Gas turbine control apparatus, gas turbine system and gas turbine control method

• US 20050107942A1
• Filed: 08/31/2004
• Published: 05/19/2005
• Est. Priority Date: 10/30/2003
• Status: Active Grant

• Current Assignee: Mitsubishi Power Limited (Mitsubishi Heavy Industries, Ltd.)
• Original Assignee: Mitsubishi Heavy Industries, Ltd.
• Inventors: Nomura, Masumi, Kawakami, Tomo, Iba, Hiroyuki, Toyama, Kozo
• Granted Patent: US 7,188,019 B2
• Time in Patent Office: Days
• US Class Current: 701/100
• CPC Class Codes: F02C 9/28 Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed F02C9/30 - F02C9/38, F02C9/44 take precedence
• CPC Class Codes: F05D 2270/083 by monitoring combustion conditions
• CPC Class Codes: F05D 2270/301 Pressure

Abstract

A gas turbine control apparatus, etc. are provided by which combustion fluctuation, even if arising in plural frequency bands, can be effectively suppressed. If the combustion fluctuation arises in plural frequency bands, corresponding to a predetermined priority order, adjustment is done so that the combustion fluctuation of the frequency band of a high priority order is suppressed. If the gas turbine state changes after the adjustment, this is reflected on a data base 30. If no sufficient data is stored yet in the data base 30 for any the reason, such as immediately after installation of the gas turbine, correction is made using data of countermeasures based on data of another same type gas turbine contained in a basic data base 31 and data of countermeasures based on experiences of skilled adjusting operators contained in a knowledge data base 32. Also, in a stabilized operation, operation condition may be varied so that an optimal operation condition is automatically searched.

Claims

1. A gas turbine control apparatus comprising:

a frequency analyzing portion carrying out a frequency analysis of fluctuation of pressure or acceleration in a combustor of a gas turbine and putting out an analysis result divided into frequency bands in which the result of said frequency analysis is divided into a plurality of frequency bands,

a priority order information containing portion containing information on a priority order set for said plurality of frequency bands,

a combustion characteristic grasping portion grasping a characteristic of combustion fluctuation of said gas turbine, based on said analysis result divided into frequency bands and process data of said gas turbine, and

a control portion adjusting at least one of a flow rate of fuel and a flow rate of air to be supplied into said combustor so that the combustion fluctuation of a frequency band of a high priority order is suppressed, based on the information on said priority order contained in said priority order information containing portion, when said combustion characteristic grasping portion grasps that the combustion fluctuation arises in a plurality of frequency bands.

2. A gas turbine control apparatus as claimed in claim 1, wherein, when said control portion adjusts at least one of the flow rate of fuel and the flow rate of air to be supplied into said combustor, said control portion stores in a data base contents of the adjustment and information related with changes in a combustion state in said combustor as the result of the adjustment.

3. A gas turbine control apparatus as claimed in claim 2, wherein said gas turbine control apparatus further comprises a basic data base in which information obtained by an analysis based on said information stored in said data base in another gas turbine is contained and said control portion adjusts at least one of the flow rate of fuel and the flow rate of air to be supplied into said combustor, based on said information obtained by the analysis and contained in said basic data base.

4. A gas turbine control apparatus as claimed in claim 1, wherein said gas turbine control apparatus further comprises a turbine abnormality detecting portion detecting an abnormality of said gas turbine and, when said turbine abnormality detecting portion detects an abnormality of said gas turbine, said control portion carries out no adjustment but notifies outside that there arises an abnormality.

5. A gas turbine control apparatus as claimed in claim 1, wherein said gas turbine control apparatus further comprises a sensor detecting the fluctuation of pressure or acceleration in said combustor and a sensor abnormality detecting portion detecting an abnormality of said sensor and, when said sensor abnormality detecting portion detects an abnormality of said sensor, said control portion carries out no adjustment but notifies outside that there arises an abnormality.

6. A gas turbine control apparatus as claimed in claim 1, wherein said control portion corrects contents of the adjustment made for at least one of the flow rate of fuel and the flow rate of air to be supplied into said combustor, based on a composition of the fuel to be supplied into said combustor.

7. A gas turbine system comprising:

a gas turbine containing a combustor,

a frequency analyzing portion carrying out a frequency analysis of fluctuation of pressure or acceleration in said combustor and putting out an analysis result divided into frequency bands in which the result of said frequency analysis is divided into a plurality of frequency bands,

a priority order information containing portion containing information on a priority order set for said plurality of frequency bands,

a combustion characteristic grasping portion grasping a characteristic of combustion fluctuation of said gas turbine, based on said analysis result divided into frequency bands and process data of said gas turbine, and

a control portion adjusting at least one of a flow rate of fuel and a flow rate of air to be supplied into said combustor so that the combustion fluctuation of a frequency band of a high priority order is suppressed, based on the information on said priority order contained in said priority order information containing portion, when said combustion characteristic grasping portion grasps that the combustion fluctuation arises in a plurality of frequency bands.

8. A gas turbine control method comprising:

a step of carrying out a frequency analysis of fluctuation of pressure or acceleration in a combustor of a gas turbine and putting out an analysis result divided into frequency bands in which the result of said frequency analysis is divided into a plurality of frequency bands,

a step of grasping a characteristic of combustion fluctuation of said gas turbine, based on said analysis result divided into frequency bands and process data of said gas turbine, and

a step of adjusting at least one of a flow rate of fuel and a flow rate of air to be supplied into said combustor so that the combustion fluctuation of a frequency band of a high priority order is suppressed, based on a predetermined priority order, when the combustion fluctuation arises in a plurality of frequency bands.

9. A gas turbine control apparatus comprising:

a frequency analyzing portion carrying out a frequency analysis of fluctuation of pressure or acceleration in a combustor of a gas turbine and putting out an analysis result divided into frequency bands in which the result of said frequency analysis is divided into a plurality of frequency bands,

a combustion characteristic grasping portion grasping a characteristic of combustion fluctuation of said gas turbine, based on said analysis result divided into frequency bands and process data of said gas turbine,

a control portion adjusting at least one of a flow rate of fuel and a flow rate of air to be supplied into said combustor so that the combustion fluctuation is suppressed, when said combustion characteristic grasping portion grasps that the combustion fluctuation arises, and

a search and control portion searching an optimal operation condition by varying at least one of the flow rate of fuel and the flow rate of air to be supplied into said combustor in the state that said control portion is not carrying out an adjustment to suppress the combustion fluctuation and, corresponding to said optimal operation condition obtained, adjusting at least one of the flow rate of fuel and the flow rate of air to be supplied into said combustor.

10. A gas turbine control apparatus as claimed in claim 9, wherein said search and control portion decides said optimal operation condition as an operation condition in which a stability against the combustion fluctuation is highest.

11. A gas turbine control apparatus as claimed in claim 9, wherein said search and control portion searches said optimal operation condition by evaluating a thermal efficiency of said gas turbine in addition to the stability against the combustion fluctuation.

12. A gas turbine control apparatus as claimed in claim 9, wherein said search and control portion varies at least one of the flow rate of fuel and the flow rate of air to be supplied into said combustor based on a predetermined profile.

13. A gas turbine control apparatus as claimed in claim 12, wherein, when said search and control portion varies at least one of the flow rate of fuel and the flow rate of air to be supplied into said combustor based on said profile, said search and control portion predicts whether the combustion fluctuation may arise or not and, if it is so predicted that the combustion fluctuation may arise, said search and control portion stops to vary at least one of the flow rate of fuel and the flow rate of air to be supplied into said combustor.

14. A gas turbine control apparatus as claimed in claim 9, wherein, if the combustion fluctuation arises as the result of said search and control portion varying at least one of the flow rate of fuel and the flow rate of air to be supplied into said combustor, said search and control portion stops to vary at least one of the flow rate of fuel and the flow rate of air to be supplied into said combustor.

15. A gas turbine control apparatus as claimed in claim 14, wherein, if the combustion fluctuation arises as the result of said search and control portion varying at least one of the flow rate of fuel and the flow rate of air to be supplied into said combustor, said control portion adjusts at least one of the flow rate of fuel and the flow rate of air to be supplied into said combustor so that the combustion fluctuation is suppressed.

16. A gas turbine system comprising:

a gas turbine containing a combustor and

a search and control portion searching an optimal operation condition by varying at least one of a flow rate of fuel and a flow rate of air to be supplied into said combustor in the state that there is no combustion fluctuation in said gas turbine and, corresponding to said optimal operation condition obtained, adjusting at least one of the flow rate of fuel and the flow rate of air to be supplied into said combustor.

17. A gas turbine system as claimed in claim 16, wherein said search and control portion searches an optimal operation condition at the time of start or stop of said gas turbine by varying at least one of the flow rate of fuel and the flow rate of air to be supplied into said combustor on each time of the start or stop of said gas turbine as well as by carrying out the start or stop with a plurality of times.

18. A gas turbine control method comprising:

a result putting out step carrying out a frequency analysis of fluctuation of pressure or acceleration in a combustor of a gas turbine and putting out an analysis result thereof,

a characteristic grasping step grasping a characteristic of combustion fluctuation of said gas turbine, based on said analysis result and process data of said gas turbine,

a fluctuation suppressing step adjusting at least one of a flow rate of fuel and a flow rate of air to be supplied into said combustor so that the combustion fluctuation is suppressed, if the combustion fluctuation arises as the result of said characteristic grasping step grasping the characteristic of the combustion fluctuation of said gas turbine, and

a condition searching step searching an optimal operation condition by varying at least one of the flow rate of fuel and the flow rate of air to be supplied into said combustor in the state that said fluctuation suppressing step is not being carried out and, corresponding to said optimal operation condition obtained, adjusting at least one of the flow rate of fuel and the flow rate of air to be supplied into said combustor.