pressure sensors.

[0047] In a specific embodiment of the present application, as shown in Figure 1As shown, the first fuel branch pipeline 5 is provided with a second pressure sensor 52 and a third pressure sensor 54, the second pressure sensor 52 is located between the third quick cut-off valve 51 and the first regulating valve 53, and the third pressure sensor 54 is located between the first regulating valve 53 and the first fuel annular pipe 81; the second fuel branch pipeline 6 is provided with a fourth pressure sensor 62 and a fifth pressure sensor 64, the fourth pressure sensor 62 is located between the fourth quick cut-off valve 61 and the second regulating valve 63, and the fifth pressure sensor 64 is located between the second regulating valve 63 and the second fuel annular pipe 82; the third fuel branch pipeline 7 is provided with a sixth pressure sensor 72 and a seventh pressure sensor 74, the sixth pressure sensor 72 is located between the fifth quick cut-off valve 71 and the third regulating valve 73, and the seventh pressure sensor 74 is located between the third regulating valve 73 and the third fuel annular pipe 83.

[0048] It needs to be clear that the fuel supply system of the gas turbine proposed in the embodiments of the present application realizes that the amount of fuel delivered by the second control assembly to the combustor through the fuel branch pipeline can be controlled by the arrangement of the plurality of fuel branch pipelines corresponding to the fuel annular pipes and the second control assembly corresponding to the fuel branch pipeline. That is, the fuel supply system of the gas turbine can adjust the amount of fuel burned in each stage of the combustor based on the working state of the gas turbine, so that the stability of combustion can be ensured and the flame temperature can be reduced to achieve low emission of pollutants in different working conditions of the gas turbine.

[0049] After introducing all the embodiments of the fuel supply system of the gas turbine proposed in the present application, all the embodiments of the fuel supply method of the gas turbine proposed in the present application are introduced below.

[0050] Specifically, the embodiments of the present application propose a fuel supply method of a gas turbine, as shown in the method comprises: Figure 1

[0051] Step S100: acquiring first data and a target working state of the gas turbine.

[0052] Specifically, in the embodiments of the present application, the first data can be any data capable of representing the working state of the gas turbine. For example, in the embodiments of the present application, the first data can be the rotating speed of the gas turbine or the power of the gas turbine. In the embodiments of the present application, the first data can be data automatically read by the gas turbine based on its own working state, or can be manually input data.

[0053] ​It should be noted that, in the embodiments of the present application, the target working state of the gas turbine refers to the working state that the gas turbine is expected to reach, which includes but is not limited to the following: the stop state, the warm-up state, the low working state and the high working state. It can be easily understood that, in the embodiments of the present application, the target working state of the gas turbine can be obtained by the gas turbine according to its current working state. For example, in an embodiment of the present application, if the gas turbine is automatically promoted from the stop state (i.e. the current working state) to the high working state (i.e. the target working state) after the gas turbine is started, the gas turbine can automatically switch from the stop state (i.e. the current working state) to the warm-up state (i.e. the target working state), from the warm-up state (i.e. the current working state) to the low working state (i.e. the target working state), and from the low working state (i.e. the current working state) to the high working state (i.e. the target working state) according to its own state. In other embodiments of the present application, the target working state of the gas turbine can be set by manual operation. For example, in an embodiment of the present application, if the gas turbine is in the stop state and the target working state is manually input after the gas turbine is started, the gas turbine can only switch from the stop state (i.e. the current working state) to the corresponding working state (i.e. the target working state).

[0054] Step S200: obtaining the current working state of the gas turbine based on the first data.

[0055] It should be noted that, if the gas turbine is in different working states, some of its working parameters are different. For example, the rotational speed and the output power of the gas turbine are different when the gas turbine is in different working states. Generally, the working state of the gas turbine has the following four states: the stop state, the warm-up state, the low working state and the high working state. Among them, the rotational speed and the output power of the gas turbine in the stop state, the warm-up state, the low working state and the high working state are sequentially increased. That is, if the relevant working parameters of the gas turbine (i.e. the first data) are obtained, the working state of the gas turbine can be inferred.

[0056] It should be noted that in the embodiments of the present application, based on the first data, it can be inferred not only what working state the gas turbine is in, but also whether the gas turbine is in an uplink working state (i.e., the working condition of the gas turbine is increasing), a downlink working state (i.e., the working condition of the gas turbine is decreasing), or a stable working state (i.e., the working condition of the gas turbine is unchanged). For example, two first data are obtained in sequence according to a time line, and are sequentially named as second data and third data according to the time acquisition sequence. If the second data is greater than the third data, and the difference between the second data and the third data is greater than a first threshold, it indicates that the gas turbine is in a downlink state. If the second data is less than the third data, and the difference between the second data and the third data is greater than a second threshold, it indicates that the gas turbine is in an uplink state. If the difference between the second data and the third data is less than a third threshold, it indicates that the gas turbine is in a stable working state. The first threshold, the second threshold, and the third threshold can be set in advance.

[0057] In an embodiment of the present application, the first threshold, the second threshold, and the third threshold can all be the rotating speed of the gas turbine. In a specific embodiment of the present application, the first threshold, the second threshold, and the third threshold are the same, and the first threshold can be any rotating speed greater than or equal to 200 rpm and less than or equal to 600 rpm. Specifically, the first threshold can be any rotating speed of 200 rpm, 250 rpm, 300 rpm, 350 rpm, 400 rpm, 550 rpm, 500 rpm, 550 rpm, and 600 rpm, or any rotating speed between adjacent rotating speeds.

[0058] It should be noted that in the embodiments of the present application, defining four working states of the gas turbine does not mean that the method of the present application is only applicable to the gas turbine with the above four working states. Some gas turbines have more detailed working state division, and the gas turbine fuel supply method proposed in the present application is also applicable to them, which will not be listed here.

[0059] Step S300: Based on the current working state and the target working state of the gas turbine, the fuel supply amount of each region in the combustion chamber is controlled to make the gas turbine reach the target working state.

[0060] It should be noted that from the foregoing, if the gas turbine is in a stable working state, i.e., the current working state of the gas turbine is the same as the target working state of the gas turbine, there is no need to adjust the fuel in each region of the combustion chamber; if the gas turbine is in an uplink or downlink working state, i.e., the current working state of the gas turbine is different from the target working state of the gas turbine, the fuel in each region of the combustion chamber must be adjusted to ensure the stability of combustion and low emission of combustion pollutants.

[0061] In one embodiment of this application, using Figure 3 Taking the gas turbine fuel supply system shown as an example, we define the operating state of the gas turbine based on its rotational speed. In this embodiment, the first data point is the gas turbine's rotational speed. Specifically, if the gas turbine's rotational speed is less than or equal to N1, the gas turbine is determined to be in a warm-up state or below; if the gas turbine's rotational speed is greater than N1 and less than or equal to N2, the gas turbine is determined to be in a low-operation state; if the gas turbine's rotational speed is greater than N2, the gas turbine is determined to be in a high-operation state. N2 is greater than N1, and N1 and N2 can be preset. It is important to note that if two gas turbines have different models or structures, their N1 and N2 values ​​may also be different. In other words, N1 and N2 can be set according to the gas turbine model.

[0062] Figure 3 This is a flowchart illustrating the process of a gas turbine switching from a shutdown state to other states (warm-up state, low operating condition state, or high operating condition state). In other words, in... Figure 3 In the embodiments, the current operating state of the gas turbine is either a shutdown state or a state below warm-up; while the target state of the gas turbine is a warm-up state, a low operating condition state, or a high operating condition state.

[0063] Specifically, such as Figure 3 As shown, after starting the gas turbine, the turbine speed N (i.e., below the specified data) is obtained. Assuming that in this embodiment, the target operating state of the gas turbine is a high-operation state, the gas turbine system determines whether it is in a shutdown state. If yes, all quick-cutoff valves on the fuel lines are closed, specifically the second quick-cutoff valve 24, the third quick-cutoff valve 51, the fourth quick-cutoff valve 61, and the fifth quick-cutoff valve 71. If no, it determines whether N is less than or equal to N1. As mentioned earlier, if N is less than or equal to N1, it indicates that the gas turbine is in a working state below warm-up, and the gas turbine needs to be upgraded to a warm-up operating state. If N is greater than N1, it indicates that the gas turbine is already in a warm-up state, and the gas turbine needs to be upgraded from the warm-up state to a low-operation state, i.e., process L1 is executed.

[0064] Specifically, such as Figure 1As shown, if N is less than or equal to N1, it is determined whether N is greater than or equal to a fourth threshold value. In the embodiment of the present application, the fourth threshold value is set mainly to determine whether the rotational speed of the gas turbine can meet the ignition requirement, and if not, the gas turbine cannot be promoted from the shutdown state to the warm-up state, to ensure the safety of the gas turbine. If N is less than or equal to the fourth threshold value, the quick cut-off valve on all fuel pipes is closed; if N is greater than the fourth threshold value, it is determined whether the gas turbine is started by the diffusion stage? That is, whether the gas turbine is supplied with air through the second fuel distribution pipe 6? Specifically, if the diffusion stage is not used for starting, it is indicated that the first fuel distribution pipe 5 can only be used for air supply, that is, the pre-combustion stage is started, and at this time, the opening of the first regulating valve 53 can be controlled; if the diffusion stage is used for starting, the opening of the second regulating valve 63 can be controlled.

[0065] It should be clear that the rotational speed of the safe start of different models of gas turbines is different, that is, the fourth threshold value is different. That is, the fourth threshold value can be set based on the model or parameters of the gas turbine itself, which is not enumerated and described in detail in the present application.

[0066] Specifically, as shown in Figure 4 , if the gas turbine is started by the diffusion stage, the second quick cut-off valve 24 is opened, the fourth quick cut-off valve 61 is opened, and the second regulating valve 63 completes the opening adjustment according to the data of the fourth pressure sensor 62 and the fifth pressure sensor 64. If the gas turbine is started by the pre-combustion stage, the second quick cut-off valve 24 is opened, the third quick cut-off valve 51 is opened, and the first regulating valve 53 completes the opening adjustment according to the data of the second pressure sensor 52 and the third pressure sensor 54.

[0067] Figure 4 The flow chart for switching the gas turbine from the warm-up state to other states (low working condition state or high working condition state), that is, in the embodiment of Figure 4 , the current working state of the gas turbine is the warm-up state; and the target state of the gas turbine is the low working condition state or the high working condition state.

[0068] Specifically, as shown in Figure 5As shown, the process determines whether N is less than or equal to N2. If not, the gas turbine is already in a low-operating state and needs to be upgraded from a low-operating state to a high-operating state, i.e., process L2 is executed. If yes, after determining that N equals N1, it checks if it is within 20 seconds. If yes, it continues to determine whether N is less than or equal to N2 to prevent misjudgment of the gas turbine's own state due to fluctuations in its operating condition. If no, it needs to supply gas (i.e., fuel) to the gas turbine simultaneously through the first fuel line 5 and the second fuel line 6 to enable the gas turbine to upgrade from a warm-up state to a low-operating state. It should be noted that before upgrading the gas turbine's operating condition, if a secondary alarm occurs, all fuel lines should be shut off; if no secondary alarm occurs, the opening of the first regulating valve 53 and the second regulating valve 63 should be adjusted to the preset opening.

[0069] Figure 5 This is a flowchart illustrating the transition of a gas turbine from a low operating condition to a high operating condition. Figure 5 In this embodiment, the current operating state of the gas turbine is a low operating condition; while the target state of the gas turbine is a high operating condition.

[0070] Specifically, such as ​ As shown, after determining that N reaches the range of N2±25, is it within 20 seconds? If so, continue waiting for more than 20 seconds to prevent misjudgment of the gas turbine's own state due to fluctuations in the gas turbine's operating condition; if not, the third fuel line 7 needs to be opened to supply gas to the gas turbine so that the gas turbine can be upgraded from a low operating condition to a high operating condition. It should be clear that before upgrading the gas turbine's operating condition, if a secondary alarm occurs, all fuel lines should be shut off; if no secondary alarm occurs, the openings of the first regulating valve 53, the second regulating valve 63, and the third regulating valve 73 can be adjusted to the preset openings.

[0071] It is important to understand that the gas turbine fuel supply method proposed in this application, through the arrangement of multiple sub-fuel pipelines corresponding one-to-one with the fuel annular pipe and a second control component corresponding one-to-one with each sub-fuel pipeline, enables the second control component to control the amount of fuel delivered to the combustion chamber through the sub-fuel pipelines. In other words, this gas turbine fuel supply method can adjust the amount of fuel burned at each stage in the combustion chamber based on the operating state of the gas turbine, ensuring combustion stability under different operating conditions, reducing flame temperature, and achieving low emissions of pollutants.

[0072] While embodiments of the application have been shown and described, it is to be understood that the embodiments described are merely exemplary and that changes can be made in detail without departing from the principles and spirit of the application. The scope of the application is therefore defined by the appended claims and their equivalents.

Claims

1. A method of fuel supply for a gas turbine, applied to a gas turbine with staged combustion, said gas turbine comprising a gas turbine fuel supply system, characterized in that, The method comprises: acquiring first data and a target working state of the gas turbine; acquiring a current working state of the gas turbine based on the first data; controlling the fuel supply amount of each region in the combustion chamber based on the current working state and the target working state of the gas turbine, so as to make the gas turbine reach the target working state; the working state of the gas turbine comprises a shutdown state, a warm-up state, a low working condition state and a high working condition state; the first data comprises a rotating speed N of the gas turbine; if the rotating speed of the gas turbine is less than or equal to N1, it is determined that the gas turbine is in a warm-up state or below; if the rotating speed of the gas turbine is greater than N1 and less than or equal to N2, it is determined that the gas turbine is in a low working condition state; if the rotating speed of the gas turbine is greater than N2, it is determined that the gas turbine is in a high working condition state; wherein N2 is greater than N1, and N1 and N2 are pre-set; if the current working state of the gas turbine is a shutdown state or below, and the target state of the gas turbine is a warm-up state, a low working condition state or a high working condition state, the controlling of the fuel supply amount of each region in the combustion chamber based on the current working state and the target working state of the gas turbine, so as to make the gas turbine reach the target working state, comprises: acquiring the rotating speed N of the gas turbine; determining whether the gas turbine is in a shutdown state, if yes, closing all the quick cut-off valves on the fuel pipes; if no, determining whether N is less than or equal to N1; if N is less than or equal to N1, it indicates that the gas turbine is in a working state below the warm-up state, and the gas turbine needs to be lifted to the warm-up working state; if N is greater than N1, it indicates that the gas turbine is in a warm-up state, and the gas turbine needs to be lifted from the warm-up state to a low working condition state, that is, the flow L1 is executed; the flow L1 comprises: determining whether N is less than or equal to N2, if no, it indicates that the gas turbine is in a low working condition state, and the gas turbine needs to be lifted from the low working condition state to a high working condition state, that is, the flow L2 is executed; if yes, after determining that N is equal to N1, it is determined whether it is within 20 seconds, if yes, it is continuously determined whether N is less than or equal to N2, so as to prevent misjudgment of the state of the gas turbine due to the working condition fluctuation of the gas turbine; if no, the first sub-fuel pipe and the second sub-fuel pipe need to be simultaneously used to supply gas to the gas turbine, so that the gas turbine can be lifted from the warm-up state to the low working condition state; the flow L2 comprises: after determining that N reaches N2±25, it is determined whether it is within 20 seconds, if yes, it is continuously waited for more than 20 seconds, so as to prevent misjudgment of the state of the gas turbine due to the working condition fluctuation of the gas turbine; if no, the third sub-fuel pipe needs to be opened to supply gas to the gas turbine, so that the gas turbine can be lifted from the low working condition state to the high working condition state.

2. The gas turbine fuel supply method of claim 1 wherein, The fuel supply system of the gas turbine comprises: a main fuel pipe (2); a plurality of fuel annular pipes; a plurality of sub-fuel pipes corresponding to the fuel annular pipes, a first end of each of the sub-fuel pipes being in communication with the main fuel pipe (2), and a second end of each of the sub-fuel pipes being in communication with a corresponding fuel annular pipe; a first control assembly for controlling at least the opening and closing of the main fuel pipe (2); a second control assembly corresponding to the sub-fuel pipes for controlling at least the fuel flow of a corresponding sub-fuel pipe.

3. The gas turbine fuel supply method of claim 2 wherein, a venting assembly for venting gas in the main fuel pipe (2), the venting assembly comprising: a venting pipe (3) having a first end in communication with the main fuel pipe (2); a first stop valve (31) and a first quick cut-off valve (32) arranged in the venting pipe (3) for controlling the opening and closing of the venting pipe (3), the first stop valve (31) and the first quick cut-off valve (32) being arranged in a first direction, the first direction being from a second end of the venting pipe (3) to the first end of the venting pipe (3).

4. The gas turbine fuel supply method of claim 3 wherein, a purging assembly for purging gas in the gas turbine fuel supply system, the purging assembly comprising: a purging pipe (4) in communication with the main fuel pipe (2); a second stop valve (41) arranged in the purging pipe (4) for controlling the opening and closing of the purging pipe (4).

5. The gas turbine fuel supply method of any one of claims 2 to 4, wherein, The first control assembly comprises a second quick cut-off valve (24) arranged in the main fuel pipe (2).

6. The gas turbine fuel supply method of claim 5 wherein, The first control assembly further comprises a third stop valve (21) arranged in the main fuel pipe (2), the third stop valve (21) and the second quick cut-off valve (24) being arranged in a second direction, the second direction being parallel to the direction of fuel flow in the main fuel pipe (2).

7. The gas turbine fuel supply method of claim 6 wherein, The first control assembly further comprises a first pressure sensor (22) and a temperature sensor (23) arranged in the main fuel pipe (2), the first pressure sensor (22) and the temperature sensor (23) being located between the third stop valve (21) and the second quick cut-off valve (24), and the first pressure sensor (22) and the temperature sensor (23) being electrically connected to the second quick cut-off valve (24), respectively.

8. The gas turbine fuel supply method of any one of claims 2 to 4, wherein The second control assembly comprises a regulating valve arranged in the sub-fuel pipe.

9. The gas turbine fuel supply method of claim 8 wherein, The second control assembly further comprises a quick cut-off valve arranged in the sub-fuel pipe, the quick cut-off valve and the regulating valve being arranged in a third direction, the third direction being from the first end of the sub-fuel pipe to the second end of the sub-fuel pipe.

10. The gas turbine fuel supply method of claim 9 wherein, The second control assembly further comprises two pressure sensors arranged in the sub-fuel pipe, one of the pressure sensors being arranged between the quick cut-off valve and the regulating valve, and the pressure sensor being electrically connected to the quick cut-off valve; the other pressure sensor being arranged between the regulating valve and the fuel annular pipe, and the pressure sensor being electrically connected to the regulating valve.

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