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CN114199819A - Combustion diagnosis device and method suitable for gas turbine - Google Patents

Combustion diagnosis device and method suitable for gas turbine Download PDF

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Publication number
CN114199819A
CN114199819A CN202111343020.5A CN202111343020A CN114199819A CN 114199819 A CN114199819 A CN 114199819A CN 202111343020 A CN202111343020 A CN 202111343020A CN 114199819 A CN114199819 A CN 114199819A
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combustion
combustion chamber
temperature
gas turbine
diagnosis
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CN114199819B (en
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王玮
肖俊峰
王峰
王致程
李晓丰
胡孟起
夏林
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Xian Thermal Power Research Institute Co Ltd
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Xian Thermal Power Research Institute Co Ltd
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N21/00—Investigating or analysing materials by the use of optical means, i.e. using sub-millimetre waves, infrared, visible or ultraviolet light
    • G01N21/17—Systems in which incident light is modified in accordance with the properties of the material investigated
    • G01N21/25—Colour; Spectral properties, i.e. comparison of effect of material on the light at two or more different wavelengths or wavelength bands
    • G01N21/31—Investigating relative effect of material at wavelengths characteristic of specific elements or molecules, e.g. atomic absorption spectrometry
    • G01N21/39—Investigating relative effect of material at wavelengths characteristic of specific elements or molecules, e.g. atomic absorption spectrometry using tunable lasers
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K13/00—Thermometers specially adapted for specific purposes
    • G01K13/02—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow
    • G01K13/024—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow of moving gases

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Abstract

The invention discloses a combustion diagnosis device and method suitable for a gas turbine. During working, the operating condition parameter module determines the operating condition of the combustion chamber, and the initial state parameter access module acquires parameters such as the initial state of the combustion chamber of the gas turbine; the TDLAS combustion state monitoring module monitors temperature, pressure pulsation and H of a combustion chamber2The concentration of the O component and other state parameters; the combustion diagnosis module contrasts and analyzes the combustion chamber state parameters acquired by the TDLAS combustion monitoring module, the combustion state reference information and the combustion chamber initial state information stored by the combustion criterion storage module, and diagnoses and outputs the combustion state of the combustion chamber according to the combustion diagnosis logic. The invention can accurately position the fault combustion chamber, simplify the combustion state monitoring system of the in-service gas turbine and improve the combustion state monitoring and diagnosing precision.

Description

Combustion diagnosis device and method suitable for gas turbine
Technical Field
The invention belongs to the technical field of gas turbines, and particularly relates to a combustion diagnosis device and method suitable for a gas turbine.
Background
The combustion monitoring and diagnosis of the gas turbine mainly comprises the steps of obtaining combustion state parameters of a combustion chamber through effective monitoring equipment, diagnosing the combustion state of the combustion chamber by combining corresponding diagnosis criteria, and feeding back a combustion diagnosis result to a gas turbine control system.
The in-service gas turbine mainly monitors the temperature of the outlet of the turbine through a thermocouple, monitors the pressure pulsation of the cold end of a combustion chamber through a pressure pulsation sensor, monitors the flame luminescence condition in the combustion chamber through a flame detector, and carries out combustion fault diagnosis on the gas turbine according to corresponding combustion diagnosis criteria. Firstly, because the high-temperature gas at the outlet of the combustion chamber flows through the turbine and other rotating parts, the airflow can deflect, the combustion monitoring and diagnosing method of the gas turbine in service cannot accurately diagnose the combustion overtemperature fault of the specific combustion chamber by referring to the outlet temperature of the turbine, and because the outlet temperature of the combustion chamber is reversely pushed by the outlet temperature of the turbine, the self error and the cold end monitoring can further reduce the accuracy of the combustion monitoring and diagnosing of the gas turbine in service. Secondly, the combustion monitoring and diagnosing method of the in-service gas turbine needs to integrate and process dozens of thermocouples at the outlet of the turbine, dozens of pressure pulsation sensors at the cold end of the combustion chamber and multi-source and multi-type real-time signals of a plurality of flame detectors, has large data volume and is relatively complex, thereby invisibly increasing the diagnostic error of the in-service gas turbine and reducing the combustion monitoring and diagnosing precision. In order to improve the combustion fault monitoring and diagnosing precision of the gas turbine and reduce the complexity of the method, a combustion diagnosing device and a method suitable for the gas turbine can be developed based on a tunable laser absorption spectroscopy (TDLAS) technology.
Disclosure of Invention
The invention provides a combustion diagnosis device and method suitable for a gas turbine, and aims to solve the problems of complex combustion monitoring diagnosis system, inaccurate combustion state monitoring diagnosis and the like of an in-service gas turbineMethod for monitoring combustion temperature, combustion stability and H of gas turbine2And the concentration of O, and can realize fault diagnosis of combustion overtemperature, combustion stability, ignition and the like of the gas turbine.
The invention is realized by the following technical scheme:
a combustion diagnosis device suitable for a gas turbine comprises an operation condition parameter module, an initial state access module, a TDLAS combustion state parameter monitoring module, a combustion criterion storage module and a combustion state diagnosis module;
the operation condition parameter module is used for acquiring operation condition parameters of the gas turbine to judge the operation condition of the combustion chamber and is connected with the combustion criterion storage module and the combustion state diagnosis module; the initial state access module is used for acquiring initial state parameters of the combustion chamber and is connected with the combustion state diagnosis module; the combustion criterion storage module is used for storing combustion chamber diagnosis criteria and is connected with the combustion state diagnosis module; the combustion diagnostic module diagnoses a combustion state based on the combustion diagnostic logic and sends a combustion chamber combustion state word to the combustion engine control system.
A combustion diagnostic method for a gas turbine, comprising the steps of:
step 1, obtaining an IGV angle, fuel flow and temperature and a gas turbine load of a gas turbine, and determining the operating condition of the gas turbine;
step 2, obtaining a combustion state diagnosis criterion of the combustion chamber of the gas turbine according to the operation condition of the gas turbine, wherein the diagnosis criterion comprises temperature reference information and H of the combustion chamber of the gas turbine under the operation condition2O concentration reference information and pressure reference information;
step 3, obtaining atmospheric humidity, and converting the atmospheric humidity into initial H of the combustion chamber of the gas turbine2The concentration of O; acquiring the exhaust temperature and the exhaust pressure of a gas compressor, and taking the exhaust temperature and the exhaust pressure as the initial temperature and the initial pressure of a combustion chamber of the gas turbine;
step 4, acquiring the combustion temperature, the combustion chamber pressure and the combustion chamber H of the combustion chamber by using the TDLAS combustion monitoring module2O concentration combustion state parameters, and converting combustion pressure into pressure pulsation frequency and amplitude through fast Fourier transform;
step 5, comparing and analyzing initial H of the combustion chamber2O concentration and captured combustor real-time H2The method comprises the steps of O concentration, comparing and analyzing initial temperature of a combustion chamber and acquired real-time combustion temperature of the combustion chamber, diagnosing whether flame exists in the combustion chamber according to combustion diagnosis logic, diagnosing the ignition state of the combustion chamber, and sending signals of successful ignition and unsuccessful flameless ignition of the combustion chamber according to a diagnosis result;
step 6, comparing and analyzing the initial temperature of the combustion chamber, the acquired real-time temperature of the combustion chamber and the combustion temperature reference information in the combustion diagnosis criterion, diagnosing the temperature of the combustion chamber according to the combustion diagnosis logic, and sending out signs such as normal combustion temperature, high combustion temperature early warning and overtemperature trip of the combustion temperature according to the diagnosis result;
and 7, comparing and analyzing the initial pressure of the combustion chamber, the obtained pressure pulsation information of the combustion chamber and the combustion pressure reference information in the combustion diagnosis criterion, diagnosing the combustion stability according to the combustion diagnosis logic, and sending signals of stable combustion, high combustion pressure pulsation early warning and unstable combustion trip according to the diagnosis result.
The invention is further improved in that the IGV angle, the fuel flow and the temperature and the engine load parameters in the step 1 can be obtained from a gas turbine control system and stored in an operating condition parameter storage module.
The invention further improves that the temperature reference information of the combustion chamber of the gas turbine in the diagnosis criterion of the combustion state of the combustion chamber of the gas turbine in the step 2 at least comprises an array T of normal ranges of the combustion temperature of the combustion chamber under different working conditionsZEarly warning value TC,10And an alarm value TC,20The stored combustion chamber pressure reference information includes the natural acoustic frequency P of the combustion chamber componentsHC,0And early warning value P of pressure pulsation amplitude of combustion chamber under different working conditionsAC,10Sum trip value PAC,20And the combustion state diagnosis criteria of the combustion chamber of the gas turbine under different working conditions are stored in the combustion criterion diagnosis module.
The invention is further improved in that the existing atmospheric humidity monitoring equipment of the gas turbine is adopted to obtain and convert the atmospheric humidity in the step 3For initial H of gas turbine combustion chamber2Concentration D of OH2O,0(ii) a The method is characterized in that the existing compressor exhaust temperature and exhaust pressure equipment of the gas turbine are adopted for obtaining and taking the temperature and the exhaust pressure as the initial temperature T of a combustion chamber of the gas turbineC,0And an initial pressure PC,0And the data is stored in the initial state access module of the combustion chamber.
The further improvement of the invention is that in the TDLAS combustion monitoring module in step 4, 2 pieces capable of emitting can be H2The laser absorbed by O is single-mode laser, the wavelength of the laser is between 1260nm and 1650nm, and the numerical difference of the spectral line intensity of the two lasers at 450-1800 ℃ is not large;
the TDLAS combustion monitoring module is used for monitoring combustion flow field parameters near an outlet of a transition section of the combustion chamber, and converting the parameters into temperature values T of a flow field to be measured of the combustion chamber according to a single-value conversion formula between light intensity and temperature by analyzing light intensity change information of laser absorption spectrumC,t(ii) a The one-to-one correspondence relation between the broadening of the absorption spectrum signal and the pressure is analyzed, and the one-to-one correspondence relation is converted into a pressure value P of a flow field to be measured in the combustion chamberC,tAnd then FFT conversion is carried out on the flow field pressure to obtain the pressure pulsation frequency P of the flow field to be measured in the combustion chamberHC,tAnd corresponding amplitude value PAC,t(ii) a Analyzing the linear and second harmonic peak information of the laser absorption spectrum signal, and acquiring the H of the flow field to be measured of the combustion chamber according to the corresponding relation between the component concentration and the second harmonic peak and combining the combustion temperature and the combustion pressure information2Concentration D of OH2O,t。
A further development of the invention consists in the fact that, in step 5, the combustion chamber H provided by the TDLAS monitoring module is analyzed by contrast2Concentration D of OH2O,tH stored by the combustion chamber initial state access module2Concentration D of OH2O,Z0And analyzing the combustion chamber temperature T provided by the TDLAS monitoring moduleC,tThe initial temperature T of the combustion chamber stored by the combustion initial state parameter access moduleC,0And diagnosing the ignition state of the combustion chamber according to the combustion diagnosis logic and sending information of successful ignition and failed ignition of the combustion chamber to the gas turbine control system.
A further development of the invention is that, in step 6, the fractions are separated by comparisonAnalyzing the initial state and taking the initial temperature T of the combustion chamber obtained by the moduleC,0The temperature T of the combustion chamber provided by the TDLAS monitoring moduleC,tThe early warning value T of the combustion temperature of the combustion chamber under different working conditions stored by the combustion diagnosis criterion storage moduleC,10And an alarm value TC,20And diagnosing the temperature state of the combustion chamber according to the combustion diagnosis logic, and sending information of normal combustion temperature, high combustion temperature and over-temperature combustion state of the combustion temperature to the gas turbine control system.
A further development of the invention consists in the fact that in step 7 the combustion chamber pressure pulsation frequency P provided by the TDLAS monitoring module is analyzed by comparisonHC,tAnd corresponding amplitude value PAC,tThe combustion chamber pressure reference information stored by the combustion diagnosis criterion storage module comprises natural acoustic frequency P of the combustion chamber component under different working conditionsHC,0Pressure pulsation amplitude and frequency of the early warning value PAC,10Sum trip value PAC,20And diagnosing the combustion stability of the combustion chamber according to the combustion diagnosis logic, and sending out combustion pressure pulsation stability, combustion instability early warning and combustion instability trip combustion state information to the gas turbine control system.
In a further development of the invention, the combustion diagnosis logic for use in the combustion diagnosis method for a gas turbine is as follows:
if TCt–TC0Not less than 0 and DH2O,t–DH2O,0If the flame is more than 0, indicating that continuous flame exists in the combustion chamber, and outputting a combustion chamber ignition success and continuous flame state word by the combustion diagnosis module;
if D isH2O,t–DH2O,0The flame state word is less than or equal to 0, which indicates that no continuous flame exists in the combustion chamber, and the combustion diagnosis module outputs the state word of the combustion chamber which is failed to ignite and does not have continuous flame;
if TC,t－TC,0> 0 and TC,t–TC,10If the value is less than 0, the combustion chamber temperature is normal, and the combustion diagnosis module sends a combustion chamber temperature normal state word;
if TC,t－TC,0> 0 and TC,t–TC,10Not less than 0 and TC,t–TC,20< 0, indicating the combustion temperature of the combustion chamberThe temperature of the combustion chamber is higher and approaches the upper line of the temperature of the combustion chamber, and the combustion diagnosis module sends out early warning state words of high temperature of the combustion chamber;
if TC,t－TC,0> 0 and TC,t–TC,20The combustion diagnosis module sends out a combustion overtemperature alarm state word when the temperature of the combustion chamber exceeds the safe operation range of the combustion chamber is larger than or equal to 0;
if PHC,t－PHC,0If the absolute value is less than 50Hz, the pressure pulsation frequency of the combustion chamber is close to the inherent frequency of the combustion chamber, the combustion chamber is likely to resonate, the combustion diagnosis system sends out a combustion chamber resonance state word, and the combustion engine trips;
if PHC,t－PHC,0| is not less than 50Hz, and PAC,t－PAC,10If the frequency is less than 0, the pressure pulsation frequency and the pressure pulsation amplitude of the combustion chamber are both in the safe and stable combustion range, the combustion of the combustion chamber is stable, and the combustion diagnosis module outputs a combustion stable state word;
if PHC,t－PHC,0| is not less than 50Hz, and PAC,t－PAC,10Not less than 0 and PAC,t－PAC,20If the combustion pressure pulse frequency is less than 0, the combustion chamber pressure pulse frequency is in a safety range, but the combustion chamber pressure pulse amplitude is close to a safety upper limit, and the combustion diagnosis module sends out a combustion pressure pulse early warning state word;
if PHC,t－PHC,0| is not less than 50Hz, and PAC,t－PAC,20And if the combustion pressure pulsation frequency is more than or equal to 0, the combustion chamber pressure pulsation frequency is in a safety range, but the combustion chamber pressure pulsation amplitude exceeds the safety upper limit of the combustion chamber pressure pulsation amplitude, and the combustion diagnosis module sends a combustion pressure pulsation high alarm state word.
The invention has at least the following beneficial technical effects:
according to the combustion diagnosis device and method suitable for the gas turbine, provided by the invention, the measurement data of a plurality of monitoring equipment primary measurement elements do not need to be processed and analyzed, the measurement error caused by a plurality of measurement elements is not introduced, the processing flow of the combustion state monitoring data of the gas turbine in service can be simplified, and the combustion state monitoring and diagnosis precision can be improved.
Further, in the present invention,according to the combustion diagnosis device and method suitable for the gas turbine, provided by the invention, under the condition of not contacting high-temperature gas in a combustion chamber of the gas turbine, the temperature, the pressure and the H of a combustion flow field can be directly obtained by processing and analyzing laser absorption spectrum signals2Combustion state parameters such as O concentration and the like can avoid the back-pushing of combustion temperature and H by introducing an empirical formula into an in-service gas turbine2O concentration, etc.
Furthermore, the TDLAS combustion monitoring and diagnosing module can replace a combustion temperature monitoring system arranged near a turbine outlet, a flame detecting system arranged near a combustion chamber nozzle, a pressure pulsation monitoring system and the like of an in-service gas turbine, so that data interaction among multiple systems is avoided, the combustion state parameter measuring accuracy of the gas turbine is improved, and the complexity of the existing combustion state monitoring system of the gas turbine is simplified.
Furthermore, the combustion diagnosis device and method applicable to the gas turbine only need to compare and analyze the initial state parameters of the combustion chamber acquired by the initial state access module, the combustion chamber state parameters acquired by the TDLAS combustion state parameter monitoring module in real time, the combustion chamber temperature reference values and the H stored by the combustion criterion storage module under different working conditions2The combustion state of the combustion chamber of the gas turbine can be diagnosed by the aid of the O concentration reference value and the pressure reference value, and the combustion state diagnosis logic of the combustion chamber of the gas turbine can be simplified to a certain extent; and when the combustion chamber has combustion failure, the failure combustion chamber can be accurately positioned, and the phenomenon that the failure combustion chamber cannot be accurately positioned due to hot spot migration caused by the rotation action of the turbine blade can be avoided.
Drawings
Fig. 1 is a schematic diagram of the system architecture and workflow of the present invention.
Fig. 2 is a schematic diagram of an embodiment of the present invention.
Description of reference numerals:
1. an operating condition parameter module; 2. an initial state access module; a TDLAS combustion state parameter monitoring module; 4. a combustion criterion storage module; 5. a combustion status diagnostic module.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
The field of application of the present invention is a combustion diagnosis apparatus suitable for a gas turbine as shown in fig. 1. As shown in fig. 1, the combustion diagnosis device for a gas turbine provided by the present invention includes an operating condition parameter module 1, an initial state access module 2, a TDLAS combustion state parameter monitoring module 3, a combustion criterion storage module 4, and a combustion state diagnosis module 5.
During operation, the operation condition parameter module 1 obtains the operation condition of the gas turbine from the existing control system of the gas turbine, and outputs the operation condition parameter to the combustion diagnosis criterion storage module 4 and the combustion diagnosis module 5. The initial state access module 2 obtains the exhaust temperature and the exhaust pressure of the compressor by the existing measurement system of the gas turbine and takes the exhaust temperature and the exhaust pressure as the initial state parameter T of the combustion chamberC,0And PC,0(ii) a Air humidity is obtained by an air humidity measuring device in an air inlet of a gas turbine and is converted into initial H of a combustion chamber2Concentration D of OH2O,0And will TC,0、PC,0And DH2O,0Etc. are provided to the combustion state diagnostic module 5. The TDLAS combustion state parameter monitoring module 3 is provided with 2 pieces of data which can be processed by H2The narrow-band laser signal absorbed by O is coupled into a beam of parallel light, the parallel light to be coupled into a beam is received by a TDLAS combustion state monitoring module after passing through a flow field to be measured of a combustion chamber of the gas turbine, and the beam is converted into the real-time temperature T of the combustion chamber through calculation and analysisC,tAnd combustion of the sameChamber pressure pulsation frequency PHC,tAmplitude P of pressure pulsation at different frequenciesAC,tAnd H2Concentration D of O componentH2O,tAnd waits for the combustion state parameters to be real-time information and provides it to the combustion state diagnostic module 5. The combustion criterion storage module 4 prestores combustion temperature early warning values and warning values of the outlet plane of the combustion chamber of the gas turbine under different working conditions, the inherent acoustic frequency of combustion chamber components, the early warning values of the pressure pulsation frequency and amplitude of the combustion chamber under different working conditions, trip values and other information, and screens the early warning values T of the combustion temperature of the combustion chamber under corresponding working conditions according to the operating condition parameters input by the operating condition parameter module 1C,10And an alarm value TC,20And natural acoustic frequency P of the combustion chamber componentHC,0Pressure pulsation amplitude and frequency of the early warning value PAC,10Sum trip value PAC,20And so on to the combustion diagnostic module 5.
The combustion state diagnosis module 5 integrates data and information provided by the operation condition parameter module 1, the initial state access module 2, the TDLAS combustion state parameter monitoring module 3 and the combustion criterion storage module 4, and sends combustion state information such as normal combustion temperature, high combustion temperature, over-temperature combustion temperature and the like to the gas turbine control system by comparing and analyzing the initial temperature of the combustion chamber acquired by the initial state access module, the temperature of the combustion chamber provided by the TDLAS monitoring module and the combustion temperature reference value stored by the combustion criterion storage module; combustion chamber H provided by comparing and analyzing TDLAS monitoring module2O and H stored by combustion criterion storage module2O concentration, which sends information of successful ignition, failure of ignition and the like of the combustion chamber to a gas turbine control system; the accessible contrasts information such as combustion chamber pressure pulsation amplitude and frequency that analysis TDLAS monitoring module provided, sends combustion state information such as combustion stability, unstable early warning of burning and burning unstability to gas turbine control system.
Preferably, the TDLAS combustion state monitoring module is established to provide an optical monitoring window by utilizing the high-temperature gas of the combustion chamber isolated by the high-temperature-resistant quartz glass, so that the TDLAS combustion state monitoring module can ensure that the laser can smoothly pass through the gas turbine on the premise of not contacting the high-temperature gas in the combustion chamber of the gas turbineThe flow field to be measured of the combustion chamber of the engine realizes combustion temperature, pressure and H2Monitoring the state parameters of O component and the like.
Preferably, the combustion criterion storage module 3 stores the stored combustion chamber temperature reference information of the gas turbine combustion chamber, H2O concentration reference information, pressure reference information, etc., and the stored combustor temperature reference information is derived from the temperature of the gas turbine combustor transition section exit plane, H2Average values of combustion state parameters such as O concentration and pressure.
Preferably, the combustion diagnosis module 5 diagnoses, by simple logic, combustion state information such as whether the combustion temperature of the combustion chamber is normal, whether the combustion temperature is too high, whether the combustion temperature is over-temperature, and the like by comparing the temperature reference value of the combustion chamber under different working conditions with the real-time temperature of the combustion chamber provided by the TDLAS combustion temperature monitoring system; combustion chamber H as provided by comparative analysis TDLAS monitoring Module 22O and H stored by combustion criterion storage module 32O concentration, information such as diagnosis of combustion chamber ignition success and ignition failure; if the difference between the information such as the amplitude and the frequency of the pressure pulsation of the combustion chamber provided by the TDLAS monitoring module and the combustion pressure pulsation reference information stored in the storage module 3 is contrasted and analyzed, the combustion state information such as stable combustion, unstable combustion early warning and unstable combustion of the combustion chamber of the gas turbine is diagnosed; and sends the diagnosis result to the gas turbine control system.
Preferably, a combustion diagnosis logic suitable for use in a combustion diagnosis method of a gas turbine is as follows:
if TCt–TC0Not less than 0 and DH2O,t–DH2O,0If the flame is more than 0, indicating that continuous flame exists in the combustion chamber, and outputting a state word of successful ignition of the combustion chamber and the like by the combustion diagnosis module;
if D isH2O,t–DH2O,0The flame is less than or equal to 0, which indicates that no continuous flame exists in the combustion chamber, and the combustion diagnosis module outputs state words such as ignition failure of the combustion chamber and the like;
if TC,t－TC,0> 0 and TC,t–TC,10If the temperature is less than 0, the combustion chamber temperature is normal, and the combustion diagnosis module sends outA combustion chamber temperature normal status word;
if TC,t－TC,0> 0 and TC,t–TC,10Not less than 0 and TC,t–TC,20If the combustion temperature is lower than 0, the combustion temperature of the combustion chamber is close to the upper line of the combustion chamber temperature, and the combustion diagnosis module sends out early warning state words of high combustion chamber temperature;
if TC,t－TC,0> 0 and TC,t–TC,20The combustion diagnosis module sends out a combustion overtemperature alarm state word when the temperature of the combustion chamber exceeds the safe operation range of the combustion chamber is larger than or equal to 0;
if PHC,t－PHC,0If the absolute value is less than 50Hz, the pressure pulsation frequency of the combustion chamber is close to the inherent frequency of the combustion chamber, the combustion chamber is likely to resonate, the combustion diagnosis system sends out a combustion chamber resonance state word, and the combustion engine trips;
if PHC,t－PHC,0| is not less than 50Hz, and PAC,t－PAC,10If the frequency is less than 0, the pressure pulsation frequency and the pressure pulsation amplitude of the combustion chamber are both in the safe and stable combustion range, the combustion of the combustion chamber is stable, and the combustion diagnosis module outputs a combustion stable state word;
if PHC,t－PHC,0| is not less than 50Hz, and PAC,t－PAC,10Not less than 0 and PAC,t－PAC,20If the combustion pressure pulse frequency is less than 0, the combustion chamber pressure pulse frequency is in a safety range, but the combustion chamber pressure pulse amplitude is close to a safety upper limit, and the combustion diagnosis module sends out a combustion pressure pulse early warning state word;
if PHC,t－PHC,0| is not less than 50Hz, and PAC,t－PAC,20And if the combustion pressure pulsation frequency is more than or equal to 0, the combustion chamber pressure pulsation frequency is in a safety range, but the combustion chamber pressure pulsation amplitude exceeds the safety upper limit of the combustion chamber pressure pulsation amplitude, and the combustion diagnosis module sends a combustion pressure pulsation high alarm state word.
Examples
As shown in FIG. 2, when the gas turbine combustor works, the operation condition parameter module 1 obtains the operation condition of the gas turbine from the existing control system of the gas turbine and outputs the operation condition parameter to the combustionA diagnostic criteria storage module 4 and a combustion diagnostic module 5. The initial state access module 2 obtains the exhaust temperature and the exhaust pressure of the compressor by the existing measurement system of the gas turbine and takes the exhaust temperature and the exhaust pressure as the initial state parameter T of the combustion chamberC,0And PC,0(ii) a Air humidity is obtained by an air humidity measuring device in an air inlet of a gas turbine and is converted into initial H of a combustion chamber2Concentration D of OH2O,0And will TC,0、PC,0And DH2O,0Etc. are provided to the combustion state diagnostic module 5. The TDLAS combustion state parameter monitoring module 3 is provided with 2 pieces of data which can be processed by H2The narrow-band laser signal absorbed by O is coupled into a beam of parallel light, the parallel light to be coupled into a beam is received by a TDLAS combustion state monitoring module after passing through a flow field to be measured of a combustion chamber of the gas turbine, and the beam is converted into the real-time temperature T of the combustion chamber through calculation and analysisC,tPressure pulsation frequency P of combustion chamberHC,tAmplitude P of pressure pulsation at different frequenciesAC,tAnd H2Concentration D of O componentH2O,tAnd waits for the combustion state parameters to be real-time information and provides it to the combustion state diagnostic module 5. The combustion criterion storage module 4 prestores combustion temperature early warning values and warning values of the outlet plane of the combustion chamber of the gas turbine under different working conditions, the inherent acoustic frequency of combustion chamber components, the early warning values of the pressure pulsation frequency and amplitude of the combustion chamber under different working conditions, trip values and other information, and screens the early warning values T of the combustion temperature of the combustion chamber under corresponding working conditions according to the operating condition parameters input by the operating condition parameter module 1C,10And an alarm value TC,20And natural acoustic frequency P of the combustion chamber componentHC,0Pressure pulsation amplitude and frequency of the early warning value PAC,10Sum trip value PAC,20And so on to the combustion diagnostic module 5.
The combustion state diagnosis module 5 integrates data and information provided by the operation condition parameter module 1, the initial state access module 2, the TDLAS combustion state parameter monitoring module 3 and the combustion criterion storage module 4, and sends combustion temperature to the gas turbine control system by comparing and analyzing the initial temperature of the combustion chamber acquired by the initial state access module, the temperature of the combustion chamber provided by the TDLAS monitoring module and the combustion temperature reference value stored by the combustion criterion storage moduleNormal, high combustion temperature, and over-temperature combustion state information; combustion chamber H provided by comparing and analyzing TDLAS monitoring module2O and H stored by combustion criterion storage module2O concentration, which sends information of successful ignition, failure of ignition and the like of the combustion chamber to a gas turbine control system; the accessible contrasts information such as combustion chamber pressure pulsation amplitude and frequency that analysis TDLAS monitoring module provided, sends combustion state information such as combustion stability, unstable early warning of burning and burning unstability to gas turbine control system.
Preferably, the gas turbine combustion chamber utilizes high-temperature-resistant quartz glass to isolate high-temperature gas; the diameter of the high-temperature-resistant quartz glass is not more than 10mm, the thickness of the high-temperature-resistant quartz glass is not less than 10mm, the high-temperature-resistant quartz glass is arranged near the outlet plane of the transition section of the combustion chamber of the gas turbine, and the plane of the high-temperature-resistant quartz glass, which is in contact with high-temperature gas, is flush with the inner wall surface of the combustion chamber, so that the internal flow field structure of the combustion chamber is not influenced, and the influence on the structural strength of combustion chamber parts is small; based on high-temperature-resistant quartz glass, the TDLAS combustion state monitoring module can be formed to provide an optical monitoring window, so that on the premise that the TDLAS combustion state monitoring module is not in contact with high-temperature gas in the gas turbine combustion chamber, laser can smoothly penetrate through a flow field to be detected of the gas turbine combustion chamber, and the combustion temperature, the pressure and the H are achieved2Monitoring the state parameters of O component and the like.
Preferably, 2 pieces which can be emitted by the TDLAS combustion state monitoring module 3 can be replaced by H2The laser absorbed by O is single-mode laser, the wavelength of the laser is between 1260nm and 1650nm, the laser is in the working wave band of the DFB diode laser for communication, and the numerical value of the spectral line intensity of the two lasers at 450-1800 ℃ has little difference.
Preferably, the combustion criterion storage module 4 stores a stored reference value for the combustion chamber temperature of the gas turbine combustion chamber, H2A reference O concentration value, a reference pressure value, etc., and the stored reference combustion chamber temperature value is an average combustion temperature value in the plane of the transition section outlet of the combustion chamber.
Preferably, the combustion diagnosis module 5 can diagnose the combustion ignition state, the combustion temperature state and the combustion stability state of the combustion chamber of the gas turbine through a simple combustion diagnosis logic, and can send combustion state information such as successful ignition, failed ignition, normal combustion temperature, high combustion temperature early warning, excessive combustion temperature trip, combustion resonance, stable combustion, high combustion pressure pulsation amplitude early warning and high combustion pressure pulsation amplitude warning to the gas turbine control system.
Preferably, a combustion diagnosis logic suitable for use in a combustion diagnosis method of a gas turbine is as follows:
if TCt–TC0Not less than 0 and DH2O,t–DH2O,0If the flame is more than 0, indicating that continuous flame exists in the combustion chamber, and outputting a state word of successful ignition of the combustion chamber and the like by the combustion diagnosis module;
if D isH2O,t–DH2O,0The flame is less than or equal to 0, which indicates that no continuous flame exists in the combustion chamber, and the combustion diagnosis module outputs state words such as ignition failure of the combustion chamber and the like;
if TC,t－TC,0> 0 and TC,t–TC,10If the value is less than 0, the combustion chamber temperature is normal, and the combustion diagnosis module sends a combustion chamber temperature normal state word;
if TC,t－TC,0> 0 and TC,t–TC,10Not less than 0 and TC,t–TC,20If the combustion temperature is lower than 0, the combustion temperature of the combustion chamber is close to the upper line of the combustion chamber temperature, and the combustion diagnosis module sends out early warning state words of high combustion chamber temperature;
if TC,t－TC,0> 0 and TC,t–TC,20The combustion diagnosis module sends out a combustion overtemperature alarm state word when the temperature of the combustion chamber exceeds the safe operation range of the combustion chamber is larger than or equal to 0;
if PHC,t－PHC,0If the absolute value is less than 50Hz, the pressure pulsation frequency of the combustion chamber is close to the inherent frequency of the combustion chamber, the combustion chamber is likely to resonate, the combustion diagnosis system sends out a combustion chamber resonance state word, and the combustion engine trips;
if PHC,t－PHC,0| is not less than 50Hz, and PAC,t－PAC,10If the frequency is less than 0, the pressure pulsation frequency and the pressure pulsation amplitude of the combustion chamber are both in the safe and stable range of combustion, the combustion of the combustion chamber is stable, and the combustion diagnosis module outputs the stable combustion stateA word;
if PHC,t－PHC,0| is not less than 50Hz, and PAC,t－PAC,10Not less than 0 and PAC,t－PAC,20If the combustion pressure pulse frequency is less than 0, the combustion chamber pressure pulse frequency is in a safety range, but the combustion chamber pressure pulse amplitude is close to a safety upper limit, and the combustion diagnosis module sends out a combustion pressure pulse early warning state word;
if PHC,t－PHC,0| is not less than 50Hz, and PAC,t－PAC,20And if the combustion pressure pulsation frequency is more than or equal to 0, the combustion chamber pressure pulsation frequency is in a safety range, but the combustion chamber pressure pulsation amplitude exceeds the safety upper limit of the combustion chamber pressure pulsation amplitude, and the combustion diagnosis module sends a combustion pressure pulsation high alarm state word.
Although the invention has been described in detail hereinabove with respect to a general description and specific embodiments thereof, it will be apparent to those skilled in the art that modifications or improvements may be made thereto based on the invention. Accordingly, such modifications and improvements are intended to be within the scope of the invention as claimed.

Claims (10)

1.一种适用于燃气轮机的燃烧诊断装置，其特征在于，包括运行工况参数模块、初始状态取数模块、TDLAS燃烧状态参数监测模块、燃烧判据存储模块和燃烧状态诊断模块；1. a combustion diagnostic device applicable to a gas turbine, is characterized in that, comprises an operating condition parameter module, an initial state fetching module, a TDLAS combustion state parameter monitoring module, a combustion criterion storage module and a combustion state diagnosis module; 运行工况参数模块用于获取燃气轮机运行工况参数判断燃烧室的运行工况，且与燃烧判据存储模块、燃烧状态诊断模块相连；初始状态取数模块用于获取燃烧室的初始状态参数，且与燃烧状态诊断模块相连；燃烧判据存储模块用于存储燃烧室诊断判据，并与燃烧状态诊断模块相连；燃烧诊断模块基于燃烧诊断逻辑诊断燃烧状态，并向燃机控制系统发送燃烧室燃烧状态字。The operating condition parameter module is used to obtain the operating condition parameters of the gas turbine to determine the operating condition of the combustion chamber, and is connected to the combustion criterion storage module and the combustion state diagnosis module; the initial state acquisition module is used to obtain the initial state parameters of the combustion chamber, It is connected to the combustion state diagnosis module; the combustion criterion storage module is used to store the combustion chamber diagnosis criterion and is connected to the combustion state diagnosis module; the combustion diagnosis module diagnoses the combustion state based on the combustion diagnosis logic, and sends the combustion chamber to the combustion engine control system Burning status word. 2.一种适用于燃气轮机的燃烧诊断方法，其特征在于，包括以下步骤：2. A combustion diagnosis method applicable to a gas turbine, comprising the following steps: 步骤1、获取燃气轮机IGV角度、燃料流量和温度、燃机负荷，确定燃气轮机运行工况；Step 1. Obtain the gas turbine IGV angle, fuel flow and temperature, and gas turbine load, and determine the gas turbine operating conditions; 步骤2、根据燃气轮机运行工况，获取燃气轮机燃烧室的燃烧状态诊断判据，包括该运行工况下燃气轮机燃烧室的温度基准信息、H2O浓度基准信息和压力基准信息；Step 2, according to the gas turbine operating condition, obtain the combustion state diagnosis criterion of the gas turbine combustion chamber, including the temperature reference information, H 2 O concentration reference information and pressure reference information of the gas turbine combustion chamber under the operating condition; 步骤3、获取大气湿度，将其转化为燃气轮机燃烧室初始H2O浓度；获取压气机排气温度和排气压力，并将其作为燃气轮机燃烧室初始温度和压力；Step 3. Obtain atmospheric humidity and convert it into the initial H 2 O concentration of the gas turbine combustion chamber; obtain the exhaust gas temperature and exhaust pressure of the compressor, and use them as the initial temperature and pressure of the gas turbine combustion chamber; 步骤4、利用TDLAS燃烧监测模块获取燃烧室的燃烧温度、燃烧室压力以及燃烧室H2O浓度燃烧状态参数，并通过快速傅立叶变换将燃烧压力转化为压力脉动频率和幅值；Step 4, using the TDLAS combustion monitoring module to obtain the combustion temperature, the combustion chamber pressure and the combustion state parameters of the combustion chamber H 2 O concentration, and convert the combustion pressure into the pressure pulsation frequency and amplitude through fast Fourier transform; 步骤5、对比分析燃烧室初始H2O浓度和获取的燃烧室实时H2O浓度、对比分析燃烧室初始温度和获取的燃烧室实时燃烧温度，根据燃烧诊断逻辑诊断燃烧室是否存在火焰，诊断燃烧室的点火状态，并根据诊断结果，发出点火成功和燃烧室无火焰点火不成功信号；Step 5, compare and analyze the initial H 2 O concentration of the combustion chamber and the acquired real-time H 2 O concentration of the combustion chamber, compare and analyze the initial temperature of the combustion chamber and the acquired real-time combustion temperature of the combustion chamber, and diagnose whether there is a flame in the combustion chamber according to the combustion diagnosis logic, and diagnose The ignition state of the combustion chamber, and according to the diagnosis result, the successful ignition and the unsuccessful ignition of the combustion chamber without flame are sent out; 步骤6、对比分析燃烧室初始温度、获取的燃烧室实时温度以及燃烧诊断判据中的燃烧温度基准信息，根据燃烧诊断逻辑诊断燃烧室温度，并根据诊断结果，发出燃烧温度正常、燃烧温度高预警和燃烧温度超温跳机等号；Step 6. Comparatively analyze the initial temperature of the combustion chamber, the acquired real-time temperature of the combustion chamber, and the combustion temperature reference information in the combustion diagnosis criterion, diagnose the combustion chamber temperature according to the combustion diagnosis logic, and according to the diagnosis result, send out that the combustion temperature is normal and the combustion temperature is high. Early warning and combustion temperature over-temperature tripping are equal signs; 步骤7、对比分析燃烧室初始压力、获取的燃烧室压力脉动信息以及燃烧诊断判据中的燃烧压力基准信息，根据燃烧诊断逻辑诊断诊断燃烧稳定性，并根据诊断结果，发出燃烧稳定、燃烧压力脉动高预警和燃烧不稳定跳机信号。Step 7: Compare and analyze the initial pressure of the combustion chamber, the obtained pressure pulsation information of the combustion chamber, and the combustion pressure reference information in the combustion diagnosis criterion, diagnose and diagnose the combustion stability according to the combustion diagnosis logic, and issue the combustion stability and combustion pressure according to the diagnosis result. Pulsation high warning and combustion instability trip signal. 3.根据权利要求2所述的一种适用于燃气轮机的燃烧诊断方法，其特征在于，步骤1中的IGV角度、燃料流量和温度、燃机负荷参数可从燃气轮机控制系统获取，并存储在运行工况参数存储模块。3. A combustion diagnosis method applicable to a gas turbine according to claim 2, wherein the IGV angle, fuel flow and temperature, and gas turbine load parameters in step 1 can be obtained from the gas turbine control system, and stored in the operation. Working condition parameter storage module. 4.根据权利要求2所述的一种适用于燃气轮机的燃烧诊断方法，其特征在于，步骤2中燃气轮机燃烧室燃烧状态诊断判据中所述的燃气轮机燃烧室的温度基准信息，至少包括不同工况下燃烧室燃烧温度的正常范围数组TZ、预警值TC,10以及报警值TC,20，存储的燃烧室压力基准信息包括燃烧室部件的固有声学频率PHC,0、不同工况下燃烧室压力脉动幅值的预警值PAC,10和跳机值PAC,20，且燃气轮机燃烧室不同工况下的燃烧状态诊断判据存储在燃烧判据诊断模块。4 . A combustion diagnosis method suitable for a gas turbine according to claim 2 , wherein the temperature reference information of the combustion chamber of the gas turbine described in the combustion state diagnosis criterion of the combustion chamber of the gas turbine in step 2 at least includes different working conditions. 5 . The normal range array T Z of the combustion temperature of the combustion chamber, the warning value T C , 10 and the alarm value T C,20 under the condition of The pre-warning value P AC,10 and the trip value P AC,20 of the lower combustion chamber pressure pulsation amplitude, and the combustion state diagnosis criteria of the gas turbine combustion chamber under different working conditions are stored in the combustion criterion diagnosis module. 5.根据权利要求2所述的一种适用于燃气轮机的燃烧诊断方法，其特征在于，步骤3中采用燃气轮机现有的大气湿度监测设备获取，并将其转化为燃气轮机燃烧室初始H2O浓度DH2O,0；采用燃气轮机现有的压气机排气温度和排气压力设备获取，并将其作为燃气轮机燃烧室初始温度TC,0和初始压力PC,0，且数据存储在燃烧室初始状态取数模块。5 . The combustion diagnosis method applicable to a gas turbine according to claim 2 , wherein in step 3, the existing atmospheric humidity monitoring equipment of the gas turbine is used to obtain and convert it into the initial H 2 O concentration of the combustion chamber of the gas turbine. 6 . D H2O,0 ; obtained by using the existing compressor exhaust temperature and exhaust pressure equipment of the gas turbine, and used as the initial temperature T C,0 and initial pressure P C,0 of the combustion chamber of the gas turbine, and the data is stored in the initial combustion chamber Status fetching module. 6.根据权利要求2所述的一种适用于燃气轮机的燃烧诊断方法，其特征在于，步骤4中的TDLAS燃烧监测模块，能够发射的2条可被H2O吸收的激光为单模激光，其波长介于1260nm-1650nm之间，且两条激光在450℃～1800℃的谱线强度数值相差不大；6. A combustion diagnosis method suitable for a gas turbine according to claim 2, characterized in that, in the TDLAS combustion monitoring module in step 4, the 2 lasers that can be emitted that can be absorbed by H 2 O are single-mode lasers, Its wavelength is between 1260nm-1650nm, and the spectral line intensity values of the two lasers at 450℃～1800℃ are not much different; TDLAS燃烧监测模块用于监测燃烧室过渡段出口附近的燃烧流场参数，其通过分析激光吸收光谱的光强变化信息，依据光强与温度之间的单值转化公式，将其转化为燃烧室待测流场的温度值TC,t；通过分析吸收光谱信号的展宽与压力的一一对应关系，将其转化为燃烧室待测流场的压力值PC,t，再对流场压力进行FFT转换获取燃烧室待测流场的压力脉动频率PHC,t及相应幅值PAC,t；分析激光吸收光谱信号的线型、二次谐波峰值信息，依据组分浓度与二次谐波峰值之间的对应关系，并结合燃烧温度和燃烧压力信息，获取燃烧室待测流场的H2O浓度DH2O,t。The TDLAS combustion monitoring module is used to monitor the combustion flow field parameters near the exit of the transition section of the combustion chamber. It analyzes the light intensity change information of the laser absorption spectrum and converts it into the combustion chamber according to the single-value conversion formula between light intensity and temperature. The temperature value T C,t of the flow field to be measured; by analyzing the one-to-one correspondence between the broadening of the absorption spectrum signal and the pressure, it is converted into the pressure value P C,t of the flow field to be measured in the combustion chamber, and then the pressure of the flow field is measured. Perform FFT conversion to obtain the pressure pulsation frequency P HC,t and corresponding amplitude P AC,t of the flow field to be measured in the combustion chamber; analyze the line shape and second harmonic peak information of the laser absorption spectrum signal, according to the component concentration and the second harmonic peak information The corresponding relationship between the harmonic peaks, and combined with the combustion temperature and combustion pressure information, the H2O concentration D H2O,t of the flow field to be measured in the combustion chamber is obtained. 7.根据权利要求2所述的一种适用于燃气轮机的燃烧诊断方法，其特征在于，步骤5中通过对比分析TDLAS监测模块提供的燃烧室H2O浓度DH2O,t与燃烧室初始状态取数模块存储的H2O浓度DH2O,Z0，以及对比分析TDLAS监测模块提供的燃烧室温度TC,t与燃烧初始状态参数取数模块存储的燃烧室初始温度TC,0，根据燃烧诊断逻辑诊断燃烧室点火状态向燃气轮机控制系统发出燃烧室点火成功和点火失败信息。7. A combustion diagnosis method applicable to a gas turbine according to claim 2, wherein in step 5, the combustion chamber H 2 O concentration D H 2 O , t and the initial state of the combustion chamber are obtained by comparing and analyzing the combustion chamber H 2 O concentration D H 2 O provided by the TDLAS monitoring module. Calculate the H 2 O concentration D H2O,Z0 stored in the data module, and compare and analyze the combustion chamber temperature T C,t provided by the TDLAS monitoring module and the combustion initial state parameters to obtain the combustion chamber initial temperature T C,0 stored by the data module. The logic diagnosis combustor ignition status sends combustor ignition success and ignition failure information to the gas turbine control system. 8.根据权利要求2所述的一种适用于燃气轮机的燃烧诊断方法，其特征在于，步骤6中通过对比分析初始状态取数模块获取的燃烧室的初始温度TC,0、TDLAS监测模块提供的燃烧室温度TC,t与燃烧诊断判据存储模块存储的不同工况下燃烧室燃烧温度的预警值TC,10以及报警值TC,20，根据燃烧诊断逻辑诊断燃烧室温度状态，向燃气轮机控制系统发出燃烧温度正常、燃烧温度高以及燃烧温度超温燃烧状态信息。8. A combustion diagnosis method applicable to a gas turbine according to claim 2, characterized in that in step 6, the initial temperature T C,0 of the combustion chamber, the TDLAS monitoring module obtained by comparative analysis of the initial state fetching module provides The combustion chamber temperature T C,t and the pre-warning value T C,10 and the alarm value T C,20 of the combustion chamber combustion temperature under different working conditions stored in the combustion diagnosis criterion storage module, the combustion chamber temperature state is diagnosed according to the combustion diagnosis logic, Send out the normal combustion temperature, high combustion temperature and over temperature combustion state information to the gas turbine control system. 9.根据权利要求2所述的一种适用于燃气轮机的燃烧诊断方法，其特征在于，步骤7中通过对比分析TDLAS监测模块提供的燃烧室压力脉动频率PHC,t及相应幅值PAC,t和燃烧诊断判据存储模块存储的燃烧室压力基准信息包括不同工况下燃烧室部件的固有声学频率PHC,0、压力脉动幅值和频率的预警值PAC,10和跳机值PAC,20，根据燃烧诊断逻辑诊断燃烧室燃烧稳定性，向燃气轮机控制系统发出燃烧压力脉动稳定、燃烧不稳定预警以及燃烧不稳定跳机燃烧状态信息。9. a kind of combustion diagnosis method that is applicable to gas turbine according to claim 2, is characterized in that, in step 7, by comparatively analyzing the combustion chamber pressure pulsation frequency P HC that TDLAS monitoring module provides, t and corresponding amplitude P AC, The combustion chamber pressure reference information stored by the t and combustion diagnostic criteria storage module includes the natural acoustic frequency P HC,0 of the combustion chamber components under different working conditions, the pre-warning value P AC,10 of the amplitude and frequency of the pressure pulsation and the trip value P AC,20 , according to the combustion diagnosis logic to diagnose the combustion stability of the combustion chamber, and send out the combustion pressure pulsation stability, combustion instability warning and combustion unstable combustion state information to the gas turbine control system. 10.根据权利要求2所述的一种适用于燃气轮机的燃烧诊断方法，其特征在于，适用于燃气轮机的燃烧诊断方法中的燃烧诊断逻辑如下：10. A combustion diagnosis method suitable for a gas turbine according to claim 2, wherein the combustion diagnosis logic in the combustion diagnosis method suitable for a gas turbine is as follows: 若TCt–TC0≥0且DH2O,t–DH2O,0＞0，表明燃烧室内有连续火焰存在，燃烧诊断模块输出燃烧室点火成功和存在连续火焰状态字；If T Ct –T C0 ≥0 and D H2O,t –D H2O,0 > 0, it indicates that there is a continuous flame in the combustion chamber, and the combustion diagnosis module outputs the combustion chamber ignition success and the existence of a continuous flame status word; 若DH2O,t–DH2O,0≤0，表明燃烧室内没有连续火焰存在，燃烧诊断模块输出燃烧室点火失败、不存在连续火焰状态字；If D H2O,t –D H2O,0 ≤0, it means that there is no continuous flame in the combustion chamber, the combustion diagnosis module outputs the combustion chamber ignition failure and no continuous flame status word; 若TC,t－TC,0＞0且TC,t–TC,10＜0,表明燃烧室温度正常，燃烧诊断模块发出燃烧室温度正常状态字；If T C,t - T C,0 > 0 and T C,t - T C,10 < 0, it indicates that the combustion chamber temperature is normal, and the combustion diagnosis module sends out the combustion chamber temperature normal status word; 若TC,t－TC,0＞0且TC,t–TC,10≥0且TC,t–TC,20＜0，表明燃烧室燃烧温度较高已接近燃烧室温度上线，燃烧诊断模块发出燃烧室温度高预警状态字；If T C,t - T C,0 > 0 and T C,t - T C,10 ≥ 0 and T C,t - T C,20 <0, it indicates that the combustion chamber combustion temperature is relatively high and is close to the upper line of the combustion chamber temperature , the combustion diagnosis module sends out the high warning status word of the combustion chamber temperature; 若TC,t－TC,0＞0且TC,t–TC,20≥0，表明燃烧室温度超过燃烧室安全运行范围，燃烧诊断模块发出燃烧超温报警状态字；If T C,t - T C,0 > 0 and T C,t - T C,20 ≥ 0, it indicates that the combustion chamber temperature exceeds the safe operating range of the combustion chamber, and the combustion diagnosis module will issue a combustion over-temperature alarm status word; 若|PHC,t－PHC,0|＜50Hz，表明燃烧室压力脉动频率接近燃烧室固有频率，燃烧室极有可能发生共振，燃烧诊断系统发出燃烧室共振状态字，燃机跳机；If |P HC,t -P HC,0 |＜50Hz, it indicates that the pressure pulsation frequency of the combustion chamber is close to the natural frequency of the combustion chamber, the combustion chamber is very likely to resonate, the combustion diagnosis system sends out the combustion chamber resonance status word, and the combustion engine trips; 若|PHC,t－PHC,0|≥50Hz，且PAC,t－PAC,10＜0，表明燃烧室压力脉动频率和压力脉动幅值均处于燃烧安全稳定范围内，燃烧室燃烧稳定，燃烧诊断模块输出燃烧稳定状态字；If |P HC,t -P HC,0 |≥50Hz, and P AC,t -P AC,10 <0, it means that the pressure pulsation frequency and pressure pulsation amplitude of the combustion chamber are both within the safe and stable range of combustion, and the combustion chamber will burn Stable, the combustion diagnosis module outputs the combustion steady state word; 若|PHC,t－PHC,0|≥50Hz，且PAC,t－PAC,10≥0且PAC,t－PAC,20＜0，表明燃烧室压力脉动频率处于安全范围内，但燃烧室压力脉动幅值接近安全上限，燃烧诊断模块发出燃烧压力脉动预警状态字；If |P HC,t -P HC,0 |≥50Hz, and P AC,t -P AC,10 ≥0 and P AC,t -P AC,20 <0, it indicates that the pressure pulsation frequency of the combustion chamber is within the safe range , but the pressure pulsation amplitude of the combustion chamber is close to the upper limit of safety, and the combustion diagnosis module sends out the combustion pressure pulsation warning status word; 若|PHC,t－PHC,0|≥50Hz，且PAC,t－PAC,20≥0，表明燃烧室压力脉动频率处于安全范围内，但燃烧室压力脉动幅值超过燃烧室压力脉动幅值安全上限，燃烧诊断模块发出燃烧压力脉动高报警状态字。If |P HC,t -P HC,0 |≥50Hz, and P AC,t -P AC,20 ≥0, it indicates that the combustion chamber pressure pulsation frequency is within the safe range, but the combustion chamber pressure pulsation amplitude exceeds the combustion chamber pressure The safe upper limit of the pulsation amplitude, the combustion diagnosis module sends out the high alarm status word of the combustion pressure pulsation.
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CN115962950B (en) * 2022-12-01 2025-07-15 西安热工研究院有限公司 A method and device for determining the acoustic natural frequency of a gas turbine combustion chamber
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CN119492543A (en) * 2024-11-20 2025-02-21 上海交通大学 System and method for detecting forward and reverse switching process of reversible gas turbine
CN120101174A (en) * 2025-05-09 2025-06-06 中国人民解放军海军工程大学 A method and device for rapid detection of combustion oscillation fault

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