CN221120128U - Fuel supply system of gas turbine - Google Patents

Abstract

The application discloses a fuel supply system of a gas turbine, and relates to the technical field of gas turbines. The gas turbine fuel supply system includes: a main fuel line; a plurality of fuel annular tubes; the fuel annular pipes are provided with a plurality of fuel distribution pipelines, the first ends of the fuel distribution pipelines are communicated with the main fuel pipelines, and the second ends of the fuel distribution pipelines are communicated with the corresponding fuel annular pipes; the first control component is at least used for controlling the on-off of the main fuel pipeline; and the second control components are in one-to-one correspondence with the fuel dividing pipelines and are at least used for controlling the fuel flow of the corresponding fuel dividing pipelines. The application realizes that the quantity of fuel conveyed into the combustion chamber by the fuel distribution pipelines can be controlled by the second control components through the arrangement of the plurality of fuel distribution pipelines which are in one-to-one correspondence with the fuel annular pipes and the second control components which are in one-to-one correspondence with the fuel distribution pipelines.

Description

Fuel supply system of gas turbine

Technical Field

The application relates to the technical field of gas turbines, in particular to a fuel supply system of a gas turbine.

Background

With the continuous enhancement of public environmental awareness, the requirements of the market on pollutant emission of gas turbines are gradually increased, namely, the requirements on emission of flue gas NOx and CO in the energy combustion process are more stringent. At present, the generation of pollutants in the fuel combustion process is reduced, and the research is focused on the large-scale power generation and power driving which are highly dependent on fossil energy sources. In order to meet the low emissions of pollutants, low emission combustion technology is one of the technical challenges gas turbines must address. The current mature low-emission combustion technology is a staged combustion technology adopting a lean oil premixing mode. It should be clear that staged combustion refers to the provision of air and fuel for the staged combustion at different locations along the combustion path to participate in the combustion to achieve the purposes of controlling combustion temperature and reducing pollutant emissions.

It should be apparent that gas turbines require the use of nozzles to supply fuel into the combustor. In the prior art, in order to realize staged combustion, a plurality of flow channels are required to be arranged in the nozzle, and the flow channels are in one-to-one correspondence with areas needing fuel in the combustion chamber. The main fuel pipeline of the gas turbine is directly communicated with the nozzle, and the main fuel pipeline can convey fuel to the corresponding area of the combustion chamber through a flow passage in the nozzle. It will be readily appreciated that under the same fluid pressure conditions, the amount of fluid delivered is proportional to the flow path of the flow channels, i.e. by controlling the flow path of each flow channel in the nozzle, a corresponding amount of fuel delivery to different regions of the combustion chamber can be achieved. It follows that fuel is supplied to the combustion chamber in this manner, and that the fuel proportions in different regions of the combustion chamber are substantially uniform over the full operating range of the gas turbine. If the fuel in the combustion chamber can only be maintained at a certain proportion, the technical problems of backfire, oscillation combustion and the like are easily caused by insufficient fuel or excessive fuel in the working condition lifting process of the gas turbine, and the technical problems of insufficient combustion, overhigh combustion temperature, increased discharged pollutants and the like are easily caused.

Disclosure of utility model

The application aims to provide a fuel supply system of a gas turbine, which solves the technical problem that the fuel proportion of different areas in a combustion chamber cannot be adjusted in the prior art.

In order to achieve the above purpose, the present application provides the following technical solutions:

Specifically, the technical scheme of the application provides a gas turbine fuel supply system, which comprises: a main fuel line; a plurality of fuel annular tubes; the fuel annular pipes are provided with a plurality of fuel distribution pipelines, the first ends of the fuel distribution pipelines are communicated with the main fuel pipelines, and the second ends of the fuel distribution pipelines are communicated with the corresponding fuel annular pipes; the first control component is at least used for controlling the on-off of the main fuel pipeline; and the second control components are in one-to-one correspondence with the fuel dividing pipelines and are at least used for controlling the fuel flow of the corresponding fuel dividing pipelines.

As a specific scheme in the technical scheme of the application, the application further comprises a bleeding component, wherein the bleeding component is used for bleeding gas in the main fuel pipeline; the diffusing assembly includes: the first end of the diffusing pipeline is communicated with the main fuel pipeline; the first stop valve and the first quick stop valve are arranged on the diffusing pipeline and used for controlling the on-off of the diffusing pipeline; the first stop valve and the first quick stop valve are sequentially arranged along a first direction, and the second end of the bleeding pipeline points to the first end of the bleeding pipeline in the first direction.

As a specific scheme in the technical scheme of the application, the gas turbine fuel supply system further comprises a purging component, wherein the purging component is used for purging gas in the gas turbine fuel supply system; the purge assembly includes: a purge line in communication with the main fuel line; and the second stop valve is arranged on the purging pipeline and used for controlling the on-off of the purging pipeline.

As a specific aspect of the technical solution of the present application, the first control assembly includes a second quick shut-off valve disposed on the main fuel line.

As a specific scheme in the technical scheme of the application, the first control assembly further comprises a third stop valve arranged on the main fuel pipeline, the third stop valve and the second quick stop valve are sequentially arranged along a second direction, and the second direction is parallel to the fuel flowing direction in the main fuel pipeline.

As a specific scheme in the technical scheme of the application, the first control assembly further comprises a first pressure sensor and a temperature sensor which are arranged on the main fuel pipeline, the first pressure sensor and the temperature sensor are positioned between the third stop valve and the second quick stop valve, and the first pressure sensor and the temperature sensor are respectively and electrically connected with the second quick stop valve.

As a specific aspect of the technical solution of the present application, the second control component includes a regulating valve disposed on the fuel distributing pipeline.

As a specific scheme in the technical scheme of the application, the second control assembly further comprises a quick cut-off valve arranged on the fuel dividing pipeline, the quick cut-off valve and the regulating valve are distributed in sequence along a third direction, and the third direction points to the second end from the first end of the fuel dividing pipeline.

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

Compared with the prior art, the application has the beneficial effects that:

Through the arrangement of a plurality of fuel distribution pipelines corresponding to the fuel annular pipes one by one and a second control assembly corresponding to the fuel distribution pipelines one by one, the fuel quantity which can be conveyed into the combustion chamber through the fuel distribution pipelines is controlled by the second control assembly. That is, the application can adjust the fuel amount of each stage of combustion in the combustion chamber based on the working state of the gas turbine, so that the gas turbine can ensure the combustion stability in different working conditions, reduce the flame temperature and realize low emission of pollutants.

Drawings

FIG. 1 is a schematic diagram of a gas turbine fuel supply system according to an embodiment of the present application;

FIG. 2 is a flow chart of a method for supplying fuel to a gas turbine in accordance with an embodiment of the present application;

FIG. 3 is a flow chart illustrating a gas turbine from a shutdown state to a warm-up state according to an embodiment of the present application;

FIG. 4 is a flow chart illustrating a gas turbine from a warm state to a low condition state according to an embodiment of the present application;

FIG. 5 is a flow chart illustrating a gas turbine engine according to an embodiment of the present application from a low condition to a high condition.

In the figure: 2. a main fuel line; 21. a third stop valve; 22. a first pressure sensor; 23. a temperature sensor; 24. a second quick disconnect valve; 3. a bleeding pipeline; 31. a first stop valve; 32. a first quick disconnect valve; 4. purging the pipeline; 41. a second shut-off valve; 5. a first fuel dividing pipeline; 51. a third quick disconnect valve; 52. a second pressure sensor; 53. a first regulating valve; 54. a third pressure sensor; 6. a second fuel-split line; 61. a fourth quick disconnect valve; 62. a fourth pressure sensor; 63. a second regulating valve; 64. a fifth pressure sensor; 7. a third fuel dividing line; 71. a fifth quick disconnect valve; 72. a sixth pressure sensor; 73. a third regulating valve; 74. a seventh pressure sensor; 81. a first fuel annular tube; 82. a second fuel annular tube; 83. and a third fuel annular tube.

Detailed Description

The following description of the embodiments of the present application will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present application, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.

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 orientations or positional relationships based on the orientations or positional relationships shown in the drawings, only for convenience in describing the present application and simplifying the description, and do not indicate or imply that the apparatus or elements to be referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present application.

Furthermore, it should be understood that the dimensions of the various elements shown in the figures are not drawn to actual scale, e.g., the thickness or width of some layers may be exaggerated relative to other layers for ease of description.

It should be noted that like reference numerals and letters refer to like items in the following figures, and thus once an item is defined or illustrated in one figure, no further detailed discussion or description thereof will be necessary in the following description of the figures.

In order to solve the technical problem in the background art, as shown in fig. 1, the present application proposes an embodiment of a fuel supply system of a gas turbine, specifically, the fuel supply system of the gas turbine includes: the device comprises a plurality of fuel annular pipes, a main fuel pipeline 2, a plurality of fuel sub-pipelines corresponding to the fuel annular pipes one by one, a first control assembly and a second control assembly corresponding to the fuel sub-pipelines one by one. Wherein a first end of each fuel dividing pipe is communicated with the main fuel pipe 2, and a second end of each fuel dividing pipe is communicated with a corresponding fuel annular pipe. The first control component is at least used for controlling the on-off of the main fuel pipeline 2. The second control components which are in one-to-one correspondence with the fuel dividing pipelines are at least used for controlling the fuel flow of the corresponding fuel dividing pipelines.

In particular, the fuel annular tube is mainly of annular tubular structure for connecting a plurality of nozzles so that each nozzle can be distributed in an annular shape in the combustion chamber. Since the fuel annular tube is a mature prior art, the fuel annular tube is not described in detail in the embodiments of the present application. It should be clear that in prior art gas turbines only one fuel annular tube is typically provided, whereas in embodiments of the present application the number of fuel annular tubes needs to be determined based on the type of runner of the staged combustion. That is, in the embodiment of the present application, at least two fuel annular pipes need to be provided.

In particular, since the types of staged combustion gas turbines are various, it is difficult to list the gas turbines of various staged combustion types one by one. The following description will be made of various embodiments of the present application taking an application scenario in which a gas turbine has a pre-combustion stage flow path, a diffusion stage flow path, and a main combustion stage flow path as an example. As can be seen from the foregoing, if the gas turbine has a pre-stage flow path, a diffusion stage flow path, and a main stage flow path, the supply system of the gas turbine fuel needs to include a first fuel annular pipe 81 corresponding to the pre-stage flow path, a second fuel annular pipe 82 corresponding to the diffusion stage flow path, and a third fuel annular pipe 83 corresponding to the main stage flow path, as shown in fig. 1.

It is readily understood that in embodiments of the present application, a pre-combustion stage flow path, a diffusion stage flow path, and a main combustion stage flow path may be provided in a single nozzle, respectively. When installed, the first fuel annular tube 81 may be placed in communication with the pre-combustion stage flow path in the nozzle, the second fuel annular tube 82 with the diffusion stage flow path in the nozzle, and the third fuel annular tube 83 with the main combustion stage flow path in the nozzle. In other embodiments of the present application, three nozzles may be provided, which are a precombustion stage nozzle, a diffusion stage nozzle, and a main combustion stage nozzle, respectively, that is, the precombustion stage nozzle is provided with a precombustion stage flow channel, the diffusion stage nozzle is provided with a diffusion stage flow channel, and the main combustion stage nozzle is provided with a main combustion stage flow channel. At the time of installation, the first fuel annular pipe 81 may be made to communicate with the pre-combustion stage nozzle, the second fuel annular pipe 82 may be made to communicate with the diffusion stage nozzle, and the third fuel annular pipe 83 may be made to communicate with the main combustion stage nozzle.

It is clear that the embodiment of the application realizes that the quantity of fuel conveyed into the combustion chamber through the fuel distribution pipelines can be controlled by the second control assembly through the arrangement of the plurality of fuel distribution pipelines which are in one-to-one correspondence with the fuel annular pipes and the second control assembly which is in one-to-one correspondence with the fuel distribution pipelines. That is, the embodiment of the application can adjust the fuel quantity of each stage of combustion in the combustion chamber based on the working state of the gas turbine, so that the gas turbine can ensure the combustion stability in different working conditions, reduce the flame temperature and realize low emission of pollutants.

In order to ensure safety after a gas turbine shutdown, in an embodiment of the application, the gas turbine fuel supply system may further comprise a bleeding assembly for bleeding off the gas in the main fuel line 2. It will be readily appreciated that in one embodiment of the application, as shown in fig. 1, the bleeding assembly may include a bleeding line 3, with a first end of the bleeding line 3 communicating with the main fuel line 2. That is, after the gas turbine is stopped, the combustible gas in the main fuel line 2 can be discharged through the discharge line 3 to reduce the safety hazard. In order to control the on/off of the bleeding pipe 3, in one embodiment of the present application, as shown in fig. 1, the bleeding assembly may further include a first quick-disconnect valve 32 disposed on the bleeding pipe 3, where the first quick-disconnect valve 32 is used to control the on/off of the bleeding pipe 3. In order to avoid the first quick shut-off valve 32 from malfunctioning and failing to shut off the bleeding pipe 3 to cause a safety accident, in another embodiment of the present application, as shown in fig. 1, the bleeding assembly may further include a first shut-off valve 31 disposed on the bleeding pipe 3, where the first shut-off valve 31 is also used to control the on/off of the bleeding pipe 3. And the first shut-off valve 31 and the first quick shut-off valve 32 are arranged in sequence in a first direction directed from the second end of the bleeding line 3 to the first end of the bleeding line 3. If the first quick shut-off valve 32 fails, the first shut-off valve 31 may be used to shut off the blow-off line 3.

It should be clear that the venting assembly in the above embodiments enables the gas in the main fuel line 2 to be vented along the venting line 3, mainly based on the gas pressure in the main fuel line 2 being greater than the gas pressure in the venting line 3. In other embodiments of the application, to reduce the gas pressure in the blow-down line 3, the blow-down assembly may further comprise a pump for pumping the gas in the blow-down line 3 to reduce the gas pressure in the blow-down line 3.

In order to ensure safety before or after a start-up of the gas turbine, in an embodiment of the application, the supply system of gas turbine fuel may further comprise a purge assembly for purging gas within the gas turbine fuel supply system. In an embodiment of the application, as shown in fig. 1, the purge assembly includes a purge line 4. From the foregoing, it can be seen that, since the main fuel line 2 can be in communication with all other lines in the gas turbine fuel supply system, in order to achieve that the purge line 4 can purge all the lines in the gas turbine fuel supply system according to the embodiment of the present application, as shown in fig. 1, the purge line 4 can be in communication with the main fuel line 2.

Specifically, before or after the gas turbine is started or stopped, the gas in the main fuel pipeline 2, the diffusing pipeline 3 and each fuel dividing pipeline can be replaced by the purging pipeline 4 to form protective gas, so that the safety of the fuel supply system of the gas turbine is ensured. In the embodiment of the present application, the type of the shielding gas is not limited at all, and may be nitrogen or inert gas.

In order to control the on-off of the purge line 4, in one embodiment of the present application, as shown in fig. 1, the purge assembly may further include a second stop valve 41 disposed on the purge line 4, where the second stop valve 41 is used to control the on-off of the purge line 4. It is easy to understand that in order to control the on-off of the purge line 4 more safely, a quick shut-off valve may also be provided on the purge line 4.

As can be seen from the foregoing, the first control component is mainly used for controlling the on-off of the main fuel pipeline 2. It will be readily appreciated that the first control assembly may be any valve or switch that can be used to control the on-off of the pipeline. In one embodiment of the application, as shown in FIG. 1, the first control assembly may include a second quick disconnect valve 24 disposed in the main fuel line 2.

In an embodiment of the present application, the second quick disconnect valve 24 may be controlled in any control manner, for example: manual control, electric control or pneumatic control is adopted. In order to enable a quick shut-off of the main fuel line 2 in the event of an abnormal operation of the gas turbine, the second quick shut-off valve 24 is electrically controlled in one embodiment of the application, and the first control assembly may further comprise a first pressure sensor 22 and a temperature sensor 23 provided to said main fuel line 2. Wherein, the first pressure sensor 22 and the temperature sensor 23 are respectively electrically connected with the second quick disconnect valve 24. The first pressure sensor 22 is for monitoring the fuel pressure in the main fuel line 2 and the temperature sensor 23 is for monitoring the fuel temperature in the main fuel line 2. If the fuel pressure or temperature in the main fuel line 2 is abnormal, the main fuel line 2 is shut off by the second quick shut-off valve 24.

In order to ensure effectiveness of the shut-off of the main fuel line 2, in one embodiment of the application, as shown in fig. 1, the first control assembly may further comprise a third shut-off valve 21 provided to the main fuel line 2, the third shut-off valve 21 and the second quick shut-off valve 24 being arranged in sequence in a second direction, the second direction being parallel to the fuel flow direction in the main fuel line 2. The first pressure sensor 22 and the temperature sensor 23 are located between the third shut-off valve 21 and the second quick shut-off valve 24. By the arrangement of the third shut-off valve 21, if the second quick shut-off valve 24 fails, the main fuel line 2 can still be shut off by the third shut-off valve 21 to promote the fault tolerance of the shut-off of the main fuel line 2.

As can be seen from the foregoing, the second control component is mainly used for controlling the fuel flow of the corresponding fuel distribution pipeline. It will be readily appreciated that in embodiments of the present application, the second control assembly may be any valve or switch that can be used to control the flow of the pipeline. In one embodiment of the application, the second control assembly includes a regulator valve disposed in the split fuel line. As shown in fig. 1, in a specific embodiment of the present application, the fuel-dividing lines include a first fuel-dividing line 5, a second fuel-dividing line 6, and a third fuel-dividing line 7; the second control assembly comprises a first regulating valve 53 provided in the first sub fuel line 5, a second regulating valve 63 provided in the second sub fuel line 6 and a third regulating valve 73 provided in the third sub fuel line 7.

In order to quickly control the on-off of each fuel distribution pipeline, in one embodiment of the application, the second control assembly can further comprise a quick cut-off valve arranged on each fuel distribution pipeline. That is, in the embodiment of the application, the on-off of the fuel dividing pipeline can be rapidly controlled through the rapid shut-off valve. In an embodiment of the application, the quick shut-off valve and the regulating valve are distributed in sequence along a third direction, which is directed from the first end to the second end of the fuel dividing line. That is, the quick shutoff valve on the branch fuel line is located closer to the main fuel line 2, and if the fuel supply in the main fuel line 2 is abnormal, the quick shutoff valve can quickly shut off the branch fuel line. As shown in fig. 1, in a specific embodiment of the present application, a third quick shut-off valve 51 is provided in the first fuel-dividing line 5, a fourth quick shut-off valve 61 is provided in the second fuel-dividing line 6, and a fifth quick shut-off valve 71 is provided in the third fuel-dividing line 7.

In order to further ensure the safety of each fuel dividing pipeline and precisely control the fuel flow in each fuel dividing pipeline. In an embodiment of the present application, the second control assembly further includes two pressure sensors disposed on the fuel distribution pipeline, wherein one pressure sensor is disposed between the quick shut-off valve and the regulating valve, and the pressure sensor is electrically connected with the quick shut-off valve. Specifically, the pressure sensor is used for measuring the fuel pressure of the fuel distribution pipeline, and if the fuel pressure is abnormal, the fuel distribution pipeline is cut off through the quick cut-off valve so as to ensure the safety of the fuel distribution pipeline. The other pressure sensor is arranged between the regulating valve and the fuel annular pipe and is electrically connected with the regulating valve. That is, in the embodiment of the present application, the pressure sensors are disposed before and after the regulating valve in each split fuel line, and the regulating valve can precisely control the fuel flow in the split fuel line based on the data of the two pressure sensors.

In a specific embodiment of the present application, as shown in fig. 1, a second pressure sensor 52 and a third pressure sensor 54 are provided in the first fuel-dividing line 5, the second pressure sensor 52 being located between the third quick shut-off valve 51 and the first regulator valve 53, the third pressure sensor 54 being located between the first regulator valve 53 and the first fuel-annular pipe 81; a fourth pressure sensor 62 and a fifth pressure sensor 64 are arranged in the second fuel-dividing pipeline 6, the fourth pressure sensor 62 is positioned between the fourth quick cut-off valve 61 and the second regulating valve 63, and the fifth pressure sensor 64 is positioned between the second regulating valve 63 and the second fuel annular pipe 82; a sixth pressure sensor 72 and a seventh pressure sensor 74 are provided in the third fuel-dividing line 7, the sixth pressure sensor 72 being located between the fifth quick shut-off valve 71 and the third regulator valve 73, and the seventh pressure sensor 74 being located between the third regulator valve 73 and the third fuel annular pipe 83.

It should be clear that the fuel supply system of the gas turbine provided by the embodiment of the application realizes that the amount of fuel delivered into the combustion chamber through the fuel distribution pipelines can be controlled by the second control assembly through the arrangement of the plurality of fuel distribution pipelines corresponding to the fuel annular pipes one by one and the second control assembly corresponding to the fuel distribution pipelines one by one. That is, the gas turbine fuel supply system can adjust the fuel amount of each stage of combustion in the combustion chamber based on the working state of the gas turbine, so that the gas turbine can ensure the combustion stability under different working conditions, reduce the flame temperature and realize low emission of pollutants.

Having described all embodiments of the proposed gas turbine fuel supply system, all embodiments of the proposed gas turbine fuel supply method are described below.

Specifically, an embodiment of the present application proposes a gas turbine fuel supply method, as shown in fig. 1, including:

Step S100: first data is acquired and a target operating state of the gas turbine is obtained.

Specifically, in embodiments of the present application, the first data may be any data that is capable of characterizing the operating state of the gas turbine. For example, in an embodiment of the application, the first data may be a rotational speed of the gas turbine or a power of the gas turbine. In the embodiment of the application, the first data may be data automatically read by the gas turbine based on the working state of the gas turbine, or may be manually input data.

It should be appreciated that in embodiments of the present application, the target operating state of the gas turbine refers to an operating state that the gas turbine is expected to achieve, including, but not limited to, a shutdown state, a warm-up state, a low operating state, a high operating state, and the like, hereinafter. It is readily understood that in embodiments of the present application, the target operating state of the gas turbine may be obtained by the gas turbine based on its current operating state, for example: in one embodiment of the present application, if the gas turbine automatically increases from the shutdown state (i.e., the current operating state) to the high operating state (i.e., the target operating state) after the gas turbine is started, the gas turbine may sequentially automatically switch from the shutdown state (i.e., the current operating state) to the warm-up state (i.e., the target operating state), automatically switch from the warm-up state (i.e., the current operating state) to the third operating state (i.e., the target operating state), and automatically switch from the low operating state (i.e., the current operating state) to the high operating state (i.e., the target operating state) according to the state thereof. In other embodiments of the present application, the target operating state of the gas turbine may be set manually, for example, in embodiments of the present application, if the gas turbine is in a shutdown state and the target operating state is only manually input after the gas turbine is turned on, the gas turbine may be switched from the shutdown state (i.e., the current operating state) to the corresponding operating state (i.e., the target operating state).

Step S200: and acquiring the current working state of the gas turbine based on the first data.

It should be clear that certain operating parameters of a gas turbine are different if it is in different operating conditions. For example, if the gas turbine is in different operating states, the gas turbine speed and the output power are different. In general, the operating states of the gas turbine include a shutdown state, a warm state, a low operating state, and a high operating state. The rotation speed and the output power of the gas turbine in the shutdown state, the warm state, the low working condition state and the high working condition state are sequentially increased. That is, if the relevant operating parameters (i.e., the first data) of the gas turbine are obtained, it can be inferred what operating state the gas turbine is in.

It should be clear that in embodiments of the present application, based on the first data, it is possible to infer not only what operating state the gas turbine is in, but also whether the gas turbine is in an upstream operating state (i.e., the gas turbine operating condition is increasing), a downstream operating state (i.e., the gas turbine operating condition is decreasing), or a steady (i.e., the gas turbine operating condition is unchanged) operating state. For example, sequentially acquiring two first data according to a time line, sequentially naming the two first data as second data and third data according to a time acquisition sequence, and if the second data is larger than the third data and the difference value between the second data and the third data is larger than a first threshold value, indicating that the gas turbine belongs to a downlink state; if the second data is smaller than the third data and the difference value between the second data and the third data is larger than a second threshold value, the gas turbine is in an uplink state; and if the difference value between the second data and the third data is smaller than the third threshold value, the gas turbine is in a stable working state. The first threshold, the second threshold and the third threshold may be preset.

In one embodiment of the application, the first, second, and third thresholds may each be a rotational speed of the gas turbine. In a specific embodiment of the present application, the first threshold value, the second threshold value, and the third threshold value are the same, and the first threshold value may be any one of a rotation speed of 200 rotations per minute or more and 600 rotations per minute or less. Specifically, the first threshold may be any one of 200 rpm, 250 rpm, 300 rpm, 350 rpm, 400 rpm, 550 rpm, 500 rpm, 550 rpm, and 600 rpm, or any rotational speed between the adjacent rotational speeds.

It should be clear that in the embodiments of the present application, the definition of the four operating states of the gas turbine does not represent that the method of the present application is only applicable to gas turbines having the four operating states described above. Some gas turbines have finer operating status divisions, and are also suitable for the gas turbine fuel supply method provided by the present application, and are not described herein.

Step S300: based on the current operating state and the target operating state of the gas turbine, the fuel supply amount to each region in the combustion chamber is controlled so that the gas turbine reaches the target operating state.

It should be clear from the foregoing that if the gas turbine is in a stable operating state, that is, the current operating state of the gas turbine is the same as the target operating state of the gas turbine, there is no need to adjust the fuel in each region in the combustion chamber; if the gas turbine is in an upstream or downstream operating state, i.e. the current operating state of the gas turbine is different from the target operating state of the gas turbine, the fuel in each region of the combustion chamber must be regulated to ensure combustion stability and low emissions of combustion pollutants.

In one embodiment of the application, the gas turbine fuel supply system shown in FIG. 1 is used as an example. We define the operating state of the gas turbine on the basis of the rotational speed of the gas turbine, that is, in this embodiment, the first data is the rotational speed of the gas turbine. Specifically, if the rotational speed of the gas turbine is equal to or less than N1, it is determined that the gas turbine is in a warmed-up state or a state below the warmed-up state; if the rotating speed of the gas turbine is greater than N1 and less than or equal to N2, judging that the gas turbine is in a low working condition state; and if the rotating speed of the gas turbine is greater than N2, judging that the gas turbine is in a high working condition state. Where N2 is greater than N1, and N1 and N2 may be preset, it should be appreciated that if the two gas turbines are of different models or configurations, then N1 and N2 may also be different. That is, N1 and N2 may be set according to the model of the gas turbine.

FIG. 3 is a flow chart of a gas turbine switching from a shutdown state to another state (a warm state, a low state, or a high state). That is, in the embodiment of FIG. 3, the current operating state of the gas turbine is a shutdown state or a state below warm-up; and the target state of the gas turbine is a warm state, a low operating state, or a high operating state.

Specifically, as shown in fig. 3, after the gas turbine is started, the rotation speed N (i.e., lower than the data) of the gas turbine is obtained; it is assumed that in an embodiment of the present application, the target operating state of the gas turbine is a high operating state. The system of the gas turbine determines that it is in a shutdown state? If so, all the quick-cut valves on the fuel lines, that is, the second quick-cut valve 24, the third quick-cut valve 51, the fourth quick-cut valve 61, and the fifth quick-cut valve 71 are closed; if not, judging whether N is less than or equal to N1, and if N is less than or equal to N1, indicating that the gas turbine is in an operating state below the warm-up state, and lifting the gas turbine to the warm-up operating state is required; if N is greater than N1, it indicates that the gas turbine is already in the warmed-up state, and the gas turbine needs to be lifted from the warmed-up state to the low-working-condition state, that is, the flow L1 is executed.

Specifically, as shown in fig. 3, if N is equal to or smaller than N1, it is determined whether N is equal to or larger than a fourth threshold. In the embodiment of the application, the fourth threshold is mainly set for determining whether the rotation speed of the gas turbine can reach the ignition requirement, and if not, the gas turbine cannot be lifted from the shutdown state to the warm-up state so as to ensure the safety of the gas turbine. If N is smaller than or equal to a fourth threshold value, closing all the quick shut-off valves on the fuel pipelines; if N is greater than the fourth threshold, then determine if the gas turbine is diffusion stage started? I.e. is the gas turbine supplied via the second fuel-dividing line 6? Specifically, if the diffusion stage is not used for starting, it is only necessary to control the opening of the first regulating valve 53 when the first fuel-dividing pipeline 5 is used for supplying air, that is, when the pre-combustion stage is started; when the diffusion stage is used for starting, the opening degree of the second regulator valve 63 may be controlled.

It should be clear that the rotational speed of the safe start-up differs for different models of gas turbines, i.e. the fourth threshold value differs. That is, the fourth threshold may be set based on the model or parameters of the gas turbine itself, which is not described in detail herein.

Specifically, as shown in fig. 1, when the gas turbine is started using the diffusion stage, the second quick cut valve 24 is opened, the fourth quick cut valve 61 is opened, and the second regulator valve 63 completes the opening degree adjustment based on 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 valve 24 is opened, the third quick cut valve 51 is opened, and the first regulating valve 53 completes the opening degree regulation according to the data of the second pressure sensor 52 and the third pressure sensor 54.

FIG. 4 is a flow chart for switching the gas turbine from the warmed-up state to the other state (low-operating state or high-operating state), that is, in the embodiment of FIG. 4, the current operating state of the gas turbine is the warmed-up state; while the target state of the gas turbine is either a low operating state or a high operating state.

Specifically, as shown in fig. 4, whether N is less than or equal to N2 is determined, if not, the description gas turbine is already 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 that it is within 20 seconds? If yes, continuously judging whether N is less than or equal to N2 or not so as to prevent misjudgment of the state of the gas turbine due to fluctuation of the working condition of the gas turbine; if not, the gas turbine needs to be supplied with air (i.e., fuel) simultaneously through the first fuel-dividing line 5 and the second fuel-dividing line 6 so that the gas turbine can be lifted from the warmed-up state to the low-operating state. It should be clear that, before the operating mode of the gas turbine is lifted, if a secondary alarm occurs, all the fuel lines are closed; if the second-stage warning does not occur, the opening degrees of the first and second regulating valves 53 and 63 may be adjusted to the preset opening degree.

FIG. 5 is a flow chart for switching the gas turbine from a low operating condition to a high operating condition, that is, in the embodiment of FIG. 5, the current operating condition of the gas turbine is a low operating condition; while the target state of the gas turbine is a high regime state.

Specifically, as shown in fig. 5, after N reaches the range of n2±25, it is determined that N is within 20 seconds? If yes, continuing waiting time exceeding 20 seconds to prevent misjudgment of the state of the gas turbine due to fluctuation of the working condition of the gas turbine; if not, the third fuel dividing pipeline 7 needs to be opened to supply air to the gas turbine so that the gas turbine can be lifted from the low working condition state to the high working condition state. It should be clear that, before the operating mode of the gas turbine is lifted, if a secondary alarm occurs, all the fuel lines are closed; if the second-stage warning does not occur, the opening degrees of the first, second, and third regulating valves 53, 63, 73 may be adjusted to the preset opening degrees.

It should be clear that the method for supplying fuel to the gas turbine provided by the embodiment of the application realizes that the amount of fuel delivered to the combustion chamber through the fuel distribution pipelines can be controlled by the second control assembly through the arrangement of the plurality of fuel distribution pipelines corresponding to the fuel annular pipes one by one and the second control assembly corresponding to the fuel distribution pipelines one by one. That is, the method for supplying the fuel of the gas turbine can adjust the fuel amount of each stage of combustion in the combustion chamber based on the working state of the gas turbine, so that the gas turbine can ensure the stability of combustion under different working conditions, reduce the flame temperature and realize low emission of pollutants.

Although embodiments of the present application have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the application, the scope of which is defined in the appended claims and their equivalents.

Claims (9)

1. A gas turbine fuel supply system, comprising:

a main fuel line (2);

A plurality of fuel annular tubes;

the fuel annular pipes are in one-to-one correspondence, the first end of each fuel annular pipe is communicated with the main fuel pipe (2), and the second end of each fuel annular pipe is communicated with the corresponding fuel annular pipe;

The first control component is at least used for controlling the on-off of the main fuel pipeline (2);

and the second control components are in one-to-one correspondence with the fuel dividing pipelines and are at least used for controlling the fuel flow of the corresponding fuel dividing pipelines.

2. The gas turbine fuel supply system of claim 1, further comprising a bleeding assembly for bleeding off gas in the main fuel line (2); the diffusing assembly includes:

a bleeding line (3), a first end of the bleeding line (3) being in communication with the main fuel line (2);

The first stop valve (31) and the first quick stop valve (32) are arranged on the diffusing pipeline (3) and used for controlling the on-off of the diffusing pipeline (3); the first stop valve (31) and the first quick stop valve (32) are arranged in sequence along a first direction, and the second end of the bleeding pipeline (3) points to the first end of the bleeding pipeline (3) in the first direction.

3. The gas turbine fuel supply system of claim 2, further comprising a purge assembly for purging gas within the gas turbine fuel supply system; the purge assembly includes:

a purge line (4) communicating with the main fuel line (2);

And the second stop valve (41) is arranged on the purging pipeline (4) and used for controlling the on-off of the purging pipeline (4).

4. A gas turbine fuel supply system according to any one of claims 1 to 3, wherein the first control assembly comprises a second quick disconnect valve (24) provided to the main fuel line (2).

5. The gas turbine fuel supply system of claim 4, wherein the first control assembly further comprises a third shut-off valve (21) provided to the main fuel line (2), the third shut-off valve (21) and the second quick shut-off valve (24) being arranged in sequence along a second direction, the second direction being parallel to a fuel flow direction in the main fuel line (2).

6. The gas turbine fuel supply system of claim 5, wherein the first control assembly further comprises a first pressure sensor (22) and a temperature sensor (23) disposed in the main fuel line (2), the first pressure sensor (22) and the temperature sensor (23) are located between the third shut-off valve (21) and the second quick shut-off valve (24), and the first pressure sensor (22) and the temperature sensor (23) are electrically connected to the second quick shut-off valve (24), respectively.

7. A gas turbine fuel supply system according to any one of claims 1 to 3, wherein the second control assembly comprises a regulator valve provided to the split fuel line.

8. The gas turbine fuel supply system of claim 7, wherein the second control assembly further comprises a quick disconnect valve disposed in the split fuel rail, the quick disconnect valve and the regulator valve being sequentially distributed along a third direction, the third direction being directed from the first end to the second end of the split fuel rail.

9. The gas turbine fuel supply system of claim 8, wherein the second control assembly further comprises two pressure sensors disposed in the split fuel line, wherein one pressure sensor is disposed between the quick disconnect valve and the regulator valve and is electrically connected to the quick disconnect valve; the other pressure sensor is arranged between the regulating valve and the fuel annular pipe and is electrically connected with the regulating valve.