Wide-range fuel staging method for gas turbines

Abstract

The present invention discloses a wide-range fuel staging method for a gas turbine. The combustion chamber head of the gas turbine is provided with a fuel injector, and the fuel injector is provided with a central nozzle and a plurality of peripheral nozzles spaced around the central nozzle. The wide-range fuel staging method for a gas turbine proposed by the present invention realizes a variety of speed-increasing and load-increasing paths by changing the working nozzles. In the ignition stage and the speed-increasing stage, ignition and speed-increasing can be achieved by using only the central nozzle, or by using some peripheral nozzles, or by using a combination of the central nozzle and some peripheral nozzles. In the load-increasing stage, as the amount of fuel increases, the nozzles are gradually added to work in coordination to achieve load-increasing. By adjusting the staging scheme of the central nozzle and the peripheral nozzles, it is possible to match a variety of speed-increasing and load-increasing paths of the gas turbine without changing the combustion chamber structure, so that the gas turbine has a wider working range.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a wide-range fuel staging method for gas turbines. Background Art

[0002] With the development of gas turbines, the basic performance and structural form of gas turbine combustion systems are basically fixed. Most gas turbines use multiple combustion chambers to achieve reliable and efficient gas turbine operation. In order to match different power plants, different compressor performance and turbine performance, and meet the requirements of various models, the combustion chamber of the gas turbine needs to use a wider fuel operating range. Therefore, how to set up the fuel injection system at the head of the combustion chamber to adapt to a wide range of operating conditions is an important factor restricting the operating range of the gas turbine. The related technology usually adopts a fixed and single fuel staging scheme, so the adaptability to the fuel range is narrow, and it cannot match different power plants, different compressor performance and turbine performance, and cannot meet the requirements of various models. Summary of the Invention

[0003] The present invention aims to solve at least one of the technical problems in the related art to a certain extent. To this end, an embodiment of the present invention provides a wide range fuel staging method for a gas turbine.

[0004] A wide-range fuel staging method for a gas turbine according to an embodiment of the present invention is provided. The gas turbine adopts a premixed combustion mode. A fuel injector is provided at a combustion chamber head of the gas turbine. The fuel injector includes a central nozzle and a plurality of peripheral nozzles spaced around the central nozzle. The central nozzle and each peripheral nozzle operate independently. The fuel staging method includes:

[0005] During the ignition phase, the central nozzle and / or at least one of the peripheral nozzles are used for operation;

[0006] During the speed increase phase, the central nozzle and / or part of the peripheral nozzles are operated until the speed of the gas turbine reaches a preset speed value;

[0007] During the load increase phase, the central nozzle and at least part of the peripheral nozzles are operated until the rotation speed of the gas turbine increases to a preset load value.

[0008] The wide-range fuel staging method for a gas turbine proposed in an embodiment of the present invention achieves multiple speed and load increase paths by varying the operating nozzles. During the ignition and speed increase phases, the gas turbine's air volume is typically low, correspondingly resulting in a low fuel volume. Therefore, ignition and speed increase can be achieved using only the central nozzle, some peripheral nozzles, or a combination of the central and peripheral nozzles. During the load increase phase, as the fuel volume increases, it is necessary to gradually increase the number of nozzles in operation. Load increase can be achieved by increasing the number of central nozzles or by increasing the number of peripheral nozzles. Of course, speed increase can also be achieved by increasing the number of nozzles in operation during the speed increase phase. Therefore, the wide-range fuel staging method for a gas turbine proposed in an embodiment of the present invention, by adjusting the staging scheme of the central and peripheral nozzles, can achieve a variety of speed and load increase paths for the gas turbine without changing the combustion chamber structure. This provides the gas turbine with a wide operating range, adapting to different power plants, compressor performance, and turbine performance, meeting the requirements of various engine models, and satisfying gas turbine start-up, shutdown, operation, and environmental protection requirements.

[0009] In some embodiments, the operation of the gas turbine includes multiple speed-up stages, each speed-up stage corresponding to a different preset speed value, and the final preset speed value is reached by sequentially completing the speed-up stages. The fuel staging method specifically includes:

[0010] In the first speed increase stage, the central nozzle and / or part of the peripheral nozzles are used to operate until the speed of the gas turbine increases to a first preset speed value r1;

[0011] In the second speed increase stage, at least the nozzles in the first speed increase stage are kept in operation, and the central nozzle and / or part of the peripheral nozzles are added to operate until the speed of the gas turbine increases to a second preset speed value r2, wherein r2 is greater than r1;

[0012] Continue to add working nozzles until the speed reaches the final preset speed value.

[0013] In some embodiments, the operation of the gas turbine has multiple load ramp-up stages, each load ramp-up stage corresponding to a different preset load value, and the fuel staging method specifically includes:

[0014] In the first load increasing stage, the central nozzle and part of the peripheral nozzles are operated until a first preset load value p1 is matched;

[0015] In the second load increasing stage, at least the nozzles in the first load increasing stage are kept in operation, and the remaining peripheral nozzles are added to operate until a second preset load value p2 is matched, wherein p2 is greater than p1;

[0016] Continue adding peripheral nozzles until the final load value is matched.

[0017] In some embodiments, the peripheral nozzle includes a plurality of first peripheral nozzles and a plurality of second peripheral nozzles, and the fuel staging method includes:

[0018] During the ignition phase, the central nozzle and the first peripheral nozzle are used for operation;

[0019] In the speed increasing stage, the central nozzle is used to gradually increase the speed to a final preset speed value;

[0020] In a first load increasing stage, the central nozzle and the first peripheral nozzle are operated until the first preset load value p1 is matched;

[0021] In the second load increasing stage, the central nozzle and the first peripheral nozzle are kept in operation, and the second peripheral nozzle is increased in operation until a second preset load value p2 is matched, wherein p2 is greater than p1.

[0022] In some embodiments, the peripheral nozzle includes a plurality of first peripheral nozzles and a plurality of second peripheral nozzles, and the fuel staging method includes:

[0023] During the ignition phase, the central nozzle and the first peripheral nozzle are used for operation;

[0024] In the speed increase phase, the central nozzle is operated until the speed reaches a first preset speed value r1, the central nozzle is maintained, and the first peripheral nozzles are increased to operate until the speed of the gas turbine reaches a final preset speed value, wherein the final preset speed value is greater than r1;

[0025] In a first load increasing stage, the central nozzle and the first peripheral nozzle are operated until the first preset load value p1 is matched;

[0026] In the second load increasing stage, the central nozzle and the first peripheral nozzle are kept in operation, and the second peripheral nozzle is increased in operation until a second preset load value p2 is matched, wherein p2 is greater than p1.

[0027] In some embodiments, the peripheral nozzle includes a plurality of first peripheral nozzles and a plurality of second peripheral nozzles, and the fuel staging method includes:

[0028] During the ignition phase, the central nozzle and the first peripheral nozzle are used for operation;

[0029] During the speed increasing stage, the first peripheral nozzle is used to operate until the final preset speed value;

[0030] In a first load increasing stage, the central nozzle and the first peripheral nozzle are operated until the first preset load value p1 is matched;

[0031] In the second load increasing stage, the central nozzle and the first peripheral nozzle are kept in operation, and the second peripheral nozzle is increased in operation until a second preset load value p2 is matched, wherein p2 is greater than p1.

[0032] In some embodiments, the air volume of the central nozzle accounts for 10%-25% of the total air volume, and the air volume of the plurality of peripheral nozzles accounts for 75%-90% of the total air volume.

[0033] In some embodiments, the igniter of the gas turbine is disposed near one of the peripheral nozzles, and the gas turbine wide-range fuel staging method further comprises:

[0034] During the ignition phase, at least the peripheral nozzle close to the igniter and the central nozzle or another peripheral nozzle are used to operate, the peripheral nozzle close to the igniter is ignited, and after the flame is transferred to the operating central nozzle and / or other peripheral nozzles, the peripheral nozzle close to the igniter is closed;

[0035] When the pressure in the combustion chamber rises to a certain level, the igniter automatically rebounds and moves away from the peripheral nozzle.

[0036] In some embodiments, during the ignition stage, at least the central nozzle and the peripheral nozzle close to the igniter are used to work, the peripheral nozzle close to the igniter is ignited, and after the flame is transferred to the central nozzle, the peripheral nozzle close to the igniter is closed.

[0037] In some embodiments, during the ignition stage, the central nozzle and the peripheral nozzles close to the igniter are operated, the peripheral nozzles close to the igniter are ignited, and after the flame is transferred to the central nozzle, the peripheral nozzles close to the igniter are closed, and at least one of the peripheral nozzles away from the igniter is operated, and after the flame of the central nozzle is transferred to the working peripheral nozzle, the central nozzle is closed;

[0038] Alternatively, during the ignition stage, all of the peripheral nozzles are in operation, the peripheral nozzle close to the igniter is ignited, and after the flame is transferred to other peripheral nozzles, the peripheral nozzle close to the igniter is closed. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Figure 1 Schematic diagram of a fuel injector for a gas turbine according to an embodiment of the present invention.

[0040] Figure 2 Schematic diagram of the relationship between the combustion volume and the rotational speed of a gas turbine provided by an embodiment of the present invention.

[0041] Figure 3 It is a flow chart of the wide range fuel staging method for a gas turbine in the first embodiment of the present invention.

[0042] Figure 4 It is a flow chart of a wide range fuel staging method for a gas turbine in the second embodiment of the present invention.

[0043] Figure 5 It is a flow chart of the wide range fuel staging method for a gas turbine in the third embodiment of the present invention.

[0044] Reference numerals:

[0045] Fuel injector 100 , central nozzle 1 , peripheral nozzle 2 , first peripheral nozzle 21 , second peripheral nozzle 22 , igniter 3 . DETAILED DESCRIPTION

[0046] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to be used to explain the present invention, but should not be understood as limiting the present invention.

[0047] The following is based on Figure 1-Figure 5 The present invention provides a method for wide-range fuel staging for a gas turbine. The gas turbine utilizes premixed combustion. A fuel injector 100 is provided at the combustion chamber head of the gas turbine. The fuel injector 100 includes a central nozzle 1 and multiple peripheral nozzles 2. The multiple peripheral nozzles 2 are spaced apart around the central nozzle 1. The central nozzle 1 and each peripheral nozzle 2 operate independently of one another.

[0048] The combustion process of a gas turbine has a wide operating range depending on different power plants, compressor performance, and turbine performance. Typically, the operating process of a gas turbine includes an ignition phase, a speed increase phase, and a load increase phase. To adapt to the changing conditions of various power plants and match compressors and turbine performance with different efficiency levels, an embodiment of the present invention proposes a fuel staging method based on the aforementioned gas turbine, including the following:

[0049] During the ignition phase, the central nozzle 1 and / or at least one peripheral nozzle 2 are used;

[0050] In the speed increase phase, the central nozzle 1 and / or part of the peripheral nozzles 2 are used to operate until the speed of the gas turbine increases to a preset speed value;

[0051] During the load increase phase, the central nozzle 1 and at least part of the peripheral nozzles 2 are operated until the speed of the gas turbine increases to a preset load value.

[0052] The wide-range fuel staging method for a gas turbine proposed in an embodiment of the present invention achieves multiple speed and load increase paths by varying the operating nozzles. During the ignition and speed increase phases, the gas turbine's air volume is typically low, correspondingly resulting in a low fuel volume. Therefore, ignition and speed increase can be achieved using only the central nozzle, some peripheral nozzles, or a combination of the central and peripheral nozzles. During the load increase phase, as the fuel volume increases, it is necessary to gradually increase the number of nozzles in operation. Load increase can be achieved by increasing the number of central nozzles or by increasing the number of peripheral nozzles. Of course, speed increase can also be achieved by increasing the number of nozzles in operation during the speed increase phase. Therefore, the wide-range fuel staging method for a gas turbine proposed in an embodiment of the present invention, by adjusting the staging scheme of the central and peripheral nozzles, can achieve a variety of speed and load increase paths for the gas turbine without changing the combustion chamber structure. This provides the gas turbine with a wide operating range, adapting to different power plants, compressor performance, and turbine performance, meeting the requirements of various engine models, and satisfying gas turbine start-up, shutdown, operation, and environmental protection requirements.

[0053] Optionally, the air volume of the central nozzle 1 accounts for 10%-25% of the total air volume, and the air volume of the plurality of peripheral nozzles 2 accounts for 75%-90% of the total air volume.

[0054] In some embodiments, the operation of a gas turbine includes multiple speed-up stages, each corresponding to a different preset speed value. The final preset speed value is reached by sequentially completing the speed-up stages. For example, the operation of the gas turbine includes a first speed-up stage, a second speed-up stage, ..., which respectively match a first preset speed value r1, a second preset speed value r2, ..., until the final preset speed value. By sequentially completing the first speed-up stage, the second speed-up stage, ..., the speed of the gas turbine reaches the first preset speed value r1, the second preset speed value r2, ..., in stages, until the final preset speed value.

[0055] The fuel grading method specifically includes:

[0056] In the first speed increase stage, the central nozzle 1 and / or part of the peripheral nozzles 2 are used to operate until the speed of the gas turbine increases to a first preset speed value r1;

[0057] In the second speed increase stage, at least the nozzles in the first speed increase stage are kept in operation, and the central nozzle 1 and / or part of the peripheral nozzles 2 are added to operate until the speed of the gas turbine increases to a second preset speed value r2, where r2 is greater than r1;

[0058] Continue to add working nozzles until the speed reaches the final preset speed value.

[0059] For example, if the central nozzle 1 and some of the peripheral nozzles 2 are operated in the first speed increase stage, the speed can be further increased in the second speed increase stage by adding the remaining non-operating peripheral nozzles 2. If some of the peripheral nozzles 2 are operated in the first speed increase stage, the speed can be further increased in the second speed increase stage by adding the central nozzle 1 or the remaining non-operating peripheral nozzles 2.

[0060] In other alternative embodiments, the combustion amount is small, and only one grading method may be retained until the speed reaches the final preset speed value.

[0061] Optionally, the central nozzle 1 and the peripheral nozzles 2 are divided into 2-6 stages.

[0062] In some embodiments, the operation of the gas turbine includes multiple load-increasing stages, each corresponding to a different preset load value. The load-increasing stages are sequentially completed to match the final preset load value. For example, the operation of the gas turbine includes a first load-increasing stage, a second load-increasing stage, ..., which respectively match the first preset load value p1, the second preset load value p2, ..., until the final preset load value. By sequentially completing the first load-increasing stage, the second load-increasing stage, ..., the speed of the gas turbine reaches the first preset load value p1, the second preset load value p2, ..., in stages until the final preset load value.

[0063] The fuel grading method specifically includes:

[0064] In the first load increasing stage, the central nozzle 1 and part of the peripheral nozzles 2 are operated until the first preset load value p1 is matched;

[0065] In the second speed increase stage, at least the nozzles in the first load increase stage are kept in operation, and the remaining peripheral nozzles 2 are added to operate until a second preset load value p2 is matched, where p2 is greater than p1;

[0066] Continue adding peripheral nozzles until the final load value is matched.

[0067] Optionally, the central nozzle 1 and the peripheral nozzles 2 are divided into 2-6 stages.

[0068] Of course, in other alternative embodiments, in the first load increase stage, at least part of the peripheral nozzles 2 can be used to work until the first preset load value p1 is matched; in the second speed increase stage, the nozzles in the first load increase stage are retained, and the central nozzle 1 or the remaining peripheral nozzles 2 are added to work until the second preset load value p2 is matched.

[0069] The following is based on Figure 1-Figure 5Several specific embodiments of the wide-range fuel staging method for a gas turbine provided by the present invention are described. It should be noted that the staging scheme for the central nozzle 1 and the peripheral nozzle 2 can be designed based on the actual power plant, compressor performance, and turbine performance. The following embodiments are intended only as examples and are not intended to limit this application.

[0070] Example 1:

[0071] like Figure 1 As shown, the fuel injector 100 is equipped with a central nozzle 1 and six peripheral nozzles 2, which are evenly spaced around the central nozzle 1. The peripheral nozzles 2 include two first peripheral nozzles 21 and four second peripheral nozzles 22. They are arranged circumferentially in a pattern of first peripheral nozzle 21 - two second peripheral nozzles 22 - first peripheral nozzle 21 - two second peripheral nozzles 22. In this embodiment, the first peripheral nozzles 21 and the second peripheral nozzles 22 have the same structure, so the amount of air passing through the peripheral nozzles is essentially the same.

[0072] The wide-range fuel staging method for a gas turbine provided in this embodiment includes:

[0073] During the ignition phase, the central nozzle 1 and the first peripheral nozzle 21 are used;

[0074] In the speed increasing stage, the central nozzle 1 is used to gradually increase the speed to the final preset speed value;

[0075] In the first load increasing stage, the central nozzle 1 and the first peripheral nozzle 21 are operated until the first preset load value p1 is matched;

[0076] In the second load increasing stage, the central nozzle 1 and the first peripheral nozzle 21 are kept in operation, and the second peripheral nozzle 22 is increased in operation until a second preset load value p2 is matched, wherein p2 is greater than p1.

[0077] like Figure 2 As shown, the combustion amount in this embodiment is relatively low, so only the central nozzle 1 can be used during the entire speed increase process until the rated speed is reached.

[0078] Specifically, if Figure 3 As shown, the operation of the gas turbine in this embodiment has three speed-increasing stages: the first speed-increasing stage, the second speed-increasing stage, and the third speed-increasing stage. The speed value reached in the first speed-increasing stage is matched to a first preset speed value r1; the speed value reached in the second speed-increasing stage is matched to a second preset speed value r2; and the speed value reached in the third speed-increasing stage is matched to a final preset speed value, i.e., the full speed value. Among them, r2 is greater than r1, and the final preset speed value is greater than r2.

[0079] During the speed increase phase, the fuel staging method specifically includes:

[0080] In the first speed increase stage, the central nozzle 1 is used to increase the speed of the gas turbine to a first preset speed value r1;

[0081] In the second speed increase stage, the central nozzle 1 is kept in operation to increase the speed of the gas turbine to a second preset speed value r2;

[0082] In the third speed increase stage, the central nozzle 1 continues to operate until the speed reaches the final preset speed value.

[0083] Furthermore, if Figure 3 As shown, the operation of the gas turbine in this embodiment has two load-increasing stages, namely, a first load-increasing stage and a second load-increasing stage. The load value reached in the first load-increasing stage is matched to a first preset load value p1; the load value reached in the second load-increasing stage is matched to a second preset load value p2. Wherein, p2 is greater than p1.

[0084] During the load ramp-up phase, the fuel staging method specifically includes:

[0085] In the first load increase stage, two first peripheral nozzles 21 are added to operate, and the flame of the burning central nozzle 1 is transferred to the two first peripheral nozzles 21 for combustion. The central nozzle 1 and the two first peripheral nozzles 21 are operated until the first preset load value p1 is matched.

[0086] In the second load increase phase, the central nozzle 1 and the two first peripheral nozzles 21 are kept in operation, and 2-4 second peripheral nozzles 22 are added to operate until the second preset load value p2 is matched, thereby gradually matching the final load point.

[0087] In other alternative embodiments, in the first load-increasing stage, two second peripheral nozzles 22 may be added to operate, or one first peripheral nozzle 21 and one second peripheral nozzle 22 may be added to operate, and the present invention does not impose any restrictions thereto.

[0088] Of course, in other embodiments, the number of peripheral nozzles 2 can be other, and the number of first peripheral nozzles 21 and second peripheral nozzles 22 can also be other. The number and position of the additional peripheral nozzles 22 in different speed increase stages and different load increase stages can be designed according to actual conditions.

[0089] Optionally, the number of the peripheral nozzles 2 is 6-8.

[0090] In other alternative embodiments, during the ignition stage, the central nozzle 1 and the second peripheral nozzle 22 are used for operation, or, during the ignition stage, the central nozzle 1 , the first peripheral nozzle 21 and the second peripheral nozzle 22 are used for operation.

[0091] Example 2:

[0092] like Figure 1 As shown, the central nozzle 1 and the six peripheral nozzles 2 of the fuel injector 100 are similar to those in the first embodiment, and are not described in detail here, and only the differences are described.

[0093] The wide-range fuel staging method for a gas turbine provided in this embodiment includes:

[0094] During the ignition phase, the central nozzle 1 and the first peripheral nozzle 21 are used;

[0095] In the speed increase phase, the central nozzle 1 is operated until the speed reaches the first preset speed value r1, and then the central nozzle 1 is kept in operation, and the first peripheral nozzle 21 is added to operate until the speed of the gas turbine reaches the final preset speed value, wherein the final preset speed value is greater than r1;

[0096] In the first load increasing stage, the central nozzle 1 and the first peripheral nozzle 21 are operated until the first preset load value p1 is matched;

[0097] In the second load increasing stage, the central nozzle 1 and the first peripheral nozzle 21 are kept in operation, and the second peripheral nozzle is increased in operation until a second preset load value p2 is matched, wherein p2 is greater than p1.

[0098] like Figure 2 As shown, the combustion volume in this embodiment is relatively high, so the single central nozzle 1 cannot bring the gas turbine to the rated speed. Therefore, in the speed increase stage, the first peripheral nozzle 21 is added to increase the speed of the gas turbine to the final preset speed value.

[0099] Specifically, if Figure 4 As shown, the operation of the gas turbine in this embodiment has three speed-increasing stages: the first speed-increasing stage, the second speed-increasing stage, and the third speed-increasing stage. The speed value reached in the first speed-increasing stage is matched to a first preset speed value r1; the speed value reached in the second speed-increasing stage is matched to a second preset speed value r2; and the speed value reached in the third speed-increasing stage is matched to a final preset speed value, i.e., the full speed value. Among them, r2 is greater than r1, and the final preset speed value is greater than r2.

[0100] In the first speed increase stage, the central nozzle 1 is used to operate until the speed reaches the first preset speed value r1;

[0101] In the second speed increase stage, the central nozzle 1 is kept in operation, and two first peripheral nozzles 21 are added to operate until the speed of the gas turbine increases to a second preset speed value r2;

[0102] In the third speed increase stage, the central nozzle 1 and the two first peripheral nozzles 21 are kept in operation until the speed of the gas turbine increases to a final preset speed value.

[0103] Furthermore, if Figure 4 As shown, the operation of the gas turbine in this embodiment has two load-increasing stages, namely, a first load-increasing stage and a second load-increasing stage. The load value reached in the first load-increasing stage is matched to a first preset load value p1; the load value reached in the second load-increasing stage is matched to a second preset load value p2. Wherein, p2 is greater than p1.

[0104] During the load ramp-up phase, the fuel staging method specifically includes:

[0105] In the first load increasing stage, the central nozzle 1 and the two first peripheral nozzles 21 are kept in operation until the first preset load value p1 is matched;

[0106] In the second load increase phase, the central nozzle 1 and the two first peripheral nozzles 21 are kept in operation, and 2-4 second peripheral nozzles 22 are added to operate until the second preset load value p2 is matched, thereby gradually matching the final load point.

[0107] Example 3:

[0108] like Figure 1 As shown, the central nozzle 1 and the six peripheral nozzles 2 of the fuel injector 100 are similar to those in the first embodiment, and will not be described in detail here, and only the differences will be described.

[0109] The wide-range fuel staging method for a gas turbine provided in this embodiment includes:

[0110] During the ignition phase, the central nozzle 1 and the first peripheral nozzle 21 are used;

[0111] In the speed increasing stage, the first peripheral nozzle 21 is used to operate until the final preset speed value;

[0112] In the first load increasing stage, the central nozzle 1 and the first peripheral nozzle 21 are operated until the first preset load value p1 is matched;

[0113] In the second load increasing stage, the central nozzle 1 and the first peripheral nozzle 21 are kept in operation, and the second peripheral nozzle 22 is increased in operation until a second preset load value p2 is matched, wherein p2 is greater than p1.

[0114] like Figure 2 As shown, the combustion rate in this embodiment is moderate, so a single center nozzle 1 cannot bring the gas turbine to rated speed. If the center nozzle 1 is used at the load, the fuel rate is too low. If the center nozzle 1 is used with two first peripheral nozzles 21, the fuel rate is too high. Therefore, the first peripheral nozzle 21 can be used to operate until the gas turbine reaches rated speed, and then the center nozzle 1 and the second peripheral nozzle 22 can be added until the final load point is matched.

[0115] Specifically, if Figure 5As shown, the operation of the gas turbine in this embodiment has three speed-increasing stages: the first speed-increasing stage, the second speed-increasing stage, and the third speed-increasing stage. The speed value reached in the first speed-increasing stage is matched to a first preset speed value r1; the speed value reached in the second speed-increasing stage is matched to a second preset speed value r2; and the speed value reached in the third speed-increasing stage is matched to a final preset speed value, i.e., the full speed value. Among them, r2 is greater than r1, and the final preset speed value is greater than r2.

[0116] In the first speed increasing stage, the two first peripheral nozzles 21 are used to operate until the speed reaches the first preset speed value r1;

[0117] In the second speed increasing stage, the two first peripheral nozzles 21 are kept in operation until the speed of the gas turbine increases to a second preset speed value r2;

[0118] In the third speed increasing stage, the two first peripheral nozzles 21 are kept in operation until the speed of the gas turbine increases to a final preset speed value.

[0119] Furthermore, if Figure 5 As shown, the operation of the gas turbine in this embodiment has two load-increasing stages, namely, a first load-increasing stage and a second load-increasing stage. The load value reached in the first load-increasing stage is matched to a first preset load value p1; the load value reached in the second load-increasing stage is matched to a second preset load value p2. Wherein, p2 is greater than p1.

[0120] During the load ramp-up phase, the fuel staging method specifically includes:

[0121] In the first load increasing stage, the central nozzle 1 and the two first peripheral nozzles 21 are kept in operation until the first preset load value p1 is matched;

[0122] In the second load increase phase, the central nozzle 1 and the two first peripheral nozzles 21 are kept in operation, and 2-4 second peripheral nozzles 22 are added to operate until the second preset load value p2 is matched, thereby gradually matching the final load point.

[0123] Furthermore, an embodiment of the present invention also provides a method for protecting an igniter.

[0124] The igniter 3 of the gas turbine provided in the embodiment of the present invention is arranged near one of the peripheral nozzles 2, and the wide range fuel staging method for the gas turbine further includes:

[0125] During the ignition phase, at least the peripheral nozzle 2 close to the igniter 3 and the central nozzle 1 or another peripheral nozzle 2 are used to work. The peripheral nozzle 2 close to the igniter 3 is ignited. After the flame is transferred to the working central nozzle 1 and / or other peripheral nozzles 2, the peripheral nozzle 2 close to the igniter 2 is closed to protect the igniter 3.

[0126] When the pressure in the combustion chamber rises to a certain level, the igniter 3 automatically rebounds and moves away from the peripheral nozzle 2, and then the peripheral nozzle 2 can be used normally.

[0127] At least the peripheral nozzle 2 near the igniter 3 and the central nozzle 1 or another peripheral nozzle 2 are used for operation, which means: at least the peripheral nozzle 2 near the igniter 3 and the central nozzle 1 are used for operation, at least the peripheral nozzle 2 near the igniter 3 and another peripheral nozzle 2 are used for operation, and in some embodiments, the peripheral nozzle 2 near the igniter 3, the central nozzle 1 and at least one peripheral nozzle 2 at other positions are used for operation.

[0128] In some embodiments, during the ignition stage, at least the central nozzle 1 and the peripheral nozzle 2 near the igniter 3 are used to work, the peripheral nozzle 2 near the igniter 3 is ignited, and after the flame is transferred to the central nozzle 1, the peripheral nozzle 2 near the igniter 3 is closed.

[0129] For example, Figure 1 As shown, igniter 3 is positioned near a second peripheral nozzle 22. During ignition, at least this second peripheral nozzle 22 and the central nozzle 1 are activated. After the second peripheral nozzle 22 ignites and the flame is transferred to the central nozzle 1, the second peripheral nozzle 22 is closed, thereby protecting igniter 3. When the pressure in the combustion chamber rises to a certain level, igniter 3 automatically rebounds. At this time, the second peripheral nozzle 22, which is closer to igniter 3, is activated again without affecting the safety of igniter 3.

[0130] In some embodiments, during the ignition stage, the central nozzle 1 and the peripheral nozzle 2 near the igniter 3 are used to work, the peripheral nozzle 2 near the igniter 3 is ignited, and after the flame is transferred to the central nozzle 1, the peripheral nozzle 2 near the igniter 3 is closed, and at least one peripheral nozzle 2 away from the igniter 3 is worked, and after the flame of the central nozzle 1 is transferred to the working peripheral nozzle 2, the central nozzle 1 is closed.

[0131] For example, Figure 1 As shown, the igniter 3 is positioned near a second peripheral nozzle 22. During ignition, at least the second peripheral nozzle 22 and the central nozzle 1 are activated. After the second peripheral nozzle 22 is ignited and the flame is transferred to the central nozzle 1, the second peripheral nozzle 22 is closed, thereby protecting the igniter 3. Subsequently, the first peripheral nozzle 21 and / or the second peripheral nozzle 22, located away from the igniter 3, are activated. After the flame from the central nozzle 1 is transferred to these peripheral nozzles 2, the central nozzle 1 is closed, allowing the gas turbine to increase its speed while the peripheral nozzles 2 are in operation. This ignition method is applicable to Example 3.

[0132] In some embodiments, during the ignition stage, all peripheral nozzles 2 are operated, the peripheral nozzle 2 close to the igniter 3 is ignited, and after the flame is transferred to other peripheral nozzles 2, the peripheral nozzle 2 close to the igniter 3 is closed.

[0133] For example, Figure 1 As shown, the igniter 3 is positioned near a second peripheral nozzle 22. During ignition, all peripheral nozzles 2 (including the first peripheral nozzle 21 and the second peripheral nozzle 22) are activated. After the second peripheral nozzle 22 near the igniter 3 is ignited, the flame is transferred to the other peripheral nozzles 2, igniting all peripheral nozzles 2. Next, at least the second peripheral nozzle 22 near the igniter 3 is closed, and preferably, both a first peripheral nozzle 21 and a second peripheral nozzle 22 adjacent to the second peripheral nozzle 22 are closed, leaving only the peripheral nozzles 22 away from the igniter 3. This allows the gas turbine to increase its speed while the peripheral nozzles 2 are operating without affecting the safety of the igniter 3. The above ignition method can be applied to Example 3.

[0134] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0135] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "plurality" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0136] In the present invention, unless otherwise specified or limited, the terms "installed," "connected," "connect," "fixed," etc. should be understood in a broad sense. For example, they can refer to fixed connection, detachable connection, or integration; mechanical connection, electrical connection, or communication; direct connection or indirect connection through an intermediate medium; internal communication between two elements or interaction between two elements, unless otherwise specified. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0137] In the present invention, unless otherwise expressly specified or limited, when a first feature is "above" or "below" a second feature, it may mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediary. Furthermore, when a first feature is "above," "above," or "above" a second feature, it may mean that the first feature is directly above or diagonally above the second feature, or simply means that the first feature is at a higher level than the second feature. When a first feature is "below," "below," or "below" a second feature, it may mean that the first feature is directly below or diagonally below the second feature, or simply means that the first feature is at a lower level than the second feature.

[0138] In the present invention, the terms "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and the features of different embodiments or examples without contradiction.

[0139] Although the embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and are not to be construed as limitations on the present invention. A person skilled in the art may change, modify, replace and modify the above embodiments within the scope of the present invention.

Claims

1. A method for wide-range fuel staging of a gas turbine, characterized in that: The gas turbine adopts a premixed combustion mode. A fuel injector is provided at the combustion chamber head of the gas turbine. The fuel injector includes a central nozzle and a plurality of peripheral nozzles spaced around the central nozzle. The central nozzle and each peripheral nozzle operate independently. The fuel staging method includes: During the ignition phase, the central nozzle and / or at least one of the peripheral nozzles are used for operation; During the speed increase phase, the central nozzle and / or part of the peripheral nozzles are operated until the speed of the gas turbine reaches a preset speed value; During a load increase phase, the central nozzle and at least a portion of the peripheral nozzles are operated until the speed of the gas turbine reaches a preset load value; The igniter of the gas turbine is arranged at a position close to one of the peripheral nozzles, and the wide range fuel staging method for the gas turbine further comprises: During the ignition phase, at least the peripheral nozzle close to the igniter and the central nozzle or another peripheral nozzle are used to operate, the peripheral nozzle close to the igniter is ignited, and after the flame is transferred to the operating central nozzle and / or other peripheral nozzles, the peripheral nozzle close to the igniter is closed; When the pressure in the combustion chamber rises to a certain level, the igniter automatically rebounds and moves away from the peripheral nozzle.

2. The method for wide-range fuel staging for a gas turbine according to claim 1, wherein: The operation of the gas turbine has multiple speed-up stages, each speed-up stage corresponds to a different preset speed value, and the final preset speed value is reached by completing the speed-up stages in sequence. The fuel staging method specifically includes: In the first speed increase stage, the central nozzle and / or part of the peripheral nozzles are used to operate until the speed of the gas turbine increases to a first preset speed value r1; In the second speed increase stage, at least the nozzles in the first speed increase stage are kept in operation, and the central nozzle and / or part of the peripheral nozzles are added to operate until the speed of the gas turbine increases to a second preset speed value r2, wherein r2 is greater than r1; Continue to add working nozzles until the speed reaches the final preset speed value.

3. The method for wide-range fuel staging for a gas turbine according to claim 1, wherein: The operation of the gas turbine has multiple load-raising stages, each of which corresponds to a different preset load value. The load-raising stages are completed in sequence to match the final preset load value. The fuel staging method specifically includes: In the first load increasing stage, the central nozzle and part of the peripheral nozzles are operated until a first preset load value p1 is matched; In the second load increasing stage, at least the nozzles in the first load increasing stage are kept in operation, and the remaining peripheral nozzles are added to operate until a second preset load value p2 is matched, wherein p2 is greater than p1; Continue adding peripheral nozzles until the final load value is matched.

4. The method for wide-range fuel staging for a gas turbine according to any one of claims 1 to 3, characterized in that: The peripheral nozzles include a plurality of first peripheral nozzles and a plurality of second peripheral nozzles, and the fuel staging method includes: During the ignition phase, the central nozzle and the first peripheral nozzle are used for operation; In the speed increasing stage, the central nozzle is used to gradually increase the speed to a final preset speed value; In the first load increasing stage, the central nozzle and the first peripheral nozzle are operated until a first preset load value p1 is matched; In the second load increasing stage, the central nozzle and the first peripheral nozzle are kept in operation, and the second peripheral nozzle is increased in operation until a second preset load value p2 is matched, wherein p2 is greater than p1.

5. The method for wide-range fuel staging for a gas turbine according to any one of claims 1 to 3, characterized in that: The peripheral nozzles include a plurality of first peripheral nozzles and a plurality of second peripheral nozzles, and the fuel staging method includes: During the ignition phase, the central nozzle and the first peripheral nozzle are used for operation; In the speed increase phase, the central nozzle is operated until the speed reaches a first preset speed value r1, the central nozzle is maintained, and the first peripheral nozzles are increased to operate until the speed of the gas turbine reaches a final preset speed value, wherein the final preset speed value is greater than r1; In the first load increasing stage, the central nozzle and the first peripheral nozzle are operated until a first preset load value p1 is matched; In the second load increasing stage, the central nozzle and the first peripheral nozzle are kept in operation, and the second peripheral nozzle is increased in operation until a second preset load value p2 is matched, wherein p2 is greater than p1.

6. The method for wide-range fuel staging for a gas turbine according to any one of claims 1 to 3, characterized in that: The peripheral nozzles include a plurality of first peripheral nozzles and a plurality of second peripheral nozzles, and the fuel staging method includes: During the ignition phase, the central nozzle and the first peripheral nozzle are used for operation; During the speed increasing stage, the first peripheral nozzle is used to operate until the final preset speed value; In the first load increasing stage, the central nozzle and the first peripheral nozzle are operated until a first preset load value p1 is matched; In the second load increasing stage, the central nozzle and the first peripheral nozzle are kept in operation, and the second peripheral nozzle is increased in operation until a second preset load value p2 is matched, wherein p2 is greater than p1.

7. The method for wide-range fuel staging for a gas turbine according to claim 1, wherein: The air volume of the central nozzle accounts for 10%-25% of the total air volume, and the air volume of the multiple peripheral nozzles accounts for 75%-90% of the total air volume.

8. The method for wide-range fuel staging for a gas turbine according to claim 1, wherein: During the ignition stage, at least the central nozzle and the peripheral nozzles close to the igniter are used to work, the peripheral nozzles close to the igniter are ignited, and after the flame is transferred to the central nozzle, the peripheral nozzles close to the igniter are closed.

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