Gas turbine starting pre-detection method, device, equipment, storage medium and product

Abstract

The invention relates to the technical field of gas turbines, in particular to a gas turbine starting pre-detection method, device and equipment, a storage medium and a product. In the gas turbine starting stage, the rotating speed of a synchronous motor of a gas turbine is detected, so that the ignition moment is determined according to the rotating speed of the synchronous motor, and the ignition starting operation efficiency of the gas turbine is improved; the electromagnetic power and the mechanical power of the gas turbine in the continuous operation process after ignition are synchronously counted, the operation state of the gas turbine is controlled according to the electromagnetic power and the mechanical power until the gas turbine is stably ignited and operated, and the power generation efficiency of the gas turbine skipping from the starting stage to the power generation loading stage is improved; the technical problems that in the prior art, the starting stage of the gas turbine cannot be effectively controlled, and the power generation efficiency is reduced are solved.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a gas turbine startup pre-check method, device, equipment, storage medium and product. Background Art

[0002] The power generation system based on micro gas turbine is a distributed power source with wide application and development prospects. The operation process of the gas turbine is divided into the starting process and the power generation loading process. In this field, in order to reduce the emission of pollutants, combustion control is generally performed during the operation of the gas turbine. This process is mainly for the power generation loading process. At present, there is a lack of control schemes for the start-up of the gas turbine in this field. When the gas turbine is started, if the starting ignition conditions are not met, it will cause the gas turbine to shut down or deflagrate during the startup phase, thereby reducing the power generation efficiency and affecting the service life of the equipment.

[0003] The above contents are only used to assist in understanding the technical solution of the present invention and do not constitute an admission that the above contents are prior art. Summary of the invention

[0004] The main purpose of the present invention is to provide a gas turbine startup pre-inspection method, device, equipment, storage medium and product, aiming to solve the technical problem in the prior art that the startup phase of the gas turbine cannot be effectively controlled, thereby reducing the power generation efficiency.

[0005] To achieve the above object, the present invention provides a gas turbine startup pre-check method, the method comprising the following steps:

[0006] When the gas turbine is started, detecting the speed of the synchronous motor of the gas turbine;

[0007] When the speed of the synchronous motor is greater than or equal to a preset ignition speed threshold, igniting the gas turbine;

[0008] Counting electromagnetic power and mechanical power of the gas turbine during continuous operation;

[0009] The operating state of the gas turbine is controlled according to the electromagnetic power and the mechanical power until the gas turbine is successfully started.

[0010] Optionally, the ignition operation on the gas turbine includes:

[0011] Determining model information and basic properties of the gas turbine;

[0012] determining a fuel startup ratio according to the model information and the basic properties;

[0013] detecting a current ratio of each fuel in a combustion chamber of the gas turbine;

[0014] calculating a ratio error between the current ratio and the fuel start ratio;

[0015] When the proportional error is less than or equal to a preset error, an ignition operation is performed on the gas turbine.

[0016] Optionally, after calculating the ratio error between the current ratio and the fuel startup ratio, the method further includes:

[0017] When the proportional error is greater than a preset error, determining an influence factor of each fuel, wherein the influence factor represents the influence degree of the proportional error;

[0018] The opening of the control valve of each fuel inlet is adjusted according to the influencing factor to reduce the ratio error between the current ratio and the fuel startup ratio.

[0019] Optionally, controlling the operating state of the gas turbine according to the electromagnetic power and the mechanical power includes:

[0020] Determine the time difference from the ignition moment of the gas turbine when the electromagnetic power and the mechanical power are the same;

[0021] When the time difference is greater than or equal to a preset time threshold, the gas turbine is controlled to shut down.

[0022] Optionally, the gas turbine startup pre-check method further includes:

[0023] When the time difference is less than a preset time threshold, obtaining a pressure pulsation parameter in the combustion chamber;

[0024] Predicting the load state of the combustion chamber according to the electromagnetic power, the mechanical power and the pressure pulsation parameter;

[0025] The valve opening of at least one fuel inlet communicating with the combustion chamber is adjusted according to the load state.

[0026] Optionally, adjusting the valve opening of at least one fuel inlet communicating with the combustion chamber according to the load state comprises:

[0027] When the load state is a high load state, reducing the valve opening of at least one fuel inlet connected to the combustion chamber;

[0028] When the load state is a low load state, the valve opening of at least one fuel inlet communicating with the combustion chamber is increased.

[0029] In addition, to achieve the above-mentioned purpose, the present invention also provides a gas turbine startup pre-check device, the gas turbine startup pre-check device comprising:

[0030] A detection module, used for detecting the speed of the synchronous motor of the gas turbine when the gas turbine is started;

[0031] An ignition module, used for igniting the gas turbine when the speed of the synchronous motor is greater than or equal to a preset ignition speed threshold;

[0032] A statistical module, used for counting electromagnetic power and mechanical power of the gas turbine during continuous operation;

[0033] A control module is used to control the operating state of the gas turbine according to the electromagnetic power and the mechanical power until the gas turbine is successfully started.

[0034] In addition, to achieve the above-mentioned purpose, the present invention also proposes a gas turbine start-up precheck device, which includes: a memory, a processor, and a gas turbine start-up precheck program stored in the memory and executable on the processor, and the gas turbine start-up precheck program is configured to implement the steps of the gas turbine start-up precheck method described above.

[0035] In addition, to achieve the above-mentioned purpose, the present invention also proposes a storage medium, on which a gas turbine start-up pre-check program is stored. When the gas turbine start-up pre-check program is executed by a processor, the steps of the gas turbine start-up pre-check method described above are implemented.

[0036] In addition, to achieve the above-mentioned purpose, the present application also provides a computer program product, which includes a computer program, and when the computer program is executed by a processor, the steps of the gas turbine startup pre-check method as described above are implemented.

[0037] One or more technical solutions proposed in the present invention have at least the following technical effects: The present invention discloses a gas turbine start-up pre-check method, which comprises: when the gas turbine is started, detecting the speed of the synchronous motor of the gas turbine; when the speed of the synchronous motor is greater than or equal to a preset ignition speed threshold, igniting the gas turbine; counting the electromagnetic power and mechanical power of the gas turbine during continuous operation; and controlling the operating state of the gas turbine according to the electromagnetic power and the mechanical power until the gas turbine is successfully started. Compared with the prior art, the present invention improves the ignition start-up efficiency of the gas turbine by detecting the speed of the synchronous motor of the gas turbine during the start-up phase of the gas turbine to determine the ignition time according to the speed of the synchronous motor, and simultaneously counting the electromagnetic power and mechanical power of the gas turbine during continuous operation after ignition, and controlling the operating state of the gas turbine according to the electromagnetic power and the mechanical power until the gas turbine is stably ignited and operated, thereby improving the power generation efficiency of the gas turbine when it jumps from the start-up phase to the power generation loading phase, thereby avoiding the technical problem in the prior art that the start-up phase of the gas turbine cannot be effectively controlled and the power generation efficiency is reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present application and, together with the description, serve to explain the principles of the present application.

[0039] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, for ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.

[0040] Figure 1 It is a schematic flow chart of a first embodiment of a gas turbine startup pre-check method of the present invention;

[0041] Figure 2 It is a schematic flow chart of a second embodiment of a gas turbine startup pre-check method of the present invention;

[0042] Figure 3 A schematic diagram of a flow chart of a third embodiment of a gas turbine startup pre-check method according to the present invention;

[0043] Figure 4 It is a structural block diagram of a first embodiment of a gas turbine startup pre-check device of the present invention;

[0044] Figure 5 It is a structural schematic diagram of a gas turbine startup pre-check device in a hardware operating environment involved in an embodiment of the present invention.

[0045] The realization of the purpose, functional features and advantages of the present invention will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0046] It should be understood that the specific embodiments described herein are only used to explain the technical solutions of the present application and are not used to limit the present application.

[0047] In order to better understand the technical solution of the present application, a detailed description will be given below in conjunction with the accompanying drawings and specific implementation methods.

[0048] Based on this, the embodiment of the present invention provides a gas turbine startup pre-check method, referring to Figure 1 , Figure 1 The figure is a flow chart of a first embodiment of a gas turbine startup pre-check method according to the present invention.

[0049] In this embodiment, the gas turbine startup pre-check method includes:

[0050] Step S10: When the gas turbine is started, the speed of the synchronous motor of the gas turbine is detected.

[0051] It should be noted that the execution subject of this embodiment may be a computing service device with data processing, network communication and program running functions, such as a tablet computer, a personal computer, a mobile phone, etc., or an electronic device capable of realizing the above functions, a control chip or controller of a gas turbine, etc. The control chip of a gas turbine is taken as an example to illustrate this embodiment and the following embodiments.

[0052] It should be noted that after the gas turbine is powered on, it needs to go through the starting stage and the power generation loading stage. At the beginning of the starting stage, the synchronous click of the gas turbine will control the rotation of the rotor. At this time, the synchronous motor is in the motor operation state. After the gas turbine is ignited successfully, the combustion chamber starts to work, and the high-temperature gas drives the turbine to work. The magnetic synchronous motor obtains energy from the power grid and works together with the energy generated by the turbine to generate torque on the shaft to maintain the normal operation of the compressor. As the speed continues to increase, the power generated by the turbine can eventually meet the working requirements of the compressor and maintain the normal operation of the micro gas turbine, thereby entering the power generation loading stage and realizing the power generation process of the gas turbine.

[0053] Specifically, the speed of the synchronous motor of the gas turbine may be detected by a speed sensor installed inside the gas turbine, or may be measured by other equipment or devices that can measure the motor speed, and this embodiment does not impose any specific restrictions on this.

[0054] Step S20: When the speed of the synchronous motor is greater than or equal to a preset ignition speed threshold, ignition operation is performed on the gas turbine.

[0055] The preset ignition speed threshold is the minimum motor speed that supports the successful ignition of the gas turbine. The preset ignition speed threshold varies under different models or different environmental parameters. That is, the preset ignition speed threshold in this embodiment is associated with the model of the gas turbine and the environmental parameters of the area where the gas turbine is located. In this embodiment, it is between 8000r / min and 12000r / min, and this embodiment does not impose specific restrictions on this.

[0056] The ignition operation of the gas turbine includes but is not limited to: purging, pre-ignition and ignition. Purging refers to blowing out the flammable and explosive gases that may exist in the combustion chamber and replacing them with fresh air to avoid deflagration or explosion accidents during electric ignition; pre-ignition refers to opening the air damper to the low-fire ignition position and the electric spark igniter starts working; ignition refers to keeping the air damper at the low-fire position, opening the gas valve, and the igniter continuously releasing the arc for 3-5s.

[0057] Step S30: Counting the electromagnetic power and mechanical power of the gas turbine during continuous operation.

[0058] Mechanical power refers to the part of the gas turbine that converts the chemical energy of the fuel into mechanical energy by using the high-temperature and high-pressure gas generated by the combustion of fuel to drive the turbine to rotate; electromagnetic power usually refers to the electrical power output by the generator.

[0059] Step S40: controlling the operating state of the gas turbine according to the electromagnetic power and the mechanical power until the gas turbine is successfully started.

[0060] After the gas turbine is powered on, in order to ensure successful ignition, only electromagnetic power is output in the initial startup phase, and there is no combustion action in the combustion chamber. When the motor speed reaches a certain speed threshold, ignition is performed, the combustion chamber begins to burn, and mechanical power is generated. The mechanical power is generally in a linearly rising state. When the electromagnetic power and the mechanical power are equal, the mechanical energy generated by the combustion chamber is sufficient to provide the torque of the rotor shaft, and the motor can be switched from the engine state to the generator state, thereby realizing the power generation of the gas turbine.

[0061] This embodiment detects the speed of the synchronous motor of the gas turbine during the startup phase of the gas turbine to determine the ignition timing according to the speed of the synchronous motor, thereby improving the ignition startup efficiency of the gas turbine, and simultaneously counts the electromagnetic power and mechanical power of the gas turbine during continuous operation after ignition, and controls the operating state of the gas turbine according to the electromagnetic power and the mechanical power until the gas turbine is stably ignited and operated, thereby improving the power generation efficiency of the gas turbine when it jumps from the startup phase to the power generation loading phase, thereby avoiding the technical problem in the prior art that the startup phase of the gas turbine cannot be effectively controlled, thereby reducing the power generation efficiency.

[0062] Based on the first embodiment of the present application, in the second embodiment of the present application, the same or similar contents as those in the above-mentioned embodiment 1 can be referred to the above introduction, and will not be repeated in the following. Figure 2 , step S20, the gas turbine startup pre-check method further includes:

[0063] Step S201: Determine the model information and basic properties of the gas turbine.

[0064] Step S202: determining a fuel startup ratio according to the model information and the basic attributes.

[0065] Step S203: Detect the current ratio of each fuel in the combustion chamber of the gas turbine.

[0066] Step S204: Calculate the ratio error between the current ratio and the fuel start-up ratio.

[0067] Step S205: When the proportional error is less than or equal to a preset error, ignition operation is performed on the gas turbine.

[0068] It should be noted that the models of gas turbines include but are not limited to E100, ZK2000, etc., and the basic properties include but are not limited to the combustion chamber size of the gas turbine, the fuel type, and the environmental parameters of the area in which it is located, such as: ambient pressure, temperature, and humidity, etc. This embodiment does not impose specific restrictions on this.

[0069] The fuel startup ratio refers to the minimum ratio of each fuel in the combustion chamber of the gas turbine without explosion, flameout, etc. The ratio of each fuel in the combustion chamber can be adjusted by controlling the valve opening corresponding to each fuel.

[0070] It can be understood that the proportional error is used to evaluate the error between the combustion state of the combustion chamber of the gas turbine and the normal combustion state. The larger the proportional error between the current ratio and the fuel start-up ratio, the worse the combustion condition in the combustion chamber, and the lower the mechanical power that can be provided. The smaller the proportional error between the current ratio and the fuel start-up ratio, the better the combustion condition in the combustion chamber, and the higher the mechanical power that can be provided.

[0071] Before the formal ignition, by evaluating the proportional error between the current ratio of the combustion chamber and the fuel starting ratio, the combustion conditions during the ignition of the combustion chamber can be controlled in advance to avoid explosion or flameout.

[0072] Further, after calculating the ratio error between the current ratio and the fuel starting ratio, the method further includes:

[0073] When the proportional error is greater than a preset error, determining an influence factor of each fuel, wherein the influence factor represents the influence degree of the proportional error;

[0074] The opening of the control valve of each fuel inlet is adjusted according to the influencing factor to reduce the ratio error between the current ratio and the fuel startup ratio.

[0075] The preset error can be set to 15%. Specifically, the calculation formula of the proportional error is:

[0076] P=(a1*A+a2*B+a3*C...+a N *N)*100%

[0077] Among them, P is the proportional error, ABC, etc. are the proportional errors between each fuel and the fuel starting ratio, a1, a2...an are the influencing factors of each fuel, and the influencing factors of different fuels are different. The influencing factors of specific fuels can be obtained by querying the database, and N refers to the number of fuels.

[0078] This embodiment determines the model information and basic properties of the gas turbine; determines the fuel startup ratio according to the model information and the basic properties; detects the current ratio of each fuel in the combustion chamber of the gas turbine; calculates the proportional error between the current ratio and the fuel startup ratio; and performs an ignition operation on the gas turbine when the proportional error is less than or equal to a preset error, thereby monitoring the fuel ratio in the combustion chamber before ignition, thereby improving the ignition success rate and the subsequent power generation efficiency of the gas turbine.

[0079] Based on the second embodiment of the present application, in the third embodiment of the present application, the same or similar contents as those in the first embodiment can be referred to the above description, and will not be described in detail later. Figure 3 , step S40, the gas turbine startup pre-check method further includes:

[0080] Step S401: determining the time difference from the ignition time of the gas turbine when the electromagnetic power and the mechanical power are the same.

[0081] Step S402: When the time difference is greater than or equal to a preset time threshold, the gas turbine is controlled to shut down.

[0082] It should be noted that, due to the different effects of the synchronous motor in the gas turbine during the startup phase, it first operates as a motor and then as a generator. The conversion node lies in whether the mechanical power provided by the combustion chamber can support the energy of the shaft torque of the generator rotor. In this embodiment, if the time difference between the ignition moment and the moment when the electromagnetic power and the mechanical power are the same is long, it means that there may be incomplete combustion in the combustion chamber at this time, or other equipment failures. In order to avoid damage to the equipment, the gas turbine can be controlled to shut down and debugged. After the debugging is completed, the start-up pre-inspection is performed again.

[0083] Furthermore, the gas turbine startup pre-check method further includes:

[0084] When the time difference is less than a preset time threshold, obtaining a pressure pulsation parameter in the combustion chamber;

[0085] Predicting the load state of the combustion chamber according to the electromagnetic power, the mechanical power and the pressure pulsation parameter;

[0086] The valve opening of at least one fuel inlet communicating with the combustion chamber is adjusted according to the load state.

[0087] In the specific implementation, if the time difference between the ignition moment and the moment when the electromagnetic power and the mechanical power are the same is short, it means that the combustion chamber is operating normally. In order to further improve the combustion performance of the combustion chamber, the load state of the combustion chamber can be predicted based on the electromagnetic power, mechanical power and pressure pulsation parameters in the combustion chamber, and then the opening of the valve of each fuel can be adjusted to improve the combustion performance in the combustion chamber.

[0088] Among them, under normal operating conditions, the mechanical power provided by the combustion chamber is only generated after the combustion reaction occurs in the combustion chamber, and it is approximately a linear relationship, while the electromagnetic power first increases and then decreases until the gas turbine can sustain itself relying on the combustion performance of the combustion chamber, until the synchronous motor enters the generator state, at which time the electromagnetic power drops to the lowest.

[0089] Further, adjusting the valve opening of at least one fuel inlet connected to the combustion chamber according to the load state includes:

[0090] When the load state is a high load state, reducing the valve opening of at least one fuel inlet connected to the combustion chamber;

[0091] When the load state is a low load state, the valve opening of at least one fuel inlet communicating with the combustion chamber is increased.

[0092] Specifically, if the combustion chamber is in a high-load state, the fuel flow rate entering the combustion chamber can be reduced, thereby reducing the fuel content in the combustion chamber, avoiding incomplete combustion, and reducing the fuel load in the combustion chamber at the same time; if the combustion chamber is in a low-load state, the fuel flow rate in the combustion chamber can be increased, that is, the combustion efficiency of the combustion chamber can be increased, and the gas turbine can be prevented from shutting down due to insufficient combustion performance in a low-pressure environment.

[0093] This embodiment determines the time difference from the ignition moment of the gas turbine when the electromagnetic power and the mechanical power are the same; when the time difference is greater than or equal to a preset time threshold, the gas turbine is controlled to shut down, thereby further improving the combustion performance of the gas turbine during the startup phase.

[0094] This application also provides a gas turbine startup pre-check device, please refer to Figure 4 , the gas turbine startup pre-check device comprises:

[0095] The detection module 10 is used to detect the speed of the synchronous motor of the gas turbine when the gas turbine is started.

[0096] The ignition module 20 is used to perform an ignition operation on the gas turbine when the speed of the synchronous motor is greater than or equal to a preset ignition speed threshold.

[0097] The statistical module 30 is used to calculate the electromagnetic power and mechanical power of the gas turbine during continuous operation.

[0098] The control module 40 is used to control the operating state of the gas turbine according to the electromagnetic power and the mechanical power until the gas turbine is successfully started.

[0099] This embodiment detects the speed of the synchronous motor of the gas turbine during the startup phase of the gas turbine to determine the ignition timing according to the speed of the synchronous motor, thereby improving the ignition startup efficiency of the gas turbine, and simultaneously counts the electromagnetic power and mechanical power of the gas turbine during continuous operation after ignition, and controls the operating state of the gas turbine according to the electromagnetic power and the mechanical power until the gas turbine is stably ignited and operated, thereby improving the power generation efficiency of the gas turbine when it jumps from the startup phase to the power generation loading phase, thereby avoiding the technical problem in the prior art that the startup phase of the gas turbine cannot be effectively controlled, thereby reducing the power generation efficiency.

[0100] In one embodiment, the ignition module 20 is also used to determine the model information and basic properties of the gas turbine; determine the fuel starting ratio based on the model information and the basic properties; detect the current ratio of each fuel in the combustion chamber of the gas turbine; calculate the proportional error between the current ratio and the fuel starting ratio; and when the proportional error is less than or equal to a preset error, perform an ignition operation on the gas turbine.

[0101] In one embodiment, the ignition module 20 is also used to determine the influence factor of each fuel when the proportional error is greater than a preset error, and the influence factor represents the degree of influence of the proportional error; and adjust the opening of the control valve of each fuel inlet according to the influence factor to reduce the proportional error between the current ratio and the fuel starting ratio.

[0102] In one embodiment, the control module 40 is further used to determine the time difference from the ignition time of the gas turbine when the electromagnetic power and the mechanical power are the same; when the time difference is greater than or equal to a preset time threshold, the gas turbine is controlled to shut down.

[0103] In one embodiment, the control module 40 is also used to obtain the pressure pulsation parameters in the combustion chamber when the time difference is less than a preset time threshold; predict the load state of the combustion chamber based on the electromagnetic power, the mechanical power and the pressure pulsation parameters; and adjust the valve opening of at least one fuel inlet connected to the combustion chamber according to the load state.

[0104] In one embodiment, the control module 40 is further used to reduce the valve opening of at least one fuel inlet connected to the combustion chamber when the load state is a high load state; and to increase the valve opening of at least one fuel inlet connected to the combustion chamber when the load state is a low load state.

[0105] The present application provides a gas turbine startup pre-check device, which includes: at least one processor; and a memory communicatively connected to the at least one processor; wherein the memory stores instructions executable by the at least one processor, and the instructions are executed by the at least one processor so that the at least one processor can execute the gas turbine startup pre-check method in the above-mentioned embodiment one.

[0106] Reference below Figure 5 , which shows a schematic diagram of the structure of a gas turbine startup pre-check device suitable for implementing the embodiment of the present application. The gas turbine startup pre-check device in the embodiment of the present application may include but is not limited to mobile terminals such as mobile phones, laptop computers, digital broadcast receivers, PDAs (Personal Digital Assistants), PADs (Portable Application Descriptions), PMPs (Portable Media Players), vehicle-mounted terminals (such as vehicle-mounted navigation terminals), etc., and fixed terminals such as digital TVs, desktop computers, etc. Figure 5 The gas turbine startup pre-check device shown is only an example and should not bring any limitation to the functions and scope of use of the embodiments of the present application.

[0107] like Figure 5As shown, the gas turbine startup pre-check device may include a processing device 1001 (e.g., a central processing unit, a graphics processing unit, etc.), which can perform various appropriate actions and processes according to a program stored in a read-only memory (ROM) 1002 or a program loaded from a storage device 1003 to a random access memory (RAM) 1004. Various programs and data required for the operation of the gas turbine startup pre-check device are also stored in the RAM 1004. The processing device 1001, the ROM 1002, and the RAM 1004 are connected to each other via a bus 1005. An input / output (I / O) interface 1006 is also connected to the bus. Typically, the following systems may be connected to the I / O interface 1006: input devices 1007 including, for example, a touch screen, a touchpad, a keyboard, a mouse, an image sensor, a microphone, an accelerometer, a gyroscope, etc.; output devices 1008 including, for example, a liquid crystal display (LCD), a speaker, a vibrator, etc.; storage devices 1003 including, for example, a magnetic tape, a hard disk, etc.; and communication devices 1009. The communication device 1009 may allow the gas turbine startup pre-check device to communicate with other devices wirelessly or by wire to exchange data. Although the gas turbine startup pre-check device with various systems is shown in the figure, it should be understood that it is not required to implement or have all the systems shown. More or fewer systems may be implemented or have instead.

[0108] In particular, according to the embodiments disclosed in the present application, the process described above with reference to the flowchart can be implemented as a computer software program. For example, the embodiments disclosed in the present application include a computer program product, which includes a computer program carried on a computer-readable medium, and the computer program includes a program code for executing the method shown in the flowchart. In such an embodiment, the computer program can be downloaded and installed from a network through a communication device, or installed from a storage device 1003, or installed from a ROM 1002. When the computer program is executed by the processing device 1001, the above-mentioned functions defined in the method of the embodiment disclosed in the present application are executed.

[0109] The gas turbine startup pre-check device provided by the present application adopts the gas turbine startup pre-check method in the above embodiment, which can solve the technical problem of gas turbine startup pre-check. Compared with the prior art, the beneficial effect of the gas turbine startup pre-check device provided by the present application is the same as the beneficial effect of the gas turbine startup pre-check method provided by the above embodiment, and the other technical features in the gas turbine startup pre-check device are the same as the features disclosed in the method of the previous embodiment, which will not be repeated here.

[0110] It should be understood that the various parts disclosed in this application can be implemented by hardware, software, firmware or a combination thereof. In the description of the above embodiments, specific features, structures, materials or characteristics can be combined in any one or more embodiments or examples in a suitable manner.

[0111] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any person skilled in the art who is familiar with the present technical field can easily think of changes or substitutions within the technical scope disclosed in the present application, which should be included in the protection scope of the present application. Therefore, the protection scope of the present application should be based on the protection scope of the claims.

[0112] The present application provides a computer-readable storage medium having computer-readable program instructions (ie, computer programs) stored thereon, the computer-readable program instructions being used to execute the gas turbine startup pre-check method in the above-mentioned embodiment.

[0113] The computer-readable storage medium provided in the present application may be, for example, a USB flash drive, but is not limited to electrical, magnetic, optical, electromagnetic, infrared, or semiconductor systems, systems or devices, or any combination of the above. More specific examples of computer-readable storage media may include, but are not limited to: an electrical connection with one or more wires, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above. In this embodiment, the computer-readable storage medium may be any tangible medium containing or storing a program that can be used by or in combination with an instruction execution system, system or device. The program code contained on the computer-readable storage medium may be transmitted using any appropriate medium, including but not limited to: wires, optical cables, RF (Radio Frequency), etc., or any suitable combination of the above.

[0114] The computer-readable storage medium may be included in the gas turbine startup pre-check device; or may exist independently without being assembled into the gas turbine startup pre-check device.

[0115] The computer-readable storage medium carries one or more programs. When the one or more programs are executed by the gas turbine startup pre-check device, the gas turbine startup pre-check device is enabled to perform: gas turbine startup pre-check.

[0116] Computer program code for performing the operations of the present application may be written in one or more programming languages ​​or a combination thereof, including object-oriented programming languages ​​such as Java, Smalltalk, C++, and conventional procedural programming languages ​​such as "C" or similar programming languages. The program code may be executed entirely on the user's computer, partially on the user's computer, as a separate software package, partially on the user's computer and partially on a remote computer, or entirely on a remote computer or server. In the case of a remote computer, the remote computer may be connected to the user's computer through any type of network, including a local area network (LAN) or a wide area network (WAN), or may be connected to an external computer (e.g., via the Internet using an Internet service provider).

[0117] The flow chart and block diagram in the accompanying drawings illustrate the possible architecture, function and operation of the system, method and computer program product according to various embodiments of the present application. In this regard, each square box in the flow chart or block diagram can represent a module, a program segment or a part of a code, and the module, the program segment or a part of the code contains one or more executable instructions for realizing the specified logical function. It should also be noted that in some alternative implementations, the functions marked in the square box can also occur in a sequence different from that marked in the accompanying drawings. For example, two square boxes represented in succession can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each square box in the block diagram and / or flow chart, and the combination of the square boxes in the block diagram and / or flow chart can be implemented with a dedicated hardware-based system that performs a specified function or operation, or can be implemented with a combination of dedicated hardware and computer instructions.

[0118] The modules involved in the embodiments described in this application may be implemented by software or hardware, wherein the name of the module does not constitute a limitation on the unit itself in some cases.

[0119] The readable storage medium provided in the present application is a computer-readable storage medium, which stores computer-readable program instructions (i.e., computer programs) for executing the above-mentioned gas turbine startup pre-check method, and can solve the technical problem of gas turbine startup pre-check. Compared with the prior art, the beneficial effects of the computer-readable storage medium provided in the present application are the same as the beneficial effects of the gas turbine startup pre-check method provided in the above-mentioned embodiment, and will not be described in detail here.

[0120] The present application also provides a computer program product, comprising a computer program, wherein when the computer program is executed by a processor, the steps of the gas turbine startup pre-check method as described above are implemented.

[0121] The computer program product provided in this application can solve the technical problem of pre-checking the start of a gas turbine. Compared with the prior art, the beneficial effects of the computer program product provided in this application are the same as the beneficial effects of the pre-checking method for starting a gas turbine provided in the above embodiment, which will not be described in detail here.

[0122] The above descriptions are only some embodiments of the present application, and are not intended to limit the patent scope of the present application. All equivalent structural changes made using the contents of the present application specification and drawings under the technical concept of the present application, or direct / indirect applications in other related technical fields are included in the patent protection scope of the present application.

Claims

1. A gas turbine startup pre-check method, characterized in that: The gas turbine startup pre-check method comprises: When the gas turbine is started, detecting the speed of the synchronous motor of the gas turbine; When the speed of the synchronous motor is greater than or equal to a preset ignition speed threshold, igniting the gas turbine; Counting electromagnetic power and mechanical power of the gas turbine during continuous operation; The operating state of the gas turbine is controlled according to the electromagnetic power and the mechanical power until the gas turbine is successfully started.

2. The method according to claim 1, characterized in that The ignition operation of the gas turbine includes: Determining model information and basic properties of the gas turbine; determining a fuel startup ratio according to the model information and the basic properties; detecting a current ratio of each fuel in a combustion chamber of the gas turbine; calculating a ratio error between the current ratio and the fuel start ratio; When the proportional error is less than or equal to a preset error, an ignition operation is performed on the gas turbine.

3. The method according to claim 2, characterized in that After calculating the ratio error between the current ratio and the fuel start-up ratio, the method further includes: When the proportional error is greater than a preset error, determining an influence factor of each fuel, wherein the influence factor represents the influence degree of the proportional error; The opening of the control valve of each fuel inlet is adjusted according to the influencing factor to reduce the ratio error between the current ratio and the fuel startup ratio.

4. The method according to claim 1, characterized in that The controlling the operating state of the gas turbine according to the electromagnetic power and the mechanical power comprises: Determine the time difference from the ignition moment of the gas turbine when the electromagnetic power and the mechanical power are the same; When the time difference is greater than or equal to a preset time threshold, the gas turbine is controlled to shut down.

5. The method according to claim 4, characterized in that The gas turbine startup pre-check method further includes: When the time difference is less than a preset time threshold, obtaining a pressure pulsation parameter in the combustion chamber; Predicting the load state of the combustion chamber according to the electromagnetic power, the mechanical power and the pressure pulsation parameter; The valve opening of at least one fuel inlet communicating with the combustion chamber is adjusted according to the load state.

6. The method according to claim 5, characterized in that The step of adjusting the valve opening of at least one fuel inlet connected to the combustion chamber according to the load state comprises: When the load state is a high load state, reducing the valve opening of at least one fuel inlet connected to the combustion chamber; When the load state is a low load state, the valve opening of at least one fuel inlet communicating with the combustion chamber is increased.

7. A gas turbine startup pre-check device, characterized in that: The gas turbine startup pre-check device comprises: A detection module, used for detecting the speed of the synchronous motor of the gas turbine when the gas turbine is started; An ignition module, used for igniting the gas turbine when the speed of the synchronous motor is greater than or equal to a preset ignition speed threshold; A statistical module, used for counting electromagnetic power and mechanical power of the gas turbine during continuous operation; A control module is used to control the operating state of the gas turbine according to the electromagnetic power and the mechanical power until the gas turbine is successfully started.

8. A gas turbine startup pre-check device, characterized in that: The gas turbine start-up pre-check device comprises: a memory, a processor and a gas turbine start-up pre-check program stored in the memory and executable on the processor, wherein the gas turbine start-up pre-check program is configured to implement the steps of the gas turbine start-up pre-check method as described in any one of claims 1 to 6.

9. A storage medium, characterized in that: The storage medium stores a gas turbine startup pre-check program, and when the gas turbine startup pre-check program is executed by the processor, the steps of the gas turbine startup pre-check method according to any one of claims 1 to 6 are implemented.

10. A computer program product, characterized in that The computer program product comprises a computer program, and when the computer program is executed by a processor, the steps of the gas turbine startup pre-check method according to any one of claims 1 to 6 are implemented.

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