EP3225911A1 - Détection de chambre de combustion de la dynamique dans des systèmes de turbine - Google Patents

Détection de chambre de combustion de la dynamique dans des systèmes de turbine Download PDF

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Publication number
EP3225911A1
EP3225911A1 EP16170693.2A EP16170693A EP3225911A1 EP 3225911 A1 EP3225911 A1 EP 3225911A1 EP 16170693 A EP16170693 A EP 16170693A EP 3225911 A1 EP3225911 A1 EP 3225911A1
Authority
EP
European Patent Office
Prior art keywords
measurement values
pilot flow
criterion
minutes
pressure
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP16170693.2A
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German (de)
English (en)
Inventor
Alexey Fishkin
Anthony LATIMER
Adam MARSDEN
Mikhail Roshchin
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG, Siemens Corp filed Critical Siemens AG
Publication of EP3225911A1 publication Critical patent/EP3225911A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M11/00—Safety arrangements
    • F23M11/04—Means for supervising combustion, e.g. windows
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N5/00—Systems for controlling combustion
    • F23N5/16—Systems for controlling combustion using noise-sensitive detectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N5/00—Systems for controlling combustion
    • F23N5/20—Systems for controlling combustion with a time program acting through electrical means, e.g. using time-delay relays
    • F23N5/203—Systems for controlling combustion with a time program acting through electrical means, e.g. using time-delay relays using electronic means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N5/00—Systems for controlling combustion
    • F23N5/24—Preventing development of abnormal or undesired conditions, i.e. safety arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N5/00—Systems for controlling combustion
    • F23N5/18—Systems for controlling combustion using detectors sensitive to rate of flow of air or fuel
    • F23N2005/185—Systems for controlling combustion using detectors sensitive to rate of flow of air or fuel using detectors sensitive to rate of flow of fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2225/00—Measuring
    • F23N2225/04—Measuring pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2231/00—Fail safe
    • F23N2231/10—Fail safe for component failures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2231/00—Fail safe
    • F23N2231/20—Warning devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2241/00—Applications
    • F23N2241/20—Gas turbines

Definitions

  • the present invention relates to the field of monitoring and failure detection in turbine systems, in particular detection of combustion chamber dynamics failures in gas turbine systems.
  • Any gas turbine is instrumented with a large number of sensors which register the most important physical control parameters, e.g., gas flow, pilot split flow and flame pressure frequency bands.
  • the lean main flame is stabilized by a rich and hot pilot flame receiving the pilot split flow.
  • a service engineer monitors the turbine performance. So, in handling a turbine trip (abnormal turbine shutdown), his primal task is to figure out the failure mode (e.g., combustion chamber dynamics), then eliminate the root-cause (e.g., gas/liquid properties, split flow settings or fuel/air ratios) and start the turbine again as soon as possible (e.g., minimizing the outage hours).
  • failure mode e.g., combustion chamber dynamics
  • root-cause e.g., gas/liquid properties, split flow settings or fuel/air ratios
  • Combustion dynamics refers to the combustion process inside the combustion can and liner of the gas turbine.
  • fuel When fuel is burned, there is a pressure increase, and depending on the design of the combustor, the fuel nozzles, the liner, etc., the combustion process can be smooth or it can be subject to pressure oscillations or pulsations. These oscillations or pulsations, if not minimized, can lead to premature failure of combustion components as well as unstable flame.
  • HPCCD High Pressure Combustion Chamber Dynamics
  • the engineer may proceed in two ways:
  • the monitoring engineer is typically responsible for a number of turbines, such as 20 turbines or more. These turbines can be from different vendors, i.e., there may be different "event text" messages meaning the "HPCCD failure". Furthermore, the control system may either not report HPCCD failures in general or recognize HPCCD failures too late, e.g., when the turbine is already tripped due to significant vibrations.
  • the engineer can decide to shutdown the turbine if too many warnings or some critical alerts are issued. In the latter case, some turbine control systems may decide to shutdown the turbine in an automatic way.
  • a method of detecting combustion chamber dynamics in a turbine system comprises (a) obtaining pilot flow measurement values from at least one fuel pilot flow sensor and pressure band measurement values from at least one pressure sensor in at least two distinct pressure bands, (b) checking the pilot flow measurement values against a first criterion and the pressure band measurement values against a second criterion, and (c) detecting combustion chamber dynamics and outputting a warning or an alert if both the pilot flow measurement values and the pressure band measurement values match their respective criteria.
  • the method may rely on measurement data that are already provided by any turbine system (for use in corresponding control systems) and can thus be carried out without the need for any additional measurement hardware or other modifications of the turbine system itself.
  • steps (a), (b) and (c) of the method may be performed by one or more processors such as a microprocessors and/or microcontrollers or any other electric or electronic circuit or application-specific integrated circuit.
  • processors such as a microprocessors and/or microcontrollers or any other electric or electronic circuit or application-specific integrated circuit.
  • individual measurement values from the fuel pilot flow sensor and the pressure sensor can be obtained. That is, individual series of measurement values (e.g. with a predetermined sampling interval, such as 1s, 2s, 5s, 10s, 15s, 20s, 30s, or 60s) can be obtained for the fuel pilot flow sensor and for each pressure band of the pressure sensor.
  • a predetermined sampling interval such as 1s, 2s, 5s, 10s, 15s, 20s, 30s, or 60s
  • the method provides a simple heuristic method which can automatically recognize and report the HPCCD failures.
  • the method and device are simple in formulation and can easily be understood by any engineer.
  • the method is also simple in computation, therefore it can be realized in any modern monitoring system. It enhances the current methods realized in the control systems and can report both early HPCCD warnings as well as critical HPCCD failures. Furthermore, it can be done uniformly for a whole turbine fleet.
  • the method further comprises checking the pilot flow measurement values against the first criterion by calculating a standard deviation of the pilot flow measurement values in a first time interval, the first criterion being fulfilled if the standard deviation remains below a first threshold for a first time period; and checking the pressure band measurement values against the second criterion by calculating standard deviation values for each of the pressure band measurement values in a second time interval and a maximum value as the maximum of the standard deviation values, the second criterion being fulfilled if the maximum value exceeds a second threshold during the first time period.
  • the first time interval, the second time interval and the first time period may in particular constitute so-called moving windows in the sense that the method is performed at regular intervals (for example every minute or every 5 minutes) and that the last x minutes of measurement values preceding the time of performing the method are used.
  • the method further comprises checking the pilot flow measurement values against the first criterion by verifying that the pilot flow measurement values are larger than zero for a first time period, and checking the pressure band measurement values against the second criterion by calculating a maximum value as the maximum of the pressure band measurement values at any given point in time, the second criterion being fulfilled if the maximum value constantly exceeds a second threshold during a second time period.
  • the first time period and the second time period may in particular constitute so-called moving windows in the sense that the method is performed at regular intervals (for example every minute or every 5 minutes) and that the last x minutes of measurement values preceding the time of performing the method are used.
  • the method further comprises checking the pilot flow measurement values against the first criterion by verifying that the pilot flow measurement values are larger than zero for a first time period, and checking the pressure band measurement values against the second criterion by calculating a maximum value as the maximum of the pressure band measurement values at any given point in time, the second criterion being fulfilled if the maximum value exceeds a second threshold at least once during the first time period.
  • This embodiment provides a simple heuristic method based on the maximum function.
  • the method further comprises detecting combustion chamber dynamics and outputting a warning if the pilot flow measurement values and the pressure band measurement values match the criteria according to claim 2, in particular with the first time interval being between 5 and 15 minutes, in particular 10 minutes, the first threshold being between 30 % and 70 %, in particular 50 %, the first time period being between 15 and 45 minutes, in particular 30 minutes, the second time interval being between 2 and 10 minutes, in particular 5 minutes, and the second threshold being between 0.1 and 0.5 psi, in particular 0.2 psi.
  • This embodiment provides a simple heuristic method based on empiric time intervals, i.e., 30 and 10 minutes, and empiric pressure and pilot values. The latter can also be tuned up for a particular turbine type.
  • the method further comprises detecting combustion chamber dynamics and outputting a warning if the pilot flow measurement values and the pressure band measurement values match the criteria according to claim 3, in particular with the first time period being between 15 and 60 minutes, in particular 30 minutes, the second threshold being between 0.5 and 0.9 psi, in particular 0.8 psi, and the second time period being between 5 and 15 minutes, in particular 10 minutes.
  • This embodiment provides a simple heuristic method based on empiric time intervals, i.e., 30 and 10 minutes, and empiric pressure values, i.e. 0.8 psi.
  • empiric time intervals i.e. 30 and 10 minutes
  • empiric pressure values i.e. 0.8 psi.
  • the latter can also be tuned up for a particular turbine type.
  • the method further comprises detecting combustion chamber dynamics and outputting a warning if the pilot flow measurement values and the pressure band measurement values match the criteria according to claim 4, in particular with the first time period being between 15 and 60 minutes, in particular 30 minutes, and the second threshold being 1.0 psi.
  • This embodiment provides a simple heuristic method based on empiric time intervals, i.e., 30 minutes, and empiric pressure values, i.e. 1.0 psi.
  • empiric time intervals i.e., 30 minutes
  • empiric pressure values i.e. 1.0 psi.
  • the latter can also be tuned up for a particular turbine type.
  • the method further comprises detecting combustion chamber dynamics and outputting an alert if the pilot flow measurement values and the pressure band measurement values match the criteria according to claim 4, in particular with the first time period being between 15 and 60 minutes, in particular 30 minutes, and the second threshold being 1.4 psi.
  • This embodiment provides a simple heuristic method based on empiric time intervals, i.e., 30 minutes, and empiric pressure values, i.e. 1.4 psi.
  • empiric time intervals i.e., 30 minutes
  • empiric pressure values i.e. 1.4 psi.
  • the latter can also be tuned up for a particular turbine type.
  • a device for detecting combustion chamber dynamics in a turbine system comprises (a) a unit for obtaining individual pilot flow measurement values from at least one fuel pilot flow sensor, (b) a unit for obtaining individual pressure band measurement values from at least one pressure sensor in at least two distinct pressure bands, (c) a unit for checking the pilot flow measurement values against a first criterion, (d) a unit for checking the pressure band measurement values against a second criterion, and (e) a unit for detecting combustion chamber dynamics and outputting a warning or an alert if both the pilot flow measurement values and the pressure band measurement values match their respective criteria.
  • the second aspect of the invention is based on the same idea as the first aspect described above and provides a device capable of performing the methods according to the first aspect and the above embodiments thereof.
  • a single unit may represent several or all of the units (a) to (e).
  • the units may be one or more processors such as a microprocessors and/or microcontrollers or any other electric or electronic circuit or application-specific integrated circuit.
  • a system for monitoring a plurality of turbine systems each turbine system comprising at least one fuel pilot flow sensor and at least one pressure sensor, the monitoring system comprising (a) a communication unit for receiving measurement values from the fuel pilot flow sensor and pressure sensor of each turbine system, (b) a storage unit for storing the received measurement values, and (c) a processing unit for performing the method according to the first aspect of the invention on the stored data for each turbine system.
  • the third aspect of the invention is based on the idea that the simple method of detecting combustion chamber dynamics according to the first aspect may be used in a system for monitoring several turbine systems.
  • the measurement values from each of the turbine systems are received via a communication unit (e.g. a communication network) and stored in a storage unit for processing by a processing unit.
  • a communication unit e.g. a communication network
  • the processing unit may be one or more processors such as a microprocessors and/or microcontrollers or any other electric or electronic circuit or application-specific integrated circuit.
  • system according to the third aspect of the invention may be implemented at a plant with several turbine systems or at a remote location. In both cases, it may collect measurement data from several plants.
  • the system further comprises a notification unit transmitting a notification message to an operator of a turbine system if the processing unit has detected combustion chamber dynamics in the turbine system.
  • the notification unit transmits a notification message to the operator of the relevant turbine system in case of combustion chamber dynamics, such that the operator can take the necessary action.
  • the notification message may contain various information, such as a turbine ID, a pressure sensor ID, the time of detecting the error, etc.
  • a computer program comprising computer executable instructions, which, when executed by a processor, causes the processor to perform the steps of the method according to the first aspect or any of the above embodiments.
  • the computer program may be installed on a suitable computer system to enable performance of the methods described above.
  • a computer readable data carrier loaded with the computer program according to the fourth aspect.
  • Figure 1 shows a flowchart of a method 100 of detecting combustion chamber dynamics in a turbine system according to an embodiment of the invention.
  • the turbine system i.e. a gas turbine, comprises at least one fuel pilot flow sensor and at least one pressure sensor, the latter providing individual measurement values in at least two distinct pressure bands.
  • the fuel pilot flow sensor may be a sensor measuring the opening of a valve for the fuel pilot flow in percent. It may also be a virtual sensor using the current control setpoint for that valve as its virtual measurement value. Furthermore, the valve may be splitting fuel between pilot and main. In that case, the fuel pilot flow sensor measures the percentage of fuel being delivered to the pilot.
  • the pressure sensor can give a signal based on a change in pressure on its surface using acoustic dynamics pressure tapping.
  • the pressure tapping can be taken in the combustion cans and/or the centre casing.
  • the pressure sensor measures dynamics in three to four pressure bands.
  • the frequency ranges of the pressure bands depend on the specific turbine type. For example, a first pressure band may be in the range of 20-55 Hz, a second pressure band in the range of 140-200 Hz, and a third pressure band in the range of 280-405 Hz.
  • the method may be using two, three, four or more pressure bands.
  • the method 100 begins at step 1 where individual pilot flow measurement values as well as individual pressure band measurement values in at least two distinct pressure bands are obtained from the respective sensors.
  • the measurement values from each sensor typically have the form of a series of measurement values (or samples) separated in time by a predetermined amount, such as 1 second or 1 minute.
  • step 2 it is determined whether pilot flow measurement values match a first criterion and whether the pressure band measurement values match a second criterion.
  • pilot flow measurement values and the pressure band measurement values do not both match their respective criteria, the turbine is deemed to be working without combustion chamber dynamics and the method 100 returns to step 1.
  • step 3 combustion chamber dynamics are detected in step 3 and the method 100 proceeds to step 4, where measures are taken to notify the operator of the turbine system of the combustion chamber dynamics, e.g. by activating an alarm, sending a message, or in any other suitable manner. Thereafter, the method returns to step 1.
  • #"PILOT denote the pilot flow measurement values and #"BAND1", #"BAND2", #"BAND3" the individual pressure band measurement values obtained in three distinct pressure bands.
  • a warning "Warning: unstable CCD” is issued if sd(#"PILOT",10m) ⁇ 50 % holds true for a duration at least 30 minutes and max( sd(#"BAND1", 5m), sd(#"BAND2", 5m), sd(#"BAND3", 5m) ) > 0.2 holds true at least once.
  • the first embodiment checks for a condition when the fuel pilot flow is stable for at least 10 minutes whilst the pressure in any of the bands gets unstable.
  • a warning "Warning: HPCCD Level 0.8 psi for 10 min” is issued if #"PILOT" > 0 holds true for a duration at least 30 minutes and max(#"BAND1",#"BAND2",#”BAND3") > 0.8 holds true for a duration at least 10 minutes.
  • the second embodiment checks for a condition when the turbine already runs for at least 30 minutes whilst the pressure in any band constantly exceeds 0.8 psi for at least of 10 minutes.
  • the first two embodiments enhance the standard HPCCD conditions with the two first "early" warnings which give indications that some critical HPCCD may happen in the near future. So, the monitoring engineer has enough time to make required corrections without shutting down the running turbine, i.e., adjust the pilot flow (split ratio), change the fuel type and so on.
  • a warning "Warning: HPCCD Level 1.0 psi" is issued if #"PILOT" > 0 holds true for a duration at least 30 minutes and max(#"BAND1",#"BAND2",#"BAND3") > 1.0 holds true at least once.
  • the third embodiment checks for a condition when the turbine already runs for at least 30 minutes whilst the pressure in any band suddenly exceeds 1.0 psi.
  • an alert "Alert: HPCCD Level 1.4 psi” is issued if #"PILOT" > 0 holds true for a duration at least 30 minutes and max(#"BAND1",#"BAND2",#"BAND3") > 1.4 holds true at least once.
  • the embodiment checks for a condition when the turbine already runs for at least 30 minutes whilst the pressure in any band suddenly exceeds 1.4 psi.
  • FIG. 2 shows a block diagram of a monitoring system according to an embodiment of the invention.
  • the shown system comprises a monitoring device (or monitoring station) 205, a first turbine plant 210, a second turbine plant 220, and a third turbine plant 230.
  • the first turbine plant comprises a controller C1 and three turbine systems T11, T12 and T13.
  • the controller C1 is in communication with the turbines T11, T12 and T13 and receives measurement values from sensors in each turbine T11, T12, T13 and transmits control signals to the turbines T11, T12 and T13.
  • the second turbine plant 220 comprises a controller C2 and three turbine systems T21, T22 and T23
  • the third turbine plant 230 comprises a controller C3 and four turbine systems T31, T32, T33, and T34.
  • more turbine plants may be added and the number of turbine systems per plant may vary from what is shown in Figure 2 .
  • the device 205 is in communication with each of the turbine plants 210, 220 and 230 via a communication unit, such as a network interface, and receives the measurement values collected by the respective controllers C1, C2 and C3, preferably in a continuous manner.
  • the received measurement values are stored in a suitable storage unit and processed in accordance with the method described above in conjunction with Figure 1 . If the processing reveals combustion chamber dynamics in one of the turbine systems T11, T12, T13, T21, T22, T23, T31, T32, T33, T34, a notification unit transmits a corresponding notification message to the operator of the relevant turbine plant 210, 220, 230, such that proper action can be taken, e.g. adjusting the pilot flow (split ratio).
  • the plant operator can rely on being notified in case of combustion chamber dynamics in one of the plant turbines. Thereby, the cumbersome labor associated with the study of printed curves or unreliable messages from the controllers C1, C2, C3 is no longer necessary.
  • the turbine data therefore can be stored on a central server in a remote diagnostic center.
  • a diagnostic engineer can browse the sensor data along with the events from the control system.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Testing And Monitoring For Control Systems (AREA)
EP16170693.2A 2016-03-31 2016-05-20 Détection de chambre de combustion de la dynamique dans des systèmes de turbine Withdrawn EP3225911A1 (fr)

Applications Claiming Priority (1)

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EP16163232 2016-03-31

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Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2004204780A (ja) * 2002-12-25 2004-07-22 Mitsubishi Heavy Ind Ltd ガスタービン異常監視装置及び異常監視方法
JP2007192138A (ja) * 2006-01-19 2007-08-02 Mitsubishi Heavy Ind Ltd ガスタービンにおける異常監視方法及び装置

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2004204780A (ja) * 2002-12-25 2004-07-22 Mitsubishi Heavy Ind Ltd ガスタービン異常監視装置及び異常監視方法
JP2007192138A (ja) * 2006-01-19 2007-08-02 Mitsubishi Heavy Ind Ltd ガスタービンにおける異常監視方法及び装置

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