KR102259880B1 - Apparatus and method for the automatic tuning of gas turbine combustion system - Google Patents

Abstract

Provided is an apparatus for automatic tuning of a gas turbine combustion system. The apparatus comprises: a measurement unit for extracting combustion vibration values of a plurality of bands measured from a combustor of a gas turbine combustion system; a determination unit for determining whether at least one of the combustion vibration values of the plurality of bands is equal to or greater than a preset reference value; and a control unit. If, as a result of the determination, at least one combustion vibration value among the combustion vibration values of each of the plurality of bands is equal to or greater than a preset reference value, the control unit controls the gas turbine combustion system including the combustor so that all the combustion vibration values of the plurality of bands are less than the reference value.

Description

Apparatus and method for the automatic tuning of gas turbine combustion system

TECHNICAL FIELD The present invention relates to auto-tuning technology, and more particularly, to an apparatus and method for auto-tuning a gas turbine combustion system.

A gas turbine is a power engine that mixes and burns compressed air and fuel compressed in a compressor, and rotates the turbine with high-temperature gas generated by combustion. Gas turbines are used to power generators, aircraft, ships, trains, and the like.

A gas turbine generally includes a compressor, a combustor and a turbine. The compressor sucks in the outside air, compresses it, and delivers it to the combustor. The compressed air in the compressor is in a state of high pressure and high temperature. The combustor mixes and combusts the compressed air and fuel introduced from the compressor. The combustion gases generated by the combustion are discharged to the turbine. The combustion gas causes the turbine blades inside the turbine to rotate, which in turn generates power. The generated power is used in various fields such as power generation and driving of mechanical devices.

Korean Patent Publication No. 2010-0126773 published on December 02, 2010 (Title: Gas turbine control method and apparatus)

SUMMARY OF THE INVENTION It is an object of the present invention to provide an apparatus and method for automatic tuning of a gas turbine combustion system.

An apparatus for automatic tuning of a gas turbine combustion system is provided. The apparatus includes a measurement unit for extracting combustion vibration values of a plurality of bands measured from a combustor of a gas turbine combustion system, and determining whether at least one combustion vibration value among the combustion vibration values of a plurality of bands is greater than or equal to a preset reference value A gas including a determination unit, and the combustor so that all of the combustion vibration values of the plurality of bands are less than the reference value when at least one of the combustion vibration values of each of the plurality of bands is greater than or equal to the preset reference value as a result of the determination a control unit for controlling the turbine combustion system.

The measurement unit is characterized in that the measured combustion vibration values of the plurality of bands are normalized through threshold values of the combustion vibration values of the plurality of bands.

와 같이 대역 별로 정규화하여 정규화된 연소진동값을 도출하며, 상기 x는 대역 인덱스이고, 상기 bin은 연소진동값이고, 상기 binx는 대역 x의 연소진동값을 나타내고, 상기 threshold는 연소진동값의 임계치이며, 상기 thresholdx는 x 대역의 연소진동값 임계치를 나타낸다. The measurement unit is

Normalized for each band to derive a normalized combustion vibration value, where x is a band index, the bin is a combustion vibration value, binx represents a combustion vibration value of a band x, and the threshold is a threshold value of the combustion vibration value. , and the thresholdx represents a threshold value of the combustion vibration value of the x band.

에 따라 상기 복수의 대역의 연소진동값 중 적어도 하나가 기준치 이상인지 여부를 판단하고, 상기 bin1, 상기 bin2, 상기 bin3, 상기 bin4, 상기 bin5 및 상기 bin6은 각각 제1 내지 제6 대역의 연소진동값이고, 상기 threshold1, 상기 threshold2, 상기 threshold3, 상기 threshold4, 상기 threshold5, 상기 threshold6은 각각 제1 내지 제6 대역의 연소진동값의 임계치인 것을 특징으로 한다. The determination unit is

to determine whether at least one of the combustion vibration values of the plurality of bands is equal to or greater than a reference value, and the bin1, the bin2, the bin3, the bin4, the bin5, and the bin6 are the combustion vibrations of the first to sixth bands, respectively. values, and the threshold1, the threshold2, the threshold3, the threshold4, the threshold5, and the threshold6 are threshold values of combustion vibration values of the first to sixth bands, respectively.

에 따라 제1 대역의 연소진동값이 기준치 이상인지 여부를 판단하며, 상기 bin1은 제1 대역의 연소진동값이고, 상기 threshold1은 제1 대역의 연소진동값의 임계치인 것을 특징으로 한다. The determination unit is

, it is determined whether the combustion vibration value of the first band is equal to or greater than a reference value, wherein bin1 is the combustion vibration value of the first band, and the threshold1 is a threshold value of the combustion vibration value of the first band.

When the combustion vibration value of the first band is equal to or greater than a reference value, the controller increases the pilot fuel nozzle distribution ratio so that the combustion vibration value of the first band is less than the reference value.

에 따라 제6 대역의 연소진동값이 기준치 이상인지 여부를 판단하며, 상기 bin6은 제6 대역의 연소진동값이고, 상기 threshold6은 제6 대역의 연소진동값의 임계치인 것을 특징으로 한다. The determination unit is

, it is determined whether the combustion vibration value of the sixth band is equal to or greater than a reference value, wherein bin6 is the combustion vibration value of the sixth band, and the threshold6 is a threshold value of the combustion vibration value of the sixth band.

When the normalized combustion vibration value of the sixth band is equal to or greater than a reference value, the control unit controls at least one of a total fuel amount, fuel temperature, and an inlet guide vane (IGV) opening degree such that the combustion vibration value of the sixth band is less than the reference value. characterized in that

An apparatus for automatic tuning of a gas turbine combustion system is provided. The apparatus includes a compressor for compressing injected air, a combustor for burning the compressed air supplied from the compressor and injected fuel to discharge combustion gas, and a plurality of turbine blades rotated by the combustion gas. A gas turbine to produce, a measurement unit for extracting combustion vibration values of a plurality of bands measured from the combustor, and a determination to determine whether at least one of the combustion vibration values of the plurality of bands is equal to or greater than a preset reference value And, as a result of the determination, if at least one of the combustion vibration values of each of the plurality of bands is equal to or greater than a preset reference value, a gas turbine including the combustor so that all of the combustion vibration values of the plurality of bands are less than the reference value. a control unit for controlling the combustion system.

The measurement unit is characterized in that the measured combustion vibration values of the plurality of bands are normalized through threshold values of the combustion vibration values of the plurality of bands.

와 같이 대역 별로 정규화하여 정규화된 연소진동값을 도출하며, 상기 x는 대역 인덱스이고, 상기 bin은 연소진동값이고, 상기 binx는 대역 x의 연소진동값을 나타내고, 상기 threshold는 연소진동값의 임계치이며, 상기 thresholdx는 x 대역의 연소진동값 임계치를 나타내는 것을 특징으로 한다. The measurement unit is

Normalized for each band to derive a normalized combustion vibration value, where x is a band index, the bin is a combustion vibration value, binx represents a combustion vibration value of a band x, and the threshold is a threshold value of the combustion vibration value. , and the thresholdx is characterized in that it represents the combustion vibration value threshold of the x band.

에 따라 복수의 대역의 정규화된 연소진동값 중 적어도 하나가 기준치 이상인지 여부를 판단하고, 상기 bin1, 상기 bin2, 상기 bin3, 상기 bin4, 상기 bin5 및 상기 bin6은 각각 제1 내지 제6 대역의 연소진동값이고, 상기 threshold1, 상기 threshold2, 상기 threshold3, 상기 threshold4, 상기 threshold5, 상기 threshold6은 각각 제1 내지 제6 대역의 연소진동값의 임계치인 것을 특징으로 한다. The determination unit is

determines whether at least one of the normalized combustion vibration values of a plurality of bands is equal to or greater than a reference value, and the bin1, the bin2, the bin3, the bin4, the bin5, and the bin6 are the combustion of the first to sixth bands, respectively. is a vibration value, and the threshold1, the threshold2, the threshold3, the threshold4, the threshold5, and the threshold6 are threshold values of combustion vibration values of the first to sixth bands, respectively.

The determination unit determines whether the combustion vibration value of the first band is equal to or greater than a reference value, and as a result of the determination, if the combustion vibration value of the first band is equal to or greater than the reference value, the control unit determines that the combustion vibration value of the first band is less than the reference value It is characterized in that the pilot fuel nozzle distribution ratio is increased so as to become this.

The determination unit determines whether the combustion vibration value of the sixth band is equal to or greater than a reference value, and if the combustion vibration value of the sixth band is equal to or greater than the reference value, the control unit determines whether the combustion vibration value of the sixth band is less than the reference value. It is characterized in that at least one of a fuel amount, a fuel temperature, and an IGV (Inlet Guide Vane) opening amount is controlled.

A method for automatic tuning of a gas turbine combustion system is provided. The method includes extracting, by the measuring unit, combustion vibration values of a plurality of bands measured from the combustor of the gas turbine combustion system, and whether at least one combustion vibration value among the combustion vibration values of the plurality of bands by the determining unit is greater than or equal to a preset reference value and, as a result of the determination, if at least one combustion vibration value among the combustion vibration values of each of the plurality of bands is equal to or greater than a preset reference value, the controller controls all of the combustion vibration values of the plurality of bands to be less than the reference value. and controlling a gas turbine combustion system comprising:

After the extracting step, before the determining step, the method further includes normalizing the combustion vibration values of the plurality of bands measured by the measurement unit through the threshold values of the combustion vibration values of the plurality of bands.

에 따라 정규화하여 정규화된 연소진동값을 도출하며, 상기 x는 대역 인덱스이고, 상기 bin은 연소진동값이고, 상기 binx는 대역 x의 연소진동값을 나타내고, 상기 threshold는 연소진동값의 임계치이며, 상기 thresholdx는 x 대역의 연소진동값 임계치를 나타낸다. The measurement unit calculates the combustion vibration value by the equation

Normalized to derive a normalized combustion vibration value, wherein x is the band index, the bin is the combustion vibration value, the binx represents the combustion vibration value of the band x, and the threshold is the threshold value of the combustion vibration value, The thresholdx represents a combustion vibration value threshold in the x band.

에 따라 복수의 대역의 연소진동값 중 적어도 하나가 기준치 이상인지 여부를 판단하며, 상기 bin1, 상기 bin2, 상기 bin3, 상기 bin4, 상기 bin5 및 상기 bin6은 각각 제1 내지 제6 대역의 연소진동값이고, 상기 threshold1, 상기 threshold2, 상기 threshold3, 상기 threshold4, 상기 threshold5, 상기 threshold6은 각각 제1 내지 제6 대역의 연소진동값의 임계치인 것을 특징으로 한다. In the determining step, the determination unit is

determines whether at least one of the combustion vibration values of a plurality of bands is equal to or greater than a reference value, and the bin1, the bin2, the bin3, the bin4, the bin5, and the bin6 are the combustion vibration values of the first to sixth bands, respectively. and the threshold1, the threshold2, the threshold3, the threshold4, the threshold5, and the threshold6 are threshold values of combustion vibration values of the first to sixth bands, respectively.

After the determining, the determining unit determines whether the combustion vibration value of the first band is equal to or greater than a reference value, and as a result of the check, if the combustion vibration value of the first band is equal to or greater than the reference value, the control unit controls the first The method further includes increasing the pilot fuel nozzle distribution ratio so that the combustion vibration value of the band becomes less than the reference value.

After the checking, if the combustion vibration value of the first band is less than the reference value as a result of the checking, determining, by the determination unit, whether the combustion vibration value of the sixth band is equal to or greater than the reference value; When the combustion vibration value of the sixth band is equal to or greater than the reference value, controlling at least one of the total fuel amount, fuel temperature, and IGV (Inlet Guide Vane) opening degree so that the combustion vibration value of the sixth band is less than the reference value. include

According to the present invention, combustion tuning can be performed quickly without prioritizing a specific fuel nozzle control according to each band of combustion vibration.

1 is a block diagram for explaining the configuration of a gas turbine combustion system according to an embodiment of the present invention.
2 and 3 are diagrams for explaining the configuration of a fuel nozzle according to an embodiment of the present invention.
4 is a block diagram for explaining a detailed configuration of a control device of a gas turbine combustion system according to an embodiment of the present invention.
5 is a view for explaining a method of measuring combustion vibration according to an embodiment of the present invention.
6 is a flowchart illustrating a method for automatic tuning of a gas turbine combustion system according to an embodiment of the present invention.
7 is a diagram illustrating a computing device according to an embodiment of the present invention.

Since the present invention can apply various transformations and can have various embodiments, specific embodiments are illustrated and described in detail in the detailed description. However, this is not intended to limit the present invention to specific embodiments, and it should be understood to include all modifications, equivalents and substitutes included in the spirit and scope of the present invention.

The terms used in the present invention are only used to describe specific embodiments, and are not intended to limit the present invention. The singular expression includes the plural expression unless the context clearly dictates otherwise. In the present invention, terms such as 'comprise' or 'have' are intended to designate that the features, numbers, steps, operations, components, parts, or combinations thereof described in the specification exist, but one or more other features It should be understood that this does not preclude the existence or addition of numbers, steps, operations, components, parts, or combinations thereof.

First, a configuration of a gas turbine combustion system according to an embodiment of the present invention will be described. 1 is a block diagram for explaining the configuration of a gas turbine combustion system according to an embodiment of the present invention. 2 and 3 are diagrams for explaining the configuration of a fuel nozzle according to an embodiment of the present invention. 4 is a block diagram illustrating a detailed configuration of a control device of a gas turbine combustion system according to an embodiment of the present invention. And FIG. 5 is a view for explaining a method of measuring combustion vibration according to an embodiment of the present invention.

First, referring to FIG. 1 , a combustion system according to an embodiment of the present invention includes a combustion device 100 and a tuning device 200 . The thermodynamic cycle of the combustion device 100 ideally follows the Brayton cycle. The Brayton cycle consists of four processes: isentropic compression (adiabatic compression), static pressure rapid heat, isentropic expansion (adiabatic expansion), and static pressure dissipation. In other words, it sucks air from the atmosphere, compresses it to a high pressure, burns fuel in a static pressure environment to release thermal energy, expands this hot combustion gas to convert it into kinetic energy, and then releases the exhaust gas containing the remaining energy into the atmosphere. . That is, the cycle consists of four processes: compression, heating, expansion, and heat dissipation.

The combustion apparatus 100 includes a compressor 110 , a combustor 120 , and a turbine 130 . The compressor 110 of the combustion device 100 is a part that sucks air and compresses it, and while supplying the combustion air to the combustor 120 , the cooling air in the high temperature region requiring cooling in the combustion device 100 . Its main role is to provide Since the sucked air undergoes an adiabatic compression process in the compressor 110 , the pressure and temperature of the air passing through the compressor 110 are increased.

The compressor 110 included in the combustion device 100 may be designed as centrifugal compressors or axial compressors, but the embodiment of the present invention will be described with an example of an axial compressor.

The compressor 110 compresses air introduced from the outside and supplies it to the combustor 120 . The amount of air introduced into the compressor 110 is adjusted according to the opening/closing amount of the first valve V1. The compressor 110 is driven using a part of the power output from the turbine 130 . To this end, the rotation shaft of the compressor 110 and the rotation shaft of the turbine 130 are directly connected. A portion of the output produced by the turbine 130 is consumed to drive the compressor 110 . Accordingly, improving the efficiency of the compressor 110 has a direct and profound effect on improving the overall efficiency of the combustion device 100 .

The combustor 120 mixes the compressed air supplied from the outlet of the compressor 110 with fuel and performs isostatic combustion to produce combustion gas of high energy. At this time, the combustor 120 mixes the compressed air compressed in the compressor 110 with the fuel injected and burns it, and discharges the combustion gas generated through such combustion. The amount of fuel injected into the combustor 120 may be adjusted according to the opening/closing amount of the second valve V2.

The combustor 120 is disposed downstream of the compressor 110 , and a plurality of burners 122 are disposed. 2 is a cross-sectional view of a combustion chamber 124 including a plurality of fuel nozzles 123 . 3 is a plan view of the fuel nozzle 123 viewed in the direction A in FIG. 2 . As shown, a plurality of fuel nozzles 123 (FC1, FC2, FC3, FCP, FCQ) are shown.

2 and 3 , each burner 122 is provided with a plurality of fuel nozzles 123: FC1, FC2, FC3, FCP, and FCQ, and a plurality of fuel nozzles 123: FC1, FC2, FC3. , FCP, FCQ) is mixed with air in an appropriate ratio to achieve a state suitable for combustion. Referring to FIGS. 2 and 3 , compressed air enters the combustion chamber 124 after being mixed with the fuel injected from the fuel nozzle 123 . The initial ignition of the mixed gas is made using the igniter (IG), and then, when the combustion is stabilized, the combustion is maintained by supplying fuel and air. One of the fuel nozzles 123 of the plurality of fuel nozzles 123 (FC1, FC2, FC3, FCP, and FCQ) is disposed at a different position on the axis NX in the longitudinal direction with respect to the other fuel nozzles 123. They are arranged to blow air together. The igniter IG is disposed in the region FX where the plurality of fuel nozzles 123 (FC1, FC2, FC3, FCP, and FCQ) inject fuel to ignite, and a flame is formed in the region FX. That is, a flame is formed in the region FZ in which the fuel nozzle 123 in the combustion chamber 124 injects fuel.

In the combustion device 100 , gas fuel and liquid fuel, or a combination fuel thereof may be used. It is important to create a combustion environment to reduce the amount of exhaust gases such as carbon monoxide and nitrogen oxides, which are subject to legal regulation. Although combustion control is relatively difficult, it has the advantage of reducing the exhaust gas by lowering the combustion temperature and making uniform combustion In recent years, premixed combustion is widely applied. In the case of premixed combustion, compressed air is mixed with the fuel injected from the fuel nozzle 123 and then enters the combustion chamber 124 . The initial ignition of the premixed gas is made using an igniter, and then, when the combustion is stabilized, the combustion is maintained by supplying fuel and air.

The turbine 130 includes a plurality of turbine blades. The turbine 130 generates electric power by rotating the turbine blades by the combustion gas burned by the combustor 120 . The high-temperature, high-pressure combustion gas produced in the combustor 120 is supplied to the turbine 130 . In the turbine 130 , the thermal energy of the combustion gas is converted into mechanical energy in which the rotary shaft rotates by colliding with a plurality of turbine blades radially disposed on the rotary shaft of the turbine 130 while the combustion gas expands adiabatically and by giving a reaction force. A portion of the mechanical energy obtained from the turbine 130 is supplied as energy required for compressing air in the compressor, and the remainder is utilized as effective energy such as driving a generator to generate electric power.

The tuning device 200 receives the combustion vibration values of a plurality of bands measured from the plurality of combustors 120, and determines whether at least one combustion vibration value among the combustion vibration values of the plurality of bands is greater than or equal to a preset reference value. , when at least one of the combustion vibration values of each of the plurality of bands is equal to or greater than a preset reference value, control the gas turbine combustion system including the combustor 120 so that all of the combustion vibration values of the plurality of bands are less than the reference value do. To this end, the tuning device 200 may control a pilot fuel nozzle distribution ratio, a total fuel amount, a fuel temperature, an IGV opening degree, and the like.

Then, the detailed configuration of the above-described tuning device 200 will be described in more detail. 4 and 5 , the tuning device 200 includes a measuring unit 210 , a determining unit 220 , and a control unit 230 . The measurement unit 210 measures combustion vibrations for a plurality of bands of the combustor 120 through a dynamic pressure sensor. The combustion vibration frequency may appear differently depending on the combustion conditions. For example, anti-inflammation may be observed through 15 to 30 Hz, a low load region may be observed through 50 to 80 Hz, and a high load region may be observed through 100 Hz to 400 Hz. Also, different specific frequencies may occur depending on the combustor geometry. The combustor 120 includes a plurality of combustor cans, and a dynamic pressure sensor is installed corresponding to each of the plurality of combustor cans. Accordingly, the measurement unit 210 may measure a plurality of combustion vibrations corresponding to a plurality of preset bands corresponding to each of the plurality of combustor cans through a dynamic pressure sensor installed corresponding to each of the plurality of combustor cans. The division of these bands may be set differently depending on the content to be measured and the resolution.

For example, referring to FIG. 5 , the combustor 120 may include 16 combustor cans CAN01, CAN02, ..., CAN16. The dynamic pressure sensor is disposed corresponding to each of the plurality of combustor cans, and the dynamic pressure sensor detects combustion vibration of a plurality of bands, for example, six bands (BAND1, BAND2, BAND3, BAND4, BAND5, BAND6) for any one combustor can. measure For example, the dynamic pressure sensor may measure combustion vibrations for each of six bands, such as (CAN01, BAND1), (CAN01, BAND2), ..., (CAN01, BAND6) for the first combustor can (CAN01).

The measurement unit 210 is to extract combustion vibration values of a plurality of bands of the combustor 120 and provide the extracted combustion vibration values to the determination unit 220 . The measurement unit 210 extracts combustion vibration values of a plurality of bands measured from the combustor 120 . That is, after receiving the plurality of combustion vibration values from the dynamic pressure sensor, the measurement unit 210 divides the received plurality of combustion vibration values for each band and extracts the combustion vibration values for each band. That is, there are a plurality of combustor cans for each preset band, and the measuring unit 210 measures the combustion vibration value of each of the plurality of combustor cans in each band through a dynamic pressure sensor, and the average or maximum value of the combustion vibrations measured for each band can be extracted as the combustion vibration value of the corresponding band.

After extracting the combustion vibration value, the measurement unit 210 normalizes the combustion vibration value of the plurality of bands. For example, the measurement unit 210 may normalize the combustion vibration value for each band as shown in Equation 1 below.

Here, x is a band index, and bin is a combustion vibration value. Accordingly, binx represents the combustion vibration value of the band x. In addition, the threshold means the threshold of the combustion vibration value. That is, thresholdx represents the combustion vibration value threshold of the band x.

The determination unit 220 basically determines whether at least one of the normalized combustion vibration values of the plurality of bands is equal to or greater than a reference value.

At this time, assuming that six bands exist, the determination unit 220 may determine whether at least one of the normalized combustion vibration values of the plurality of bands is equal to or greater than a reference value according to Equation 2 below.

In Equation 2, bin1, bin2, bin3, bin4, bin5, and bin6 represent combustion vibration values of the first to sixth bands, respectively. In addition, threshold1, threshold2, threshold3, threshold4, threshold5, and threshold6 respectively represent threshold values of combustion vibration values in the first to sixth bands. Accordingly, the determination unit 220 may determine whether at least one of the combustion vibration values of the first to sixth bands normalized through the threshold of the combustion vibration values of each band through Equation 2 is equal to or greater than 1, which is a reference value. have. That is, when at least one of the normalized combustion vibration values of the first to sixth bands is 1 or more, the determination unit 220 may determine that at least one of the normalized combustion vibration values of the plurality of bands is equal to or greater than the reference value.

Also, the determination unit 220 may determine whether the combustion vibration value of the first band is equal to or greater than a reference value. In this case, the determination unit 220 may determine whether the combustion vibration value of the first band is equal to or greater than a reference value through Equation 3 below.

In Equation 3, bin1 represents the combustion vibration value of the first band. In addition, threshold1 represents a threshold value of the combustion vibration value of the first band. Accordingly, when the combustion vibration value of the first band normalized through the threshold value of the combustion vibration value of the first band through Equation 3 is 1 or more, the determination unit 220 determines that the combustion vibration value of the first band is equal to or greater than the reference value. can judge

And the determination unit 220 determines whether the combustion vibration value of the sixth band is equal to or greater than a reference value. In this case, the determination unit 220 may determine whether the combustion vibration value of the sixth band is equal to or greater than a reference value through Equation 4 below.

In Equation 4, bin6 represents the combustion vibration value of the sixth band. In addition, threshold6 represents a threshold value of the combustion vibration value of the first band. Accordingly, when the combustion vibration value of the sixth band normalized through the threshold of the combustion vibration value of the sixth band through Equation 4 is 1 or more, the determination unit 220 determines that the combustion vibration value of the sixth band is equal to or greater than the reference value. can judge

The control unit 230 performs tuning for the gas turbine combustion system. In this case, the controller 230 may control the oxygen, fuel, and fuel distribution ratio supplied to the gas turbine combustion system so that the combustion vibration values of all bands are less than the reference value.

In particular, when the combustion vibration value of the first band is equal to or greater than the reference value, the control unit 230 increases the pilot fuel nozzle distribution ratio.

Also, when the combustion vibration value of the sixth band is equal to or greater than the reference value, the controller 230 may control at least one of a total fuel amount, a fuel temperature, and an inlet guide vane (IGV) opening degree.

Then, a method for automatic tuning of the gas turbine combustion system according to an embodiment of the present invention of the tuning device 200 will be described in more detail. 6 is a flowchart illustrating a method for automatic tuning of a gas turbine combustion system according to an embodiment of the present invention.

Referring to FIG. 6 , the measurement unit 210 of the tuning device 200 extracts combustion vibration values of a plurality of bands measured through a dynamic pressure sensor from the combustor 120 of the gas turbine combustion system in step S110 . In the embodiment of the present invention, it is exemplarily described that the plurality of bands are divided into a first band to a sixth band, and it is assumed that the first band to the sixth band are sequentially from the lowest frequency to the highest frequency. That is, the measurement unit 210 measures a plurality of combustion vibration values through the dynamic pressure sensor, classifies the plurality of combustion vibration values for each band, and extracts the combustion vibration values for each band. According to another alternative embodiment, there are a plurality of combustor cans for each band, and the measurement unit 210 measures a combustion vibration value of each of the plurality of combustor cans in each band through a dynamic pressure sensor, and then the measured combustion vibration value The average or maximum value of can be extracted as the combustion vibration value of the corresponding band.

Next, the measurement unit 210 normalizes the combustion vibration values of the plurality of bands in step S120 . For example, the measurement unit 210 may normalize the combustion vibration value for each band as in Equation 1 above. In Equation 1, x is a band index, and bin represents a combustion vibration value. Accordingly, binx represents the combustion vibration value of the band x. In addition, the threshold means the threshold of the combustion vibration value. That is, thresholdx represents the combustion vibration value threshold of the band x. That is, the measurement unit 210 normalizes the combustion vibration values of the plurality of bands through the threshold values of the combustion vibration values of each of the plurality of bands.

Next, the determination unit 220 determines whether at least one of the combustion vibration values of the plurality of bands is equal to or greater than a reference value in step S130 . In this case, assuming that six bands exist, the determination unit 220 may determine whether at least one of the combustion vibration values of the plurality of bands is equal to or greater than a reference value according to Equation 2 above. In Equation 2, bin1, bin2, bin3, bin4, bin5, and bin6 represent combustion vibration values of the first to sixth bands, respectively. In addition, threshold1, threshold2, threshold3, threshold4, threshold5, and threshold6 respectively represent threshold values of combustion vibration values in the first to sixth bands. As described above, the combustion vibration values of the first to sixth bands are normalized through the thresholds of the respective combustion vibration values. Therefore, when at least one of the normalized combustion vibration values of the first to sixth bands is 1 or more, the determination unit 220 may determine that at least one of the combustion vibration values of the first to sixth bands is equal to or greater than the reference value.

As a result of the determination in step S130, if all of the combustion vibration values of the plurality of bands are less than the reference value, the process returns to step S110 to continue the process.

On the other hand, as a result of the determination in step S130, if at least one of the normalized combustion vibration values of the plurality of bands is greater than or equal to the reference value, that is, if at least one of the normalized combustion vibration values of the first to sixth bands is greater than or equal to 1, the determination unit ( 220) proceeds to step S140.

In step S140 , the determination unit 220 determines whether the combustion vibration value of the first band is equal to or greater than a reference value. In this case, the determination unit 220 may determine whether the combustion vibration value of the first band is equal to or greater than a reference value through Equation 3 above. In Equation 3, bin1 represents the combustion vibration value of the first band. In addition, threshold1 represents a threshold value of the combustion vibration value of the first band. Accordingly, when the combustion vibration value of the first band normalized through Equation 3 is 1 or more, the determination unit 220 may determine that the combustion vibration value of the first band is equal to or greater than the reference value.

As a result of the determination in step S140, if the combustion vibration value of the first band is equal to or greater than the reference value, the process proceeds to step S150. The controller 230 increases the distribution ratio of the pilot fuel nozzles FC1 and FCP in step S150. That is, when the combustion vibration value of the first band having the lowest frequency is equal to or greater than the reference value, there is a possibility of anti-inflammation. Therefore, increase the pilot to maintain the flame. For example, referring to FIG. 3 , the controller 230 increases the distribution ratio of the pilot fuel nozzles FC1 and FCP among the plurality of fuel nozzles 123: FC1, FC2, FC3, FCP, and FCQ.

On the other hand, if it is determined in step S140 that the combustion vibration value of the first band is less than the reference value, the process proceeds to step S160.

In step S160, the determination unit 220 determines whether the combustion vibration value of the sixth band is equal to or greater than a reference value. In this case, the determination unit 220 may determine whether the combustion vibration value of the sixth band is equal to or greater than a reference value through Equation 4 above. In Equation 4, bin6 represents the combustion vibration value of the sixth band. In addition, threshold6 represents a threshold value of the combustion vibration value of the first band. Accordingly, when the normalized combustion vibration value of the sixth band is equal to or greater than 1, the determination unit 220 may determine that the combustion vibration value of the sixth band is equal to or greater than the reference value.

As a result of the determination in step S160, if the combustion vibration value of the sixth band is equal to or greater than the reference value, the process proceeds to step S170. The controller 230 may control at least one of a total fuel amount, a fuel temperature, and an inlet guide vane (IGV) opening degree in step S170 .

Here, the sixth band corresponds to the high-frequency region, and when the combustion vibration value of the sixth band is equal to or greater than the reference value, it may cause damage to thin plates and parts with low amplitude. Therefore, the control unit 230 controls at least one of the total fuel amount, fuel distribution ratio, fuel temperature, and IGV (Inlet Guide Vane) opening degree to prevent damage to the thin plate and parts to change the impedance characteristics of air and fuel to reduce combustion vibration. reduce On the other hand, if it is determined in step S160 that the combustion vibration value of the sixth band is less than the reference value, the process proceeds to step S180. Then, the control unit 230 performs tuning for the gas turbine combustion system in step S180. That is, the control unit 230 controls the gas turbine combustion system including the combustor so that all of the combustion vibration values of the plurality of bands are less than the reference value. As such, when the combustion vibration value in the entire band is equal to or greater than the reference value, the control unit 230 sequentially controls the fuel distribution ratio, fuel temperature, total fuel amount, and IGV opening amount in order to reduce combustion vibration to less than the reference value. do. That is, first, the controller 230 controls the fuel distribution ratio within a preset control range to perform combustion tuning so that combustion vibration is reduced to less than a reference value. At this time, when the combustion vibration is not reduced below the reference value, the second combustion tuning is performed so that the combustion vibration is reduced to less than the reference value by controlling the fuel temperature within a preset control range. Also, when the combustion vibration is not reduced below the reference value, thirdly, the combustion tuning is performed so that the combustion vibration is reduced to less than the reference value by controlling the total fuel amount within a preset control range. Similarly, when the combustion vibration is not reduced below the reference value, the combustion tuning is performed so that the combustion vibration is reduced to less than the reference value by controlling the IGV opening amount within the last preset control range.

7 is a diagram illustrating a computing device according to an embodiment of the present invention. The computing device TN100 of FIG. 7 may be an apparatus described herein (eg, an apparatus for automatic tuning of a gas turbine combustion system, etc.).

In the embodiment of FIG. 7 , the computing device TN100 may include at least one processor TN110 , a transceiver device TN120 , and a memory TN130 . In addition, the computing device TN100 may further include a storage device TN140 , an input interface device TN150 , an output interface device TN160 , and the like. Components included in the computing device TN100 may be connected by a bus TN170 to communicate with each other.

The processor TN110 may execute a program command stored in at least one of the memory TN130 and the storage device TN140. The processor TN110 may mean a central processing unit (CPU), a graphics processing unit (GPU), or a dedicated processor on which methods according to an embodiment of the present invention are performed. The processor TN110 may be configured to implement procedures, functions, methods, and the like described in connection with an embodiment of the present invention. The processor TN110 may control each component of the computing device TN100 .

Each of the memory TN130 and the storage device TN140 may store various information related to the operation of the processor TN110 . Each of the memory TN130 and the storage device TN140 may be configured as at least one of a volatile storage medium and a non-volatile storage medium. For example, the memory TN130 may include at least one of a read only memory (ROM) and a random access memory (RAM).

The transceiver TN120 may transmit or receive a wired signal or a wireless signal. The transceiver TN120 may be connected to a network to perform communication.

On the other hand, the various methods according to the embodiment of the present invention described above may be implemented in the form of a program readable by various computer means and recorded in a computer readable recording medium. Here, the recording medium may include a program command, a data file, a data structure, etc. alone or in combination. The program instructions recorded on the recording medium may be specially designed and configured for the present invention, or may be known and available to those skilled in the art of computer software. For example, the recording medium includes magnetic media such as hard disks, floppy disks and magnetic tapes, optical recording media such as CD-ROMs and DVDs, and magneto-optical media such as floppy disks ( magneto-optical media), and hardware devices specially configured to store and execute program instructions, such as ROM, RAM, flash memory, and the like. Examples of program instructions may include not only machine language wires such as those generated by a compiler, but also high-level language wires that can be executed by a computer using an interpreter or the like. Such hardware devices may be configured to operate as one or more software modules to perform the operations of the present invention, and vice versa.

In the above, although an embodiment of the present invention has been described, those of ordinary skill in the art can add, change, delete or add components within the scope that does not depart from the spirit of the present invention described in the claims. It will be said that various modifications and changes of the present invention can be made by, and this is also included within the scope of the present invention.

100: combustion device
110: compressor
120: combustor
130: turbine
200: tuning device
210: measurement unit
220: judgment unit
230: control unit

Claims (20)

a plurality of dynamic pressure sensors installed in each of a plurality of combustor cans of a combustor of a gas turbine combustion system, and measuring combustion vibrations in a plurality of bands for the combustor cans respectively installed therein;
a measurement unit for extracting an average value of combustion vibration for each band from combustion vibrations of a plurality of bands measured by each of the plurality of dynamic pressure sensors as combustion vibration values of a plurality of bands;
a determination unit for determining whether at least one of the combustion vibration values of the plurality of bands is equal to or greater than a preset reference value; and
As a result of the determination, if at least one combustion vibration value among the combustion vibration values of each of the plurality of bands is greater than or equal to a preset reference value, a gas turbine combustion system including the combustor so that all of the combustion vibration values of the plurality of bands are less than the reference value a control unit to control;
characterized by comprising
Device for automatic tuning of gas turbine combustion systems. According to claim 1,
The measuring unit
Normalizing the measured combustion vibration values of the plurality of bands through the threshold values of the combustion vibration values of the plurality of bands
Device for automatic tuning of gas turbine combustion systems. 3. The method of claim 2,
The measuring unit
formula

Normalized for each band as shown, and normalized combustion vibration values are derived.
where x is a band index,
The bin is the combustion vibration value,
The binx represents the combustion vibration value of the band x,
The threshold is a threshold of the combustion vibration value,
The thresholdx is characterized in that it represents the combustion vibration value threshold of the x band
Device for automatic tuning of gas turbine combustion systems. 3. The method of claim 2,
the judging unit
formula

to determine whether at least one of the combustion vibration values of the plurality of bands is equal to or greater than a reference value,
The bin1, the bin2, the bin3, the bin4, the bin5, and the bin6 are combustion vibration values of the first to sixth bands, respectively,
wherein the threshold1, the threshold2, the threshold3, the threshold4, the threshold5, and the threshold6 are threshold values of combustion vibration values in the first to sixth bands, respectively.
Device for automatic tuning of gas turbine combustion systems. 5. The method of claim 4,
the judging unit
formula

to determine whether the combustion vibration value of the first band is equal to or greater than the reference value,
The bin1 is the combustion vibration value of the first band,
wherein the threshold1 is a threshold value of the combustion vibration value of the first band
Device for automatic tuning of gas turbine combustion systems. 6. The method of claim 5,
the control unit
When the combustion vibration value of the first band is equal to or greater than a reference value, the pilot fuel nozzle distribution ratio is increased so that the combustion vibration value of the first band is less than the reference value.
Device for automatic tuning of gas turbine combustion systems. 5. The method of claim 4,
the judging unit
formula

to determine whether the combustion vibration value of the 6th band is above the standard value,
The bin6 is the combustion vibration value of the sixth band,
wherein the threshold6 is a threshold value of the combustion vibration value of the sixth band
Device for automatic tuning of gas turbine combustion systems. 8. The method of claim 7,
the control unit
When the normalized combustion vibration value of the sixth band is equal to or greater than a reference value, at least one of a total fuel amount, fuel temperature, and an inlet guide vane (IGV) opening degree is controlled so that the combustion vibration value of the sixth band is less than the reference value. to do
Device for automatic tuning of gas turbine combustion systems. a compressor that compresses the injected air;
a combustor including a plurality of combustor cans, the combustor combusting the compressed air supplied from the compressor and the injected fuel to discharge combustion gas;
a gas turbine generating electric power through a plurality of turbine blades rotated by the combustion gas;
a plurality of dynamic pressure sensors installed in each of the plurality of combustor cans and measuring combustion vibrations of a plurality of bands with respect to the combustor cans each installed;
a measurement unit for extracting an average value of combustion vibration for each band from combustion vibrations of a plurality of bands measured by each of the plurality of dynamic pressure sensors as combustion vibration values of a plurality of bands;
a determination unit for determining whether at least one of the combustion vibration values of the plurality of bands is equal to or greater than a preset reference value; and
As a result of the determination, if at least one combustion vibration value among the combustion vibration values of each of the plurality of bands is greater than or equal to a preset reference value, a gas turbine combustion system including the combustor so that all of the combustion vibration values of the plurality of bands are less than the reference value a control unit to control;
characterized by comprising
Device for automatic tuning of gas turbine combustion systems. 10. The method of claim 9,
The measuring unit
Normalizing the measured combustion vibration values of the plurality of bands through thresholds of the combustion vibration values of the plurality of bands
Device for automatic tuning of gas turbine combustion systems. 11. The method of claim 10,
The measuring unit
formula

Normalized for each band as shown, and normalized combustion vibration values are derived.
where x is a band index,
The bin is the combustion vibration value,
The binx represents the combustion vibration value of the band x,
The threshold is a threshold of the combustion vibration value,
The thresholdx is characterized in that it represents the combustion vibration value threshold of the x band
Device for automatic tuning of gas turbine combustion systems. 10. The method of claim 9,
the judging unit
formula

to determine whether at least one of the normalized combustion vibration values of a plurality of bands is equal to or greater than a reference value,
The bin1, the bin2, the bin3, the bin4, the bin5, and the bin6 are combustion vibration values of the first to sixth bands, respectively,
wherein the threshold1, the threshold2, the threshold3, the threshold4, the threshold5, and the threshold6 are threshold values of combustion vibration values in the first to sixth bands, respectively.
Device for automatic tuning of gas turbine combustion systems. 13. The method of claim 12,
The determination unit determines whether the combustion vibration value of the first band is equal to or greater than a reference value,
As a result of the determination, if the combustion vibration value of the first band is equal to or greater than the reference value, the control unit increases the pilot fuel nozzle distribution ratio so that the combustion vibration value of the first band is less than the reference value.
Device for automatic tuning of gas turbine combustion systems. 13. The method of claim 12,
the judging unit
It is determined whether the combustion vibration value of the sixth band is equal to or greater than a reference value,
If the combustion vibration value of the sixth band is equal to or greater than the reference value,
wherein the control unit controls at least one of a total fuel amount, a fuel temperature, and an inlet guide vane (IGV) opening degree so that the combustion vibration value of the sixth band is less than a reference value.
Device for automatic tuning of gas turbine combustion systems. A plurality of dynamic pressure sensors installed in each of a plurality of combustor cans of a combustor of a gas turbine combustion system, respectively, measuring combustion vibrations in a plurality of bands for the combustor cans;
extracting, by a measuring unit, an average value of combustion vibrations for each band from combustion vibrations of a plurality of bands measured by each of the plurality of dynamic pressure sensors as combustion vibration values of a plurality of bands;
determining, by the determination unit, whether at least one of the combustion vibration values of the plurality of bands is equal to or greater than a preset reference value; and
As a result of the determination, if at least one combustion vibration value among the combustion vibration values of each of the plurality of bands is equal to or greater than the preset reference value, the control unit is a gas turbine combustion including the combustor so that all of the combustion vibration values of the plurality of bands are less than the reference value. controlling the system;
characterized by comprising
A method for automatic tuning of a gas turbine combustion system. 16. The method of claim 15,
After the step of extracting, before the step of determining,
Normalizing the combustion vibration values of the plurality of bands measured by the measurement unit through threshold values of the combustion vibration values of the plurality of bands; characterized in that it further comprises
A method for automatic tuning of a gas turbine combustion system. 17. The method of claim 16,
The measuring unit
Equation for the combustion vibration value

Normalized according to deriving the normalized combustion vibration value,
where x is a band index,
The bin is the combustion vibration value,
The binx represents the combustion vibration value of the band x,
The threshold is a threshold of the combustion vibration value,
The thresholdx is characterized in that it represents the combustion vibration value threshold of the x band
A method for automatic tuning of a gas turbine combustion system. 16. The method of claim 15,
The judging step
The determination unit

to determine whether at least one of the combustion vibration values of the plurality of bands is equal to or greater than the reference value,
The bin1, the bin2, the bin3, the bin4, the bin5, and the bin6 are combustion vibration values of the first to sixth bands, respectively,
wherein the threshold1, the threshold2, the threshold3, the threshold4, the threshold5, and the threshold6 are threshold values of combustion vibration values in the first to sixth bands, respectively.
A method for automatic tuning of a gas turbine combustion system. 19. The method of claim 18,
After the determining step,
determining, by the determination unit, whether the combustion vibration value of the first band is equal to or greater than a reference value; and
As a result of the check, if the combustion vibration value of the first band is equal to or greater than the reference value, increasing, by the controller, the pilot fuel nozzle distribution ratio so that the combustion vibration value of the first band is less than the reference value;
A method for automatic tuning of a gas turbine combustion system. 20. The method of claim 19,
After the confirming step,
As a result of the check, if the combustion vibration value of the first band is less than the reference value,
determining, by the determination unit, whether the combustion vibration value of the sixth band is equal to or greater than a reference value; and
As a result of the determination, when the control unit determines that the combustion vibration value of the sixth band is equal to or greater than the reference value, at least one of a total fuel amount, fuel temperature, and an inlet guide vane (IGV) opening degree such that the combustion vibration value of the sixth band is less than the reference value. Controlling the; characterized in that it further comprises
A method for automatic tuning of a gas turbine combustion system.

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