Method, System, Electronic Device and Medium for Preventing Gas Turbine Thermal Hanging Fault

Abstract

The present invention discloses a method, a system, an electronic device and a medium for preventing a gas turbine from having a thermal suspension fault. The method for preventing a gas turbine from having a thermal suspension fault includes: determining the current speed of a static frequency conversion starting device connected to the gas turbine, the current acceleration of the gas turbine and the current turbine exhaust temperature; when the current speed is greater than or equal to the warm-up speed and less than or equal to the impending tripping speed, the current acceleration is less than the first acceleration threshold and the current turbine exhaust temperature is greater than the temperature threshold, increasing the current acceleration to the first acceleration set value or reducing the current turbine exhaust temperature; when the current speed is greater than the impending tripping speed and less than or equal to the tripping speed, the current acceleration is less than the second acceleration threshold and the current turbine exhaust temperature is greater than the temperature threshold, increasing the tripping speed by a preset number of revolutions. In this way, it is judged what state the gas turbine is in during startup, corresponding treatment means are started, and the thermal suspension fault of the gas turbine is eliminated targeted, so that the gas turbine can be started smoothly.

Description

Technical Field

[0001] The present invention relates to the field of gas turbines, and particularly to a method, a system, an electronic device and a medium for preventing the hot hanging fault of a gas turbine. Background Art

[0002] A gas turbine is an internal combustion power machine that uses continuously flowing gas as the working medium to drive the impeller to rotate at a high speed and converts the energy of fuel into useful work. It is a rotary impeller type heat engine. The three major components of a gas turbine are a compressor, a combustor, and a gas turbine. During the startup process of a gas turbine, a hot hanging fault may occur, resulting in the failure of the gas turbine to start. The hot hanging fault of a gas turbine refers to the situation where during the startup process of the gas turbine, the rotational speed of the gas turbine rises slowly or even stops rising, fails to reach the no-load speed, and the exhaust temperature of the unit rises rapidly while the rotational speed does not rise. This state is the hot hanging fault state. The main reason for the occurrence of hot hanging is that the startup process line is close to the compressor surge boundary. After the startup device trips, the remaining torque of the unit decreases significantly. If the operation is improper before tripping and the fuel flow rate increases too fast, the operating point will move closer to the surge boundary, and the compressor may stall. The efficiency of the compressor decreases, the resistance torque increases, and the remaining torque may be zero, causing the rotor to stop rising in speed. At this time, if the fuel flow rate is increased, the turbine inlet temperature rises and the driving torque increases, but the operating point is closer to the surge boundary, the efficiency of the compressor further decreases, and the remaining torque becomes negative, resulting in a decrease in rotational speed and ultimately leading to the failure of startup. Currently, in most cases, the method for solving the hot hanging fault of a gas turbine is to adjust the fuel quantity and monitor whether the acceleration during startup is lower than the set value. If it is lower than the set value, corresponding alarms or trip protection are taken. Such methods cannot determine what state the gas turbine is in during startup based on the actual rotational speed and cannot take targeted elimination measures to eliminate the hot hanging fault of the unit. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to overcome the defect in the prior art that it cannot accurately determine what state the gas turbine is in during startup and cannot take targeted elimination measures to eliminate the hot hanging fault of the unit, and to provide a method, a system, an electronic device and a medium for preventing the hot hanging fault of a gas turbine.

[0004] The present invention solves the above technical problem through the following technical solutions:

[0005] A method for preventing the hot hanging fault of a gas turbine includes the following steps:

[0006] Determine the current rotational speed of the static frequency conversion startup device connected to the gas turbine, the current acceleration of the gas turbine, and the current turbine exhaust temperature of the gas turbine;

[0007] When the current speed is greater than or equal to the warm-up speed and less than or equal to the impending trip speed, the current acceleration is less than the first acceleration threshold and the current turbine exhaust temperature is greater than the temperature threshold, increase the current acceleration to the first acceleration set value or decrease the current turbine exhaust temperature;

[0008] When the current speed is greater than the impending trip speed and less than or equal to the trip speed, the current acceleration is less than the second acceleration threshold and the current turbine exhaust temperature is greater than the temperature threshold, increase the trip speed by a preset number of revolutions;

[0009] Wherein, the impending trip speed is the difference between the trip speed and the preset number of revolutions.

[0010] Preferably, decreasing the current turbine exhaust temperature includes:

[0011] Adjust the fuel quantity according to the temperature difference between the current turbine exhaust temperature and the set value of the turbine exhaust temperature and the opening of the compressor guide vane to decrease the current turbine exhaust temperature; the fuel quantity is negatively correlated with the difference and positively correlated with the opening of the compressor guide vane.

[0012] Preferably, adjusting the current acceleration to the acceleration set value includes:

[0013] Adjust the fuel quantity according to the acceleration difference between the acceleration set value and the current acceleration so that the current acceleration of the gas turbine reaches the first acceleration set value; the difference is positively correlated with the fuel quantity.

[0014] Preferably, the method for preventing the hot hung-up fault of the gas turbine further includes: when the gas turbine trips from the connected static frequency conversion starting device, adjust the current acceleration to the second acceleration set value;

[0015] Wherein, the second acceleration set value is greater than the first acceleration set value.

[0016] Preferably, the step of adjusting the current acceleration to the second acceleration set value includes:

[0017] Raise the current acceleration from the first acceleration set value to the second acceleration set value at a preset slope.

[0018] Preferably, the method for preventing the hot hung-up fault of the gas turbine further includes:

[0019] When the current speed is greater than or equal to the warm-up speed and less than or equal to the impending trip speed, the current acceleration is less than the first acceleration threshold and the current turbine exhaust temperature is greater than the temperature threshold, generate a first hot hung-up warning prompt;

[0020] When the current rotational speed is greater than or equal to the impending tripping speed and less than or equal to the tripping speed, the current acceleration is less than the second acceleration threshold, and the current turbine exhaust temperature is greater than the temperature threshold, a second thermal suspension warning prompt is generated.

[0021] Preferably, after the step of increasing the tripping speed by a preset number of revolutions, the method further includes:

[0022] Determine whether the current acceleration is less than the second acceleration threshold and whether the current turbine exhaust temperature is greater than the temperature threshold;

[0023] If so, increase the tripping speed by a preset number of revolutions.

[0024] A system for preventing thermal suspension faults of a gas turbine, the system for preventing thermal suspension faults of a gas turbine includes:

[0025] A determination module, configured to determine the current rotational speed of a static frequency conversion starting device connected to the gas turbine, the current acceleration of the gas turbine, and the current turbine exhaust temperature of the gas turbine;

[0026] A first adjustment module, configured to increase the current acceleration to a first acceleration set value or reduce the current turbine exhaust temperature when the current rotational speed is greater than or equal to the warm-up speed and less than or equal to the impending tripping speed, the current acceleration is less than the first acceleration threshold, and the current turbine exhaust temperature is greater than the temperature threshold;

[0027] A second adjustment module, configured to increase the tripping speed by a preset number of revolutions when the current rotational speed is greater than the impending tripping speed and less than or equal to the tripping speed, the current acceleration is less than the second acceleration threshold, and the current turbine exhaust temperature is greater than the temperature threshold;

[0028] Wherein, the impending tripping speed is the difference between the tripping speed and the preset number of revolutions.

[0029] An electronic device, including a memory, a processor, and a computer program stored on the memory and executable on the processor, wherein when the processor executes the computer program, the method for preventing thermal suspension faults of a gas turbine described in any one of the above is implemented.

[0030] A computer-readable medium, on which a computer program is stored, wherein when the computer program is executed by a processor, the method for preventing thermal suspension faults of a gas turbine described in any one of the above is implemented.

[0031] The positive and progressive effects of the present invention are as follows: By determining the current rotational speed state of the static frequency conversion starting device connected to the gas turbine, and judging the relationship between the current acceleration of the gas turbine and the current turbine exhaust temperature of the gas turbine and the corresponding thresholds, corresponding processing means are started according to the judged state of the gas turbine during startup. In this way, targeted elimination means are adopted to eliminate the hot hanging fault of the gas turbine unit, enabling the gas turbine to start smoothly in practical applications. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 FIG. 1 is a flowchart of a method for preventing hot hanging fault of a gas turbine provided in Embodiment 1 of the present invention.

[0033] Figure 2 FIG. 2 is a starting process diagram of the gas turbine of the present invention.

[0034] Figure 3 FIG. 3 is a fuel stroke reference diagram of the gas turbine of the present invention in different states.

[0035] Figure 4 FIG. 4 is an acceleration requirement diagram of the gas turbine of the present invention.

[0036] Figure 5 FIG. 5 is a module schematic diagram of a system for preventing hot hanging fault of a gas turbine provided in Embodiment 2 of the present invention.

[0037] Figure 6 FIG. 6 is a structural schematic diagram of an electronic device provided in Embodiment 3 of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0038] The present invention will be further described below by way of embodiments, but the present invention is not limited to the scope of the described embodiments.

[0039] Embodiment 1

[0040] This embodiment provides a method for preventing hot hanging fault of a gas turbine. Before introducing this solution, the principle of gas turbine startup is first introduced: Refer to Figure 2 , the startup process of the gas turbine is roughly divided into three stages: In the first stage, the gas turbine is accelerated from a stationary state to the ignition speed by the torque (M st ) provided by the static frequency conversion starting device. This stage is called the cold acceleration stage of the gas turbine; In the second stage, after successful ignition, as the inlet temperature of the turbine increases significantly, the gas turbine turbine starts to generate torque M T . In this stage, the gas turbine relies on the static frequency conversion starting device and the turbine to jointly provide torque (M N + M T ) to overcome the resistance torque (M CAdding to Mm, the resistance torque is the compressor resistance torque and the friction resistance torque), and there is a certain remaining torque M (M = (M N + M T ) - (M C + Mm)) for acceleration use. This stage is called the thermal acceleration stage; when the rotational speed reaches ns, the torque provided by the turbine is just equal to the resistance torque (M T = M C + Mm). At this time, the static frequency conversion starting device can trip. For safety reasons, it trips only when nb > ns. The third stage, also called the continuous thermal acceleration stage, in this stage, the gas turbine completely relies on the torque (M T ) provided by the turbine to overcome the resistance torque (M C + Mm) for acceleration, and its rotational speed increases from nb to n0. Refer to Figure 3 , when the gas turbine starts normally, for the start fuel control, it adopts open-loop control, and ensures the normal start of the gas turbine by successively giving the ignition fuel quantity, warm-up fuel quantity, small speed-up fuel quantity, speed switching point fuel quantity, and large speed-up fuel quantity.

[0041] See Figure 1 , the method for preventing the hot hang-up fault of the gas turbine includes the following steps:

[0042] S101. Determine the current rotational speed of the static frequency conversion starting device connected to the gas turbine, the current acceleration of the gas turbine, and the current turbine exhaust temperature of the gas turbine;

[0043] Among them, it is necessary to determine the current rotational speed of the static frequency conversion starting device connected to the gas turbine to judge what state the static frequency conversion starting device is in before tripping. It is also necessary to determine the turbine exhaust temperature and acceleration of the gas turbine to provide parameters for subsequent step judgment. Among them, the turbine exhaust temperature of the gas turbine can be measured by a high-temperature thermal capacitance, and the current acceleration can be calculated from the numerical difference of the instantaneous speed of the previous cycle measured by the eddy current on the gas turbine shaft, or can be calculated according to the differential of the rotational speed measurement signal. In this embodiment, the measurement methods of the rotational speed of the static frequency conversion starting device, the turbine exhaust temperature of the gas turbine, and the acceleration of the gas turbine are not specifically limited, and any other method can be used to measure the above three parameters.

[0044] S1021. When the current rotational speed is greater than or equal to the warm-up rotational speed and less than or equal to the about-to-trip rotational speed, the current acceleration is less than the first acceleration threshold, and the current turbine exhaust temperature is greater than the temperature threshold, increase the current acceleration to the first acceleration set value or lower the current turbine exhaust temperature;

[0045] Among them, when the current speed of the static frequency conversion starting device connected to the gas turbine is greater than or equal to the warm-up speed and less than or equal to the impending tripping speed, the relationship between the current acceleration a of the gas turbine and the first acceleration threshold is judged, and the first acceleration threshold is K1; and the relationship between the current turbine exhaust temperature of the gas turbine and the temperature threshold is judged, and the temperature threshold is the difference between the turbine exhaust temperature set value and K2. If a < K1, and T 当前透平排气 >T 透平排气设定值 > T - K2, it is necessary to adjust the current acceleration of the gas turbine and reduce the current turbine exhaust temperature.

[0046] S1022. When the current speed is greater than the impending tripping speed and less than or equal to the tripping speed, the current acceleration is less than the second acceleration threshold and the current turbine exhaust temperature is greater than the temperature threshold, the tripping speed is increased by a preset number of revolutions;

[0047] Among them, the impending tripping speed is the difference between the tripping speed and the preset number of revolutions.

[0048] Among them, when the current speed of the static frequency conversion starting device connected to the gas turbine is greater than the impending tripping speed and less than or equal to the tripping speed, the relationship between the current acceleration a of the gas turbine and the second acceleration threshold is judged, and the second acceleration threshold is a1 * K1; and the relationship between the current turbine exhaust temperature of the gas turbine and the temperature threshold is judged, and the temperature threshold is the difference between the turbine exhaust temperature set value and K2. If a < a1 * K1, and T 当前透平排气 >T 透平排气设定值 > T - K2, it is necessary to increase the tripping speed of the static frequency conversion starting device connected to the gas turbine by a preset number of revolutions, so that the current speed of the static frequency conversion starting device reaches the tripping speed later, and then the static frequency converter starting device and the gas turbine trip later. a1 is set according to the parameters of the gas turbine. For example, assume that the tripping speed of the static frequency conversion starting device connected to the gas turbine is 2000 r / min, and the impending tripping speed is 1900 r / min. When a < a1 * K1, and T 当前透平排气 >T 透平排气设定值 > T - K2, the tripping speed can be increased to 2100 r / min, and the impending tripping speed is 2000 r / min. K1 and K2 are coefficients set during use. In some specific cases, a range between 0 and 1 can be selected, but no specific limitation is made on this. After the tripping speed is increased, the current state of the current speed of the static frequency conversion starting device connected to the gas turbine will be judged again, and the corresponding processing means will be restarted. It can be understood that the above two judgment processes are inseparable.

[0049] In this embodiment, by determining the current speed state of the static frequency conversion starting device connected to the gas turbine, and judging the relationship between the current acceleration of the gas turbine and the current turbine exhaust temperature of the gas turbine and the corresponding thresholds, corresponding processing means are started according to the determined state of the gas turbine during startup. In this way, targeted elimination means are adopted to eliminate the hot hanging fault of the gas turbine unit, so that the gas turbine can be started smoothly in actual application.

[0050] In one embodiment, reducing the current turbine exhaust temperature of the gas turbine includes: adjusting the fuel quantity according to the temperature difference between the current turbine exhaust temperature and the set value of the turbine exhaust temperature and the opening degree of the compressor guide vane, so as to reduce the current turbine exhaust temperature; the fuel quantity is negatively correlated with the difference and positively correlated with the opening degree of the compressor guide vane.

[0051] The temperature difference between the current turbine exhaust temperature and the set value of the turbine exhaust temperature is controlled by a temperature control loop, and the temperature control loop is controlled by a PID control method. The calculation method of the fuel quantity in the temperature control loop is: Temperature control loop fuel quantity = (T 当前透平排气 -T 透平排气设定值 ) × Kp + IGVerr × Ki + current fuel quantity. Wherein, the current fuel quantity is the fuel quantity currently added to the combustion chamber, and the fuel quantity adjusted based on this calculation method adjusts the current fuel quantity. Kp and Ki are the parameters of the PID control, and the parameters can be set according to the actual situation; IGVerr is the opening degree of the compressor guide vane. By increasing the opening degree of the gas turbine guide vane and simultaneously adjusting the fuel valve to limit the input of the fuel quantity, the flow rate among the compressor, combustion chamber and turbine in the three components of the gas turbine can be optimized. The fuel quantity can be converted into a corresponding electrical signal through an analog-to-digital converter, and a filter is designed to filter the fuel value with a sharp input change. The filter equation can be 1 - 1 / (1 + S). Thus, when the current turbine exhaust temperature exceeds the set value of the turbine exhaust temperature, it will be immediately adjusted to reduce the current turbine exhaust temperature, so that the current turbine exhaust temperature is lower than the set value of the turbine exhaust temperature.

[0052] In this embodiment, a temperature control loop and PID regulation are adopted. The PID regulation has good adaptability and strong robustness, making the temperature regulation more accurate.

[0053] In one embodiment, adjusting the current acceleration to the acceleration set value includes: adjusting the fuel quantity according to the acceleration difference between the acceleration set value and the current acceleration, so that the current acceleration of the gas turbine reaches the first acceleration set value; the difference is positively correlated with the fuel quantity.

[0054] Among them, according to the acceleration difference between the acceleration set value and the current acceleration, the current acceleration is controlled by an acceleration control loop. The acceleration control loop is controlled by a PI control method. The calculation method of the fuel quantity in the acceleration control loop is: acceleration control loop fuel quantity = (acceleration set value - measured acceleration) × Kp + current fuel quantity. Ki is a parameter of the PI control, and the parameter can be set according to the actual situation. See Figure 4 , after the warm-up of the gas turbine, the acceleration process is divided into two stages. Before the static frequency conversion starting device connected to the gas turbine reaches the tripping speed, it is the small acceleration stage, and the current acceleration is controlled to reach the first acceleration set value a1.

[0055] In this embodiment, an acceleration control loop and PI regulation are adopted to make the acceleration regulation more accurate.

[0056] In one embodiment, during the startup and operation of the gas turbine, a multi-loop control low-selection method is adopted for control. The core idea of the multi-control loop low-selection is to linearly segment the non-linear gas turbine operating conditions and adopt different control means at different operating conditions of the gas turbine. Among them, it includes but is not limited to an open-loop control loop, an acceleration control loop, a speed / load control loop, a temperature control loop, a compressor pressure ratio limit control loop, and an output power limit control loop. When dealing with different operating conditions of the gas turbine, the corresponding control loop is selected by a low selector for control.

[0057] In one embodiment, after the gas turbine trips from the connected static frequency conversion starting device, the current acceleration is adjusted to the second acceleration set value; among them, the second acceleration set value is greater than the first acceleration set value.

[0058] Among them, see Figure 4 , after the warm-up of the gas turbine, the acceleration process is divided into two stages. Before the static frequency conversion starting device connected to the gas turbine reaches the tripping speed, it is the small acceleration stage; after the static frequency conversion starting device trips from the gas turbine, it is the large acceleration stage, and the acceleration is the second acceleration set value a = a2. The second acceleration set value is greater than the first acceleration set value. For example, the first acceleration set value is 3 m / s 2 , and the second acceleration set value is 5 m / s 2 .

[0059] In this embodiment, by setting the acceleration values in the small acceleration stage and the large acceleration stage, the gas turbine can start stably according to the preset acceleration value, reducing the probability of startup failure.

[0060] In one embodiment, the step of adjusting the current acceleration to the second acceleration setting value includes: increasing the current acceleration from the first acceleration setting value to the second acceleration setting value at a preset slope.

[0061] The method of increasing the current acceleration from the first acceleration setting value to the second acceleration setting value at a preset slope can adopt an interpolation table. The preset slope increase can effectively prevent the acceleration value from suddenly jumping at the moment of tripping. For example, the static variable frequency starting device connected to the gas turbine at the moment of tripping increases the acceleration value from the first acceleration setting value 3m / s 2 Rapidly jump to the second acceleration setting value of 5m / s 2 .

[0062] In one embodiment, when the current speed is greater than or equal to the warm-up speed and less than or equal to the speed about to trip, the current acceleration is less than the first acceleration threshold and the current turbine exhaust temperature is greater than the temperature threshold, a first thermal suspension warning prompt is generated; when the current speed is greater than or equal to the speed about to trip and less than or equal to the tripping speed, the current acceleration is less than the second acceleration threshold and the current turbine exhaust temperature is greater than the temperature threshold, a second thermal suspension warning prompt is generated.

[0063] Among them, the hot hanging warning prompt can be generated in multiple ways such as screen, staff terminal equipment and sound and light alarm. The hot hanging warning can not only be displayed directly, such as a flashing red light; it can also be divided into a first hot hanging warning and a second hot hanging warning according to the different states of the gas turbine, for example, the first hot hanging warning has a flashing yellow light and the second hot hanging warning has a flashing red light.

[0064] In this embodiment, the thermal suspension warning can be used to promptly notify the staff when a thermal suspension failure is about to occur, and the first thermal suspension warning and the second thermal suspension warning can make the staff more aware of the state of the gas turbine.

[0065] In one embodiment, after the step of increasing the tripping speed by a preset number of revolutions, the method further includes:

[0066] It is determined whether the current acceleration is less than the second acceleration threshold and whether the current turbine exhaust temperature is greater than the temperature threshold; if so, the tripping speed is increased by a preset number of revolutions.

[0067] Among them, on the basis that the tripping speed has been increased by a preset number of revolutions once, if after adjustment, the current acceleration is still less than the second acceleration threshold and the current turbine exhaust temperature is still greater than the temperature threshold, the tripping speed is increased by the preset number of revolutions again. If after the adjustment again, the current acceleration is still less than the second acceleration threshold and the current turbine exhaust temperature is still greater than the temperature threshold, the protection system will be activated. The specific number of times to increase the tripping speed by the preset number of revolutions can be determined according to actual conditions.

[0068] In this embodiment, by increasing the preset speed, the tripping of the static frequency conversion starting device connected to the gas turbine can be postponed, so that the system can reduce the occurrence of thermal suspension through adjustment, rather than starting the protection system when it is first judged that a fault is about to occur.

[0069] In one embodiment, for a mature gas turbine unit, a 10% margin is usually reserved for the maximum speed of the static frequency conversion starting device.

[0070] Embodiment 2

[0071] This embodiment provides a system for preventing thermal suspension faults of a gas turbine. Refer to Figure 5 , the system for preventing thermal suspension faults of a gas turbine in this embodiment includes:

[0072] A determination module 1, configured to determine the current speed of the static frequency conversion starting device connected to the gas turbine, the current acceleration of the gas turbine, and the current turbine exhaust temperature of the gas turbine;

[0073] Among them, it is necessary to determine the current speed of the static frequency conversion starting device connected to the gas turbine to judge what state the static variable starting device is in before tripping. It is also necessary to determine the turbine exhaust temperature and acceleration of the gas turbine to provide parameters for subsequent step judgments. Among them, the turbine exhaust temperature of the gas turbine can be measured by a high-temperature thermal capacitor, and the current acceleration can be calculated from the instantaneous speed numerical difference of the previous cycle measured by the eddy current on the gas turbine shaft, or can be calculated by differentiating the speed measurement signal. In this embodiment, the measurement methods of the speed of the static frequency conversion starting device, the turbine exhaust temperature of the gas turbine, and the acceleration of the gas turbine are not specifically limited, and any other method can be used to measure the above three parameters.

[0074] A first adjustment module 2, configured to increase the current acceleration to a first acceleration set value or reduce the current turbine exhaust temperature when the current speed is greater than or equal to the warm-up speed and less than or equal to the impending tripping speed, the current acceleration is less than the first acceleration threshold, and the current turbine exhaust temperature is greater than the temperature threshold;

[0075] Among them, when the current speed of the static frequency conversion starting device connected to the gas turbine is greater than or equal to the warm-up speed and less than or equal to the impending tripping speed, judge the relationship between the current acceleration a of the gas turbine and the first acceleration threshold, and the first acceleration threshold is K1; and judge the relationship between the current turbine exhaust temperature of the gas turbine and the temperature threshold, and the temperature threshold is the difference between the turbine exhaust temperature set value and K2. If a < K1, and T 当前透平排气 > T 透平排气设定值 -K2, it is necessary to adjust the current acceleration of the gas turbine and reduce the current turbine exhaust temperature.

[0076] The second adjustment module 3 is configured to increase the tripping speed by a preset number of revolutions per minute when the current speed is greater than the impending tripping speed and less than or equal to the tripping speed, the current acceleration is less than the second acceleration threshold, and the current turbine exhaust temperature is greater than the temperature threshold;

[0077] Wherein, the impending tripping speed is the difference between the tripping speed and the preset number of revolutions per minute.

[0078] Wherein, when the current speed of the static frequency conversion starting device connected to the gas turbine is greater than the impending tripping speed and less than or equal to the tripping speed, the relationship between the current acceleration a of the gas turbine and the second acceleration threshold is judged, and the second acceleration threshold is a1*K1; and the relationship between the current turbine exhaust temperature of the gas turbine and the temperature threshold is judged, and the temperature threshold is the difference between the turbine exhaust temperature set value and K2. If a < a1*K1, and T 当前透平排气 >T 透平排气设定值 - K2, it is necessary to increase the tripping speed of the static frequency conversion starting device connected to the gas turbine by a preset number of revolutions per minute, so that the current speed of the static frequency conversion starting device reaches the tripping speed later, thereby delaying the tripping of the static frequency converter starting device and the gas turbine. a1 is set according to the parameters of the gas turbine. For example, assume that the tripping speed of the static frequency conversion starting device connected to the gas turbine is 2000 revolutions per minute, and the impending tripping speed is 1900 revolutions per minute. When a < a1*K1, and T 当前透平排气 >T 透平排气设定值 - K2, the tripping speed can be increased to 2100 revolutions per minute, and the impending tripping speed is 2000 revolutions per minute. K1 and K2 are coefficients set during use. In some specific cases, a range between 0 and 1 can be selected, but no specific limitation is made thereto. After the tripping speed is increased, the current state of the static frequency conversion starting device connected to the gas turbine will be judged again, and the corresponding processing means will be restarted. It can be understood that the above two judgment processes are inseparable.

[0079] In this embodiment, by judging the current state of the static frequency conversion starting device connected to the gas turbine, and judging the relationship between the current acceleration of the gas turbine and the current turbine exhaust temperature and the corresponding thresholds, according to the state of the gas turbine during startup, the corresponding processing means are started. In this way, targeted elimination means are adopted to eliminate the thermal suspension fault of the gas turbine unit, so that the gas turbine can be started smoothly in practical applications.

[0080] In one embodiment, the first adjustment module 2 includes:

[0081] A temperature adjustment reduction unit is used to adjust the fuel quantity according to the temperature difference between the current turbine exhaust temperature and the set value of the turbine exhaust temperature and the opening degree of the compressor guide vane, so as to reduce the current turbine exhaust temperature; the fuel quantity is negatively correlated with the difference value and positively correlated with the opening degree of the compressor guide vane.

[0082] The temperature difference between the current turbine exhaust temperature and the set value of the turbine exhaust temperature is controlled by a temperature control loop. The temperature control loop uses a PID control method for control. The calculation method of the fuel quantity in the temperature control loop is: Temperature control loop fuel quantity = (T 当前透平排气 -T 透平排气设定值 ) × Kp + IGVerr × Ki + current fuel quantity. Wherein, the current fuel quantity is the fuel quantity currently added to the combustion chamber. The fuel quantity adjusted based on this calculation method adjusts the current fuel quantity. Kp and Ki are the parameters of the PID control, and the parameters can be set according to the actual situation; IGVerr is the opening degree of the compressor guide vane. By increasing the opening degree of the gas turbine guide vane and at the same time adjusting the fuel quantity input by restricting the gas valve, the flow between the compressor, the combustion chamber, and the turbine in the three components of the gas turbine can be optimized. The fuel quantity can be converted into a corresponding electrical signal through an analog-to-digital converter, and a filter is designed to filter the fuel value with a sharp input change. The filter equation can be 1 - 1 / (1 + S). Thus, when the current turbine exhaust temperature exceeds the set value of the turbine exhaust temperature, adjustment will be immediately carried out to reduce the current turbine exhaust temperature, so that the current turbine exhaust temperature is lower than the set value of the turbine exhaust temperature.

[0083] In this embodiment, a temperature control loop and PID adjustment are adopted. The PID adjustment has good adaptability and strong robustness, making the temperature adjustment more accurate.

[0084] In one embodiment, the first adjustment module 2 includes:

[0085] An acceleration adjustment unit is used to adjust the fuel quantity according to the acceleration difference between the acceleration set value and the current acceleration, so that the current acceleration of the gas turbine reaches the first acceleration set value; the difference value is positively correlated with the fuel quantity.

[0086] Wherein, according to the acceleration difference between the acceleration set value and the current acceleration, the current acceleration is controlled by an acceleration control loop. The acceleration control loop uses a PI control method for control. The calculation method of the fuel quantity in the acceleration control loop is: Acceleration control loop fuel quantity =

[0087] (Acceleration set value - measured acceleration) × Kp + current fuel quantity. Ki is the parameter of the PI control, and the parameter can be set according to the actual situation. See Figure 4, the acceleration process after the gas turbine warm-up is divided into two stages. Before the static frequency conversion starting device connected to the gas turbine reaches the tripping speed, it is the small acceleration stage, and the current acceleration is controlled to reach the first acceleration setting value a1.

[0088] In this embodiment, an acceleration control loop and PI regulation are adopted to make the acceleration regulation more accurate.

[0089] In one embodiment, during the startup and operation of the gas turbine, a multi-loop control low-selection method is used for control. The core idea of multi-control loop low-selection is to segment-linearize the non-linear gas turbine operating conditions and adopt different control means at different operating conditions of the gas turbine. Among them, it includes but is not limited to an open control loop, an acceleration control loop, a speed / load control loop, a temperature control loop, a compressor pressure ratio limit control loop, and an output power limit control loop. When dealing with different operating conditions of the gas turbine, the corresponding control loop is selected by a low selector for control.

[0090] In one embodiment, after the gas turbine trips from the connected static frequency conversion starting device, the current acceleration is adjusted to the second acceleration setting value; wherein, the second acceleration setting value is greater than the first acceleration setting value.

[0091] Among them, referring to Figure 4 , the acceleration process after the gas turbine warm-up is divided into two stages. Before the static frequency conversion starting device connected to the gas turbine reaches the tripping speed, it is the small acceleration stage; after the static frequency conversion starting device trips from the gas turbine, it is the large acceleration stage, and the acceleration is the second acceleration setting value a = a2. The second acceleration setting value is greater than the first acceleration setting value. For example, the first acceleration setting value is 3m / s 2 , and the second acceleration setting value is 5m / s 2 .

[0092] In this embodiment, by setting the acceleration values in the small acceleration stage and the large acceleration stage, the gas turbine can start stably according to the preset acceleration value, reducing the probability of startup failure.

[0093] In one embodiment, the step of adjusting the current acceleration to the second acceleration setting value includes: raising the current acceleration from the first acceleration setting value to the second acceleration setting value at a preset slope.

[0094] Among them, the method of raising the current acceleration from the first acceleration setting value to the second acceleration setting value at a preset slope can use an interpolation table. Rising at a preset slope can effectively prevent the sudden jump of the acceleration value at the moment of tripping. For example, when the static frequency conversion starting device connected to the gas turbine trips, the acceleration value jumps from the first acceleration setting value of 3m / s 2Quickly jump to the second acceleration set value of 5 m / s 2 .

[0095] In one embodiment, when the current speed is greater than or equal to the warm-up speed and less than or equal to the impending tripping speed, and when the current acceleration is less than the first acceleration threshold and the current turbine exhaust temperature is greater than the temperature threshold, a first thermal hang-up warning prompt is generated; when the current speed is greater than or equal to the impending tripping speed and less than or equal to the tripping speed, and the current acceleration is less than the second acceleration threshold and the current turbine exhaust temperature is greater than the temperature threshold, a second thermal hang-up warning prompt is generated.

[0096] Among them, the thermal hang-up warning prompt can be generated in various ways such as on the screen, the staff terminal device, and the audible and visual alarm. The thermal hang-up warning can not only be directly displayed, for example, the red light flashes; it can also be divided into the first thermal hang-up warning and the second thermal hang-up warning according to the different states of the gas turbine. For example, the first thermal hang-up warning has the yellow light flashing, and the second thermal hang-up warning has the red light flashing.

[0097] In this embodiment, through the thermal hang-up warning, when the thermal hang-up fault is about to occur, the staff can be notified in time, and through the first thermal hang-up warning and the second thermal hang-up warning, the staff can more clearly know what state the gas turbine is in.

[0098] In one embodiment, after the step of increasing the tripping speed by a preset number of revolutions, the following steps are further included:

[0099] Judge whether the current acceleration is less than the second acceleration threshold and whether the current turbine exhaust temperature is greater than the temperature threshold; if so, increase the tripping speed by a preset number of revolutions.

[0100] Among them, on the basis that the tripping speed has been increased by a preset number of revolutions once, if after adjustment, the current acceleration is still less than the second acceleration threshold and the current turbine exhaust temperature is still greater than the temperature threshold, increase the tripping speed by a preset number of revolutions again. If after re-adjustment, the current acceleration is still less than the second acceleration threshold and the current turbine exhaust temperature is still greater than the temperature threshold, the protection system will be started. How many times to specifically increase the tripping speed by a preset number of revolutions can be determined according to the actual situation.

[0101] In this embodiment, by increasing the preset number of revolutions, the tripping of the static frequency conversion starting device connected to the gas turbine can be postponed, so that the system can be adjusted to reduce the occurrence of thermal hang-up, rather than starting the protection system when it is first judged that a fault is about to occur.

[0102] In one embodiment, for a mature gas turbine unit, a 10% margin is usually reserved for the maximum speed of the static frequency conversion starting device.

[0103] Embodiment 3

[0104] This embodiment provides an electronic device, which can be presented in the form of a computing device (for example, it can be a server device), including a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the computer program, it can implement the method for preventing the hot suspension fault of a gas turbine provided in Embodiment 1.

[0105] Figure 6 The schematic diagram of the hardware structure of this embodiment is shown, as Figure 6 shown, the electronic device 9 specifically includes:

[0106] At least one processor 91, at least one memory 92, and a bus 93 for connecting different system components (including the processor 91 and the memory 92), where:

[0107] The bus 93 includes a data bus, an address bus, and a control bus.

[0108] The memory 92 includes volatile memory, such as a random access memory (RAM) 921 and / or a cache memory 922, and may further include a read-only memory (ROM) 923.

[0109] The memory 92 further includes a program / utility 925 having a set (at least one) of program modules 924. Such program modules 924 include but are not limited to: an operating system, one or more application programs, other program modules, and program data. Each or some combination of these examples may include the implementation of a network environment.

[0110] The processor 91 executes various functional applications and data processing by running the computer program stored in the memory 92, such as the method for preventing the hot suspension fault of a gas turbine provided in Embodiment 1 of the present invention.

[0111] The electronic device 9 can further communicate with one or more external devices 94 (such as a keyboard, a pointing device, etc.). Such communication can be carried out through an input / output (I / O) interface 95. And, the electronic device 9 can also communicate with one or more networks (such as a local area network (LAN), a wide area network (WAN), and / or a public network, such as the Internet) through a network adapter 96. The network adapter 96 communicates with other modules of the electronic device 9 through the bus 93. It should be understood that although not shown in the figure, other hardware and / or software modules can be used in combination with the electronic device 9, including but not limited to: microcode, device drivers, redundant processors, external disk drive arrays, RAID (disk array) systems, tape drives, and data backup storage systems, etc.

[0112] It should be noted that although several units / modules or sub-units / modules of the electronic device are mentioned in the above detailed description, this division is merely exemplary and not mandatory. In fact, according to the embodiments of the present application, the features and functions of two or more units / modules described above can be embodied in one unit / modules. Conversely, the features and functions of one unit / modules described above can be further divided and embodied by multiple units / modules.

[0113] Embodiment 4

[0114] This embodiment provides a computer-readable medium on which a computer program is stored, and when the program is executed by a processor, the steps of the method for preventing the hot suspension failure of a gas turbine provided in Embodiment 1 are implemented.

[0115] Among them, the more specific forms that the readable medium can adopt may include but are not limited to: portable disks, hard disks, random access memories, read-only memories, erasable programmable read-only memories, optical storage devices, magnetic storage devices, or any suitable combination of the above.

[0116] In a possible implementation manner, the present invention can also be implemented in the form of a program product, which includes program code. When the program product runs on a terminal device, the program code is used to cause the terminal device to execute the steps of the method for preventing the hot suspension failure of a gas turbine described in Embodiment 1.

[0117] Among them, the program code for executing the present invention can be written in any combination of one or more programming languages, and the program code can be executed entirely on the user device, partially on the user device, executed as an independent software package, partially on the user device and partially on a remote device, or entirely on a remote device.

[0118] Although the specific implementation manners of the present invention are described above, those skilled in the art should understand that this is only an example, and the protection scope of the present invention is defined by the appended claims. Without departing from the principles and essence of the present invention, those skilled in the art can make various changes or modifications to these implementation manners, but these changes and modifications all fall within the protection scope of the present invention.

Claims

1. A method for preventing hot hung fault of gas turbine, characterized in that, The method includes the following steps: Determine the current speed of the static frequency conversion starting device connected to the gas turbine, the current acceleration of the gas turbine, and the current turbine exhaust temperature of the gas turbine; When the current speed is greater than or equal to the warm-up speed and less than or equal to the impending tripping speed, the current acceleration is less than the first acceleration threshold, and the current turbine exhaust temperature is greater than the temperature threshold, increase the current acceleration to the first acceleration set value or reduce the current turbine exhaust temperature; When the current speed is greater than the impending tripping speed and less than or equal to the tripping speed, the current acceleration is less than the second acceleration threshold, and the current turbine exhaust temperature is greater than the temperature threshold, increase the tripping speed by a preset number of revolutions; Wherein, the impending tripping speed is the difference between the tripping speed and the preset number of revolutions; Adjusting the current acceleration to the acceleration set value includes: Adjust the fuel quantity according to the acceleration difference between the acceleration set value and the current acceleration so that the current acceleration of the gas turbine reaches the first acceleration set value; the difference is positively correlated with the fuel quantity.

2. The method for preventing the hot suspension fault of a gas turbine according to claim 1, wherein, Reducing the current turbine exhaust temperature includes: Adjust the fuel quantity according to the temperature difference between the current turbine exhaust temperature and the turbine exhaust temperature set value and the compressor guide vane opening to reduce the current turbine exhaust temperature; the fuel quantity is negatively correlated with the temperature difference and positively correlated with the compressor guide vane opening.

3. The method for preventing the hot suspension fault of a gas turbine according to claim 1, wherein The method further includes: after the gas turbine trips from the connected static frequency conversion starting device, adjust the current acceleration to the second acceleration set value; Wherein, the second acceleration set value is greater than the first acceleration set value.

4. The method for preventing hot hung fault of gas turbine according to claim 3, characterized in that, The step of adjusting the current acceleration to the second acceleration set value includes: increasing the current acceleration from the first acceleration set value to the second acceleration set value at a preset slope.

5. The method for preventing the hot hung fault of a gas turbine according to claim 1, characterized in that, It further includes: When the current speed is greater than or equal to the warm-up speed and less than or equal to the impending tripping speed, the current acceleration is less than the first acceleration threshold, and the current turbine exhaust temperature is greater than the temperature threshold, generate a first thermal hang-up warning prompt; When the current speed is greater than or equal to the impending tripping speed and less than or equal to the tripping speed, the current acceleration is less than the second acceleration threshold, and the current turbine exhaust temperature is greater than the temperature threshold, generate a second thermal hang-up warning prompt.

6. The method for preventing the hot hung fault of a gas turbine according to claim 1, characterized in that, After the step of increasing the tripping speed by a preset number of revolutions, it further includes: Judge whether the current acceleration is less than the second acceleration threshold and whether the current turbine exhaust temperature is greater than the temperature threshold; If so, increase the tripping speed by a preset number of revolutions.

7. A system for preventing hot hung faults of a gas turbine, characterized in that, The system for preventing the thermal hang-up fault of the gas turbine includes: A determination module for determining the current speed of the static frequency conversion starting device connected to the gas turbine, the current acceleration of the gas turbine, and the current turbine exhaust temperature of the gas turbine; The first adjustment module is used to increase the current acceleration to a first acceleration set value or reduce the current turbine exhaust temperature when the current speed is greater than or equal to the warm-up speed and less than or equal to the impending trip speed, the current acceleration is less than a first acceleration threshold, and the current turbine exhaust temperature is greater than a temperature threshold; The second adjustment module is used to increase the trip speed by a preset number of revolutions when the current speed is greater than the impending trip speed and less than or equal to the trip speed, the current acceleration is less than a second acceleration threshold, and the current turbine exhaust temperature is greater than a temperature threshold; Wherein, the impending trip speed is the difference between the trip speed and the preset number of revolutions; The first adjustment module includes an acceleration adjustment unit; The acceleration adjustment unit is used to adjust the fuel quantity according to the acceleration difference between the acceleration set value and the current acceleration, so that the current acceleration of the gas turbine reaches the first acceleration set value; the difference is positively correlated with the fuel quantity.

8. An electronic device, comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, characterized in that, When the processor executes the computer program, it implements the method for preventing the hot hang-up fault of the gas turbine according to any one of claims 1-6.

9. A computer-readable medium having a computer program stored thereon, characterized in that, When the computer program is executed by the processor, it implements the method for preventing the hot hang-up fault of the gas turbine according to any one of claims 1-6.

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