A gas turbine

Abstract

The application discloses a gas turbine, comprising: a dual fuel channel; a plurality of dual fuel nozzles; a second gas fuel channel and a gas fuel ignition nozzle, the second gas fuel channel being communicated with the gas fuel ignition nozzle; a second liquid fuel channel and a liquid fuel ignition nozzle, the second liquid fuel channel being communicated with the liquid fuel ignition nozzle; a compressed air channel; a gas fuel module for opening or closing the gas fuel channel; a liquid fuel module for opening or closing the liquid fuel channel; and an air bleed module for opening or closing the compressed air channel. The application sets the liquid fuel ignition nozzle and the gas fuel ignition nozzle, so that when fuel gas of a sea platform is insufficient, ignition can be based on the liquid fuel ignition nozzle, and when fuel gas of the sea platform is sufficient, ignition can be based on the gas fuel ignition nozzle; and the dual fuel channel and the dual fuel nozzle are further set, so that fuel can be switched during operation, and stable operation is ensured.

Description

Technical Field

[0001] This application relates to the field of gas turbines, and more particularly to a gas turbine. Background Technology

[0002] Currently, gas turbines are often used on offshore platforms. When gas turbines are used on offshore platforms, they can be ignited and operated using fuel gas extracted from the offshore platform. However, there is a shortage of fuel gas extracted from offshore platforms. Therefore, during the ignition, start-up and operation phases of the gas turbine, when there is insufficient fuel gas, it will lead to abnormal ignition, start-up and operation of the gas turbine. Utility Model Content

[0003] This application proposes a gas turbine designed to address the problems of abnormal ignition and start-up and abnormal operation of gas turbines when they are used on offshore platforms and the fuel gas extracted from the offshore platform is insufficient.

[0004] In this application embodiment, a gas turbine is proposed, comprising:

[0005] A dual-fuel channel, comprising a first gaseous fuel channel and a first liquid fuel channel;

[0006] Multiple dual-fuel nozzles, each of which is connected to the dual-fuel channel, the dual-fuel nozzles including gas fuel nozzles and liquid fuel nozzles, each gas fuel nozzle being connected to the first gas fuel channel, and each liquid fuel nozzle being connected to the first liquid fuel channel;

[0007] A second gas fuel passage and a gas fuel ignition nozzle, wherein the second gas fuel passage is connected to the gas fuel ignition nozzle;

[0008] A second liquid fuel passage and a liquid fuel ignition nozzle, wherein the second liquid fuel passage is connected to the liquid fuel ignition nozzle;

[0009] The compressed air passage includes a first passage, a second passage, a third passage, and a fourth passage. The first passage is connected to the atomizing air passage of each of the dual-fuel nozzles. The second passage is connected to the first gaseous fuel passage. The third passage is connected to the first liquid fuel passage. The fourth passage is connected to the second liquid fuel passage.

[0010] A gas fuel module is used to open or close the first gas fuel channel and the second gas fuel channel;

[0011] The liquid fuel module is used to open or close the first liquid fuel channel and the second liquid fuel channel;

[0012] The air intake module is used to open or close the first channel, the second channel, the third channel, and the fourth channel.

[0013] In this embodiment of the application, the first gas fuel channel is connected to each of the gas fuel nozzles and is used to supply fuel gas to each of the gas fuel nozzles during ignition based on gas fuel ignition and gas fuel operation, and to maintain the supply of fuel gas to each of the gas fuel nozzles after successful ignition and after successful start-up.

[0014] The second gas fuel channel is connected to the gas fuel ignition nozzle and is used to supply fuel gas to the gas fuel ignition nozzle during ignition based on gas fuel ignition and gas fuel operation, and to stop supplying fuel gas to the gas fuel ignition nozzle after successful ignition.

[0015] The third channel is connected to each of the liquid fuel nozzles and is used to supply compressed air to each of the liquid fuel nozzles after successful start-up based on gas fuel ignition and gas fuel operation.

[0016] In this embodiment of the application, the second gaseous fuel channel is connected to the gaseous fuel ignition nozzle and is used to supply fuel gas to the gaseous fuel ignition nozzle during ignition based on gaseous fuel ignition and based on liquid fuel operation; after successful ignition, the supply of fuel gas to the gaseous fuel ignition nozzle is stopped.

[0017] The first liquid fuel channel is connected to each of the liquid fuel nozzles and is used to supply liquid fuel to each of the liquid fuel nozzles during ignition based on gas fuel ignition and based on liquid fuel operation; after successful ignition, the supply of liquid fuel to each of the liquid fuel nozzles is maintained; after successful start-up, the supply of liquid fuel to each of the liquid fuel nozzles is maintained.

[0018] The first channel is connected to the atomizing air channel of each of the dual-fuel nozzles and is used to supply compressed air to the atomizing air channel of each of the dual-fuel nozzles after successful start-up based on gas fuel ignition and liquid fuel operation.

[0019] The second channel is connected to the first gaseous fuel channel and is used to supply compressed air to the first gaseous fuel channel after a successful start-up based on gaseous fuel ignition and liquid fuel operation.

[0020] In this embodiment of the application, the first liquid fuel channel is connected to each of the liquid fuel nozzles and is used to supply liquid fuel to each of the liquid fuel nozzles during ignition based on liquid fuel ignition and operation; after successful ignition, the supply of liquid fuel to each of the liquid fuel nozzles is maintained; after successful start-up, the supply of liquid fuel to each of the liquid fuel nozzles is maintained.

[0021] The second liquid fuel channel is connected to the liquid fuel ignition nozzle and is used to supply liquid fuel to the liquid fuel ignition nozzle during ignition based on liquid fuel ignition and operation; after successful ignition, the supply of liquid fuel to the liquid fuel ignition nozzle is stopped.

[0022] The first channel is connected to the atomizing air channel of each of the dual-fuel nozzles, and is used to supply compressed air to the atomizing air channel of each of the dual-fuel nozzles after successful ignition based on liquid fuel ignition and operation.

[0023] The fourth channel is connected to the liquid fuel ignition nozzle, and the fourth channel is provided with a first gear, which is used to supply compressed air to the liquid fuel ignition nozzle at the supply amount or supply time corresponding to the first gear after successful ignition based on liquid fuel ignition and operation, and to stop supplying compressed air after reaching the supply amount or supply time corresponding to the first gear.

[0024] The second channel is connected to the first gaseous fuel channel and is used to supply compressed air to the first gaseous fuel channel after successful start-up based on liquid fuel ignition and operation.

[0025] In this embodiment of the application, the second liquid fuel channel is connected to the liquid fuel ignition nozzle and is used to supply liquid fuel to the liquid fuel ignition nozzle during ignition based on liquid fuel and gas fuel operation; after successful ignition, the supply of liquid fuel to the liquid fuel ignition nozzle is stopped.

[0026] The first gas fuel channel is connected to each of the gas fuel nozzles and is used to supply fuel gas to each of the gas fuel nozzles during ignition based on liquid fuel ignition and gas fuel operation; after successful ignition, it continues to supply gas fuel to each of the gas fuel nozzles; after successful start-up, it continues to supply gas fuel to each of the gas fuel nozzles.

[0027] The fourth channel is connected to the liquid fuel ignition nozzle, and the fourth channel is provided with a second gear, which is used to supply compressed air to the liquid fuel ignition nozzle at the supply amount or supply time corresponding to the second gear after successful ignition based on liquid fuel ignition and gas fuel operation, and to stop supplying compressed air after reaching the supply amount or supply time corresponding to the second gear.

[0028] The third channel is connected to the first liquid fuel channel and is used to supply compressed air to the first liquid fuel channel after successful start-up of the gas fuel-based operation based on liquid fuel ignition.

[0029] In this embodiment of the application, the bleed gas module is configured to: shut down the second channel before switching from liquid fuel to gaseous fuel;

[0030] The first liquid fuel channel is provided with a first liquid fuel supply position, a second liquid fuel supply position, and a third liquid fuel supply position. The first liquid fuel supply position is used to reduce the liquid fuel supplied by the first liquid fuel channel to each liquid fuel nozzle to 90%-95% of the rated supply amount during the first stage of switching from liquid fuel to gaseous fuel, according to the deceleration rate corresponding to the first liquid fuel supply position. The second liquid fuel supply position is used to reduce the liquid fuel supplied by the first liquid fuel channel to each liquid fuel nozzle to 5%-10% of the rated supply amount during the second liquid fuel supply position, according to the deceleration rate corresponding to the second liquid fuel supply position. The third liquid fuel supply position is used to reduce the liquid fuel supplied by the first liquid fuel channel to each liquid fuel nozzle to 0 during the third stage of switching from liquid fuel to gaseous fuel, according to the deceleration rate corresponding to the third liquid fuel supply position. The absolute values ​​of the deceleration rates corresponding to the first and third liquid fuel supply positions gradually increase, while the deceleration rate corresponding to the second liquid fuel supply position is a fixed value.

[0031] The first gas fuel channel is provided with a first gas fuel supply setting, a second gas fuel supply setting, and a third gas fuel supply setting. The first gas fuel supply setting is used to increase the liquid fuel supplied by the first gas fuel channel to each gas fuel nozzle to 5%-10% of the rated operating supply amount according to the acceleration corresponding to the first gas fuel supply setting during the first stage of switching from liquid fuel to gas fuel. The second gas fuel supply setting is used to increase the gas fuel supplied by the first gas fuel channel to each gas fuel nozzle to 90-90% of the rated operating supply amount according to the acceleration corresponding to the second gas fuel supply setting. The third gas fuel supply setting is used to increase the gas fuel supplied by the first gas fuel channel to each gas fuel nozzle to the rated supply amount according to the acceleration corresponding to the third gas fuel supply setting during the third stage of switching from liquid fuel to gas fuel. The acceleration corresponding to the first and third gas fuel supply settings gradually increases, while the acceleration corresponding to the second gas fuel supply setting is a fixed value.

[0032] After the switching is completed, the gas fuel module is configured to maintain the first gas fuel channel supplying fuel gas to each of the gas fuel nozzles; the bleed air module is also configured to open the third channel to supply compressed air to the first liquid fuel channel.

[0033] In this embodiment of the application, the bleed gas module is configured to: close the third channel and open the first channel before switching from gaseous fuel to liquid fuel;

[0034] The first gas fuel channel is provided with a fourth gas fuel supply position, a fifth gas fuel supply position, and a sixth gas fuel supply position. The first gas fuel supply position is used to reduce the liquid fuel supplied by the first gas fuel channel to each gas fuel nozzle to 90%-95% of the rated supply amount during the first stage of switching from gaseous fuel to liquid fuel, according to the deceleration corresponding to the fourth gas fuel supply position. The fifth gas fuel supply position is used to reduce the gaseous fuel supplied by the first gas fuel channel to each gas fuel nozzle to 5%-10% of the rated supply amount during the first stage of switching from gaseous fuel to liquid fuel, according to the deceleration corresponding to the sixth gas fuel supply position. The sixth gas fuel supply position is used to reduce the gaseous fuel supplied by the first gas fuel channel to each gas fuel nozzle to 0 during the third stage of switching from gaseous fuel to liquid fuel, according to the deceleration corresponding to the sixth gas fuel supply position. The absolute values ​​of the deceleration corresponding to the fourth and sixth gas fuel supply positions gradually increase, while the deceleration corresponding to the fifth gas fuel supply position is a fixed value.

[0035] The first liquid fuel channel is provided with a fourth liquid fuel supply position, a fifth liquid fuel supply position, and a sixth liquid fuel supply position. The fourth liquid fuel supply position is used to increase the liquid fuel supplied by the first liquid fuel channel to each liquid fuel nozzle to 5%-10% of the rated operating supply amount according to the acceleration corresponding to the fourth liquid fuel supply position during the first stage of switching from gaseous fuel to liquid fuel. The fifth liquid fuel supply position is used to increase the liquid fuel supplied by the first liquid fuel channel to each liquid fuel nozzle to 90-90% of the rated operating supply amount according to the acceleration corresponding to the fifth gaseous fuel supply position during the second stage of switching from gaseous fuel to liquid fuel. The sixth liquid fuel supply position is used to increase the gaseous fuel supplied by the first liquid fuel channel to each liquid fuel nozzle to the rated supply amount according to the acceleration corresponding to the sixth liquid fuel supply position during the third stage of switching from gaseous fuel to liquid fuel. The accelerations corresponding to the fourth and sixth liquid fuel supply positions gradually increase, while the acceleration corresponding to the fifth liquid fuel supply position is a fixed value.

[0036] After the switching is completed, the air intake module is also configured to: open the second channel and supply compressed air to the first gas fuel channel.

[0037] In this embodiment of the application, the gas turbine further includes:

[0038] A pressure relief channel is provided, which is connected to the combustion chamber of the gas turbine. The pressure relief channel is provided with multiple pressure relief branches, and each pressure relief branch is provided with a pneumatic valve. The pneumatic valve is used to open or close its corresponding pressure relief branch.

[0039] Multiple control channels are provided, one end of each control channel is connected to the compressed air channel, and the other end is connected to the pneumatic valve on each of the pressure relief branches. Each control channel is equipped with a solenoid valve, which is used to open or close the control channel to supply compressed air to the corresponding pneumatic valve.

[0040] In this embodiment of the application, the pressure relief channel includes: a first pressure relief branch, a second pressure relief branch, and a third pressure relief branch;

[0041] The control channel includes a first control channel, a second control channel, and a third control channel, wherein the first control channel, the second control channel, and the third control channel correspond to the first pressure relief branch, the second pressure relief branch, and the third pressure relief branch, respectively.

[0042] The solenoid valve on the first control channel is connected to the pneumatic valve on the first pressure relief branch, and is used to supply compressed air to the pneumatic valve on the first pressure relief branch when the rotational speed of the gas turbine shaft reaches the first preset speed, and to stop supplying compressed air when the rotational speed of the gas turbine shaft drops to the second preset speed.

[0043] The solenoid valve on the second control channel is connected to the pneumatic valve on the second pressure relief branch, and is used to supply compressed air to the pneumatic valve on the second pressure relief branch when the rotational speed of the gas turbine shaft reaches the third preset speed, and to stop supplying compressed air when the rotational speed of the gas turbine shaft drops to the second preset speed.

[0044] The solenoid valve on the third control channel is connected to the pneumatic valve on the third pressure relief branch, and is used to supply compressed air to the pneumatic valve on the third pressure relief branch when the rotational speed of the gas turbine shaft reaches the fourth preset speed, and to stop supplying compressed air when the rotational speed of the gas turbine shaft drops to the second preset speed.

[0045] The first preset speed, the third preset speed, and the fourth preset speed are all different and all greater than the second preset speed.

[0046] In this embodiment of the application, the gas turbine further includes a friction speed reduction module, which includes a multi-stage friction assembly. Each stage of the friction assembly includes a speed-reducing friction wheel and a speed-reducing friction plate. The speed-reducing friction wheel in each stage of the friction assembly is located on the rotating shaft of the gas turbine, and the speed-reducing friction plate in each stage of the friction assembly is located on the periphery of the speed-reducing friction wheel of the same stage.

[0047] The thickness of the deceleration friction wheel in each friction assembly and the gap between the deceleration friction wheel and the deceleration friction plate are used to ensure that the deceleration friction wheel in each friction assembly contacts the deceleration friction plate when the rotational speed of the gas turbine shaft reaches the preset rotational speed corresponding to each friction assembly.

[0048] In this embodiment of the application, the friction reduction module includes: a first-stage friction assembly, a second-stage friction assembly, and a third-stage friction assembly;

[0049] The deceleration friction wheel in the first-stage friction assembly has a first thickness and a first gap between the deceleration friction wheel and the deceleration friction plate, so that when the rotational speed of the gas turbine shaft reaches a fifth preset speed, the deceleration friction wheel in the first-stage friction assembly deforms to contact the deceleration friction plate.

[0050] The deceleration friction wheel in the second-stage friction assembly has a second thickness and a second gap between the deceleration friction wheel and the deceleration friction plate. When the rotational speed of the gas turbine shaft reaches a sixth preset speed, the deceleration friction wheel in the second-stage friction assembly deforms to contact the deceleration friction plate.

[0051] The deceleration friction wheel in the third-stage friction assembly has a third thickness and a third gap between the deceleration friction wheel and the deceleration friction plate. When the rotational speed of the gas turbine shaft reaches a seventh preset speed, the deceleration friction wheel in the third-stage friction assembly deforms to contact the deceleration friction plate.

[0052] The fifth preset speed, the sixth preset speed, and the seventh preset speed are all different.

[0053] In this embodiment, the output shaft of the gas turbine is connected to the input shaft of the generator via a coupling. A torque-limiting friction wheel is provided on the output shaft, and two opposing torque-limiting friction plates are provided on the coupling. The torque-limiting friction wheel is positioned between the two torque-limiting friction plates, and a preset static friction force exists between the two torque-limiting friction plates and the torque-limiting friction wheel. This preset static friction force is used to keep the two torque-limiting friction plates and the torque-limiting friction wheel relatively stationary when the torque of the gas turbine output shaft is less than a preset value, and to allow relative sliding between the two torque-limiting friction plates and the torque-limiting friction wheel when the torque of the gas turbine output shaft reaches the preset value.

[0054] In this embodiment of the application, the outer surface of the gas turbine blades is provided with a zirconium oxide layer, and a nickel-chromium-chromium carbide layer is also provided on the surface of the zirconium oxide layer.

[0055] In this embodiment, by setting up liquid fuel ignition nozzles and gas fuel ignition nozzles, ignition can be performed based on liquid fuel ignition nozzles when the fuel gas on the offshore platform is insufficient, and ignition can also be performed based on gas fuel ignition nozzles when the fuel gas on the offshore platform is sufficient. Furthermore, a dual fuel channel and dual fuel nozzles are set up so that the fuel can be switched when the fuel gas or liquid fuel is insufficient during operation, ensuring that the gas turbine can operate stably. Attached Figure Description

[0056] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0057] Figure 1This is a schematic diagram of the structure of a gas turbine in one embodiment of this application.

[0058] Explanation of reference numerals in the attached figures:

[0059] 100-Gas turbine, 101-Combustion chamber, 102-Blade, 103-Shaft, 110-Dual fuel nozzle, 111-Atomizing air passage, 120-First liquid fuel passage, 121-Second liquid fuel passage, 130-First gaseous fuel passage, 131-Second gaseous fuel passage, 140-Liquid fuel ignition nozzle, 141-Gaseous fuel ignition nozzle, 150-Compressed air passage, 151-First passage, 152-Second passage, 153-Third passage, 154- Fourth channel, 155-First control channel, 156-Second control channel, 157-Third control channel, 158-Solenoid valve, 160-First pressure relief branch, 161-Second pressure relief branch, 162-Third pressure relief branch, 163-Pneumatic valve, 170-Friction reduction module, 171-First-stage friction assembly, 172-Second friction assembly, 173-Third-stage friction assembly, 174-Speed ​​reduction friction wheel, 175-Speed ​​reduction friction plate, 180-Torque limiting friction wheel, 181-Torque limiting friction plate.

[0060] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0061] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of the embodiments. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.

[0062] It should be noted that if the embodiments of this application involve directional indicators (such as up, down, left, right, front, back, etc.), the directional indicators are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicators will also change accordingly.

[0063] Furthermore, if the embodiments of this application involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, features defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the technical solutions of various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. If the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed in this application.

[0064] like Figure 1 As shown in the figure, this application provides a gas turbine 100, comprising:

[0065] A dual-fuel channel, the dual-fuel channel including a first gaseous fuel channel 130 and a first liquid fuel channel 120;

[0066] Multiple dual-fuel nozzles 110 are provided, each of which is connected to the dual-fuel channel. Each dual-fuel nozzle 110 includes a gas fuel nozzle and a liquid fuel nozzle. Each gas fuel nozzle is connected to the first gas fuel channel 130, and each liquid fuel nozzle is connected to the first liquid fuel channel 120.

[0067] The second gas fuel passage 131 and the gas fuel ignition nozzle 141 are connected to the gas fuel ignition nozzle 141.

[0068] The second liquid fuel passage 121 and the liquid fuel ignition nozzle 140 are connected to the liquid fuel ignition nozzle 140.

[0069] The compressed air passage 150 includes a first passage 151, a second passage 152, a third passage 153, and a fourth passage 154. The first passage 151 is connected to the atomizing air passage 111 of each of the dual-fuel nozzles 110. The second passage 152 is connected to the first gaseous fuel passage 130. The third passage 153 is connected to the first liquid fuel passage 120. The fourth passage 154 is connected to the second liquid fuel passage 121.

[0070] A gas fuel module is used to open or close the first gas fuel channel 130 and the second gas fuel channel 131.

[0071] The liquid fuel module is used to open or close the first liquid fuel channel 120 and the second liquid fuel channel 121;

[0072] The air intake module is used to open or close the first channel 151, the second channel 152, the third channel 153, and the fourth channel 154.

[0073] In this embodiment, the gas turbine 100 has multiple flame tubes, each flame tube containing a dual-fuel nozzle 110, and the flame tubes are arranged in a ring array, such as... Figure 1 As shown, Figure 1 Only one of the dual-fuel nozzles 110 in the flame tube is shown. The dual-fuel channel is connected to each dual-fuel nozzle 110 in the flame tube. The first gaseous fuel channel 130 in the dual-fuel channel is connected to a fuel gas source and its opening and closing are controlled by a gaseous fuel module. Additionally, the gaseous fuel module can control the flow rate of the fuel gas supplied to the first gaseous fuel channel 130. The first liquid fuel channel 120 in the dual-fuel channel is connected to a liquid fuel source and its opening and closing are controlled by a liquid fuel module. Additionally, the liquid fuel module can control the flow rate of the liquid fuel supplied to the first liquid fuel channel 120.

[0074] Continue to refer to Figure 1 In this embodiment of the application, a second gas fuel channel 131 and a second liquid fuel channel 121 are also provided. The second gas fuel channel 131 is also connected to the gas fuel source and its opening or closing and flow rate are controlled by the gas fuel module. The second liquid fuel channel 121 is connected to the liquid fuel source and its opening or closing and flow rate are controlled by the liquid fuel module.

[0075] In addition, in this embodiment of the application, the gas turbine 100 is also provided with a liquid fuel ignition nozzle 140 and a gas fuel ignition nozzle 141. The liquid fuel ignition nozzle 140 and the gas fuel ignition nozzle 141 are both located outside each flame tube and can be connected to any flame tube through an ignition pipe. Since all flame tubes are connected, when ignition is performed through the liquid fuel ignition nozzle 140 or the gas fuel ignition nozzle 141, the ignited flame is guided to any flame tube through the ignition pipe, so that the liquid fuel or fuel gas in each flame tube can be ignited.

[0076] Continue to refer to Figure 1 The second liquid fuel passage 121 is connected to the liquid fuel ignition nozzle 140, providing liquid fuel for ignition to the liquid fuel ignition nozzle 140; the second gas fuel passage 131 is connected to the gas fuel ignition nozzle 141, providing gas fuel for ignition to the gas fuel ignition nozzle 141.

[0077] Continue to refer to Figure 1In this embodiment of the application, each channel included in the compressed air channel 150 is used to provide compressed air to each component of the gas turbine 100, and the bleed air module controls the opening or closing of each channel. For example, the first channel 151 is connected to the atomizing air channel 111 of the dual-fuel nozzles 110 in each flame tube, and is used to provide compressed air to each dual-fuel nozzle 110 to improve the atomization effect of the liquid fuel sprayed by each dual-fuel nozzle 110; the second channel 152 is connected to the first gas fuel channel 130 in the dual-fuel channel, and is used to cool the gas fuel nozzles in each dual-fuel nozzle 110 when running solely on liquid fuel; the third channel 153 is connected to the first liquid fuel channel 120 in the dual-fuel channel, and is used to purge the liquid fuel remaining in the liquid fuel nozzles in each dual-fuel nozzle 110, or to cool the liquid fuel nozzles in each dual-fuel nozzle 110 when running solely on gas fuel; the fourth channel 154 is connected to the second liquid fuel channel 121, and is used to purge the liquid fuel in the liquid fuel ignition nozzle 140 after ignition and start-up based on the liquid fuel ignition nozzle 140.

[0078] In this embodiment, by providing a liquid fuel ignition nozzle 140 and a gas fuel ignition nozzle 141, ignition can be performed using the liquid fuel ignition nozzle 140 when the fuel gas supply to the offshore platform is insufficient, and ignition can also be performed using the gas fuel ignition nozzle 141 when the fuel gas supply to the offshore platform is sufficient. Furthermore, a dual fuel channel and a dual fuel nozzle 110 are provided, so that the fuel can be switched when the fuel gas supply or the liquid fuel supply is insufficient during operation, ensuring that the gas turbine 100 can operate stably.

[0079] In this embodiment, ignition can be performed based on the gaseous fuel ignition nozzle 141, and operation can be based on gaseous fuel, such as... Figure 1 As shown,

[0080] The first gas fuel passage 130 is connected to each of the gas fuel nozzles and is used to supply fuel gas to each of the gas fuel nozzles during ignition based on gas fuel ignition and operation based on gas fuel. After successful ignition, the supply of fuel gas to each of the gas fuel nozzles is maintained. After successful start-up, the supply of fuel gas to each of the gas fuel nozzles is maintained.

[0081] The second gas fuel passage 131 is connected to the gas fuel ignition nozzle 141 and is used to supply fuel gas to the gas fuel ignition nozzle 141 during ignition based on gas fuel ignition and gas fuel operation, and to stop supplying fuel gas to the gas fuel ignition nozzle 141 after successful ignition.

[0082] The third channel 153 is connected to each of the liquid fuel nozzles and is used to supply compressed air to each of the liquid fuel nozzles after successful ignition and start-up based on gas fuel.

[0083] The gas turbine 100 can be divided into three stages from ignition to operation: the ignition stage, the start-up stage after successful ignition, and the operation stage after successful start-up. During gaseous fuel ignition and operation, in the ignition stage, the gaseous fuel module opens the first gaseous fuel channel 130 and the second gaseous fuel channel 131. The gaseous fuel ignition nozzle 141 ignites the fuel gas supplied by the second gaseous fuel channel 131. The ignited flame is guided to each flame tube and then ignites the fuel gas injected by the gaseous fuel nozzle in the dual fuel nozzle 110 of each flame tube. After successful ignition, the start-up phase begins. At this stage, the gas fuel module closes the second gas fuel passage 131, maintaining only the first gas fuel passage 130 supplying fuel gas to the gas fuel nozzles in each flame tube for gas turbine 100 startup. After successful startup, the operation phase begins. During this phase, the gas fuel module continues to supply fuel gas to the gas fuel nozzles in each flame tube via the first gas fuel passage 130, and can also change the operating conditions of the gas turbine 100 by altering the rate of fuel gas supply through the first gas fuel passage 130. Additionally, after successful startup, the bleed air module opens the third passage 153 to supply compressed air to the liquid fuel nozzles of each dual-fuel nozzle 110 to reduce the temperature of each liquid fuel nozzle.

[0084] In this embodiment, ignition can also be performed based on the gaseous fuel ignition nozzle 141, and operation can be based on liquid fuel, such as... Figure 1 As shown, the second gaseous fuel passage 131 is connected to the gaseous fuel ignition nozzle 141 and is used to supply fuel gas to the gaseous fuel ignition nozzle 141 during ignition based on gaseous fuel ignition and liquid fuel operation; after successful ignition, the supply of fuel gas to the gaseous fuel ignition nozzle 141 is stopped.

[0085] The first liquid fuel channel 120 is connected to each of the liquid fuel nozzles and is used to supply liquid fuel to each of the liquid fuel nozzles during ignition based on gas fuel ignition and liquid fuel operation; after successful ignition, it continues to supply liquid fuel to each of the liquid fuel nozzles; after successful start-up, it continues to supply liquid fuel to each of the liquid fuel nozzles.

[0086] The first channel 151 is connected to the atomizing air channel of each of the dual-fuel nozzles 110, and is used to supply compressed air to the atomizing air channel of each of the dual-fuel nozzles 110 after successful start-up based on gas fuel ignition and liquid fuel operation.

[0087] The second channel 152 is connected to the first gas fuel channel 130 and is used to supply compressed air to the first gas fuel channel 130 after successful start-up based on gas fuel ignition and liquid fuel operation.

[0088] In the case of gas fuel ignition, the liquid fuel module opens the first liquid fuel channel 120 to supply liquid fuel to the liquid fuel nozzles of each flame tube, and the gas fuel module opens the second gas fuel channel 131 to supply fuel gas to the gas fuel ignition nozzle 141 for ignition. The ignited flame is guided to each flame tube to ignite the atomized liquid fuel in each flame tube. After successful ignition, the start-up phase begins. At this time, the gas fuel module closes the second gas fuel channel 131, while the liquid fuel module maintains the first liquid fuel channel 120 to supply liquid fuel to each flame tube. The first channel 151 maintains the supply of compressed air to improve the atomization degree of the liquid fuel in each flame tube. After successful start-up, the operation phase begins. At this time, the liquid fuel module continues to maintain the first liquid fuel channel 120 to supply liquid fuel to each flame tube, and can also change the operating conditions of the gas turbine 100 by changing the rate at which the first liquid fuel channel 120 supplies liquid fuel. The bleed air module maintains the supply of compressed air to the first channel 151 to continuously improve the atomization degree of the liquid fuel in each flame tube, and opens the second channel 152 to supply compressed air to the first gas fuel channel 130 to reduce the temperature of the gas fuel nozzle in the dual fuel nozzle 110 in each flame tube.

[0089] In this embodiment of the application, ignition can also be based on the liquid fuel ignition nozzle 140, and operation can be based on liquid fuel, such as... Figure 1 As shown, the first liquid fuel channel 120 is connected to each of the liquid fuel nozzles and is used to supply liquid fuel to each of the liquid fuel nozzles during ignition based on liquid fuel ignition and operation; after successful ignition, it continues to supply liquid fuel to each of the liquid fuel nozzles; after successful start-up, it continues to supply liquid fuel to each of the liquid fuel nozzles.

[0090] The second liquid fuel channel 121 is connected to the liquid fuel ignition nozzle 140 and is used to supply liquid fuel to the liquid fuel ignition nozzle 140 during ignition based on liquid fuel ignition and operation; after successful ignition, the supply of liquid fuel to the liquid fuel ignition nozzle 140 is stopped.

[0091] The first channel 151 is connected to the atomizing air channel of each of the dual-fuel nozzles 110, and is used to supply compressed air to the atomizing air channel of each of the dual-fuel nozzles 110 after successful ignition based on liquid fuel ignition and operation.

[0092] The fourth channel 154 is connected to the liquid fuel ignition nozzle 140, and the fourth channel 154 is provided with a first gear, which is used to supply compressed air to the liquid fuel ignition nozzle 140 at the supply amount or supply time corresponding to the first gear after successful ignition based on liquid fuel ignition and operation, and to stop supplying compressed air after reaching the supply amount or supply time corresponding to the first gear.

[0093] The second channel 152 is connected to the first gas fuel channel 130 and is used to supply compressed air to the first gas fuel channel 130 after successful start-up based on liquid fuel ignition and operation.

[0094] In the liquid fuel-based ignition and operation phase, during the ignition phase, the liquid fuel module opens the first liquid fuel channel 120 and the second liquid fuel channel 121. The liquid fuel ignition nozzle 140 ignites based on the liquid fuel supplied by the second liquid fuel channel 121. The ignited flame is guided to each flame tube, thereby igniting the liquid fuel sprayed by the liquid fuel nozzles in the dual fuel nozzles 110 of each flame tube. After successful ignition, the start-up phase begins. At this time, the liquid fuel module can close the second liquid fuel channel 121, maintaining only the first liquid fuel channel 120 supplying liquid fuel to each flame tube. In addition, after successful ignition, the bleed air module opens the first channel 151 to supply compressed air to the dual fuel nozzles 110 in each flame to improve the atomization degree of the liquid fuel in each flame tube, and opens the fourth channel 154 to the first position to purge the residual liquid fuel in the liquid fuel ignition nozzle 140. After reaching the compressed air supply time or supply amount corresponding to the first position, the fourth channel 154 is closed. After successful startup, the system enters the operation phase. At this time, the liquid fuel module continues to supply liquid fuel to each flame tube through the first liquid fuel channel 120. It can also change the operating conditions of the gas turbine 100 by changing the rate at which liquid fuel is supplied through the first liquid fuel channel 120. Meanwhile, the first channel 151 continues to supply compressed air to each flame tube, continuously improving the atomization degree of the liquid fuel in each flame tube. In addition, the second channel 152 is opened to supply compressed air to the first gas fuel channel 130 of the dual-fuel channel to reduce the temperature of the gas fuel nozzle in the dual-fuel nozzle 110 in each flame tube.

[0095] In this embodiment of the application, ignition can also be based on liquid fuel ignition nozzle 140, and operation can be based on gaseous fuel, such as... Figure 1 As shown, the second liquid fuel channel 121 is connected to the liquid fuel ignition nozzle 140 and is used to supply liquid fuel to the liquid fuel ignition nozzle 140 during ignition based on liquid fuel ignition and gas fuel operation; after successful ignition, the supply of liquid fuel to the liquid fuel ignition nozzle 140 is stopped.

[0096] The first gas fuel passage 130 is connected to each of the gas fuel nozzles and is used to supply fuel gas to each of the gas fuel nozzles during ignition based on liquid fuel ignition and gas fuel operation; after successful ignition, it continues to supply gas fuel to each of the gas fuel nozzles; after successful start-up, it continues to supply gas fuel to each of the gas fuel nozzles.

[0097] The fourth channel 154 is connected to the liquid fuel ignition nozzle 140, and the fourth channel 154 is provided with a second gear, which is used to supply compressed air to the liquid fuel ignition nozzle 140 at the supply amount or supply time corresponding to the second gear after successful ignition based on liquid fuel ignition and gas fuel operation, and to stop supplying compressed air after reaching the supply amount or supply time corresponding to the second gear.

[0098] The third channel 153 is connected to the first liquid fuel channel 120 and is used to supply compressed air to the first liquid fuel channel 120 after successful start-up of the gas fuel-based operation based on liquid fuel ignition.

[0099] In the liquid fuel ignition and gas fuel operation, during ignition, the liquid fuel module opens the second liquid fuel channel 121, and the gas fuel module opens the first gas fuel channel 130. The liquid fuel ignition nozzle 140 ignites based on the liquid fuel supplied by the second liquid fuel channel 121. After the ignition flame is guided to each flame tube, it ignites the fuel gas injected by the gas fuel nozzle in the dual fuel nozzle 110 of each flame tube. After successful ignition, the start-up phase begins. At this time, the liquid fuel module can close the second liquid fuel channel 121 and maintain the first gas fuel channel 130 supplying fuel gas to each flame tube. In addition, after successful ignition, the bleed air module also opens the fourth channel 154 to the second position, supplying compressed air at the corresponding supply amount or supply time of the second position to the liquid fuel ignition nozzle 140 to purge the liquid fuel remaining in the liquid fuel ignition nozzle 140. The supply is closed after the corresponding supply amount or supply time of the second position is reached. It should be noted that the supply amount or supply time corresponding to the first position and the second position can be the same. After a successful start-up, the gas fuel module continues to supply fuel gas to each flame tube through the first gas fuel channel 130, and can also change the operating conditions of the gas turbine 100 by changing the rate at which the first gas fuel channel 130 supplies fuel gas; in addition, the third channel 153 is opened to supply compressed air to the first liquid fuel channel 120 of the dual fuel channel in order to reduce the temperature of the liquid fuel nozzle in the dual fuel nozzle 110 in each flame tube.

[0100] The gas turbine 100 in this application can also switch fuels during operation, such as switching from liquid fuel to gaseous fuel, or vice versa.

[0101] For the switch from liquid fuel to gaseous fuel

[0102] like Figure 1 As shown in this embodiment, the bleed gas module is configured to shut down the second channel 152 before switching from liquid fuel to gaseous fuel;

[0103] The first liquid fuel channel 120 is provided with a first liquid fuel supply position, a second liquid fuel supply position, and a third liquid fuel supply position. The first liquid fuel supply position is used to reduce the liquid fuel supplied by the first liquid fuel channel 120 to each liquid fuel nozzle to 90%-95% of the rated supply amount during operation, according to the deceleration corresponding to the first liquid fuel supply position, in the first stage when switching from liquid fuel to gaseous fuel. The second liquid fuel supply position is used to reduce the liquid fuel supplied by the first liquid fuel channel 120 to each liquid fuel nozzle to 5%-10% of the rated supply amount during operation, according to the deceleration corresponding to the second liquid fuel supply position. The third liquid fuel supply position is used to reduce the liquid fuel supplied by the first liquid fuel channel 120 to each liquid fuel nozzle to 0 during the third stage when switching from liquid fuel to gaseous fuel, according to the deceleration corresponding to the third liquid fuel supply position. The absolute values ​​of the deceleration corresponding to the first liquid fuel supply position and the third liquid fuel supply position gradually increase, while the deceleration corresponding to the second liquid fuel supply position is a fixed value.

[0104] The first gas fuel channel 130 is provided with a first gas fuel supply position, a second gas fuel supply position, and a third gas fuel supply position. The first gas fuel supply position is used to increase the liquid fuel supplied by the first gas fuel channel 130 to each gas fuel nozzle to 5%-10% of the rated supply amount during operation, according to the acceleration corresponding to the first gas fuel supply position, in the first stage when switching from liquid fuel to gas fuel. The second gas fuel supply position is used to increase the gas fuel supplied by the first gas fuel channel 130 to each gas fuel nozzle to 90-90% of the rated supply amount during operation, according to the acceleration corresponding to the second gas fuel supply position. The third gas fuel supply position is used to increase the gas fuel supplied by the first gas fuel channel 130 to each gas fuel nozzle to the rated supply amount during the third stage when switching from liquid fuel to gas fuel, according to the acceleration corresponding to the third gas fuel supply position. The accelerations corresponding to the first and third gas fuel supply positions gradually increase, while the acceleration corresponding to the second gas fuel supply position is a fixed value.

[0105] After the switching is completed, the gas fuel module is configured to maintain the first gas fuel channel 130 supplying fuel gas to each of the gas fuel nozzles; the bleed air module is also configured to open the third channel 153 to supply compressed air to the first liquid fuel channel 120.

[0106] When the gas turbine 100 is running on liquid fuel, the second channel 152 continuously supplies compressed gas to the first gas fuel channel 130 to reduce the temperature of the gas fuel nozzle in the dual fuel nozzle 110 in each combustion chamber. Therefore, when switching from liquid fuel to gas fuel, the second channel 152 needs to be closed first.

[0107] After closing the second channel 152, the switching process can be divided into three stages. Assuming that under the same operating conditions, when the gas turbine 100 operates solely on liquid fuel, the liquid fuel supply of the first liquid fuel channel 120 is M1, and when operating solely on gas fuel, the fuel gas supply of the first gas fuel channel 130 is M2, then in this embodiment, in the first stage, the liquid fuel module adjusts the first liquid fuel channel 120 to the first liquid fuel supply position. Under the deceleration of the first liquid fuel supply position, it rapidly reduces the liquid fuel supply of the first liquid fuel channel 120 to 0.9M1-0.95M1 at the fastest speed. Simultaneously, the gas fuel module opens the first gas fuel channel 130 to the first gas fuel supply position. Under the acceleration of the first gas fuel supply position, it rapidly increases the fuel gas supply of the first gas fuel channel 130 to 0.05M2-0.1M2 at the fastest speed. In the second stage, the liquid fuel module adjusts the first liquid fuel channel... In the third stage, the liquid fuel module adjusts the first liquid fuel channel 120 to the second liquid fuel supply position. The deceleration of the second liquid fuel supply position is a fixed value, that is, the liquid fuel supply of the first liquid fuel channel 120 is reduced uniformly to 0.05M1-0.1M1. At the same time, the gas fuel module adjusts the first gas fuel channel 130 to the second gas fuel supply position. The acceleration of the second gas fuel supply position is a fixed value, that is, the fuel gas supply of the first gas fuel channel 130 is increased uniformly to 0.9M2-0.95M2. In the third stage, the liquid fuel module adjusts the first liquid fuel channel 120 to the third liquid fuel supply position. Under the deceleration of the third liquid fuel supply position, the liquid fuel supply of the first liquid fuel channel 120 is reduced rapidly to 0 at the fastest speed. At the same time, the gas fuel module adjusts the first gas fuel channel 130 to the third gas fuel supply position. Under the acceleration of the third gas fuel supply position, the fuel gas supply of the first gas fuel channel 130 is increased rapidly to M2 at the fastest speed. In this embodiment of the application, with the gas fuel module and liquid fuel module configured in this way, the gas turbine 100 can always maintain stable operation during each stage of switching from liquid fuel to gas fuel.

[0108] In addition, after the switching is completed, the gas fuel module is also configured to: maintain the first gas fuel channel 130 to supply fuel gas to the gas fuel nozzle at a supply rate of M2, and maintain the subsequent gas turbine 100 to operate stably according to the operating conditions based on liquid fuel operation. At the same time, the bleed air module opens the third channel 153 to supply compressed air to the first liquid fuel channel 120 to reduce the temperature of the liquid fuel nozzle in the dual fuel nozzle 110 in each flame tube.

[0109] For the switch from gaseous fuel to liquid fuel

[0110] like Figure 1As shown in this embodiment, the bleed gas module is configured to: close the third channel 153 and open the first channel 151 before switching from gaseous fuel to liquid fuel;

[0111] The first gas fuel channel 130 is provided with a fourth gas fuel supply position, a fifth gas fuel supply position, and a sixth gas fuel supply position. The first gas fuel supply position is used to reduce the liquid fuel supplied by the first gas fuel channel 130 to each gas fuel nozzle to 90%-95% of the rated supply amount during operation, according to the deceleration corresponding to the fourth gas fuel supply position, in the first stage when switching from gaseous fuel to liquid fuel. The fifth gas fuel supply position is used to reduce the gaseous fuel supplied by the first gas fuel channel 130 to each gas fuel nozzle to 5%-10% of the rated supply amount during operation, according to the deceleration corresponding to the fifth gas fuel supply position. The sixth gas fuel supply position is used to reduce the gaseous fuel supplied by the first gas fuel channel 130 to each gas fuel nozzle to 0 during the third stage when switching from gaseous fuel to liquid fuel, according to the deceleration corresponding to the sixth gas fuel supply position. The absolute values ​​of the deceleration corresponding to the fourth and sixth gas fuel supply positions gradually increase, while the deceleration corresponding to the fifth gas fuel supply position is a fixed value.

[0112] The first liquid fuel channel 120 is provided with a fourth liquid fuel supply position, a fifth liquid fuel supply position, and a sixth liquid fuel supply position. The fourth liquid fuel supply position is used to, in the first stage of switching from gaseous fuel to liquid fuel, increase the liquid fuel supplied by the first liquid fuel channel 120 to each liquid fuel nozzle to 5%-10% of the rated supply amount during operation, according to the acceleration corresponding to the fourth liquid fuel supply position. The fifth liquid fuel supply position is used to, in the second stage of switching from gaseous fuel to liquid fuel, increase the liquid fuel supplied by the first liquid fuel channel 120 to each liquid fuel nozzle to 5%-10% of the rated supply amount during operation, according to the acceleration corresponding to the fifth gaseous fuel supply position. The first liquid fuel supply channel 120 is used to increase the liquid fuel supplied to each liquid fuel nozzle to 90-90% of the rated supply amount during operation. The sixth liquid fuel supply level is used to increase the gaseous fuel supplied to each liquid fuel nozzle by the first liquid fuel supply channel 120 to the rated supply amount according to the acceleration corresponding to the sixth liquid fuel supply level during the third stage of switching from gaseous fuel to liquid fuel. The acceleration corresponding to the fourth and sixth liquid fuel supply levels gradually increases, while the acceleration corresponding to the fifth liquid fuel supply level is a fixed value.

[0113] After the switching is completed, the air intake module is also configured to: open the second channel 152 and supply compressed air to the first gas fuel channel 130.

[0114] In this configuration, when the gas turbine 100 is operating on gaseous fuel, the third channel 153 continuously supplies compressed gas to the first liquid fuel channel 120 to reduce the temperature of the liquid fuel nozzles in the dual-fuel nozzles 110 of each combustion chamber. Therefore, when switching from gaseous fuel to liquid fuel, the third channel 153 must first be closed. Additionally, when switching to liquid fuel, the first channel 151 must be opened to provide compressed air to the atomizing air channels 111 of each dual-fuel nozzle 110 to improve the atomization degree of the liquid fuel injected by each liquid fuel nozzle.

[0115] After closing the third channel 153 and opening the first channel 151, the switching process can be divided into three stages. Similarly, taking the gas turbine 100 operating under the same conditions, with the liquid fuel supply of the first liquid fuel channel 120 being M1 when operating solely on liquid fuel and the fuel gas supply of the first gas fuel channel 130 being M2 when operating solely on gas fuel as an example, in this embodiment, in the first stage, the gas fuel module adjusts the first gas fuel channel 130 to the fourth gas fuel supply position. Under the deceleration of the fourth gas fuel supply position, the fuel gas supply of the first gas fuel channel 130 is rapidly reduced to 0.9M2-0.95M2 at the fastest speed. Simultaneously, the liquid fuel module opens the first liquid fuel channel 120 to the fourth liquid fuel supply position. Under the acceleration of the fourth liquid fuel supply position, the liquid fuel supply of the first liquid fuel channel 120 is rapidly increased to 0.05M1-0.1M1 at the fastest speed. In the second stage, the gas fuel module adjusts the first gas fuel channel 130 to the fifth gas fuel supply position. In the first stage, the gas fuel module adjusts the first gas fuel channel 120 to the fifth gas fuel supply position. The deceleration corresponding to the fifth gas fuel supply position is a fixed value, that is, the fuel gas supply of the first gas fuel channel 130 is reduced at a constant speed to 0.05M2-0.1M2. At the same time, the liquid fuel module adjusts the first liquid fuel channel 120 to the fifth liquid fuel supply position. The acceleration of the fifth liquid fuel supply position is a fixed value, that is, the liquid fuel supply of the first liquid fuel channel 120 is increased at a constant speed to 0.9M1-0.95M1. In the third stage, the gas fuel module adjusts the first gas fuel channel 130 to the sixth gas fuel supply position. Under the deceleration of the sixth gas fuel supply position, the fuel gas supply of the first gas fuel channel 130 is reduced to 0 at the fastest speed. At the same time, the liquid fuel module adjusts the first liquid fuel channel 120 to the sixth liquid fuel supply position. Under the acceleration of the sixth liquid fuel supply position, the liquid fuel supply of the first liquid fuel channel 120 is increased to M1 at the fastest speed. In this embodiment of the application, with the gas fuel module and liquid fuel module configured in this way, the gas turbine 100 can always maintain stable operation during each stage of switching from gas fuel to liquid fuel.

[0116] In addition, after the switching is completed, the liquid fuel module is also configured to: maintain the first liquid fuel channel 120 to supply fuel gas to the liquid fuel nozzle at a supply rate of M1, and maintain the subsequent gas turbine 100 to operate stably according to the operating conditions based on gas fuel operation. At the same time, the bleed air module opens the second channel 152 to supply compressed air to the first gas fuel channel 130 to reduce the temperature of the gas fuel nozzle in the dual fuel nozzle 110 in each flame tube.

[0117] When the gas turbine 100 is operating on an offshore platform, it will also face the problem of sudden load changes. For example, when the gas turbine 100 is operating on an offshore platform, it drives the generator to generate electricity to power various electrical equipment on the offshore platform. However, the power of each electrical equipment on the offshore platform is relatively large. When the electrical equipment stops normally or in an emergency, it will cause a significant reduction in load. At this time, it is necessary to quickly reduce the power output of the gas turbine 100. Otherwise, the turbine of the gas turbine 100 will accelerate in a short period of time and there is a risk of over-speed.

[0118] Therefore, such as Figure 1 As shown in the embodiments of this application, the gas turbine 100 further includes:

[0119] The pressure relief channel is connected to the combustion chamber 101 of the gas turbine 100. The pressure relief channel is provided with multiple pressure relief branches, and each pressure relief branch is provided with a pneumatic valve 163. The pneumatic valve 163 is used to open or close its corresponding pressure relief branch.

[0120] Multiple control channels are provided, one end of each control channel is connected to the compressed air channel 150, and the other end is connected to the pneumatic valve 163 on each of the pressure relief branches. Each control channel is equipped with a solenoid valve 158, which is used to open or close the control channel to supply compressed air to the corresponding pneumatic valve 163.

[0121] like Figure 1 As shown in this embodiment, by setting multiple pressure relief branches, when the load of the gas turbine 100 suddenly decreases, the number of pressure relief branches that can be opened can be selected according to the degree of turbine overspeed after the load decreases, so as to quickly reduce the output power of the gas turbine 100 and thus avoid turbine overspeed. Specifically, the higher the turbine speed after the sudden load change of the gas turbine 100, the more pressure relief branches will be opened.

[0122] like Figure 1 As shown in the embodiment of this application, the pressure relief channel includes: a first pressure relief branch 160, a second pressure relief branch 161, and a third pressure relief branch 162;

[0123] The control channels include: a first control channel 155, a second control channel 156, and a third control channel 157, wherein the first control channel 155, the second control channel 156, and the third control channel 157 correspond to the first pressure relief branch 160, the second pressure relief branch 161, and the third pressure relief branch 162, respectively.

[0124] The solenoid valve 158 on the first control channel 155 is connected to the pneumatic valve on the first pressure relief branch 160, and is used to supply compressed air to the pneumatic valve 163 on the first pressure relief branch 160 when the rotational speed of the gas turbine 100 shaft 103 reaches the first preset speed, and to stop supplying compressed air when the rotational speed of the gas turbine 100 shaft 103 drops to the second preset speed.

[0125] The solenoid valve 158 on the second control channel 156 is connected to the pneumatic valve 163 on the second pressure relief branch 161, and is used to supply compressed air to the pneumatic valve 163 on the second pressure relief branch 161 when the rotational speed of the gas turbine 100 shaft 103 reaches the third preset speed, and to stop supplying compressed air when the rotational speed of the gas turbine 100 shaft 103 drops to the second preset speed.

[0126] The solenoid valve 158 on the third control channel 157 is connected to the pneumatic valve 163 on the third pressure relief branch 162, and is used to supply compressed air to the pneumatic valve 163 on the third pressure relief branch 162 when the rotational speed of the gas turbine 100 shaft 103 reaches the fourth preset speed, and to stop supplying compressed air when the rotational speed of the gas turbine 100 shaft 103 drops to the second preset speed.

[0127] The first preset speed, the third preset speed, and the fourth preset speed are all different and all greater than the second preset speed.

[0128] The rotational speed of the turbine driving the shaft 103 during normal operation of the gas turbine 100 is the second preset speed. Assuming the second preset speed is 3000 rpm, the first preset speed is 3100 rpm, the third preset speed is 3300 rpm, and the fourth preset speed is 3500 rpm.

[0129] When the shaft 103 of the gas turbine 100 is running at a speed of 3000 rpm driven by the turbine, the first pressure relief branch 160, the second pressure relief branch 161 and the third pressure relief branch 162 do not need to be opened.

[0130] When the shaft 103 of the gas turbine 100 operates at a speed greater than or equal to 3100 rpm under the drive of the turbine, the first pressure relief branch 160 is opened to release the pressure in the combustion chamber 101 and reduce the turbine speed. When the speed of the shaft 103 of the gas turbine 100 drops to 3000 rpm, the first pressure relief branch 160 can be closed. Assuming that after opening the first pressure relief branch 160, the speed of the shaft 103 of the gas turbine 100 continues to rise, reaching 3300 rpm, opening only the first pressure relief branch 160 is insufficient to reduce the turbine speed. In this case, the second pressure relief branch 161 is opened, meaning that two pressure relief branches simultaneously relieve pressure in the combustion chamber 101 until the speed of the shaft 103 of the gas turbine 100 drops to 3000 rpm. At this point, both the first and second pressure relief branches 160 can be closed. Furthermore, assuming that after opening the first pressure relief branch 160 and the second pressure relief branch 161, the rotational speed of the gas turbine 100 shaft 103 continues to rise and reaches 3500 rpm, it means that opening the two pressure relief branches cannot quickly reduce the turbine speed of the gas turbine 100. In this case, the third pressure relief branch 162 is opened, and the three pressure relief branches simultaneously depressurize the combustion chamber 101 until the rotational speed of the gas turbine 100 shaft 103 drops to 3000 rpm. At this point, the first pressure relief branch 160, the second pressure relief branch 161, and the third pressure relief branch 162 can be closed.

[0131] Additionally, it should be noted that the aforementioned first preset speed of 3100 rpm, second preset speed of 3000 rpm, third preset speed of 3300 rpm, and fourth preset speed of 3500 rpm are merely illustrative examples. The specific values ​​of the first to fourth preset speeds can be set based on the actual operating conditions of the gas turbine 100.

[0132] Continue to refer to Figure 1In this embodiment, each pressure relief branch can be controlled based on the pneumatic valve 163 on each pressure relief branch and the solenoid valve 158 on the corresponding control channel. For example, the first pressure relief branch 160 is connected to the first control channel 155. One end of the first control channel 155 is connected to the compressed air channel 150, and the other end is connected to the pneumatic valve 163 on the first pressure relief branch 160 through the solenoid valve 158. The solenoid valve 158 on the first control channel 155 can be set to open when the gas turbine 100 reaches a first preset speed. At this time, the first control channel 155 starts to supply compressed air to the pneumatic valve 163 on the first pressure relief branch 160. The compressed air can make the pneumatic valve 163 open. Valve 163 opens, allowing the high-pressure gas in combustion chamber 101 to be released from the first pressure relief branch 160. In addition, the solenoid valve 158 on the first control channel 155 is configured to close when the speed of gas turbine 100 drops to a second preset speed. When the solenoid valve 158 closes, the first control channel 155 stops supplying compressed air to the pneumatic valve 163 on the first pressure relief branch 160, the pneumatic valve 163 on the first pressure relief branch 160 closes, and the first pressure relief branch 160 stops depressurizing.

[0133] Similarly, the second pressure relief branch 161 is connected to the second control channel 156. One end of the second control channel 156 is connected to the compressed air channel 150, and the other end is connected to the pneumatic valve 163 on the second pressure relief branch 161 via a solenoid valve 158. The solenoid valve 158 on the second control channel 156 can be set to open when the gas turbine 100 reaches a third preset speed. At this time, the second control channel 156 begins to supply compressed air to the pneumatic valve 163 on the second pressure relief branch 161. The compressed air can make the pneumatic valve 163... Valve 163 opens, allowing the high-pressure gas in combustion chamber 101 to be released from the second pressure relief branch 161. In addition, the solenoid valve 158 on the second control channel 156 is configured to close when the speed of gas turbine 100 drops to a second preset speed. When the solenoid valve 158 closes, the second control channel 156 stops supplying compressed air to the pneumatic valve 163 on the second pressure relief branch 161, the pneumatic valve 163 on the second pressure relief branch 161 closes, and the second pressure relief branch 161 stops depressurizing.

[0134] Similarly, the third pressure relief branch 162 is connected to the third control channel 157. One end of the third control channel 157 is connected to the compressed air channel 150, and the other end is connected to the pneumatic valve 163 on the third pressure relief branch 162 via a solenoid valve 158. The solenoid valve 158 on the third control channel 157 can be set to open when the gas turbine 100 reaches a fourth preset speed. At this time, the third control channel 157 begins to supply compressed air to the pneumatic valve 163 on the third pressure relief branch 162. The compressed air can make the pneumatic valve... Valve 163 opens, allowing the high-pressure gas in combustion chamber 101 to be released from the third pressure relief branch 162. In addition, the solenoid valve 158 on the third control channel 157 is configured to close when the speed of gas turbine 100 drops to a second preset speed. When the solenoid valve 158 closes, the third control channel 157 stops supplying compressed air to the pneumatic valve 163 on the third pressure relief branch 162, the pneumatic valve 163 on the third pressure relief branch 162 closes, and the third pressure relief branch 162 stops depressurizing.

[0135] In addition to relieving pressure through the aforementioned pressure relief branch to reduce the turbine speed of the gas turbine 100, this embodiment of the application also includes a friction-reducing module 170 to reduce the speed of the rotating shaft 103 of the gas turbine 100.

[0136] like Figure 1 As shown in the embodiment of this application, the friction reduction module 170 includes a multi-stage friction assembly. Each stage of the friction assembly includes a speed-reducing friction wheel 174 and a speed-reducing friction plate 175. The speed-reducing friction wheel 174 in each stage of the friction assembly is disposed on the rotating shaft 103 of the gas turbine 100, and the speed-reducing friction plate 175 in each stage of the friction assembly is disposed on the periphery of the speed-reducing friction wheel 174 of the same stage.

[0137] The thickness of the deceleration friction wheel 174 in each friction assembly and the gap between the deceleration friction wheel 174 and the deceleration friction plate 175 are used to ensure that the deceleration friction wheel 174 and the deceleration friction plate 175 in each friction assembly contact when the rotational speed of the rotating shaft 103 of the gas turbine 100 reaches the preset rotational speed corresponding to each friction assembly.

[0138] Among them, such as Figure 1 As shown, the speed-reducing friction wheel 174 is mounted on the rotating shaft 103 of the gas turbine. When the gas turbine 100 is running, the speed-reducing friction wheel 174 rotates synchronously with the rotating shaft 103. When the rotating shaft 103 rotates at high speed, the speed-reducing friction wheel 174 will deform under the action of centrifugal force, resulting in an increase in its diameter. As the rotational speed increases, the diameter of the friction wheel will also gradually increase, thus contacting the speed-reducing friction plate 175 on its periphery. After the speed-reducing friction wheel 174 and the speed-reducing friction plate 175 come into contact, the speed-reducing friction plate 175 can brake the speed-reducing friction wheel 174, thereby reducing the rotational speed of the rotating shaft 103.

[0139] In addition, in this embodiment, multiple sets of speed-reducing friction components are provided. When the shaft 103 of the gas turbine 100 overspeeds, at different overspeed speeds, different numbers of speed-reducing friction wheels 174 in the multiple sets of speed-reducing friction components contact the speed-reducing friction plates 175. The higher the speed overspeed of the shaft 103 of the gas turbine 100, the more speed-reducing friction components are in contact with the speed-reducing friction wheels 174 and the speed-reducing friction plates 175. The lower the speed overspeed of the shaft 103 of the gas turbine 100, the fewer speed-reducing friction components are in contact with the speed-reducing friction wheels 174 and the speed-reducing friction plates 175. This allows for more granular control of the speed of the shaft 103 of the gas turbine 100.

[0140] For example, such as Figure 1 As shown in the embodiment of this application, the friction reduction module 170 includes: a first-stage friction component 171, a second-stage friction component 172, and a third-stage friction component 173;

[0141] The deceleration friction wheel 174 in the first-stage friction assembly 171 has a first thickness and a first gap between the deceleration friction wheel 174 and the deceleration friction plate 175, so that when the rotational speed of the rotating shaft 103 of the gas turbine 100 reaches the fifth preset speed, the deceleration friction wheel 174 in the first-stage friction assembly 171 deforms to contact the deceleration friction plate 175.

[0142] The deceleration friction wheel 174 in the second-stage friction assembly 172 has a second thickness and a second gap between the deceleration friction wheel 174 and the deceleration friction plate 175, so that when the rotational speed of the rotating shaft 103 of the gas turbine 100 reaches the sixth preset speed, the deceleration friction wheel 174 in the second-stage friction assembly 172 deforms to contact the deceleration friction plate 175.

[0143] The deceleration friction wheel 174 in the third-stage friction assembly 173 has a third thickness and a gap between the deceleration friction wheel 174 and the deceleration friction plate 175. When the rotational speed of the rotating shaft 103 of the gas turbine 100 reaches the seventh preset speed, the deceleration friction wheel 174 in the third-stage friction assembly 173 deforms to contact the deceleration friction plate 175.

[0144] The fifth preset speed, the sixth preset speed, and the seventh preset speed are all different.

[0145] Taking the normal operation of the gas turbine 100 with the turbine driving the shaft 103 at a speed of 3000 rpm as an example, when the speed of the shaft 103 of the gas turbine 100 is 3000 rpm or less, the deformation of the speed-reducing friction wheel 174 in the three sets of friction components will not come into contact with its corresponding speed-reducing friction plate 175, that is, none of the three sets of friction components will have a speed-reducing effect on the shaft 103.

[0146] When the rotational speed of the shaft 103 of the gas turbine 100 reaches the fifth preset speed, assuming the fifth preset speed is 3100 rpm, at this time, the deformation of the deceleration friction wheel 174 in the first-stage friction assembly 171 is exactly in contact with its corresponding deceleration friction plate 175, so the first-stage friction assembly 171 begins to reduce the rotational speed of the shaft 103. When the rotational speed of the shaft 103 of the gas turbine 100 drops below 3100 rpm, the centrifugal force of the deceleration friction wheel 174 in the first-stage friction assembly 171 decreases, the deformation decreases, and it separates from its corresponding deceleration friction plate 175, thus no longer reducing the speed of the shaft 103 of the gas turbine 100.

[0147] If, under the deceleration effect of the first-stage friction assembly 171, the rotational speed of the shaft 103 of the gas turbine 100 continues to rise to the sixth preset speed (assuming the sixth preset speed is 3300 rpm), it means that under the current operating conditions, the first-stage friction assembly 171 alone cannot effectively reduce the rotational speed of the shaft 103. When the rotational speed of the shaft 103 of the gas turbine 100 rises to 3300 rpm, the deceleration friction wheel 174 of the second-stage friction assembly 172 will deform under the current centrifugal force. The variable comes into contact with its corresponding deceleration friction plate 175, so the second-stage friction assembly 172 also begins to decelerate the rotating shaft 103 of the gas turbine 100. When the rotational speed of the rotating shaft 103 of the gas turbine 100 drops below 3300 rpm, the centrifugal force of the deceleration friction wheel 174 in the second-stage friction assembly 172 decreases, the deformation decreases, and it separates from its corresponding deceleration friction plate 175, thus no longer decelerating the rotating shaft 103 of the gas turbine 100.

[0148] If, under the coordinated speed reduction effect of the first-stage friction assembly 171 and the second-stage friction assembly 172, the rotational speed of the shaft 103 of the gas turbine 100 continues to increase to the seventh preset speed (assuming the seventh preset speed is 3500 rpm), it means that under the current operating conditions, even with the first-stage friction assembly 171 and the second-stage friction assembly 172 working simultaneously, the rotational speed of the shaft 103 of the gas turbine 100 cannot be effectively reduced. When the rotational speed of the shaft 103 of the gas turbine 100 increases to 3500 rpm, the speed reduction of the third-stage friction assembly 173... The deformation of the friction wheel 174 under the current centrifugal force is exactly in contact with its corresponding speed-reducing friction plate 175. Thus, the third-stage friction assembly 173 also begins to reduce the speed of the rotating shaft 103 of the gas turbine 100. When the rotational speed of the rotating shaft 103 of the gas turbine 100 drops below 3500 rpm, the centrifugal force of the speed-reducing friction wheel 174 in the third-stage friction assembly 173 decreases, the deformation decreases, and it separates from its corresponding speed-reducing friction plate 175, thus no longer reducing the speed of the rotating shaft 103 of the gas turbine 100.

[0149] Furthermore, in this embodiment, the thickness of the deceleration friction wheel 174 in each friction assembly group, i.e., the first to third thicknesses, and the gap between it and the corresponding deceleration friction plate 175, i.e., the first to third gaps, can be determined through multiple experiments in advance. For example, for the first-stage friction assembly 171, it is necessary for the deceleration friction wheel 174 to contact the deceleration friction plate 175 at the fifth preset speed. Assuming the first thickness of the deceleration friction wheel 174 is d, it is installed on the rotating shaft 103 of the gas turbine 100, or any other rotating shaft 103, and rotated at the sixth preset speed. Its deformation is measured, assuming it is h. Then it can be seen that when the thickness of the deceleration friction wheel 174 is d, the first gap between it and the deceleration friction plate 175 is set to h. At the fifth preset speed, the deformation of the deceleration friction wheel 174 can just contact the deceleration friction plate 175 with a first gap of h. The second and third thicknesses of the deceleration friction wheel 174 in the second-stage friction assembly 172 and the third-stage friction assembly 173, as well as the second and third gaps with the corresponding deceleration friction plate 175, can all be determined using this method, and will not be elaborated here.

[0150] In addition, in this embodiment, the friction speed reduction module 170, the pressure relief channel, and the control channel can work together to reduce the speed of the gas turbine 100.

[0151] For example, the first and fifth preset speeds are the same, assumed to be 3100 rpm; the third and sixth preset speeds are the same, assumed to be 3300 rpm; and the fourth and seventh preset speeds are the same, assumed to be 3500 rpm. Then, when the rotational speed of the gas turbine 100 shaft 103 increases to 3100 rpm, the first pressure relief channel and the first-stage friction assembly 171 operate simultaneously. When the rotational speed of the gas turbine 100 shaft 103 increases to 3300 rpm, the second pressure relief channel and the second-stage friction assembly 172 operate simultaneously. When the rotational speed of the gas turbine 100 shaft 103 increases to 3500 rpm, the third pressure relief channel and the third-stage friction assembly 173 operate simultaneously. The specific operating methods of each pressure relief channel and friction assembly are described in the above embodiments and will not be repeated here. The coordinated operation of the pressure relief channels and friction assemblies can more effectively reduce the speed of the gas turbine 100.

[0152] like Figure 1 As shown in this embodiment, the output shaft of the gas turbine 100 is connected to the input shaft of the generator via a coupling. A torque-limiting friction wheel 180 is provided on the output shaft, and two opposing torque-limiting friction plates 181 are provided on the coupling. The torque-limiting friction wheel 180 is positioned between the two torque-limiting friction plates 181, and a preset static friction force exists between the two torque-limiting friction plates 181 and the torque-limiting friction wheel 180. This preset static friction force is used to keep the two torque-limiting friction plates 181 and the torque-limiting friction wheel 180 relatively stationary when the torque of the gas turbine 100 output shaft is less than a preset value, and to allow the two torque-limiting friction plates 181 and the torque-limiting friction wheel 180 to slide relative to each other when the torque of the gas turbine 100 output shaft reaches the preset value.

[0153] In this embodiment, the rotating shaft 103 of the gas turbine 100 is the output shaft. On the offshore platform, the rotating shaft 103 of the gas turbine 100 is connected to the input shaft of the generator via a coupling, thereby driving the generator to generate electricity, which supplies power to the electrical equipment on the offshore platform. When the electrical equipment is turned off or unexpectedly shuts down, the load on the gas turbine 100 suddenly decreases, and the turbine speed increases rapidly, resulting in excessive instantaneous torque on the rotating shaft 103, posing a risk of shaft breakage. Therefore, in this embodiment, a torque-limiting friction wheel 180 is provided on the rotating shaft 103 of the gas turbine 100, and two opposing torque-limiting friction plates 181 are provided on the coupling. The torque-limiting friction wheel 180 is positioned between the two torque-limiting friction plates 181. Under normal operating conditions of the gas turbine 100, the two torque-limiting friction plates 181 are in contact with the torque-limiting friction wheel 180 and rotate at the same speed as the torque-limiting friction wheel 180. The two torque-limiting friction plates 181 and the two torque-limiting friction wheels 180 remain relatively stationary under the action of a preset static friction force. When the load on the gas turbine 100 suddenly decreases and the turbine speed rapidly increases, the speed of the torque-limiting friction wheel 180 suddenly increases. The preset static friction force is insufficient to keep the torque-limiting friction wheel 180 and the two torque-limiting friction plates 181 relatively stationary. This causes a short-term relative sliding between the torque-limiting friction wheel 180 and the two torque-limiting friction plates 181. When the torque-limiting friction wheel 180 and the two torque-limiting friction plates 181 slide relative to each other, the sliding friction between the two torque-limiting friction plates 181 and the torque-limiting friction wheel 180 can reduce the torque of the shaft 103. After a short period of sliding, the two torque-limiting friction plates 181 and the torque-limiting friction wheel 180 remain relatively stationary and rotate synchronously, thereby limiting the torque of the shaft 103 of the gas turbine 100.

[0154] In addition, in this embodiment, the two torque-limiting friction plates 181 can be fixed by torque-adjusting bolts. By adjusting the tightening torque of the torque-adjusting bolts, the pressure applied by the two torque-limiting friction plates 181 to the torque-limiting friction wheel 180 can be changed, thereby changing the magnitude of the frictional force between the two torque-limiting friction plates 181 and the torque-limiting friction wheel 180. The greater the tightening torque, the greater the frictional force between the two torque-limiting friction plates 181 and the torque-limiting friction wheel 180, and the greater the maximum torque limited on the rotating shaft 103. Conversely, the smaller the tightening torque, the smaller the frictional force between the two torque-limiting friction plates 181 and the torque-limiting friction wheel 180, and the smaller the maximum torque limited on the rotating shaft 103. In this embodiment, the maximum limiting torque applied by the two torque-limiting friction plates 181 to the rotating shaft 103 can be set based on the safe torque of the gas turbine 100 rotating shaft 103.

[0155] like Figure 1 As shown in the embodiment of this application, the outer surface of the blade 102 of the gas turbine is provided with a zirconium oxide layer, and a nickel-chromium-chromium carbide layer is also provided on the surface of the zirconium oxide layer.

[0156] During operation, the blades 102 of the gas turbine 100 are exposed to a high-temperature environment. Hydrogen sulfide produced during fuel combustion, in an alkaline metal environment, can cause corrosion of the blades 102. Therefore, in this embodiment, a nickel-chromium-chromium carbide layer is provided on the outer surface of the blades 102 to improve their resistance to sulfur compounds. Furthermore, this application first provides a zirconium oxide layer on the outer surface of the blades 102, and then provides a nickel-chromium-chromium carbide layer on the surface of the zirconium oxide layer. This improves the adhesion and toughness of the nickel-chromium-chromium carbide layer, ensuring it will not detach under high-temperature, high-speed gas erosion.

[0157] The above description is merely an optional embodiment of this application and does not limit the patent scope of this application. Any equivalent structural transformations made based on the inventive concept of this application and the contents of the specification and drawings of this application, or direct / indirect applications in other related technical fields, are included within the patent protection scope of this application.

[0158] As can be seen from the above description, the embodiments of this application provide at least the following technical solutions, but are not limited thereto:

[0159] 1. A gas turbine, comprising:

[0160] A dual-fuel channel, comprising a first gaseous fuel channel and a first liquid fuel channel;

[0161] Multiple dual-fuel nozzles, each of which is connected to the dual-fuel channel, the dual-fuel nozzles including gas fuel nozzles and liquid fuel nozzles, each gas fuel nozzle being connected to the first gas fuel channel, and each liquid fuel nozzle being connected to the first liquid fuel channel;

[0162] A second gas fuel passage and a gas fuel ignition nozzle, wherein the second gas fuel passage is connected to the gas fuel ignition nozzle;

[0163] A second liquid fuel passage and a liquid fuel ignition nozzle, wherein the second liquid fuel passage is connected to the liquid fuel ignition nozzle;

[0164] The compressed air passage includes a first passage, a second passage, a third passage, and a fourth passage. The first passage is connected to the atomizing air passage of each of the dual-fuel nozzles. The second passage is connected to the first gaseous fuel passage. The third passage is connected to the first liquid fuel passage. The fourth passage is connected to the second liquid fuel passage.

[0165] A gas fuel module is used to open or close the first gas fuel channel and the second gas fuel channel;

[0166] The liquid fuel module is used to open or close the first liquid fuel channel and the second liquid fuel channel;

[0167] The air intake module is used to open or close the first channel, the second channel, the third channel, and the fourth channel.

[0168] 2. The gas turbine as described in technical solution 1, wherein the first gas fuel passage is connected to each of the gas fuel nozzles, and is used to supply fuel gas to each of the gas fuel nozzles during ignition based on gas fuel ignition and gas fuel operation, and to maintain the supply of fuel gas to each of the gas fuel nozzles after successful ignition, and to maintain the supply of fuel gas to each of the gas fuel nozzles after successful start-up.

[0169] The second gas fuel channel is connected to the gas fuel ignition nozzle and is used to supply fuel gas to the gas fuel ignition nozzle during ignition based on gas fuel ignition and gas fuel operation, and to stop supplying fuel gas to the gas fuel ignition nozzle after successful ignition.

[0170] The third channel is connected to each of the liquid fuel nozzles and is used to supply compressed air to each of the liquid fuel nozzles after successful start-up based on gas fuel ignition and gas fuel operation.

[0171] 3. The gas turbine as described in technical solution 1 or 2, wherein the second gas fuel passage is connected to the gas fuel ignition nozzle, and is used to supply fuel gas to the gas fuel ignition nozzle during ignition based on gas fuel ignition and operation based on liquid fuel; and to stop supplying fuel gas to the gas fuel ignition nozzle after successful ignition.

[0172] The first liquid fuel channel is connected to each of the liquid fuel nozzles and is used to supply liquid fuel to each of the liquid fuel nozzles during ignition based on gas fuel ignition and based on liquid fuel operation; after successful ignition, the supply of liquid fuel to each of the liquid fuel nozzles is maintained; after successful start-up, the supply of liquid fuel to each of the liquid fuel nozzles is maintained.

[0173] The first channel is connected to the atomizing air channel of each of the dual-fuel nozzles and is used to supply compressed air to the atomizing air channel of each of the dual-fuel nozzles after successful start-up based on gas fuel ignition and liquid fuel operation.

[0174] The second channel is connected to the first gaseous fuel channel and is used to supply compressed air to the first gaseous fuel channel after a successful start-up based on gaseous fuel ignition and liquid fuel operation.

[0175] 4. The gas turbine as described in any one of technical solutions 1-3, wherein the first liquid fuel passage is connected to each of the liquid fuel nozzles, and is used to supply liquid fuel to each of the liquid fuel nozzles during ignition based on liquid fuel ignition and operation; after successful ignition, to maintain the supply of liquid fuel to each of the liquid fuel nozzles; and after successful start-up, to maintain the supply of liquid fuel to each of the liquid fuel nozzles.

[0176] The second liquid fuel channel is connected to the liquid fuel ignition nozzle and is used to supply liquid fuel to the liquid fuel ignition nozzle during ignition based on liquid fuel ignition and operation; after successful ignition, the supply of liquid fuel to the liquid fuel ignition nozzle is stopped.

[0177] The first channel is connected to the atomizing air channel of each of the dual-fuel nozzles, and is used to supply compressed air to the atomizing air channel of each of the dual-fuel nozzles after successful ignition based on liquid fuel ignition and operation.

[0178] The fourth channel is connected to the liquid fuel ignition nozzle, and the fourth channel is provided with a first gear, which is used to supply compressed air to the liquid fuel ignition nozzle at the supply amount or supply time corresponding to the first gear after successful ignition based on liquid fuel ignition and operation, and to stop supplying compressed air after reaching the supply amount or supply time corresponding to the first gear.

[0179] The second channel is connected to the first gaseous fuel channel and is used to supply compressed air to the first gaseous fuel channel after successful start-up based on liquid fuel ignition and operation.

[0180] 5. The gas turbine as described in any one of technical solutions 1-4, wherein the second liquid fuel passage is connected to the liquid fuel ignition nozzle, and is used to supply liquid fuel to the liquid fuel ignition nozzle during ignition based on liquid fuel ignition and gas fuel operation; and to stop supplying liquid fuel to the liquid fuel ignition nozzle after successful ignition.

[0181] The first gas fuel channel is connected to each of the gas fuel nozzles and is used to supply fuel gas to each of the gas fuel nozzles during ignition based on liquid fuel ignition and gas fuel operation; after successful ignition, it continues to supply gas fuel to each of the gas fuel nozzles; after successful start-up, it continues to supply gas fuel to each of the gas fuel nozzles.

[0182] The fourth channel is connected to the liquid fuel ignition nozzle, and the fourth channel is provided with a second gear, which is used to supply compressed air to the liquid fuel ignition nozzle at the supply amount or supply time corresponding to the second gear after successful ignition based on liquid fuel ignition and gas fuel operation, and to stop supplying compressed air after reaching the supply amount or supply time corresponding to the second gear.

[0183] The third channel is connected to the first liquid fuel channel and is used to supply compressed air to the first liquid fuel channel after successful start-up of the gas fuel-based operation based on liquid fuel ignition.

[0184] 6. The gas turbine as described in any one of technical solutions 1-5, wherein the bleed air module is configured to: close the second channel before switching from liquid fuel to gaseous fuel;

[0185] The first liquid fuel channel is provided with a first liquid fuel supply position, a second liquid fuel supply position, and a third liquid fuel supply position. The first liquid fuel supply position is used to reduce the liquid fuel supplied by the first liquid fuel channel to each liquid fuel nozzle to 90%-95% of the rated supply amount during the first stage of switching from liquid fuel to gaseous fuel, according to the deceleration rate corresponding to the first liquid fuel supply position. The second liquid fuel supply position is used to reduce the liquid fuel supplied by the first liquid fuel channel to each liquid fuel nozzle to 5%-10% of the rated supply amount during the second liquid fuel supply position, according to the deceleration rate corresponding to the second liquid fuel supply position. The third liquid fuel supply position is used to reduce the liquid fuel supplied by the first liquid fuel channel to each liquid fuel nozzle to 0 during the third stage of switching from liquid fuel to gaseous fuel, according to the deceleration rate corresponding to the third liquid fuel supply position. The absolute values ​​of the deceleration rates corresponding to the first and third liquid fuel supply positions gradually increase, while the deceleration rate corresponding to the second liquid fuel supply position is a fixed value.

[0186] The first gas fuel channel is provided with a first gas fuel supply setting, a second gas fuel supply setting, and a third gas fuel supply setting. The first gas fuel supply setting is used to increase the liquid fuel supplied by the first gas fuel channel to each gas fuel nozzle to 5%-10% of the rated operating supply amount according to the acceleration corresponding to the first gas fuel supply setting during the first stage of switching from liquid fuel to gas fuel. The second gas fuel supply setting is used to increase the gas fuel supplied by the first gas fuel channel to each gas fuel nozzle to 90-90% of the rated operating supply amount according to the acceleration corresponding to the second gas fuel supply setting. The third gas fuel supply setting is used to increase the gas fuel supplied by the first gas fuel channel to each gas fuel nozzle to the rated supply amount according to the acceleration corresponding to the third gas fuel supply setting during the third stage of switching from liquid fuel to gas fuel. The acceleration corresponding to the first and third gas fuel supply settings gradually increases, while the acceleration corresponding to the second gas fuel supply setting is a fixed value.

[0187] After the switching is completed, the gas fuel module is configured to maintain the first gas fuel channel supplying fuel gas to each of the gas fuel nozzles; the bleed air module is also configured to open the third channel to supply compressed air to the first liquid fuel channel.

[0188] 7. The gas turbine as described in any one of technical solutions 1-6, wherein the bleed air module is configured to: close the third channel and open the first channel before switching from gaseous fuel to liquid fuel;

[0189] The first gas fuel channel is provided with a fourth gas fuel supply position, a fifth gas fuel supply position, and a sixth gas fuel supply position. The first gas fuel supply position is used to reduce the liquid fuel supplied by the first gas fuel channel to each gas fuel nozzle to 90%-95% of the rated supply amount during the first stage of switching from gaseous fuel to liquid fuel, according to the deceleration corresponding to the fourth gas fuel supply position. The fifth gas fuel supply position is used to reduce the gaseous fuel supplied by the first gas fuel channel to each gas fuel nozzle to 5%-10% of the rated supply amount during the first stage of switching from gaseous fuel to liquid fuel, according to the deceleration corresponding to the sixth gas fuel supply position. The sixth gas fuel supply position is used to reduce the gaseous fuel supplied by the first gas fuel channel to each gas fuel nozzle to 0 during the third stage of switching from gaseous fuel to liquid fuel, according to the deceleration corresponding to the sixth gas fuel supply position. The absolute values ​​of the deceleration corresponding to the fourth and sixth gas fuel supply positions gradually increase, while the deceleration corresponding to the fifth gas fuel supply position is a fixed value.

[0190] The first liquid fuel channel is provided with a fourth liquid fuel supply position, a fifth liquid fuel supply position, and a sixth liquid fuel supply position. The fourth liquid fuel supply position is used to increase the liquid fuel supplied by the first liquid fuel channel to each liquid fuel nozzle to 5%-10% of the rated operating supply amount according to the acceleration corresponding to the fourth liquid fuel supply position during the first stage of switching from gaseous fuel to liquid fuel. The fifth liquid fuel supply position is used to increase the liquid fuel supplied by the first liquid fuel channel to each liquid fuel nozzle to 90-90% of the rated operating supply amount according to the acceleration corresponding to the fifth gaseous fuel supply position during the second stage of switching from gaseous fuel to liquid fuel. The sixth liquid fuel supply position is used to increase the gaseous fuel supplied by the first liquid fuel channel to each liquid fuel nozzle to the rated supply amount according to the acceleration corresponding to the sixth liquid fuel supply position during the third stage of switching from gaseous fuel to liquid fuel. The accelerations corresponding to the fourth and sixth liquid fuel supply positions gradually increase, while the acceleration corresponding to the fifth liquid fuel supply position is a fixed value.

[0191] After the switching is completed, the air intake module is also configured to: open the second channel and supply compressed air to the first gas fuel channel.

[0192] 8. The gas turbine as described in any one of technical solutions 1-7, wherein the gas turbine further comprises:

[0193] A pressure relief channel is provided, which is connected to the combustion chamber of the gas turbine. The pressure relief channel is provided with multiple pressure relief branches, and each pressure relief branch is provided with a pneumatic valve. The pneumatic valve is used to open or close its corresponding pressure relief branch.

[0194] Multiple control channels are provided, one end of each control channel is connected to the compressed air channel, and the other end is connected to the pneumatic valve on each of the pressure relief branches. Each control channel is equipped with a solenoid valve, which is used to open or close the control channel to supply compressed air to the corresponding pneumatic valve.

[0195] 9. The gas turbine as described in any one of technical solutions 1-8, wherein the pressure relief passage comprises: a first pressure relief branch, a second pressure relief branch, and a third pressure relief branch;

[0196] The control channel includes a first control channel, a second control channel, and a third control channel, wherein the first control channel, the second control channel, and the third control channel correspond to the first pressure relief branch, the second pressure relief branch, and the third pressure relief branch, respectively.

[0197] The solenoid valve on the first control channel is connected to the pneumatic valve on the first pressure relief branch, and is used to supply compressed air to the pneumatic valve on the first pressure relief branch when the rotational speed of the gas turbine shaft reaches the first preset speed, and to stop supplying compressed air when the rotational speed of the gas turbine shaft drops to the second preset speed.

[0198] The solenoid valve on the second control channel is connected to the pneumatic valve on the second pressure relief branch, and is used to supply compressed air to the pneumatic valve on the second pressure relief branch when the rotational speed of the gas turbine shaft reaches the third preset speed, and to stop supplying compressed air when the rotational speed of the gas turbine shaft drops to the second preset speed.

[0199] The solenoid valve on the third control channel is connected to the pneumatic valve on the third pressure relief branch, and is used to supply compressed air to the pneumatic valve on the third pressure relief branch when the rotational speed of the gas turbine shaft reaches the fourth preset speed, and to stop supplying compressed air when the rotational speed of the gas turbine shaft drops to the second preset speed.

[0200] The first preset speed, the third preset speed, and the fourth preset speed are all different and all greater than the second preset speed.

[0201] 10. The gas turbine as described in any one of technical solutions 1-9, wherein the gas turbine further includes a friction speed reduction module, the friction speed reduction module includes a multi-stage friction assembly, each stage friction assembly includes a speed reduction friction wheel and a speed reduction friction plate, the speed reduction friction wheel in each stage friction assembly is disposed on the rotating shaft of the gas turbine, and the speed reduction friction plate in each stage friction assembly is disposed on the periphery of the speed reduction friction wheel of the same stage;

[0202] The thickness of the deceleration friction wheel in each friction assembly and the gap between the deceleration friction wheel and the deceleration friction plate are used to ensure that the deceleration friction wheel in each friction assembly contacts the deceleration friction plate when the rotational speed of the gas turbine shaft reaches the preset rotational speed corresponding to each friction assembly.

[0203] 11. The gas turbine as described in any one of technical solutions 1-10, wherein the friction-induced speed reduction module comprises: a first-stage friction assembly, a second-stage friction assembly, and a third-stage friction assembly;

[0204] The deceleration friction wheel in the first-stage friction assembly has a first thickness and a first gap between the deceleration friction wheel and the deceleration friction plate, so that when the rotational speed of the gas turbine shaft reaches a fifth preset speed, the deceleration friction wheel in the first-stage friction assembly deforms to contact the deceleration friction plate.

[0205] The deceleration friction wheel in the second-stage friction assembly has a second thickness and a second gap between the deceleration friction wheel and the deceleration friction plate. When the rotational speed of the gas turbine shaft reaches a sixth preset speed, the deceleration friction wheel in the second-stage friction assembly deforms to contact the deceleration friction plate.

[0206] The deceleration friction wheel in the third-stage friction assembly has a third thickness and a third gap between the deceleration friction wheel and the deceleration friction plate. When the rotational speed of the gas turbine shaft reaches a seventh preset speed, the deceleration friction wheel in the third-stage friction assembly deforms to contact the deceleration friction plate.

[0207] The fifth preset speed, the sixth preset speed, and the seventh preset speed are all different.

[0208] 12. The gas turbine as described in any one of technical solutions 1-11, wherein the output shaft of the gas turbine is connected to the input shaft of the generator via a coupling, a torque-limiting friction wheel is provided on the output shaft, two opposing torque-limiting friction plates are provided on the coupling, the torque-limiting friction wheel is disposed between the two torque-limiting friction plates, and a preset static friction force is present between the two torque-limiting friction plates and the torque-limiting friction wheel, the preset static friction force being used to keep the two torque-limiting friction plates and the torque-limiting friction wheel relatively stationary when the torque of the gas turbine output shaft is less than a preset value, and to make the two torque-limiting friction plates and the torque-limiting friction wheel slide relative to each other when the torque of the gas turbine output shaft reaches the preset value.

[0209] 13. The gas turbine as described in any one of technical solutions 1-12, wherein the outer surface of the blades of the gas turbine is provided with a zirconium oxide layer, and a nickel-chromium-chromium carbide layer is further provided on the surface of the zirconium oxide layer.

Claims

1. A gas turbine, characterized in that, include: A dual-fuel channel, comprising a first gaseous fuel channel and a first liquid fuel channel; Multiple dual-fuel nozzles, each of which is connected to the dual-fuel channel, the dual-fuel nozzles including gas fuel nozzles and liquid fuel nozzles, each gas fuel nozzle being connected to the first gas fuel channel, and each liquid fuel nozzle being connected to the first liquid fuel channel; A second gas fuel passage and a gas fuel ignition nozzle, wherein the second gas fuel passage is connected to the gas fuel ignition nozzle; A second liquid fuel passage and a liquid fuel ignition nozzle, wherein the second liquid fuel passage is connected to the liquid fuel ignition nozzle; The compressed air passage includes a first passage, a second passage, a third passage, and a fourth passage. The first passage is connected to the atomizing air passage of each of the dual-fuel nozzles. The second passage is connected to the first gaseous fuel passage. The third passage is connected to the first liquid fuel passage. The fourth passage is connected to the second liquid fuel passage. A gas fuel module is used to open or close the first gas fuel channel and the second gas fuel channel; The liquid fuel module is used to open or close the first liquid fuel channel and the second liquid fuel channel; The air intake module is used to open or close the first channel, the second channel, the third channel, and the fourth channel.

2. The gas turbine as described in claim 1, characterized in that, The first gas fuel channel is connected to each of the gas fuel nozzles and is used to supply fuel gas to each of the gas fuel nozzles during ignition based on gas fuel ignition and operation based on gas fuel. After successful ignition, the supply of fuel gas to each of the gas fuel nozzles is maintained. After successful start-up, the supply of fuel gas to each of the gas fuel nozzles is maintained. The second gas fuel channel is connected to the gas fuel ignition nozzle and is used to supply fuel gas to the gas fuel ignition nozzle during ignition based on gas fuel ignition and gas fuel operation, and to stop supplying fuel gas to the gas fuel ignition nozzle after successful ignition. The third channel is connected to each of the liquid fuel nozzles and is used to supply compressed air to each of the liquid fuel nozzles after successful start-up based on gas fuel ignition and gas fuel operation.

3. The gas turbine as described in claim 1, characterized in that, The second gaseous fuel passage is connected to the gaseous fuel ignition nozzle and is used to supply fuel gas to the gaseous fuel ignition nozzle during ignition based on gaseous fuel ignition and operation based on liquid fuel; after successful ignition, the supply of fuel gas to the gaseous fuel ignition nozzle is stopped. The first liquid fuel channel is connected to each of the liquid fuel nozzles and is used to supply liquid fuel to each of the liquid fuel nozzles during ignition based on gas fuel ignition and based on liquid fuel operation; after successful ignition, the supply of liquid fuel to each of the liquid fuel nozzles is maintained; after successful start-up, the supply of liquid fuel to each of the liquid fuel nozzles is maintained. The first channel is connected to the atomizing air channel of each of the dual-fuel nozzles and is used to supply compressed air to the atomizing air channel of each of the dual-fuel nozzles after successful start-up based on gas fuel ignition and liquid fuel operation. The second channel is connected to the first gaseous fuel channel and is used to supply compressed air to the first gaseous fuel channel after a successful start-up based on gaseous fuel ignition and liquid fuel operation.

4. The gas turbine as described in claim 1, characterized in that, The first liquid fuel channel is connected to each of the liquid fuel nozzles and is used to supply liquid fuel to each of the liquid fuel nozzles during ignition based on liquid fuel ignition and operation; after successful ignition, it continues to supply liquid fuel to each of the liquid fuel nozzles; after successful start-up, it continues to supply liquid fuel to each of the liquid fuel nozzles. The second liquid fuel channel is connected to the liquid fuel ignition nozzle and is used to supply liquid fuel to the liquid fuel ignition nozzle during ignition based on liquid fuel ignition and operation; after successful ignition, the supply of liquid fuel to the liquid fuel ignition nozzle is stopped. The first channel is connected to the atomizing air channel of each of the dual-fuel nozzles, and is used to supply compressed air to the atomizing air channel of each of the dual-fuel nozzles after successful ignition based on liquid fuel ignition and operation. The fourth channel is connected to the liquid fuel ignition nozzle, and the fourth channel is provided with a first gear, which is used to supply compressed air to the liquid fuel ignition nozzle at the supply amount or supply time corresponding to the first gear after successful ignition based on liquid fuel ignition and operation, and to stop supplying compressed air after reaching the supply amount or supply time corresponding to the first gear. The second channel is connected to the first gaseous fuel channel and is used to supply compressed air to the first gaseous fuel channel after successful start-up based on liquid fuel ignition and operation.

5. The gas turbine as described in claim 1, characterized in that, The second liquid fuel channel is connected to the liquid fuel ignition nozzle and is used to supply liquid fuel to the liquid fuel ignition nozzle during ignition based on liquid fuel and gas fuel operation; after successful ignition, the supply of liquid fuel to the liquid fuel ignition nozzle is stopped. The first gas fuel channel is connected to each of the gas fuel nozzles and is used to supply fuel gas to each of the gas fuel nozzles during ignition based on liquid fuel ignition and gas fuel operation; after successful ignition, it continues to supply gas fuel to each of the gas fuel nozzles; after successful start-up, it continues to supply gas fuel to each of the gas fuel nozzles. The fourth channel is connected to the liquid fuel ignition nozzle, and the fourth channel is provided with a second gear, which is used to supply compressed air to the liquid fuel ignition nozzle at the supply amount or supply time corresponding to the second gear after successful ignition based on liquid fuel ignition and gas fuel operation, and to stop supplying compressed air after reaching the supply amount or supply time corresponding to the second gear. The third channel is connected to the first liquid fuel channel and is used to supply compressed air to the first liquid fuel channel after successful start-up of the gas fuel-based operation based on liquid fuel ignition.

6. The gas turbine as described in claim 1, characterized in that, The bleed-out module is configured to shut down the second channel before switching from liquid fuel to gaseous fuel; The first liquid fuel channel is provided with a first liquid fuel supply position, a second liquid fuel supply position, and a third liquid fuel supply position. The first liquid fuel supply position is used to reduce the liquid fuel supplied by the first liquid fuel channel to each liquid fuel nozzle to 90%-95% of the rated supply amount during the first stage of switching from liquid fuel to gaseous fuel, according to the deceleration rate corresponding to the first liquid fuel supply position. The second liquid fuel supply position is used to reduce the liquid fuel supplied by the first liquid fuel channel to each liquid fuel nozzle to 5%-10% of the rated supply amount during the second liquid fuel supply position, according to the deceleration rate corresponding to the second liquid fuel supply position. The third liquid fuel supply position is used to reduce the liquid fuel supplied by the first liquid fuel channel to each liquid fuel nozzle to 0 during the third stage of switching from liquid fuel to gaseous fuel, according to the deceleration rate corresponding to the third liquid fuel supply position. The absolute values ​​of the deceleration rates corresponding to the first and third liquid fuel supply positions gradually increase, while the deceleration rate corresponding to the second liquid fuel supply position is a fixed value. The first gas fuel channel is provided with a first gas fuel supply setting, a second gas fuel supply setting, and a third gas fuel supply setting. The first gas fuel supply setting is used to increase the liquid fuel supplied by the first gas fuel channel to each gas fuel nozzle to 5%-10% of the rated operating supply amount according to the acceleration corresponding to the first gas fuel supply setting during the first stage of switching from liquid fuel to gas fuel. The second gas fuel supply setting is used to increase the gas fuel supplied by the first gas fuel channel to each gas fuel nozzle to 90-90% of the rated operating supply amount according to the acceleration corresponding to the second gas fuel supply setting. The third gas fuel supply setting is used to increase the gas fuel supplied by the first gas fuel channel to each gas fuel nozzle to the rated supply amount according to the acceleration corresponding to the third gas fuel supply setting during the third stage of switching from liquid fuel to gas fuel. The acceleration corresponding to the first and third gas fuel supply settings gradually increases, while the acceleration corresponding to the second gas fuel supply setting is a fixed value. After the switching is completed, the gas fuel module is configured to maintain the first gas fuel channel supplying fuel gas to each of the gas fuel nozzles; the bleed air module is also configured to open the third channel to supply compressed air to the first liquid fuel channel.

7. The gas turbine as described in claim 6, characterized in that, The bleed-out module is configured to close the third channel and open the first channel before switching from gaseous fuel to liquid fuel. The first gas fuel channel is provided with a fourth, a fifth, and a sixth gas fuel supply position. The first gas fuel supply position is used to, in the first stage of switching from gaseous fuel to liquid fuel, reduce the liquid fuel supplied by the first gas fuel channel to each gas fuel nozzle to 90%-95% of the rated operating supply, according to the deceleration corresponding to the fourth gas fuel supply position. The fifth gas fuel supply position is used to, according to the deceleration corresponding to the fifth gas fuel supply position, reduce the gaseous fuel supplied by the first gas fuel channel to each gas fuel nozzle to 5%-10% of the rated operating supply, according to the deceleration corresponding to the fifth gas fuel supply position. The sixth gas fuel supply position is used to, in the third stage of switching from gaseous fuel to liquid fuel, reduce the gaseous fuel supplied by the first gas fuel channel to each gas fuel nozzle to 0, according to the deceleration corresponding to the sixth gas fuel supply position. The absolute values ​​of the decelerations corresponding to the fourth and sixth gas fuel supply positions gradually increase, while the deceleration corresponding to the fifth gas fuel supply position is a fixed value. The first liquid fuel channel is provided with a fourth liquid fuel supply position, a fifth liquid fuel supply position, and a sixth liquid fuel supply position. The fourth liquid fuel supply position is used to increase the liquid fuel supplied by the first liquid fuel channel to each liquid fuel nozzle to 5%-10% of the rated operating supply amount according to the acceleration corresponding to the fourth liquid fuel supply position during the first stage of switching from gaseous fuel to liquid fuel. The fifth liquid fuel supply position is used to increase the liquid fuel supplied by the first liquid fuel channel to each liquid fuel nozzle to 90-90% of the rated operating supply amount according to the acceleration corresponding to the fifth gaseous fuel supply position during the second stage of switching from gaseous fuel to liquid fuel. The sixth liquid fuel supply position is used to increase the gaseous fuel supplied by the first liquid fuel channel to each liquid fuel nozzle to the rated supply amount according to the acceleration corresponding to the sixth liquid fuel supply position during the third stage of switching from gaseous fuel to liquid fuel. The accelerations corresponding to the fourth and sixth liquid fuel supply positions gradually increase, while the acceleration corresponding to the fifth liquid fuel supply position is a fixed value. After the switching is completed, the air intake module is also configured to: open the second channel and supply compressed air to the first gas fuel channel.

8. The gas turbine as described in claim 1, characterized in that, The gas turbine also includes: A pressure relief channel is provided, which is connected to the combustion chamber of the gas turbine. The pressure relief channel is provided with multiple pressure relief branches, and each pressure relief branch is provided with a pneumatic valve, which is used to open or close its corresponding pressure relief branch. Multiple control channels are provided, one end of each control channel is connected to the compressed air channel, and the other end is connected to the pneumatic valve on each of the pressure relief branches. Each control channel is equipped with a solenoid valve, which is used to open or close the control channel to supply compressed air to the corresponding pneumatic valve.

9. The gas turbine as described in claim 8, characterized in that, The pressure relief channel includes: a first pressure relief branch, a second pressure relief branch, and a third pressure relief branch; The control channel includes a first control channel, a second control channel, and a third control channel, wherein the first control channel, the second control channel, and the third control channel correspond to the first pressure relief branch, the second pressure relief branch, and the third pressure relief branch, respectively. The solenoid valve on the first control channel is connected to the pneumatic valve on the first pressure relief branch, and is used to supply compressed air to the pneumatic valve on the first pressure relief branch when the rotational speed of the gas turbine shaft reaches the first preset speed, and to stop supplying compressed air when the rotational speed of the gas turbine shaft drops to the second preset speed. The solenoid valve on the second control channel is connected to the pneumatic valve on the second pressure relief branch, and is used to supply compressed air to the pneumatic valve on the second pressure relief branch when the rotational speed of the gas turbine shaft reaches the third preset speed, and to stop supplying compressed air when the rotational speed of the gas turbine shaft drops to the second preset speed. The solenoid valve on the third control channel is connected to the pneumatic valve on the third pressure relief branch, and is used to supply compressed air to the pneumatic valve on the third pressure relief branch when the rotational speed of the gas turbine shaft reaches the fourth preset speed, and to stop supplying compressed air when the rotational speed of the gas turbine shaft drops to the second preset speed. The first preset speed, the third preset speed, and the fourth preset speed are all different and all greater than the second preset speed.

10. The gas turbine as described in claim 1, characterized in that, The gas turbine also includes a friction speed reduction module, which includes a multi-stage friction assembly. Each stage of the friction assembly includes a speed-reducing friction wheel and a speed-reducing friction plate. The speed-reducing friction wheel in each stage of the friction assembly is located on the rotating shaft of the gas turbine, and the speed-reducing friction plate in each stage of the friction assembly is located on the periphery of the speed-reducing friction wheel of the same stage. The thickness of the deceleration friction wheel in each friction assembly and the gap between the deceleration friction wheel and the deceleration friction plate are used to ensure that the deceleration friction wheel in each friction assembly contacts the deceleration friction plate when the rotational speed of the gas turbine shaft reaches the preset rotational speed corresponding to each friction assembly.

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