Gas turbine and method, device and apparatus for monitoring its tempering

Abstract

The application relates to a gas turbine and a tempering monitoring method, device and equipment thereof, wherein a plurality of pressure sensors and a plurality of temperature sensors are arranged on the inner wall of a premixing nozzle channel in a circumferential equidistant manner, the tempering monitoring method comprises the following steps: obtaining pressure values detected by the plurality of pressure sensors and temperature values detected by the plurality of temperature sensors; and performing tempering monitoring on a combustion chamber in the gas turbine according to the plurality of pressure values and the plurality of temperature values. Therefore, the method combines the pressure values detected by the pressure sensors and the temperature values detected by the temperature sensors to realize the tempering monitoring on the combustion chamber in the gas turbine, and the reliability of monitoring the tempering of the combustion chamber is improved.

Description

Technical Field

[0001] This application relates to the field of gas turbine technology, and in particular to a gas turbine and its backfire monitoring method, device and equipment. Background Technology

[0002] With the acceleration of global carbon neutrality, gas turbines capable of burning hydrogen are a key focus of research and development for various gas turbine manufacturers. Developing hydrogen-blended or pure hydrogen gas turbines can, on the one hand, resolve energy security issues, and on the other hand, alleviate the obstacles to the development of the gas turbine industry caused by natural gas shortages.

[0003] Compared to traditional natural gas fuels, the addition of hydrogen significantly alters the physical and chemical properties of the fuel. Hydrogen broadens the combustible range of traditional hydrocarbon fuels, accelerates flame propagation, increases combustion speed in turbulent combustion, and lowers the minimum ignition energy, making it easier for the fuel to spontaneously combust. The most significant impact of these changes on gas turbines is that they increase the likelihood of backfire in the combustion chamber. Backfire refers to the phenomenon where, under certain combustion conditions, the flame propagates upstream into the mixing channel within the combustion chamber nozzle. Backfire not only severely damages combustion chamber components but also increases pollutant emissions. Therefore, temperature sensors are typically installed in operating combustion chambers to monitor backfire and protect the safe operation of the gas turbine combustion chamber. However, temperature sensors are prone to damage, thus affecting the reliability of monitoring. Summary of the Invention

[0004] This application aims to at least partially solve one of the technical problems in the related art.

[0005] Therefore, the first objective of this application is to propose a method for monitoring backfire in a gas turbine. This method combines pressure values ​​detected by a pressure sensor and temperature values ​​detected by a temperature sensor to monitor backfire in the combustion chamber of a gas turbine, thereby improving the reliability of monitoring backfire in the combustion chamber.

[0006] The second objective of this application is to provide a gas turbine backfire monitoring device.

[0007] The third objective of this application is to provide a gas turbine backfire monitoring device.

[0008] The fourth objective of this application is to propose a gas turbine.

[0009] The fifth objective of this application is to provide a computer-readable storage medium.

[0010] To achieve the above objectives, a first aspect of this application proposes a method for monitoring backfire in a gas turbine. In this method, multiple pressure sensors and multiple temperature sensors are arranged at equal intervals along the circumferential direction on the inner wall of the premixed nozzle channel in the gas turbine. The method includes: acquiring pressure values ​​detected by the multiple pressure sensors and temperature values ​​detected by the multiple temperature sensors; and monitoring backfire in the combustion chamber of the gas turbine based on the multiple pressure values ​​and the multiple temperature values.

[0011] According to the gas turbine backfire monitoring method of this application, multiple pressure values ​​are detected by multiple pressure sensors and multiple temperature values ​​are detected by multiple temperature sensors. Backfire monitoring is then performed on the combustion chamber of the gas turbine based on these pressure and temperature values. Therefore, this method combines the pressure values ​​detected by the pressure sensors and the temperature values ​​detected by the temperature sensors to achieve backfire monitoring in the gas turbine combustion chamber, thus improving the reliability of backfire monitoring.

[0012] In addition, the gas turbine backfire monitoring method proposed in the first aspect of this application may also have the following additional technical features:

[0013] According to one embodiment of this application, the backfire monitoring of the combustion chamber in the gas turbine based on a plurality of pressure values ​​and temperature values ​​includes: in the same premixed nozzle channel, if at least one of the plurality of pressure values ​​is less than a set pressure value and at least one of the plurality of temperature values ​​is greater than a set temperature value, then it is determined that the combustion chamber has experienced backfire.

[0014] According to one embodiment of this application, the backfire monitoring of the combustion chamber in the gas turbine based on a plurality of pressure values ​​and temperature values ​​includes: in the same premixed nozzle channel, if at least one of the pressure values ​​has a pressure reduction rate greater than a set pressure reduction rate, and at least one of the temperature values ​​has a temperature greater than a set temperature value, then it is determined that the combustion chamber has experienced backfire.

[0015] According to one embodiment of this application, the backfire monitoring of the combustion chamber in the gas turbine based on a plurality of pressure values ​​and temperature values ​​includes: in the same premixed nozzle channel, if at least one of the plurality of pressure values ​​is less than a set pressure value, and at least one of the plurality of temperature values ​​has a rate of increase greater than a set rate of increase, then it is determined that the combustion chamber has experienced backfire.

[0016] According to one embodiment of this application, the backfire monitoring of the combustion chamber in the gas turbine based on a plurality of pressure values ​​and temperature values ​​includes: in the same premixed nozzle channel, if at least one of the plurality of pressure values ​​has a pressure reduction rate greater than a set pressure reduction rate, and at least one of the plurality of temperature values ​​has a temperature increase rate greater than a set temperature increase rate, then it is determined that the combustion chamber has experienced backfire.

[0017] According to one embodiment of this application, the pressure value is set to the difference between the average of a plurality of pressure values ​​and a first pressure threshold, or the difference between the theoretically calculated pressure value under the same working conditions and a second pressure threshold.

[0018] According to one embodiment of this application, the temperature value is set to the sum of the average of a plurality of temperature values ​​and a first temperature threshold, or the sum of the theoretically calculated temperature value and a second temperature threshold under the same operating conditions.

[0019] To achieve the above objectives, a second aspect of this application provides a gas turbine backfire monitoring device, wherein multiple pressure sensors and multiple temperature sensors are arranged at equal intervals along the circumferential direction on the inner wall of the premixed nozzle channel in the gas turbine. The device includes: an acquisition module for acquiring pressure values ​​detected by the multiple pressure sensors and temperature values ​​detected by the multiple temperature sensors; and a monitoring module for monitoring backfire in the combustion chamber of the gas turbine based on the multiple pressure values ​​and the multiple temperature values.

[0020] According to the gas turbine backfire monitoring device of this application embodiment, an acquisition module acquires multiple pressure values ​​detected by multiple pressure sensors and multiple temperature values ​​detected by multiple temperature sensors. This allows the monitoring module to perform backfire monitoring in the combustion chamber of the gas turbine based on the multiple pressure and temperature values. Therefore, this device combines the pressure values ​​detected by the pressure sensors and the temperature values ​​detected by the temperature sensors to achieve backfire monitoring in the combustion chamber of the gas turbine, improving the reliability of combustion chamber backfire monitoring.

[0021] In addition, the gas turbine backfire monitoring device proposed in the second aspect embodiment of this application may also have the following additional technical features:

[0022] According to one embodiment of this application, the monitoring module is specifically used to determine that backfire has occurred in the combustion chamber if at least one of the multiple pressure values ​​is less than a set pressure value and at least one of the multiple temperature values ​​is greater than a set temperature value in the same premixed nozzle channel.

[0023] According to one embodiment of this application, the monitoring module is specifically used to determine that backfire has occurred in the combustion chamber if, in the same premixed nozzle channel, at least one of the pressure values ​​has a pressure reduction rate greater than a set pressure reduction rate, and at least one of the temperature values ​​has a temperature greater than a set temperature value.

[0024] According to one embodiment of this application, the monitoring module is specifically used to determine that backfire has occurred in the combustion chamber if at least one of the multiple pressure values ​​is less than a set pressure value and at least one of the multiple temperature values ​​has a rate of increase greater than a set temperature rate of increase in the same premixed nozzle channel.

[0025] According to one embodiment of this application, the monitoring module is specifically used to determine that backfire has occurred in the combustion chamber if, in the same premixed nozzle channel, at least one of the pressure values ​​has a pressure reduction rate greater than a set pressure reduction rate, and at least one of the temperature values ​​has a temperature increase rate greater than a set temperature increase rate.

[0026] According to one embodiment of this application, the pressure value is set to the difference between the average of a plurality of pressure values ​​and a first pressure threshold, or the difference between the theoretically calculated pressure value under the same working conditions and a second pressure threshold.

[0027] According to one embodiment of this application, the temperature value is set to the sum of the average of a plurality of temperature values ​​and a first temperature threshold, or the sum of the theoretically calculated temperature value and a second temperature threshold under the same operating conditions.

[0028] To achieve the above objectives, a third aspect of this application provides a gas turbine backfire monitoring device, comprising: a processor and a memory; wherein the processor reads executable program code stored in the memory to run a program corresponding to the executable program code, so as to implement the gas turbine backfire monitoring method as proposed in the first aspect of this application.

[0029] The gas turbine backfire monitoring device according to the embodiments of this application improves the reliability of monitoring combustion chamber backfire by executing the gas turbine backfire monitoring method of the above embodiments.

[0030] To achieve the above objectives, a fourth aspect of this application provides a gas turbine, including: the gas turbine backfire monitoring device proposed in the third aspect of this application.

[0031] According to the embodiments of this application, by employing the above-described gas turbine backfire monitoring equipment, the reliability of monitoring combustion chamber backfire can be improved.

[0032] To achieve the above objectives, a fifth aspect of this application provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the gas turbine backfire monitoring method proposed in the first aspect of this application.

[0033] By executing the gas turbine backfire monitoring method of the above embodiments according to the computer-readable storage medium of the present application, the reliability of monitoring combustion chamber backfire can be improved.

[0034] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and do not limit this application. Attached Figure Description

[0035] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application, and do not constitute an undue limitation of this application.

[0036] Figure 1 This is a flowchart of a gas turbine backfire monitoring method according to an embodiment of this application;

[0037] Figure 2 This is a schematic diagram of the combustion chamber in a gas turbine according to an embodiment of this application;

[0038] Figure 3 This is a block diagram of a gas turbine backfire monitoring device according to an embodiment of this application. Detailed Implementation

[0039] To enable those skilled in the art to better understand the technical solutions of this application, the technical solutions in the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings.

[0040] It should be noted that the terms "first," "second," etc., used in the specification, claims, and accompanying drawings of this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of this application described herein can be implemented in orders other than those illustrated or described herein. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with this application. Rather, they are merely examples of apparatuses and methods consistent with some aspects of this application as detailed in the appended claims.

[0041] The following description, with reference to the accompanying drawings, describes the gas turbine and its backfire monitoring method, apparatus, and equipment provided in the embodiments of this application.

[0042] With the acceleration of global carbon neutrality, gas turbines capable of burning hydrogen are a key focus of research and development for various gas turbine manufacturers. Developing hydrogen-blended or pure hydrogen gas turbines can, on the one hand, resolve energy security issues, and on the other hand, alleviate the obstacles to the development of the gas turbine industry caused by natural gas shortages.

[0043] Compared to traditional natural gas fuels, the addition of hydrogen significantly alters the physical and chemical properties of the fuel. Hydrogen broadens the combustible range of traditional hydrocarbon fuels, accelerates flame propagation, increases combustion speed in turbulent combustion, and lowers the minimum ignition energy, making it easier for the fuel to spontaneously combust. The most significant impact of these changes on gas turbines is that they increase the likelihood of backfire in the combustion chamber. Backfire refers to the phenomenon where, under certain combustion conditions, the flame propagates upstream into the mixing channel within the combustion chamber nozzle. Backfire not only severely damages combustion chamber components but also increases pollutant emissions. Therefore, sensors are typically installed in the operating combustion chamber to monitor backfire and ensure safe operation of the gas turbine combustion chamber. For example, temperature sensors can be placed on the operating combustion chamber for backfire monitoring. However, temperature sensors are easily damaged, which affects the reliability of monitoring. Similarly, pressure sensors can be placed on the operating combustion chamber for backfire monitoring, but some backfire tests have shown that backfire is much more sensitive to temperature than to velocity. Furthermore, optical sensors, such as flame detectors, can be placed on the operating combustion chamber for backfire monitoring. However, because these optical sensors are optically connected to the combustion chamber and configured to detect optical properties related to one or more combustion zones, multiple different optical sensors are needed to monitor flame wavelengths in different combustion zones to detect backfire. Generally, optical sensors are expensive and easily damaged in high-temperature environments.

[0044] To address this, this application proposes a novel method for monitoring backfire in gas turbines. This method combines pressure values ​​detected by a pressure sensor and temperature values ​​detected by a temperature sensor to monitor backfire in the combustion chamber of a gas turbine. This not only overcomes the insufficient sensitivity of using a pressure sensor alone for backfire monitoring, but also avoids the problem of temperature sensors being easily damaged when used alone for backfire monitoring, as well as the high cost and susceptibility to damage caused by using optical sensors alone. This improves the reliability of monitoring backfire in the combustion chamber.

[0045] Figure 1 This is a flowchart of a gas turbine backfire monitoring method according to an embodiment of this application.

[0046] It should be noted that the execution subject of the gas turbine backfire monitoring method in this application embodiment can be a gas turbine backfire monitoring device, which can be configured in a gas turbine backfire monitoring equipment to realize the backfire monitoring of the combustion chamber on the gas turbine backfire monitoring equipment.

[0047] In the embodiments of this application, such as Figure 2 As shown, gases such as hydrogen are mixed in the premixed nozzle channel and delivered to the combustion chamber. In the combustion chamber, the gas and fuel are mixed and burned to produce high-temperature, high-pressure combustion gas, which is then sent to the outlet via a transition section. Multiple pressure sensors and multiple temperature sensors are arranged circumferentially at equal intervals inside the premixed nozzle channel of the gas turbine. For example, three pressure sensors and three temperature sensors are arranged circumferentially at equal intervals inside each premixed nozzle channel. It should be noted that... Figure 2 This is only a partial schematic diagram of the combustion chamber in a gas turbine. The entire combustion chamber may contain multiple such partial diagrams and multiple premixed nozzle channels.

[0048] like Figure 1 As shown, the gas turbine backfire monitoring method of this application includes the following steps:

[0049] Step S101: Obtain the pressure value detected by multiple pressure sensors and the temperature value detected by multiple temperature sensors.

[0050] Step S102: Based on multiple pressure values ​​and multiple temperature values, backfire monitoring is performed on the combustion chamber of the gas turbine.

[0051] For example, backfire monitoring in the combustion chamber of a gas turbine can be performed based on multiple pressure and temperature values ​​obtained from the same premixed nozzle channel, or all pressure and temperature values ​​obtained from all premixed nozzle channels.

[0052] Therefore, the gas turbine backfire monitoring method of this application combines multiple pressure values ​​detected by a pressure sensor and multiple temperature values ​​detected by a temperature sensor to monitor backfire in the combustion chamber of the gas turbine. This not only makes up for the insufficient sensitivity of using a pressure sensor alone to monitor backfire, but also avoids the problem of easy damage to the temperature sensor caused by using a temperature sensor alone, and also avoids the problems of high cost and easy damage caused by using an optical sensor alone, thereby improving the reliability of monitoring combustion chamber backfire.

[0053] The content of step S102 in the embodiments of this application will be described below with reference to different examples:

[0054] Example 1:

[0055] If, in the same premixed nozzle channel, at least one of the multiple pressure values ​​is less than the set pressure value, and at least one of the multiple temperature values ​​is greater than the set temperature value, then it is determined that backfire has occurred in the combustion chamber.

[0056] The pressure value is set to the difference between the average of multiple pressure values ​​and a first pressure threshold, or the difference between the theoretically calculated pressure value under the same operating conditions and a second pressure threshold. The temperature value is set to the sum of the average of multiple temperature values ​​and a first temperature threshold, or the sum of the theoretically calculated temperature value under the same operating conditions and a second temperature threshold. For example, if three oxygen sensors and three temperature sensors are circumferentially spaced at equal intervals inside each premixed nozzle channel, and the combustion chamber of the gas turbine has a total of 10 premixed nozzle channels, then the average of the multiple oxygen concentrations is the average of the oxygen concentrations obtained from 90 oxygen sensors, and the average of the multiple temperature values ​​is the average of the temperature values ​​obtained from 90 temperature sensors.

[0057] In other words, within the same premixed nozzle channel, if at least one of the multiple pressure values ​​is less than the average of the multiple pressure values, and the difference between this pressure value and the average of the multiple pressure values ​​is greater than a first pressure threshold, and

[0058] If at least one of the multiple temperature values ​​is greater than the average of the multiple temperature values, and the difference between the temperature value and the average of the multiple temperature values ​​is greater than a first temperature threshold, then it is determined that backfire has occurred in the combustion chamber.

[0059] Alternatively, in the same premixed nozzle channel, if at least one of the multiple pressure values ​​is less than the average of the multiple pressure values, and the difference between that pressure value and the average of the multiple pressure values ​​is greater than a first pressure threshold, and the multiple...

[0060] If at least one temperature value is greater than the theoretically calculated temperature value under the same operating conditions, and the difference between this temperature value and the theoretically calculated temperature value under the same operating conditions is greater than the second temperature threshold, then it is determined that backfire has occurred in the combustion chamber.

[0061] Alternatively, in the same premixed nozzle channel, if at least one of the multiple pressure values ​​is lower than that under the same operating condition...

[0062] The theoretically calculated pressure value under the given conditions, and the difference between this pressure value and the theoretically calculated pressure value under the same working conditions is greater than 0.50 ...

[0063] If the difference between the temperature value and the average of multiple temperature values ​​is greater than the first temperature threshold, then it is determined that backfire has occurred in the combustion chamber.

[0064] Alternatively, in the same premixed nozzle channel, if at least one of the multiple pressure values ​​is lower than the theoretically calculated pressure value under the same operating condition, and the difference between this pressure value and the theoretically calculated pressure value under the same operating condition is large...

[0065] The second pressure threshold is met, and at least one of the multiple temperature values ​​is greater than the theoretically calculated temperature value under the same operating condition, and the difference between this temperature value and the theoretically calculated temperature value under the same operating condition is greater than the second temperature threshold.

[0066] This confirms that backfire has occurred in the combustion chamber.

[0067] Example 2:

[0068] In the same premixed nozzle channel, if the rate of decrease of at least one of the multiple pressure values ​​is greater than the set value...

[0069] If the pressure reduction rate is such that at least one of the multiple temperature values ​​is greater than the set temperature value, then it is determined that zero backfire has occurred in the combustion chamber.

[0070] In other words, in the same premixed nozzle channel, if at least one of the multiple pressure values ​​has a pressure reduction rate greater than the set pressure reduction rate, and at least one of the multiple temperature values ​​has a temperature value greater than the average of the multiple temperature values, and the difference between the temperature value and the average of the multiple temperature values ​​is greater than a first temperature threshold, then it is determined that backfire has occurred in the combustion chamber.

[0071] 5. Alternatively, in the same premixed nozzle channel, if at least one of the multiple pressure values ​​has a large rate of decrease...

[0072] If a set pressure reduction rate is set, and at least one of the multiple temperature values ​​is greater than the theoretically calculated temperature value under the same operating condition, and the difference between the temperature value and the theoretically calculated temperature value under the same operating condition is greater than a second temperature threshold, then it is determined that backfire has occurred in the combustion chamber.

[0073] Example 3:

[0074] 0. In the same premixed nozzle channel, if at least one of the multiple pressure values ​​is less than the set pressure value, and at least one of the multiple temperature values ​​has a rate of increase greater than the set temperature rate of increase, then it is determined that backfire has occurred in the combustion chamber.

[0075] In other words, in the same premixed nozzle channel, if at least one of the multiple pressure values ​​is less than the average of the multiple pressure values, and the difference between the pressure value and the average of the multiple pressure values ​​is greater than a first pressure threshold, and at least one of the multiple temperature values ​​has a rate of increase greater than a set rate of increase, then it is determined that backfire has occurred in the combustion chamber.

[0076] Alternatively, in the same premixed nozzle channel, if at least one of the multiple pressure values ​​is less than the theoretically calculated pressure value under the same operating condition, and the difference between the pressure value and the theoretically calculated pressure value under the same operating condition is greater than the second pressure threshold, and at least one of the multiple temperature values ​​has a rate of increase greater than the set rate of increase of temperature, then it is determined that backfire has occurred in the combustion chamber.

[0077] Example 4:

[0078] If, in the same premixed nozzle channel, at least one of the multiple pressure values ​​has a pressure reduction rate greater than the set pressure reduction rate, and at least one of the multiple temperature values ​​has a temperature increase rate greater than the set temperature increase rate, then it is determined that backfire has occurred in the combustion chamber.

[0079] It should be noted that this application can also perform backfire monitoring in the combustion chamber of a gas turbine according to the following example.

[0080] Example 5:

[0081] If at least two of the multiple pressure values ​​in the same premixed nozzle channel are both less than the set pressure value, then backfire in the combustion chamber is determined to have occurred.

[0082] In other words, in the same premixed nozzle channel, if at least two of the multiple pressure values ​​are less than the average of the multiple pressure values, and the difference between these two pressure values ​​and the average of the multiple pressure values ​​is greater than the first pressure threshold, then it is determined that backfire has occurred in the combustion chamber.

[0083] Alternatively, in the same premixed nozzle channel, if at least two of the multiple pressure values ​​are lower than the theoretically calculated pressure value under the same operating condition, and the difference between these two pressure values ​​and the theoretically calculated pressure value under the same operating condition is greater than the second pressure threshold, then it is determined that backfire has occurred in the combustion chamber.

[0084] Example 6:

[0085] If at least two of the multiple temperature values ​​in the same premixed nozzle channel are greater than the set temperature value, then backfire in the combustion chamber is determined to have occurred.

[0086] In other words, if at least two of the multiple temperature values ​​in the same premixed nozzle channel are greater than the average of the multiple temperature values, and the difference between these two temperature values ​​and the average of the multiple temperature values ​​is greater than the first temperature threshold, then it is determined that backfire has occurred in the combustion chamber.

[0087] Alternatively, in the same premixed nozzle channel, if at least two of the multiple temperature values ​​are greater than the theoretically calculated temperature value under the same operating conditions, and the difference between these two temperature values ​​and the theoretically calculated temperature value under the same operating conditions is greater than the second temperature threshold, then it is determined that backfire has occurred in the combustion chamber.

[0088] Example 7:

[0089] If, in the same premixed nozzle channel, at least two of the multiple pressure values ​​have a rate of decrease that is greater than the set rate of decrease, then it is determined that backfire has occurred in the combustion chamber.

[0090] Example 8:

[0091] If, in the same premixed nozzle channel, at least one of the multiple temperature values ​​has a rate of increase that is greater than the set rate of increase, then it is determined that backfire has occurred in the combustion chamber.

[0092] It should be noted that the first pressure threshold, the second pressure threshold, the first temperature threshold, the second temperature threshold, the set pressure reduction rate, and the set temperature increase rate can be established through complete testing during the combustion chamber manufacturing process, and can also be updated based on ongoing performance analysis during the turbine engine's life cycle.

[0093] When any of the multiple pressure sensors and multiple temperature sensors fails, the test point is automatically blocked and deleted, meaning that the sensor does not participate in the process of determining whether backfire has occurred in the combustion chamber.

[0094] In summary, the gas turbine backfire monitoring method according to the embodiments of this application obtains multiple pressure values ​​through multiple pressure sensors and multiple temperature values ​​through multiple temperature sensors, and monitors the combustion chamber of the gas turbine based on these multiple pressure and temperature values. Therefore, this method combines the pressure values ​​detected by the pressure sensors and the temperature values ​​detected by the temperature sensors to achieve backfire monitoring in the gas turbine combustion chamber. This not only compensates for the insufficient sensitivity of using pressure sensors alone for backfire monitoring, but also avoids the problem of easy damage to temperature sensors when using only temperature sensors, and avoids the high cost and susceptibility to damage when using optical sensors alone, thereby improving the reliability of combustion chamber backfire monitoring.

[0095] Based on the above embodiments, this application also proposes a gas turbine backfire monitoring device.

[0096] Figure 3 This is a block diagram of a gas turbine backfire monitoring device according to an embodiment of this application.

[0097] like Figure 3As shown, the gas turbine backfire monitoring device 300 includes: an acquisition module 310 and a monitoring module 320.

[0098] The acquisition module 310 is used to acquire pressure values ​​detected by the plurality of pressure sensors and temperature values ​​detected by the plurality of temperature sensors. The monitoring module 320 is used to monitor backfire in the combustion chamber of the gas turbine based on the plurality of pressure values ​​and the plurality of temperature values.

[0099] According to one embodiment of this application, the monitoring module 320 is specifically used to determine that backfire has occurred in the combustion chamber if at least one of the multiple pressure values ​​is less than a set pressure value and at least one of the multiple temperature values ​​is greater than a set temperature value in the same premixed nozzle channel.

[0100] The pressure value is set to be the difference between the average of multiple pressure values ​​and a first pressure threshold, or the difference between the theoretically calculated pressure value under the same working conditions and a second pressure threshold.

[0101] The set temperature value is the sum of the average of multiple temperature values ​​and a first temperature threshold, or the sum of the theoretically calculated temperature value under the same operating conditions and a second temperature threshold.

[0102] According to one embodiment of this application, the monitoring module 320 is specifically used to determine that backfire has occurred in the combustion chamber if, in the same premixed nozzle channel, at least one of the pressure values ​​has a pressure reduction rate greater than a set pressure reduction rate, and at least one of the temperature values ​​has a temperature greater than a set temperature value.

[0103] According to one embodiment of this application, the monitoring module 320 is specifically used to determine that backfire has occurred in the combustion chamber if at least one of the multiple pressure values ​​is less than a set pressure value and at least one of the multiple temperature values ​​has a rate of increase greater than a set temperature rate of increase in the same premixed nozzle channel.

[0104] According to one embodiment of this application, the monitoring module 320 is specifically used to determine that backfire has occurred in the combustion chamber if, in the same premixed nozzle channel, at least one of the pressure values ​​has a pressure reduction rate greater than a set pressure reduction rate, and at least one of the temperature values ​​has a temperature increase rate greater than a set temperature increase rate.

[0105] It should be noted that for a detailed description of the functions of each module in the apparatus in the above embodiments, please refer to the above method embodiments, which will not be described in detail here.

[0106] According to the gas turbine backfire monitoring device of this application embodiment, an acquisition module acquires multiple pressure values ​​detected by multiple pressure sensors and multiple temperature values ​​detected by multiple temperature sensors. This allows the monitoring module to perform backfire monitoring in the combustion chamber of the gas turbine based on these pressure and temperature values. Therefore, this method combines the pressure values ​​detected by the pressure sensors and the temperature values ​​detected by the temperature sensors to achieve backfire monitoring in the gas turbine combustion chamber. This not only compensates for the insufficient sensitivity of using pressure sensors alone for backfire monitoring but also avoids the problem of easy damage to temperature sensors when using only temperature sensors, and avoids the high cost and susceptibility to damage associated with using optical sensors alone, thereby improving the reliability of combustion chamber backfire monitoring.

[0107] Based on the above embodiments, this application also proposes a gas turbine backfire monitoring device.

[0108] The gas turbine backfire monitoring device according to this application includes: a processor and a memory;

[0109] The processor reads the executable program code stored in the memory to run the program corresponding to the executable program code, so as to implement the gas turbine backfire monitoring method as described above.

[0110] The gas turbine backfire monitoring device provided in this application can improve the reliability of monitoring combustion chamber backfire by executing the gas turbine backfire monitoring method described above.

[0111] Based on the above embodiments, this application also proposes a gas turbine.

[0112] The gas turbine in this application embodiment includes the gas turbine backfire monitoring device described above.

[0113] The gas turbine provided in this application embodiment, by employing the aforementioned gas turbine backfire monitoring equipment, can improve the reliability of monitoring combustion chamber backfire.

[0114] Based on the above embodiments, this application also proposes a computer-readable storage medium.

[0115] The computer-readable storage medium of this application embodiment stores a computer program, which, when executed by a processor, implements the gas turbine backfire monitoring method of the above embodiment.

[0116] The computer-readable storage medium provided in this application embodiment can improve the reliability of monitoring combustion chamber backfire by executing the gas turbine backfire monitoring method of the above embodiment.

[0117] Based on the above embodiments, this application also proposes a computer program product.

[0118] The computer program product of this invention implements the above-described gas turbine backfire monitoring method when the instruction processor in the computer program product is executed.

[0119] The computer program product of this invention, by implementing the above-described gas turbine backfire monitoring method, can improve the reliability of monitoring combustion chamber backfire.

[0120] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0121] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0122] Any process or method description in the flowchart or otherwise herein can be understood as representing a module, segment, or portion of code comprising one or more executable instructions for implementing custom logic functions or processes, and the scope of the preferred embodiments of this application includes additional implementations in which functions may be performed not in the order shown or discussed, including substantially simultaneously or in reverse order depending on the functions involved, as should be understood by those skilled in the art to which embodiments of this application pertain.

[0123] The logic and / or steps represented in the flowchart or otherwise described herein, for example, can be considered as a sequenced list of executable instructions for implementing logical functions, and can be embodied in any computer-readable medium for use by, or in conjunction with, an instruction execution system, apparatus, or device (such as a computer-based system, a processor-included system, or other system that can fetch and execute instructions from, an instruction execution system, apparatus, or device). For the purposes of this specification, "computer-readable medium" can be any means that can contain, store, communicate, propagate, or transmit programs for use by, or in conjunction with, an instruction execution system, apparatus, or device. More specific examples (a non-exhaustive list) of computer-readable media include: an electrical connection having one or more wires (electronic device), a portable computer disk drive (magnetic device), random access memory (RAM), read-only memory (ROM), erasable and editable read-only memory (EPROM or flash memory), fiber optic devices, and portable optical disc read-only memory (CDROM). Alternatively, the computer-readable medium may be paper or other suitable media on which the program can be printed, since the program can be obtained electronically, for example, by optically scanning the paper or other medium, followed by editing, interpreting, or otherwise processing as necessary, and then stored in a computer memory.

[0124] It should be understood that various parts of this application can be implemented using hardware, software, firmware, or a combination thereof. In the above embodiments, multiple steps or methods can be implemented using software or firmware stored in memory and executed by a suitable instruction execution system. For example, if implemented in hardware as in another embodiment, it can be implemented using any one or a combination of the following techniques known in the art: discrete logic circuits having logic gates for implementing logical functions on data signals, application-specific integrated circuits (ASICs) having suitable combinational logic gates, programmable gate arrays (PGAs), field-programmable gate arrays (FPGAs), etc.

[0125] Those skilled in the art will understand that all or part of the steps of the methods in the above embodiments can be implemented by a program instructing related hardware. The program can be stored in a computer-readable storage medium, and when executed, the program includes one or a combination of the steps of the method embodiments.

[0126] Furthermore, the functional units in the various embodiments of this application can be integrated into a processing module, or each unit can exist physically separately, or two or more units can be integrated into a module. The integrated module can be implemented in hardware or as a software functional module. If the integrated module is implemented as a software functional module and sold or used as an independent product, it can also be stored in a computer-readable storage medium.

[0127] The storage medium mentioned above can be a read-only memory, a disk, or an optical disk, etc. Although embodiments of this application have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting this application. Those skilled in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of this application.

Claims

1. A method for monitoring backfire in a gas turbine, characterized in that, The method involves arranging multiple pressure sensors and multiple temperature sensors at equal intervals along the circumferential direction on the inner wall of the premixing nozzle channel in the gas turbine, and includes: Obtain the pressure value detected by the plurality of pressure sensors and the temperature value detected by the plurality of temperature sensors; Backfire monitoring is performed on the combustion chamber of the gas turbine based on multiple pressure values ​​and multiple temperature values; The step of monitoring backfire in the combustion chamber of the gas turbine based on multiple pressure and temperature values ​​includes: If, in the same premixed nozzle channel, at least one of the pressure values ​​is less than a set pressure value, and at least one of the temperature values ​​is greater than a set temperature value, then it is determined that backfire has occurred in the combustion chamber.

2. The method according to claim 1, characterized in that, The backfire monitoring of the combustion chamber in the gas turbine based on multiple pressure values ​​and temperature values ​​includes: If, in the same premixed nozzle channel, at least one of the pressure values ​​has a pressure reduction rate greater than a set pressure reduction rate, and at least one of the temperature values ​​has a temperature greater than a set temperature value, then it is determined that backfire has occurred in the combustion chamber.

3. The method according to claim 1, characterized in that, The backfire monitoring of the combustion chamber in the gas turbine based on multiple pressure values ​​and temperature values ​​includes: If, in the same premixed nozzle channel, at least one of the pressure values ​​is less than a set pressure value, and at least one of the temperature values ​​has a rate of increase greater than a set rate of increase, then it is determined that backfire has occurred in the combustion chamber.

4. The method according to claim 1, characterized in that, The backfire monitoring of the combustion chamber in the gas turbine based on multiple pressure values ​​and temperature values ​​includes: If, in the same premixed nozzle channel, at least one of the pressure values ​​has a pressure reduction rate greater than a set pressure reduction rate, and at least one of the temperature values ​​has a temperature increase rate greater than a set temperature increase rate, then it is determined that backfire has occurred in the combustion chamber.

5. The method according to any one of claims 2-4, characterized in that, The pressure value is set as the difference between the average of multiple pressure values ​​and a first pressure threshold, or as the difference between the theoretically calculated pressure value under the same operating conditions and a second pressure threshold.

6. The method according to any one of claims 2-4, characterized in that, The set temperature value is the sum of the average of multiple temperature values ​​and a first temperature threshold, or the sum of the theoretically calculated temperature value under the same operating conditions and a second temperature threshold.

7. A gas turbine backfire monitoring device, characterized in that, The method described in any one of claims 1-6, wherein a plurality of pressure sensors and a plurality of temperature sensors are arranged at equal intervals along the circumferential direction on the inner wall of the premixing nozzle channel in the gas turbine, the device comprising: The acquisition module is used to acquire the pressure values ​​detected by the plurality of pressure sensors and the temperature values ​​detected by the plurality of temperature sensors. The monitoring module is used to monitor backfire in the combustion chamber of the gas turbine based on multiple pressure values ​​and multiple temperature values.

8. A gas turbine backfire monitoring device, characterized in that, include: Processor and memory; The processor reads executable program code stored in the memory to run a program corresponding to the executable program code, so as to implement the gas turbine backfire monitoring method as described in any one of claims 1-7.

9. A gas turbine, characterized in that, include: The gas turbine backfire monitoring device as described in claim 8.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that, When executed by a processor, the computer program implements the gas turbine backfire monitoring method as described in any one of claims 1-6.

Images