CN117588303A - Tempering monitoring and protecting method and system for hydrogen combustion engine - Google Patents

Abstract

The application provides a hydrogen combustion engine backfire monitoring and protecting method and system, wherein the method comprises the following steps: a plurality of static pressure sensors, a plurality of tempering thermocouples and a plurality of light field multispectral pyrometers are circumferentially and equidistantly arranged on the inner wall of each fuel nozzle channel connected with a combustion chamber of the hydrogen combustion engine; acquiring a detection value acquired by each sensor in real time, calculating the data detected by each sensor, comparing the calculated data with a corresponding preset threshold value, judging whether the hydrogen gas engine is tempered or not, and determining a target fuel nozzle channel in which tempering occurs; and executing corresponding tempering protection actions by combining the operation working condition and the current tempering state of the hydrogen combustion engine. The method enhances the sensitivity of backfire monitoring, reduces the influence of possible damage of the sensor on backfire monitoring protection, and improves the accuracy, timeliness and reliability of backfire monitoring protection of the hydrogen-gas engine.

Description

Tempering monitoring and protecting method and system for hydrogen combustion engine

Technical Field

The application relates to the technical field of gas turbines, in particular to a hydrogen turbine tempering monitoring protection method and system.

Background

At present, under the trend of pushing carbon emission reduction and carbon neutralization, the traditional gas turbine using natural gas as fuel is facing carbon emission pressure, and with the development of novel low-carbon green energy equipment technology, the popularity of novel gas turbines capable of using hydrogen or other renewable gas fuels is gradually increasing. The hydrogen gas engine can realize safe and reliable clean thermal power generation with adjustable peak and sustainable and stable power generation, and is an important development direction of a gas turbine.

Wherein, for a hydrogen-loaded or pure hydrogen gas engine, the addition of hydrogen gas can result in a substantial change in the physical and chemical properties of the fuel compared to using conventional natural gas fuel, including: hydrogen can widen the combustible range of traditional hydrocarbon fuels, accelerate the flame propagation speed of fuels, improve the combustion speed in turbulent combustion of fuels, and have lower minimum ignition energy and easier spontaneous combustion, etc. The most significant effect of these changes on hydrogen engines is that they are more prone to flashback in the combustion chamber, which can not only seriously damage the combustion chamber components, but also increase the emission of pollutants, thus requiring monitoring of the flashback phenomenon of the hydrogen engine and timely execution of protective measures when flashback is determined to occur.

In the related art, in the scheme of monitoring and protecting the backfire of the hydrogen gas turbine, in addition to adopting pneumatic design to prevent backfire to a certain extent in the design stage of the nozzle of the hydrogen gas turbine, a corresponding sensor is usually arranged on the combustion chamber to monitor backfire so as to realize backfire protection on the operation control layer of the gas turbine.

However, in the above-mentioned related art tempering monitoring protection scheme, the tempering monitoring and protection modes are relatively single, the tempering monitoring sensitivity is insufficient, the occurrence of tempering may not be monitored in time, and the arranged sensor is similar to the combustion area, so that damage is easy to occur, and the tempering monitoring protection function cannot be realized.

Disclosure of Invention

The present application aims to solve, at least to some extent, one of the technical problems in the related art.

Therefore, a first object of the present application is to provide a method for monitoring and protecting the backfire of a hydrogen-gas engine, which enhances the sensitivity of backfire monitoring, reduces the influence of possible damage to the sensor on backfire monitoring and protecting, improves the accuracy, timeliness and reliability of backfire monitoring and protecting of the hydrogen-gas engine, and solves the problems of insufficient sensitivity of backfire monitoring and reduced reliability of backfire monitoring and protecting.

A second object of the present application is to provide a backfire monitoring and protecting system for a hydrogen-burning machine.

A third object of the present application is to propose a non-transitory computer readable storage medium.

To achieve the above object, a first aspect of the present application provides a method for monitoring and protecting a hydrogen turbine flashback, the method comprising the steps of:

a plurality of static pressure sensors, a plurality of tempering thermocouples and a plurality of light field multispectral pyrometers are circumferentially and equidistantly arranged on the inner wall of each fuel nozzle channel connected with a combustion chamber of the hydrogen combustion engine;

acquiring a detection value acquired by each sensor in real time, comparing the pressure value and the pressure reduction rate detected by each static pressure sensor, the temperature value and the temperature increase rate detected by each tempering thermocouple and the temperature value and the temperature increase rate detected by each light field multispectral pyrometer with corresponding preset thresholds, judging whether the hydrogen gas engine is tempered and determining a target fuel nozzle channel in which tempering occurs;

And executing corresponding tempering protection actions by combining the operation working condition and the current tempering state of the hydrogen combustion engine.

Optionally, in one embodiment of the present application, the determining whether the hydrogen combustion engine is tempered includes: calculating the average value of the pressure values detected by all static pressure sensors arranged in the hydrogen combustion engine, calculating the difference value between the pressure value detected by each static pressure sensor and the average value of pressure measurement, and judging that the hydrogen combustion engine is tempered under the condition that the corresponding difference value of any static pressure sensor is larger than a first pressure threshold value and the duration time reaches a first time threshold value; calculating the pressure reduction rate detected by each static pressure sensor, and judging that the hydrogen combustion engine is tempered under the condition that the pressure reduction rate corresponding to any static pressure sensor is larger than a pressure drop threshold value and the duration reaches a second time threshold value; and determining the current operation condition of the hydrogen gas engine, calculating the difference value between the pressure value detected by each static pressure sensor and the theoretical pressure value under the current operation condition, and judging that the hydrogen gas engine is tempered under the condition that the corresponding difference value of any static pressure sensor is larger than a second pressure threshold value and the duration time reaches a third time threshold value.

Optionally, in one embodiment of the present application, the determining whether the hydrogen combustion engine is tempered includes: calculating the average value of the temperature values detected by all tempering thermocouples arranged in the hydrogen gas engine, calculating the difference value between the temperature value detected by each tempering thermocouple and the first temperature measurement average value, and judging that the hydrogen gas engine is tempered under the condition that the corresponding difference value of any tempering thermocouple is larger than a first temperature threshold value and the duration time reaches a fourth time threshold value; calculating the temperature rise rate detected by each tempering thermocouple, and judging that the hydrogen combustion engine is tempered under the condition that the temperature rise rate corresponding to any tempering thermocouple is larger than a first temperature rise threshold value and the duration time reaches a fifth time threshold value; determining the current operation condition of the hydrogen gas engine, calculating the difference value between the temperature value detected by each tempering thermocouple and the first theoretical temperature value under the current operation condition, and judging that the hydrogen gas engine is tempered under the condition that the corresponding difference value of any tempering thermocouple is larger than the second temperature threshold and the duration time reaches the sixth time threshold.

Optionally, in one embodiment of the present application, the determining whether the hydrogen combustion engine is tempered includes: calculating the average value of temperature values detected by all light field multi-spectrum pyrometers arranged in the hydrogen gas turbine, calculating the difference value between the temperature value detected by each light field multi-spectrum pyrometer and the second temperature measurement average value, and judging that the hydrogen gas turbine is tempered under the condition that the corresponding difference value of any light field multi-spectrum pyrometer is larger than a third temperature threshold value and the duration time reaches a seventh time threshold value; calculating the temperature rise rate detected by each light field multi-spectrum pyrometer, and judging that the hydrogen combustion engine is tempered under the condition that the temperature rise rate corresponding to any light field multi-spectrum pyrometer is larger than a second temperature rise threshold value and the duration reaches an eighth time threshold value; determining the current operation condition of the hydrogen gas engine, calculating the difference value between the temperature value detected by each light field multi-spectrum pyrometer and a second theoretical temperature value under the current operation condition, and judging that the hydrogen gas engine is tempered under the condition that the corresponding difference value of any light field multi-spectrum pyrometer is larger than a fourth temperature threshold and the duration reaches a ninth time threshold.

Optionally, in an embodiment of the present application, the determining whether the hydrogen combustion engine is tempered further includes: and in the same fuel nozzle channel, judging that the hydrogen combustion engine is tempered under the condition that at least one static pressure sensor, at least one tempering thermocouple and at least one light field multispectral pyrometer exist and any calculated value is larger than a preset percentage of a corresponding threshold value.

Optionally, in one embodiment of the present application, before said determining whether the hydrogen combustion engine is tempered, the method further includes: and analyzing the current performance of the hydrogen combustion engine, and updating each preset threshold value according to the performance analysis result.

Optionally, in an embodiment of the present application, the performing, in combination with the operating condition of the hydrogen combustion engine and the current flashback condition, a corresponding flashback protection action includes: reducing the load of the hydrogen combustion engine according to a first rate under the working condition that the hydrogen combustion engine is in loaded operation; reducing fuel input to the hydrogen combustion engine according to a second rate when the hydrogen combustion engine is in an unloaded operating condition; and closing the target fuel nozzle channel, and triggering the protection tripping operation after tempering continuously occurs for a preset period of time.

To achieve the above object, a second aspect of the present application further provides a backfire monitoring and protecting system for a hydrogen combustion engine, comprising the following modules:

an arrangement module for circumferentially and equally arranging a plurality of static pressure sensors, a plurality of tempering thermocouples and a plurality of light field multispectral pyrometers on the inner wall of each fuel nozzle channel connected with a combustion chamber of the hydrogen combustion engine;

the judging module is used for acquiring a detection value acquired by each sensor in real time, comparing the pressure value and the pressure reduction rate detected by each static pressure sensor, the temperature value and the temperature increase rate detected by each tempering thermocouple and the temperature value and the temperature increase rate detected by each light field multispectral pyrometer with corresponding preset thresholds, and judging whether the hydrogen combustion engine is tempered and determining a target fuel nozzle channel in which tempering occurs;

and the protection module is used for executing corresponding tempering protection actions by combining the operation working condition of the hydrogen combustion engine and the current tempering state.

In order to achieve the above embodiments, an embodiment of a third aspect of the present application further proposes a non-transitory computer readable storage medium having stored thereon a computer program which, when executed by a processor, implements the hydrogen engine flashback monitoring protection method in the above embodiment of the first aspect.

The technical scheme provided by the embodiment of the application at least brings the following beneficial effects: the method for monitoring and judging the hydrogen gas engine by the aid of the tempering thermocouple and the optical field multispectral pyrometer comprises the steps of monitoring and judging whether the hydrogen gas engine is tempered or not by means of combining the plurality of static pressure sensors, tempering thermocouples and the optical field multispectral pyrometer, so that the defect of monitoring sensitivity caused by the fact that the static pressure sensors are singly arranged for monitoring is overcome, the influence of damage to a tempering monitoring protection function caused by singly adopting vulnerable equipment such as the tempering thermocouples is weakened, and meanwhile the characteristics of high precision and high response speed of the optical field multispectral pyrometer are fused. Therefore, the method combines a plurality of monitoring methods, can monitor the tempering condition of the combustion engine more accurately and reliably, and further adopts corresponding protection measures in time according to the working condition of the hydrogen combustion engine after judging that tempering occurs, and eliminates tempering accidents in time. Therefore, the sensitivity of tempering monitoring is enhanced, the influence of possible damage of the sensor on the tempering monitoring protection is reduced, the long-time operation of the tempering monitoring protection function of the hydrogen gas turbine can be maintained, the accuracy, timeliness and reliability of the tempering monitoring protection of the hydrogen gas turbine are improved, and the safe and reliable operation of the hydrogen gas turbine is guaranteed.

Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.

Drawings

The foregoing and/or additional aspects and advantages of the present application will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings, in which:

fig. 1 is a flowchart of a method for monitoring and protecting backfire of a hydrogen-burning machine according to an embodiment of the present application;

FIG. 2 is a schematic diagram of an arrangement of multiple types of sensors according to an embodiment of the present application;

FIG. 3 is a flow chart of a flashback determining method based on a static pressure sensor according to an embodiment of the present application;

FIG. 4 is a flow chart of a tempering judgment method based on a tempering thermocouple according to the embodiment of the present application;

FIG. 5 is a flow chart of a tempering determination method based on a light field multi-spectrum pyrometer according to an embodiment of the present application;

fig. 6 is a schematic structural diagram of a backfire monitoring and protecting system for a hydrogen-burning machine according to an embodiment of the present application.

Detailed Description

Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention.

It should be noted that the present application is applicable to various gas turbines using hydrogen-doped or pure hydrogen fuel, abbreviated as hydrogen gas turbines. Flashback of a hydrogen-powered combustion engine refers to the phenomenon in which, under certain combustion conditions, a flame propagates upstream of a mixture channel within a combustor fuel nozzle. Not only can the combustion chamber components be severely damaged when flashback occurs in the combustion chamber, but also pollutant emissions can be increased. In the related embodiments of flashback protection at the fuel engine operating control level, a static pressure sensor may be disposed within the passage of the fuel nozzle to detect and determine flashback, but since flashback is much more sensitive to temperature than speed, the monitoring method using the static pressure sensor alone is not sufficiently sensitive. In the scheme of judging the tempering by arranging the tempering thermocouple or the optical sensor, the tempering thermocouple is more easily damaged, so that the monitoring reliability is further affected, and the optical sensor has higher cost.

Therefore, the application provides a hydrogen turbine backfire monitoring and protecting method and system, which adopts a method combining a static pressure sensor, a backfire thermocouple and a light field multispectral temperature measuring method to monitor and judge the backfire of the gas turbine, so as to solve the problems.

The embodiment of the invention provides a tempering monitoring and protecting method and system for a hydrogen combustion engine, which are described in detail below with reference to the accompanying drawings.

Fig. 1 is a flowchart of a method for monitoring and protecting backfire of a hydrogen-gas engine according to an embodiment of the present application, as shown in fig. 1, the method includes the following steps:

in step S101, a plurality of static pressure sensors, a plurality of tempering thermocouples and a plurality of light field multispectral pyrometers are circumferentially and equidistantly arranged on the inner wall of each fuel nozzle channel connected with the combustion chamber of the hydrogen combustion engine.

Specifically, a plurality of types of sensors are arranged for a combustion chamber of the hydrogen combustion engine so as to detect backfire in practical application, and because the application combines a plurality of detection methods, the plurality of types of sensors including a static pressure sensor, a backfire thermocouple and a light field multispectral pyrometer are arranged, and the number of each type of sensor is a plurality of sensors, and the number of the sensors is determined according to the structure and the size parameters of the hydrogen combustion engine to be detected at present. The application is that a plurality of static pressure sensors, a plurality of tempering thermocouples and a plurality of light field multispectral pyrometers are circumferentially and equidistantly arranged on the inner wall of each fuel nozzle channel connected with a combustion chamber of the hydrogen combustion engine.

As one possible implementation, as shown in fig. 2, the hydrogen combustion engine includes a plurality of fuel nozzle channels 10, a combustion chamber 20, a transition section 30, and an outlet 40, wherein there are a plurality of fuel nozzle channels 10 connected to the combustion chamber 20, only one of which is illustrated by way of example in fig. 2. As can be seen from fig. 2, on the inner wall of the fuel nozzle channel 10, a plurality of static pressure sensors 1, a plurality of tempering thermocouples 2, and a plurality of light field multispectral pyrometers 3 are arranged in this order at equal intervals along the circumferential direction of the nozzle channel. Wherein, 1 static pressure sensor, 1 tempering thermocouple and 1 light field multispectral high Wen Jiwei are in a group, and the group is arranged in sequence, and different types of sensors are distinguished by different colors in fig. 2.

It will be appreciated that for each fuel nozzle channel 10 within a hydrogen combustion engine, x static pressure sensors, y tempering thermocouples, and z optical field multispectral pyrometers may be arranged in sequence in the arrangement described above.

Step S102, acquiring a detection value acquired by each sensor in real time, comparing the pressure value and the pressure reduction rate detected by each static pressure sensor, the temperature value and the temperature increase rate detected by each tempering thermocouple and the temperature value and the temperature increase rate detected by each light field multispectral pyrometer with corresponding preset thresholds, judging whether the hydrogen combustion engine is tempered or not, and determining a target fuel nozzle channel in which tempering occurs.

Specifically, in the actual running process of the hydrogen gas engine, the detection value of each sensor is collected in real time, the collected real-time detection values are calculated and then are respectively compared with preset corresponding thresholds, and whether tempering occurs in the hydrogen gas engine is judged according to the comparison result.

The method comprises the steps of respectively presetting a judging threshold for data detected by each type of sensor, calculating according to the data detected by any type of sensor, comparing with the corresponding threshold, and determining that the hydrogen combustion engine is tempered if any corresponding criterion is met, so that whether tempering occurs or not is judged by combining multiple monitoring modes.

In order to more clearly illustrate the specific implementation process of judging whether the hydrogen combustion engine is tempered by combining various monitoring modes, the following is an exemplary description of a specific method for judging whether the hydrogen combustion engine is tempered according to one embodiment of the present application.

First, a specific implementation process of judging whether tempering occurs by each monitoring method will be described.

Fig. 3 is a flowchart of a tempering judgment method based on a static pressure sensor according to an embodiment of the present application, as shown in fig. 3, the method includes the following steps:

step S301, calculating an average value of pressure values detected by all static pressure sensors arranged in the hydrogen gas engine, and calculating a difference value between the pressure value detected by each static pressure sensor and the average value of pressure measurement, and determining that the hydrogen gas engine is backfire when the corresponding difference value of any static pressure sensor is greater than a first pressure threshold value and the duration reaches a first time threshold value.

Specifically, after flashback propagates to a certain fuel nozzle channel, the pressure value detected by the static pressure sensor in that fuel nozzle channel decreases. Thus, the pressure values detected by all the static pressure sensors disposed in all the nozzle passages of the entire combustion chamber are summed, and an average value of the summed total pressure values, that is, a pressure measurement average value is calculated. Respectively calculating the difference value of the pressure value detected by each static pressure sensor lower than the average value of the pressure measurement, and when any one static pressure sensor exists, the difference value corresponding to the static pressure sensor is larger than a first pressure threshold value delta P _m1 And if the duration time greater than the first pressure threshold reaches the first time threshold t1, determining that the hydrogen combustion engine is tempered.

Namely, the first criterion is: at least 1 detected pressure value in the same nozzle channel static pressure sensor is lower than the pressure measurement level of all the static pressure sensors of all the nozzle channels of the whole combustion chamberDifference of mean values>Threshold ΔP _m1 Delay t1.

Step S302, calculating the pressure reduction rate detected by each static pressure sensor, and judging that the hydrogen combustion engine is backfire under the condition that the pressure reduction rate corresponding to any static pressure sensor is larger than the pressure drop threshold value and the duration time reaches the second time threshold value.

Specifically, the pressure reduction rate detected by each static pressure sensor can be obtained by calculating according to the pressure values detected by the static pressure sensors at different moments, and when the pressure reduction rate corresponding to any static pressure sensor is greater than the pressure drop threshold value delta P' ₁ And if the duration time greater than the pressure drop threshold reaches the second time threshold t2, determining that the hydrogen combustion engine is backfire.

Namely, the second criterion is: at least 1 detected rate of pressure decrease in the same nozzle channel static pressure sensor>Threshold ΔP' ₁ And delaying t2.

Step S303, determining the current operation condition of the hydrogen gas engine, calculating the difference value between the pressure value detected by each static pressure sensor and the theoretical pressure value under the current operation condition, and judging that the hydrogen gas engine is tempered under the condition that the corresponding difference value of any static pressure sensor is larger than the second pressure threshold value and the duration time reaches the third time threshold value.

Specifically, under each operating condition of the hydrogen gas engine, when the hydrogen gas engine is in normal operation and no backfire accident occurs, the pressure value which should be detected by the static pressure sensor theoretically, namely, the theoretical pressure value, is different when the operating conditions are different. In the embodiment, the current operation condition of the hydrogen gas engine is determined by combining the current operation parameters of the hydrogen gas engine, the received control instructions and other modes, and then the theoretical pressure value corresponding to the operation condition is determined.

Further, each static pressure sensor is respectively used for detecting a pressure value which is lower than a determined theoretical pressure value under the current operating condition, and when any static pressure sensor exists, the difference value which is lower than the theoretical pressure value and is larger than a second pressure threshold delta P _T1 And a duration greater than the second pressure threshold reaches a third time When the intermediate threshold t3 is set, it is determined that the hydrogen engine is backfire.

Namely, the third criterion is: at least 1 difference between detected pressure values in the same nozzle channel static pressure sensor and theoretical calculated values under the working condition>Threshold ΔP _T1 And delaying t3.

Fig. 4 is a flowchart of a tempering judgment method based on a tempering thermocouple according to an embodiment of the present application. As shown in fig. 4, the method comprises the steps of:

step S401, calculating the average value of the temperature values detected by all tempering thermocouples arranged in the hydrogen gas engine, calculating the difference value between the temperature value detected by each tempering thermocouple and the first temperature measurement average value, and judging that the hydrogen gas engine is tempered under the condition that the corresponding difference value of any tempering thermocouple is larger than a first temperature threshold value and the duration time reaches a fourth time threshold value.

Specifically, after flashback propagates to a certain fuel nozzle channel, the temperature value detected by a flashback thermocouple in that fuel nozzle channel increases. Thus, the temperature values detected by all tempering thermocouples disposed in all nozzle passages of the entire combustion chamber are summed, and an average value of all the summed temperature values, i.e., a first temperature measurement average value, is calculated. Then respectively calculating the difference value of the temperature value detected by each tempering thermocouple higher than the first temperature measurement average value, when any tempering thermocouple exists, the difference value corresponding to the tempering thermocouple is larger than a first temperature threshold delta T _m1 And if the duration time greater than the first temperature threshold reaches the fourth time threshold t4, determining that the hydrogen engine is tempered.

Namely, the fourth criterion is: at least 1 of the tempering thermocouples in the same nozzle channel have a temperature higher than the difference of the average value of the temperature measurements of all tempering thermocouples in all nozzle channels of the whole combustion chamber>Threshold DeltaT _m1 And delaying t4.

Step S402, calculating the temperature rising rate detected by each tempering thermocouple, and judging that the hydrogen combustion engine is tempered under the condition that the temperature rising rate corresponding to any tempering thermocouple is larger than a first temperature rising threshold value and the duration reaches a fifth time threshold value.

Specifically, the temperature rise rate detected by each tempering thermocouple can be obtained by calculating according to the temperature values detected by the tempering thermocouples at different moments, and when any tempering thermocouple exists, the corresponding temperature rise rate is greater than a first temperature rise threshold deltaT' ₁ And if the duration time greater than the first temperature rise threshold reaches a fifth time threshold t5, determining that the hydrogen engine is backfire.

Namely, the fifth criterion is: at least 1 detected rate of temperature rise in a tempering thermocouple for the same nozzle channel>Threshold DeltaT' ₁ And delaying t5.

Step S403, determining the current operation condition of the hydrogen gas engine, calculating the difference value between the temperature value detected by each tempering thermocouple and the first theoretical temperature value under the current operation condition, and judging that the hydrogen gas engine is tempered under the condition that the corresponding difference value of any tempering thermocouple is larger than the second temperature threshold and the duration time reaches the sixth time threshold.

Specifically, under each operating condition of the hydrogen gas engine, when the hydrogen gas engine is in normal operation and no backfire accident occurs, the backfire thermocouple should theoretically detect a temperature value, namely a first theoretical temperature value, and if the operating conditions are different, the first theoretical temperature value is also different. In the embodiment, the current operation condition of the hydrogen gas engine is determined by combining the current operation parameters of the hydrogen gas engine, the received control instructions and other modes, and then a first theoretical temperature value corresponding to the operation condition is determined.

Further, each tempering thermocouple is respectively calculated to detect a temperature value which is higher than a first theoretical temperature value under the determined current operation condition, and when any tempering thermocouple exists, the difference value which is higher than the first theoretical temperature value and is larger than a second temperature threshold delta T _T1 And if the duration time greater than the second temperature threshold reaches a sixth time threshold t6, determining that the hydrogen engine is backfire.

Namely, the sixth criterion is: at least 1 difference between detected temperature values in tempering thermocouples of the same nozzle channel and theoretical calculated values under the working condition>Threshold DeltaT _T1 And (6) delaying t6.

Fig. 5 is a flowchart of a tempering judgment method based on a light field multispectral pyrometer according to an embodiment of the present application, as shown in fig. 5, the method includes the following steps:

step S501, calculating an average value of temperature values detected by all light field multi-spectrum pyrometers arranged in the hydrogen gas turbine, calculating a difference value between the temperature value detected by each light field multi-spectrum pyrometer and the second temperature measurement average value, and judging that the hydrogen gas turbine is tempered under the condition that the corresponding difference value of any light field multi-spectrum pyrometer is larger than a third temperature threshold value and the duration time reaches a seventh time threshold value.

It should be noted that, when the light field multispectral pyrometer includes components such as a light field camera and a filter, and when the temperature detection is performed by the light field multispectral pyrometer, for an external high temperature target, namely tempering, emitted light rays are mapped into a micro lens array in the light field camera after passing through the filter, and the temperature of the high temperature target can be detected by analyzing optical properties such as a spectrum, and a specific implementation manner can refer to the light field multispectral pyrometer in the prior art and is not repeated here.

Specifically, after flashback propagates to a certain fuel nozzle channel, the temperature value detected by a light field multispectral pyrometer in that fuel nozzle channel increases. Thus, the temperature values detected by all the light field multispectral pyrometers disposed within all the nozzle channels of the entire combustion chamber are summed, and the average value of the summed total temperature values, i.e., the second temperature measurement average value, is calculated. Respectively calculating the difference value of the temperature value detected by each light field multi-spectrum pyrometer higher than the average value of the second temperature measurement, and when any light field multi-spectrum pyrometer exists, the difference value is larger than a third temperature threshold delta T _m2 And if the duration time greater than the third temperature threshold reaches a seventh time threshold t7, determining that the hydrogen engine is backfire.

Namely, the seventh criterion is: at least 1 of the detected temperatures in the same nozzle channel light field multi-spectrum pyrometers are higher than the difference of the average values of the temperature measurements of all the light field multi-spectrum pyrometers of all the nozzle channels of the whole combustion chamber>Threshold DeltaT _m2 And delaying t7.

Step S502, calculating the temperature rise rate detected by each light field multi-spectrum pyrometer, and judging that the hydrogen gas engine is tempered under the condition that the temperature rise rate corresponding to any light field multi-spectrum pyrometer is larger than a second temperature rise threshold value and the duration time reaches an eighth time threshold value.

Specifically, the temperature rise rate detected by each light field multi-spectrum pyrometer can be obtained by calculating according to the temperature values detected by the light field multi-spectrum pyrometers at different moments, and when any light field multi-spectrum pyrometer exists, the corresponding temperature rise rate is greater than a second temperature rise threshold delta T '' ₂ And under the condition that the duration time which is larger than the second temperature rise threshold reaches an eighth time threshold t8, judging that the hydrogen combustion engine is tempered.

Namely, the eighth criterion is: at least 1 detected rate of temperature rise in a same nozzle channel light field multi-spectral pyrometer>Threshold DeltaT' ₂ And delaying t8.

Step S503, determining the current operation condition of the hydrogen-gas engine, calculating the difference value between the temperature value detected by each light field multi-spectrum pyrometer and the second theoretical temperature value under the current operation condition, and judging that the hydrogen-gas engine is tempered under the condition that the corresponding difference value of any light field multi-spectrum pyrometer is larger than the fourth temperature threshold and the duration time reaches the ninth time threshold.

Specifically, under each operating condition of the hydrogen gas engine, when the hydrogen gas engine is in normal operation and no backfire accident occurs, the temperature value which should be detected by the optical field multispectral pyrometer theoretically, namely, the second theoretical temperature value, is different when the operating conditions are different, and the second theoretical temperature value is also different. In the embodiment, the current operation condition of the hydrogen gas engine is determined by combining the current operation parameters of the hydrogen gas engine, the received control instructions and other modes, and then a second theoretical temperature value corresponding to the operation condition is determined.

Further, each light field multi-spectrum pyrometer is respectively used for calculating the detected temperature value which is higher than the difference value of the second theoretical temperature value under the determined current operation condition, and when any light field multi-spectrum pyrometer corresponding to the difference value which is higher than the difference value of the second theoretical temperature value existsA value greater than a fourth temperature threshold DeltaT _T2 And if the duration time greater than the fourth temperature threshold value reaches a ninth time threshold value t9, it is determined that the hydrogen engine is backfire.

Namely, the ninth criterion is: at least 1 difference value of detected temperature value higher than theoretical calculated value under the working condition in the same nozzle channel light field multi-spectrum pyrometer>Threshold DeltaT _T2 And delaying t9.

Therefore, the embodiment of the application can combine the three methods of the static pressure sensor, the tempering thermocouple and the light field multispectral temperature measurement method to monitor and judge the tempering of the gas turbine engine. The detection is carried out through two sensors of other types, so that the defect of insufficient sensitivity of a simple static pressure sensor monitoring method is overcome. Meanwhile, by arranging various types of sensors, including arranging a static pressure sensor with higher heat resistance and the like, the reliability problem caused by the fact that a tempering thermocouple is simply adopted to damage is weakened, and even if a certain sensor is damaged, tempering monitoring can be carried out by using other types of sensors, so that smooth performance of tempering monitoring protection is ensured. And the advantages of high precision and high response speed of the measurement of the light field multispectral pyrometer are utilized, and by combining with other types of sensors, a great deal of use of the light field multispectral pyrometer is avoided, and the hardware cost of tempering monitoring protection is reduced.

In one embodiment of the present application, determining whether the hydrogen combustion engine is tempered further includes: and in the same fuel nozzle channel, determining that the hydrogen combustion engine is tempered under the condition that at least one static pressure sensor, at least one tempering thermocouple and at least one light field multispectral pyrometer exist and any calculated value is larger than a preset percentage of a corresponding threshold value.

Specifically, any calculated value may be set by calculation according to the real-time detection value of each type of sensor in the embodiments of fig. 3 to 5, for example, a difference between a pressure value detected by the static pressure sensor and a pressure measurement average value, a temperature rise rate detected by the tempering thermocouple, a difference between a temperature value detected by the optical field multispectral pyrometer and a second theoretical temperature value, and the like. If at least one sensor exists in each type of sensor in the same fuel nozzle channel, and a certain calculated value detected by the sensor is greater than a preset percentage of a threshold value corresponding to the calculated value in the embodiment, the hydrogen combustion engine is also judged to be tempered.

That is, there is also a tenth criterion: on the same nozzle channel, there are at least 1 static pressure sensor, at least 1 tempering thermocouple, at least 1 light field multispectral pyrometer, and the preset percentage of the corresponding threshold value in the above criteria 1-9 is satisfied, and the time is delayed by t10. The percentages corresponding to the different thresholds can be different, and the percentages corresponding to the thresholds respectively meet the criteria.

For example, if a difference between a pressure value detected by a static pressure sensor and a pressure measurement average value in a certain fuel nozzle channel is greater than W% of a first pressure threshold value, a temperature rise rate detected by a tempering thermocouple is greater than X% of the first temperature rise threshold value, and a difference between a temperature value detected by a light field multispectral pyrometer and a second theoretical temperature value is greater than Y% of a fourth temperature threshold value, then it is determined that tempering of the fuel nozzle channel is currently occurring.

It should be noted that, the tempering determination methods in the foregoing embodiments may be executed simultaneously in a parallel manner, and if any one of the criteria is satisfied, that is, any one of the steps in the foregoing embodiments of fig. 3 to 5 is satisfied, that is, if any one of the first to tenth criteria is satisfied, it is determined that tempering occurs.

In order to improve accuracy of flashback determination, in one embodiment of the present application, before determining whether flashback occurs in the hydrogen combustion engine, the method further includes: and analyzing the current performance of the hydrogen combustion engine, and updating each preset threshold value according to the performance analysis result.

Specifically, the above-described respective threshold values required to be used in the respective judgment bases are predetermined before the tempering judgment is performed. In this embodiment, each threshold value in the above embodiments may be established by a test performed during the manufacturing process of the combustion chamber, and the threshold value may also be updated in actual application to improve the rationality of the threshold value. In specific implementation, a threshold value can be set according to the current performance of the hydrogen gas engine, for example, the complete life cycle of the hydrogen gas engine is analyzed, the current stage of the hydrogen gas engine in the complete life cycle is determined, and the current performance of the hydrogen gas engine is determined by combining the current stage of the life cycle and the collected representative operation parameters of the hydrogen gas engine. Further, the magnitude of the threshold is updated based on the obtained performance analysis results, such as an excellent performance level or a good performance level at the present time.

Therefore, in practical application, the magnitude of each threshold value can be continuously updated according to the performance change of the hydrogen gas engine, so that the threshold value is matched with the current performance of the hydrogen gas engine, and the rationality of threshold value setting and the accuracy of tempering judgment are improved.

Furthermore, according to the flashback determination scheme, the target fuel nozzle passage in which flashback occurs in the plurality of fuel nozzle passages of the hydrogen gas engine can be determined. For example, after it is determined that flashback occurs, the fuel nozzle channel in which the target sensor satisfying the criterion is located is used as the target fuel nozzle channel, and the number of the target fuel nozzle channels may be one or more.

Step S103, executing corresponding tempering protection actions by combining the operation condition of the hydrogen combustion engine and the current tempering state.

Specifically, after the occurrence of tempering is judged, a corresponding tempering protection scheme can be adopted according to the current operation condition of the hydrogen combustion engine and the state of the tempering developed so as to eliminate tempering accidents. The current tempering state may include a duration from the beginning to the present time, and a severity of tempering.

In one embodiment of the present application, in combination with the operating condition and the current flashback condition of the hydrogen combustion engine, a corresponding flashback protection action is performed, including: the method comprises the steps of reducing the load of the hydrogen combustion engine according to a first rate under the working condition that the hydrogen combustion engine is in loaded operation; reducing fuel input to the hydrogen combustion engine according to a second rate under the condition that the hydrogen combustion engine is in an unloaded operation; and closing the target fuel nozzle channel, and triggering the protection tripping operation after tempering continuously occurs for a preset period of time.

Specifically, in the present embodiment, the following protection actions may be performed: first, if the combustion engine is in a loaded operation, a protective load shedding is triggered, and the load shedding is fast according to the speed delta L1. Second, if the combustion engine is not operating under load, the protective de-fueling is triggered directly, de-fueling at a rate Δf1. Thirdly, after judging that the tempering delay Td occurs, directly triggering the protection tripping.

Further, in the present embodiment, a corresponding protection action may also be performed for the target fuel nozzle passage determined in the previous step. For example, continuously monitoring the severity of flashback in the target fuel nozzle passage, performing an annealing action in the target fuel nozzle passage, and closing the target fuel nozzle passage, cutting off the connection to the combustion chamber by a baffle or the like, thereby avoiding the propagation of contaminants to the target fuel nozzle passage.

Therefore, the method and the device can protect the safe and reliable operation of the gas turbine by executing the adaptive tempering protection action.

In summary, according to the tempering monitoring protection method for the hydrogen gas engine, a mode of combining a plurality of static pressure sensors, tempering thermocouples and an optical field multispectral pyrometer is adopted to monitor and judge whether the hydrogen gas engine is tempered, so that the defect of monitoring sensitivity caused by monitoring by singly setting the static pressure sensors is overcome, the influence of damage to a tempering monitoring protection function caused by singly adopting vulnerable equipment such as the tempering thermocouples is weakened, and meanwhile, the characteristics of high precision and high response speed of the optical field multispectral pyrometer are fused. Therefore, the method combines a plurality of monitoring methods, can more accurately and reliably monitor the tempering condition of the combustion engine, further takes corresponding protection measures in time according to the working condition of the hydrogen combustion engine after judging that the tempering occurs, and eliminates the tempering accident in time. Therefore, the method enhances the sensitivity of the backfire monitoring, reduces the influence of the possible damage of the sensor on the backfire monitoring protection, can maintain the long-time operation of the backfire monitoring protection function of the hydrogen gas engine, improves the accuracy, timeliness and reliability of the backfire monitoring protection of the hydrogen gas engine, and is beneficial to ensuring the safe and reliable operation of the hydrogen gas engine.

In order to implement the above embodiment, the present application further provides a backfire monitoring and protecting system for a hydrogen gas turbine, and fig. 6 is a schematic structural diagram of the backfire monitoring and protecting system for a hydrogen gas turbine according to the embodiment of the present application, as shown in fig. 6, the system includes an arrangement module 100, a judgment module 200, and a protection module 300.

Wherein, the arrangement module 100 is used for arranging a plurality of static pressure sensors, a plurality of tempering thermocouples and a plurality of light field multispectral pyrometers at equal intervals in the circumferential direction on the inner wall of each fuel nozzle channel connected with the combustion chamber of the hydrogen combustion engine.

The judging module 200 is configured to obtain a detection value acquired in real time by each sensor, compare a pressure value and a pressure reduction rate detected by each static pressure sensor, a temperature value and a temperature increase rate detected by each tempering thermocouple, and a temperature value and a temperature increase rate detected by each light field multispectral pyrometer with corresponding preset thresholds, judge whether the hydrogen combustion engine is tempered, and determine a target fuel nozzle channel where tempering occurs.

The protection module 300 is configured to perform a corresponding tempering protection action in combination with an operation condition and a current tempering state of the hydrogen combustion engine.

Optionally, in one embodiment of the present application, the determining module 200 is specifically configured to: calculating the average value of the pressure values detected by all static pressure sensors arranged in the hydrogen gas engine, calculating the difference value between the pressure value detected by each static pressure sensor and the average value of pressure measurement, and judging that the hydrogen gas engine is tempered under the condition that the corresponding difference value of any static pressure sensor is larger than a first pressure threshold value and the duration time reaches a first time threshold value; calculating the pressure reduction rate detected by each static pressure sensor, and judging that the hydrogen combustion engine is tempered under the condition that the pressure reduction rate corresponding to any static pressure sensor is larger than the pressure drop threshold value and the duration time reaches the second time threshold value; and determining the current operation condition of the hydrogen gas engine, calculating the difference value between the pressure value detected by each static pressure sensor and the theoretical pressure value under the current operation condition, and judging that the hydrogen gas engine is tempered under the condition that the corresponding difference value of any static pressure sensor is larger than the second pressure threshold value and the duration time reaches the third time threshold value.

Optionally, in one embodiment of the present application, the determining module 200 is specifically configured to: calculating the average value of the temperature values detected by all tempering thermocouples arranged in the hydrogen gas engine, calculating the difference value between the temperature value detected by each tempering thermocouple and the first temperature measurement average value, and judging that the hydrogen gas engine is tempered under the condition that the corresponding difference value of any tempering thermocouple is larger than a first temperature threshold value and the duration time reaches a fourth time threshold value; calculating the temperature rise rate detected by each tempering thermocouple, and judging that the hydrogen-gas engine is tempered under the condition that the temperature rise rate corresponding to any tempering thermocouple is larger than a first temperature rise threshold value and the duration time reaches a fifth time threshold value; determining the current operation condition of the hydrogen gas engine, calculating the difference value between the temperature value detected by each tempering thermocouple and the first theoretical temperature value under the current operation condition, and judging that the hydrogen gas engine is tempered under the condition that the corresponding difference value of any tempering thermocouple is larger than the second temperature threshold and the duration time reaches the sixth time threshold.

Optionally, in one embodiment of the present application, the determining module 200 is specifically configured to: calculating the average value of the temperature values detected by all the light field multi-spectrum pyrometers arranged in the hydrogen gas turbine, calculating the difference value between the temperature value detected by each light field multi-spectrum pyrometer and the second temperature measurement average value, and judging that the hydrogen gas turbine is tempered under the condition that the corresponding difference value of any light field multi-spectrum pyrometer is larger than a third temperature threshold value and the duration time reaches a seventh time threshold value; calculating the temperature rise rate detected by each light field multi-spectrum pyrometer, and judging that the hydrogen combustion engine is tempered under the condition that the temperature rise rate corresponding to any light field multi-spectrum pyrometer is larger than a second temperature rise threshold value and the duration time reaches an eighth time threshold value; determining the current operation condition of the hydrogen gas engine, calculating the difference value between the temperature value detected by each light field multi-spectrum pyrometer and the second theoretical temperature value under the current operation condition, and judging that the hydrogen gas engine is tempered under the condition that the corresponding difference value of any light field multi-spectrum pyrometer is larger than a fourth temperature threshold value and the duration time reaches a ninth time threshold value.

Optionally, in an embodiment of the present application, the determining module 200 is further configured to: and in the same fuel nozzle channel, determining that the hydrogen combustion engine is tempered under the condition that at least one static pressure sensor, at least one tempering thermocouple and at least one light field multispectral pyrometer exist and any calculated value is larger than a preset percentage of a corresponding threshold value.

Optionally, in an embodiment of the present application, the determining module 200 is further configured to: and analyzing the current performance of the hydrogen combustion engine, and updating each preset threshold value according to the performance analysis result.

Optionally, in an embodiment of the present application, the protection module 300 is further configured to: the method comprises the steps of reducing the load of the hydrogen combustion engine according to a first rate under the working condition that the hydrogen combustion engine is in loaded operation; reducing fuel input to the hydrogen combustion engine according to a second rate under the condition that the hydrogen combustion engine is in an unloaded operation; and closing the target fuel nozzle channel, and triggering the protection tripping operation after tempering continuously occurs for a preset period of time.

It should be noted that the foregoing explanation of the embodiment of the hydrogen engine backfire monitoring protection method is also applicable to the system of this embodiment, and will not be repeated here.

In summary, in the hydrogen gas turbine tempering monitoring protection system according to the embodiment of the application, whether the hydrogen gas turbine is tempered is monitored and judged by combining a plurality of static pressure sensors, tempering thermocouples and an optical field multispectral pyrometer, so that the defect of monitoring sensitivity caused by monitoring by singly setting the static pressure sensors is overcome, the influence of damage to a tempering monitoring protection function caused by singly adopting vulnerable equipment such as the tempering thermocouples is weakened, and the characteristics of high precision and high response speed of the optical field multispectral pyrometer measurement are fused. Therefore, the system combines a plurality of monitoring methods, can monitor the tempering condition of the combustion engine more accurately and reliably, and further adopts corresponding protection measures in time according to the working condition of the hydrogen combustion engine after judging that the tempering occurs, and eliminates the tempering accident in time. Therefore, the system enhances the sensitivity of tempering monitoring, reduces the influence of possible damage of the sensor on the tempering monitoring protection, can maintain the long-time operation of the tempering monitoring protection function of the hydrogen gas turbine, improves the accuracy, timeliness and reliability of the tempering monitoring protection of the hydrogen gas turbine, and is beneficial to ensuring the safe and reliable operation of the hydrogen gas turbine.

In order to implement the above embodiments, the present application further proposes a non-transitory computer readable storage medium having stored thereon a computer program which, when executed by a processor, implements a hydrogen engine flashback monitoring protection method according to any one of the embodiments of the first aspect described above.

In the description of the present specification, a description referring to terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present application. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.

Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present application, the meaning of "plurality" is at least two, such as two, three, etc., unless explicitly defined otherwise.

Any process or method descriptions in flow charts or otherwise described herein may be understood as representing modules, segments, or portions of code which include one or more executable instructions for implementing specific logical functions or steps of the process, and additional implementations are included within the scope of the preferred embodiment of the present application in which functions may be executed out of order from that shown or discussed, including substantially concurrently or in reverse order, depending on the functionality involved, as would be understood by those reasonably skilled in the art of the embodiments of the present application.

Logic and/or steps represented in the flowcharts or otherwise described herein, e.g., a ordered listing of executable instructions for implementing logical functions, can be embodied in any computer-readable medium for use by or in connection with an instruction execution system, apparatus, or device, such as a computer-based system, processor-containing system, or other system that can fetch the instructions from the instruction execution system, apparatus, or device and execute the instructions. For the purposes of this description, a "computer-readable medium" can be any means that can contain, store, communicate, propagate, or transport the program for use by or in connection with the instruction execution system, apparatus, or device. More specific examples (a non-exhaustive list) of the computer-readable medium would include the following: an electrical connection (electronic device) having one or more wires, a portable computer diskette (magnetic device), a Random Access Memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber device, and a portable compact disc read-only memory (CDROM). In addition, the computer readable medium may even be paper or other suitable medium on which the program is printed, as the program may be electronically captured, via, for instance, optical scanning of the paper or other medium, then compiled, interpreted or otherwise processed in a suitable manner, if necessary, and then stored in a computer memory.

It is to be understood that portions of the present application may be implemented in hardware, software, firmware, or a combination thereof. In the above-described embodiments, the various steps or methods may be implemented in software or firmware stored in a memory and executed by a suitable instruction execution system. As with the other embodiments, if implemented in hardware, may be implemented using any one or combination of the following techniques, as is well known in the art: discrete logic circuits having logic gates for implementing logic functions on data signals, application specific integrated circuits having suitable combinational logic gates, programmable Gate Arrays (PGAs), field Programmable Gate Arrays (FPGAs), and the like.

Those of ordinary skill in the art will appreciate that all or a portion of the steps carried out in the method of the above-described embodiments may be implemented by a program to instruct related hardware, where the program may be stored in a computer readable storage medium, and where the program, when executed, includes one or a combination of the steps of the method embodiments.

In addition, each functional unit in each embodiment of the present application may be integrated in one processing module, or each unit may exist alone physically, or two or more units may be integrated in one module. The integrated modules may be implemented in hardware or in software functional modules. The integrated modules may also be stored in a computer readable storage medium if implemented in the form of software functional modules and sold or used as a stand-alone product.

The above-mentioned storage medium may be a read-only memory, a magnetic disk or an optical disk, or the like. Although embodiments of the present application have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the application, and that variations, modifications, alternatives, and variations may be made to the above embodiments by one of ordinary skill in the art within the scope of the application.

Claims (10)

1. The tempering monitoring and protecting method for the hydrogen-gas engine is characterized by comprising the following steps of:

a plurality of static pressure sensors, a plurality of tempering thermocouples and a plurality of light field multispectral pyrometers are circumferentially and equidistantly arranged on the inner wall of each fuel nozzle channel connected with a combustion chamber of the hydrogen combustion engine;

acquiring a detection value acquired by each sensor in real time, comparing the pressure value and the pressure reduction rate detected by each static pressure sensor, the temperature value and the temperature increase rate detected by each tempering thermocouple and the temperature value and the temperature increase rate detected by each light field multispectral pyrometer with corresponding preset thresholds, judging whether the hydrogen gas engine is tempered and determining a target fuel nozzle channel in which tempering occurs;

and executing corresponding tempering protection actions by combining the operation working condition and the current tempering state of the hydrogen combustion engine.

2. The hydrogen engine flashback monitoring and protecting method according to claim 1, wherein the judging whether flashback of the hydrogen engine occurs comprises:

calculating the average value of the pressure values detected by all static pressure sensors arranged in the hydrogen combustion engine, calculating the difference value between the pressure value detected by each static pressure sensor and the average value of pressure measurement, and judging that the hydrogen combustion engine is tempered under the condition that the corresponding difference value of any static pressure sensor is larger than a first pressure threshold value and the duration time reaches a first time threshold value;

calculating the pressure reduction rate detected by each static pressure sensor, and judging that the hydrogen combustion engine is tempered under the condition that the pressure reduction rate corresponding to any static pressure sensor is larger than a pressure drop threshold value and the duration reaches a second time threshold value;

and determining the current operation condition of the hydrogen gas engine, calculating the difference value between the pressure value detected by each static pressure sensor and the theoretical pressure value under the current operation condition, and judging that the hydrogen gas engine is tempered under the condition that the corresponding difference value of any static pressure sensor is larger than a second pressure threshold value and the duration time reaches a third time threshold value.

3. The hydrogen engine flashback monitoring and protecting method according to claim 1, wherein the judging whether flashback of the hydrogen engine occurs comprises:

Calculating the average value of the temperature values detected by all tempering thermocouples arranged in the hydrogen gas engine, calculating the difference value between the temperature value detected by each tempering thermocouple and the first temperature measurement average value, and judging that the hydrogen gas engine is tempered under the condition that the corresponding difference value of any tempering thermocouple is larger than a first temperature threshold value and the duration time reaches a fourth time threshold value;

calculating the temperature rise rate detected by each tempering thermocouple, and judging that the hydrogen combustion engine is tempered under the condition that the temperature rise rate corresponding to any tempering thermocouple is larger than a first temperature rise threshold value and the duration time reaches a fifth time threshold value;

determining the current operation condition of the hydrogen gas engine, calculating the difference value between the temperature value detected by each tempering thermocouple and the first theoretical temperature value under the current operation condition, and judging that the hydrogen gas engine is tempered under the condition that the corresponding difference value of any tempering thermocouple is larger than the second temperature threshold and the duration time reaches the sixth time threshold.

4. The hydrogen engine flashback monitoring and protecting method according to claim 1, wherein the judging whether flashback of the hydrogen engine occurs comprises:

Calculating the average value of temperature values detected by all light field multi-spectrum pyrometers arranged in the hydrogen gas turbine, calculating the difference value between the temperature value detected by each light field multi-spectrum pyrometer and the second temperature measurement average value, and judging that the hydrogen gas turbine is tempered under the condition that the corresponding difference value of any light field multi-spectrum pyrometer is larger than a third temperature threshold value and the duration time reaches a seventh time threshold value;

calculating the temperature rise rate detected by each light field multi-spectrum pyrometer, and judging that the hydrogen combustion engine is tempered under the condition that the temperature rise rate corresponding to any light field multi-spectrum pyrometer is larger than a second temperature rise threshold value and the duration reaches an eighth time threshold value;

determining the current operation condition of the hydrogen gas engine, calculating the difference value between the temperature value detected by each light field multi-spectrum pyrometer and a second theoretical temperature value under the current operation condition, and judging that the hydrogen gas engine is tempered under the condition that the corresponding difference value of any light field multi-spectrum pyrometer is larger than a fourth temperature threshold and the duration reaches a ninth time threshold.

5. The hydrogen engine flashback monitoring protection method according to any one of claims 2 to 4, wherein the determining whether flashback of the hydrogen engine occurs further comprises:

And in the same fuel nozzle channel, judging that the hydrogen combustion engine is tempered under the condition that at least one static pressure sensor, at least one tempering thermocouple and at least one light field multispectral pyrometer exist and any calculated value is larger than a preset percentage of a corresponding threshold value.

6. The hydrogen engine flashback monitoring and protecting method according to claim 5, further comprising, before said determining whether flashback of the hydrogen engine occurs:

and analyzing the current performance of the hydrogen combustion engine, and updating each preset threshold value according to the performance analysis result.

7. The hydrogen engine flashback monitoring protection method according to claim 1, wherein the performing a corresponding flashback protection action in combination with an operating condition and a current flashback condition of the hydrogen engine comprises:

reducing the load of the hydrogen combustion engine according to a first rate under the working condition that the hydrogen combustion engine is in loaded operation;

reducing fuel input to the hydrogen combustion engine according to a second rate when the hydrogen combustion engine is in an unloaded operating condition;

and closing the target fuel nozzle channel, and triggering the protection tripping operation after tempering continuously occurs for a preset period of time.

8. The tempering monitoring and protecting system for the hydrogen-burning machine is characterized by comprising the following modules:

an arrangement module for circumferentially and equally arranging a plurality of static pressure sensors, a plurality of tempering thermocouples and a plurality of light field multispectral pyrometers on the inner wall of each fuel nozzle channel connected with a combustion chamber of the hydrogen combustion engine;

the judging module is used for acquiring a detection value acquired by each sensor in real time, comparing the pressure value and the pressure reduction rate detected by each static pressure sensor, the temperature value and the temperature increase rate detected by each tempering thermocouple and the temperature value and the temperature increase rate detected by each light field multispectral pyrometer with corresponding preset thresholds, and judging whether the hydrogen combustion engine is tempered and determining a target fuel nozzle channel in which tempering occurs;

and the protection module is used for executing corresponding tempering protection actions by combining the operation working condition of the hydrogen combustion engine and the current tempering state.

9. The hydrogen turbine flashback monitoring protection system of claim 8, wherein the protection module is specifically configured to:

reducing the load of the hydrogen combustion engine according to a first rate under the working condition that the hydrogen combustion engine is in loaded operation;

Reducing fuel input to the hydrogen combustion engine according to a second rate when the hydrogen combustion engine is in an unloaded operating condition;

and closing the target fuel nozzle channel, and triggering the protection tripping operation after tempering continuously occurs for a preset period of time.

10. A non-transitory computer readable storage medium having stored thereon a computer program, wherein the computer program when executed by a processor implements the hydrogen gas turbine flashback monitoring protection method according to any one of claims 1-7.