JP2021046951A - Gas turbine combustor - Google Patents

Abstract

To provide a gas turbine combustor capable of damping pressure fluctuation due to combustion vibration and suppressing an increase in NOx emissions due to reduction of combustion air.SOLUTION: A gas turbine combustor includes: a combustor liner 12; an air hole plate having a plurality of air holes 21 concentrically arranged in multiple rows; a plurality of fuel nozzles 22 arranged coaxially with the air holes; a spring seal 26 disposed between an outer peripheral surface of a plate lip covering the outer periphery of the air hole plate and an inner peripheral surface 12a of the combustor liner; a slot 27 disposed on the inner peripheral surface of the combustor liner at the downstream position of the spring seal so as to have an approximately L-shaped cross sectional shape and extend in the peripheral direction of the combustor liner and forming an acoustic space 92; an annular band-shaped partition plate 28 disposed in the acoustic space and on an axial side wall part of the slot; and a plurality of pressure wave introduction holes 90 provided in the slot and connecting a combustion chamber with the acoustic space. The slot is disposed to cover the air holes in the outermost peripheral row of the air hole plate.SELECTED DRAWING: Figure 1

Description

The present invention relates to the structure of a gas turbine combustor, and more particularly to a technique effective when applied to a gas turbine combustor having a multi-cluster burner structure.

Thermal power plants are considering improving power generation efficiency and actively using fuels such as hydrogen other than fossil fuels as a means of reducing _{carbon dioxide (CO 2} ) emissions, which cause global warming. ing. Increasing the turbine inlet temperature of gas turbine power generation equipment is effective for improving power generation efficiency.

However, as the temperature of gas turbines rises, the emission of nitrogen oxides (NOx), which is an environmental pollutant, increases. Therefore, improving power generation efficiency and reducing NOx emissions have become important technical issues, and high temperatures. There is a demand for a low NOx combustion method for gas turbines that is compatible with carbon and hydrogen-containing fuels.

As a combustion method of a gas turbine combustor, there are generally a diffusion combustion method and a premixed combustion method. The diffusion combustion method is a form in which fuel is directly injected into the combustion chamber and the fuel and air are mixed in the combustion chamber, and the fuel is mixed to the ratio of air required for complete combustion in the combustion chamber (quantitative mixing ratio). A flame is formed from the created area. Therefore, there is no possibility of backflow of flame to the upstream of the combustion chamber and self-ignition in the fuel supply system, and combustion stability can be ensured.

However, since a flame is formed in a region where fuel and air are mixed in a stoichiometric mixture ratio in the combustion chamber, a high-temperature flame is locally formed. In this locally high temperature region, NOx emissions are large, and it is necessary to inject an inert medium such as nitrogen, water, or steam to reduce NOx emissions. Therefore, the power of an auxiliary machine that supplies the inert medium is required, and power generation efficiency is increased. May decrease.

On the other hand, the premixed combustion method is a combustion method in which fuel and air are mixed in advance and supplied to the combustion chamber, and the fuel can be burned leanly, so that NOx can be reduced. However, as the temperature of the combustion air rises as the temperature of the gas turbine rises, the fuel concentration in the premixer that mixes fuel and air increases, so there is a possibility that the structure will be burned due to the backflow of flame. There is concern that reliability will decline.

In the case of a gas turbine using a hydrogen-containing fuel as described above, hydrogen has a higher adiabatic flame temperature in a stoichiometric mixing ratio than natural gas, so that NOx emissions in the diffusion combustion method increase. On the other hand, when hydrogen-containing fuel is used for the premixed combustion method, the ignition energy of hydrogen is small and the combustion speed is high, so there is a possibility that the flame will flow back into the premixer or self-ignite in the premixer. It gets higher.

In order to solve such a problem, there is a combustor in which a plurality of fuel nozzles and a plurality of air holes arranged upstream of the combustion chamber are arranged coaxially, and fuel and air are supplied to the combustion chamber as a coaxial flow. In this type of combustor, by dispersing fuel and air and supplying them as a coaxial flow, mixing is rapidly promoted and NOx emissions can be reduced. In addition, the mixing distance can be shortened and the backflow of flame can be prevented.

However, when a fuel having a high hydrogen concentration is applied to this combustor, the amplitude of pressure fluctuation due to the generation of combustion vibration increases, and the reliability of the combustor structure may decrease. In such a case, it is effective to install an acoustic liner having an acoustic space formed on the outer peripheral surface of the liner forming the combustion chamber to attenuate the pressure fluctuation due to the combustion vibration.

The acoustic liner guides the pressure wave to the acoustic space by a plurality of pressure wave introduction holes provided on the inner wall surface of the liner, attenuates the pressure fluctuation caused by the combustion vibration of a specific frequency band according to the radial height of the acoustic space, and at the same time, acoustically. It is composed of purge air holes that guide purge air into the acoustic space to prevent flames from entering the space.

Patent Document 1 discloses, as an example, a structure in which an acoustic space is provided on the outer peripheral surface of a cylindrical member (combustion cylinder) forming a combustion chamber.

International Publication No. 2013/077394

However, in the acoustic liner disclosed in Patent Document 1, in order to prevent the backflow of flame into the acoustic space, a specific amount of purge air is required from the pressure wave introduction hole (through hole group 16), and it is used for combustion. Air may decrease and NOx emissions may increase.

Therefore, an object of the present invention is to provide a gas turbine combustor capable of attenuating pressure fluctuations due to combustion vibration and suppressing an increase in NOx emissions due to a reduction in combustion air.

In order to solve the above problems, the present invention is located concentrically with a combustion chamber that burns a mixture of fuel and air, a combustor liner that forms the combustion chamber, and an upstream side of the combustion chamber. An air hole plate having a plurality of air holes arranged in a plurality of rows, a plurality of fuel nozzles arranged coaxially with the air holes, a plate lip covering the outer periphery of the air hole plate, the plate lip and the combustion chamber. A spring seal arranged between the outer peripheral surface of the plate lip and the inner peripheral surface of the combustion chamber liner at the fitting portion with the liner, and the inner peripheral surface of the combustion chamber liner at a position downstream of the spring seal. A slot having a substantially L-shaped cross section and being arranged so as to extend in the circumferential direction of the combustion chamber liner to form an acoustic space, and a slot in the acoustic space and in the axial direction of the slot. A ring-shaped partition plate arranged on a side wall portion and a plurality of pressure wave introduction holes provided in the slot and connecting the acoustic space and the combustion chamber are provided, and the slot is provided in the air hole plate. It is characterized in that it is arranged so as to cover the air holes in the outermost row.

According to the present invention, it is possible to realize a gas turbine combustor capable of attenuating pressure fluctuations due to combustion vibration and suppressing an increase in NOx emissions due to a reduction in combustion air.

This makes it possible to improve the reliability of the gas turbine combustor and reduce NOx at the same time, which contributes to the improvement of power generation efficiency of the thermal power plant and the reduction of NOx emissions.

Issues, configurations and effects other than those described above will be clarified by the description of the following embodiments.

It is sectional drawing of the combustor burner part which concerns on Example 1 of this invention. It is a schematic block diagram of the gas turbine plant provided with the gas turbine combustor which concerns on Example 1 of this invention. It is a front view of the air hole plate which concerns on Example 1 of this invention. It is sectional drawing of the combustor burner part in the conventional example. It is sectional drawing of the combustor burner part which concerns on Example 2 of this invention. It is sectional drawing of the combustor burner part which concerns on Example 3 of this invention. It is a front view of the air hole plate which concerns on Example 3 of this invention. It is a front view of the air hole plate and liner which concerns on Example 4 of this invention.

Hereinafter, examples of the present invention will be described with reference to the drawings. In each drawing, the same components are designated by the same reference numerals, and the detailed description of overlapping portions will be omitted.

The gas turbine combustor according to the first embodiment of the present invention will be described with reference to FIGS. 1 to 4. FIG. 4 is a cross-sectional view of a combustor burner portion of a conventional gas turbine combustor shown as a comparative example in order to make the present invention easy to understand.

FIG. 2 is a schematic configuration diagram of a gas turbine plant 1 provided with the gas turbine combustor of the present embodiment. In the gas turbine plant 1, the compressed air 102 compressed by the compressor 2 passes through the diffuser 9 and then flows into the vehicle interior 13. The compressed air 102 that has flowed into the passenger compartment 13 passes through the flow sleeve 14 and flows between the outer cylinder 10 and the liner 12.

A part of the compressed air 102 flows into the combustion chamber 5 as the cooling air 103 of the liner 12. The compressed air 102 that has passed between the outer cylinder 10 and the liner 12 passes through the spring seal 26 and flows through the outer peripheral side of the plate lip 25. The lip cooling air (leak air) 105 and the air holes provided in the air hole plate 20. It is distributed to the combustion air 104 that flows into 21 and is ejected into the combustion chamber 5. The combustion air 104 is mixed with the fuel 100 ejected from the fuel nozzle 22, and a flame 83 is formed in the combustion chamber 5.

The gas turbine plant 1 burns the fuel 100 in the combustor 3, causes the generated high-temperature and high-pressure combustion gas 110 to flow into the turbine 4 to drive the turbine 4, and extracts the rotational power of the turbine 4 as electric power.

The fuel supply system 201 and the fuel supply system 202 that supply the fuel 100 to the fuel nozzle 22 are branched from the fuel supply system 200 provided with the fuel shutoff valve 60. Further, the fuel supply systems 201 and 202 are provided with fuel pressure adjusting valves 61a and 62a, respectively, and the supply pressure of the fuel 100 to be supplied can be individually controlled. Further, fuel flow rate adjusting valves 61b and 62b are provided downstream thereof, respectively.

The combustor 3 of this embodiment includes a plurality of fuel nozzles 22, and each of the fuel nozzles 22 is connected to a fuel header 23 that distributes the fuel 100. The fuel header 23 is provided inside the end cover 7, and fuel is supplied to the fuel header 23 from the fuel supply systems 201 and 202. In this embodiment, the fuel 100 is distributed to two systems, but it may be distributed to a larger number of systems.

By distributing the fuel supply system to a plurality of systems in this way, the degree of freedom of operation (combustion control) can be expanded by increasing the number of systems. In the combustor 3 of this embodiment, hydrogen-containing fuels such as coke oven gas, refinery off-gas, and coal gasification gas can be used as fuel, and many gas fuels such as liquefied natural gas (LNG) can be used. Can also be applied to.

FIG. 3 shows a front view of the air hole plate 20. A plurality of air holes 21 are arranged concentrically around the central axis of the air hole plate 20, and in FIG. 3, the first row air holes 51, 2nd row air holes 52, and the 3rd row air holes 53 are formed in three rows. ing. The central axis of the air hole 21 is inclined in the pitch circumferential direction of each row, and a turning angle is given to the ejected combustion air 104 so as to swirl around the central axis of the air hole plate 20.

Further, as shown in FIG. 2, since the air hole plate 20 is coaxial with the liner 12, the combustion air 104 is swirled and introduced into the combustion chamber 5 so as to be around the central axis of the combustion chamber 5. The swirl acts, a circulating flow (circulating vortex) 80 can be formed, and the flame can be stabilized.

FIG. 1 shows a cross-sectional view of the combustor burner portion of this embodiment. The feature of this embodiment is that a slot 27 having a substantially L-shaped cross section is arranged on the inner peripheral surface 12a of the liner 12 on the downstream side of the spring seal 26 so as to extend (extend) in the circumferential direction, and the slot 27 is provided. The acoustic space 92 is formed by arranging so that the radial height of the air holes 21 covers the outermost peripheral row of the air holes 21, an annular partition plate 28 is provided on the axial side wall portion of the slot 27, and a plurality of slot 27s are provided. The pressure wave introduction hole 90 is provided.

FIG. 4 shows a cross-sectional view of the upstream side of the combustor of the conventional example. The operation and effect of this embodiment will be described in comparison with the cross-sectional structure on the upstream side of the combustor of the conventional example. In the cross-sectional structure on the upstream side of the combustor of the conventional example, as shown in FIG. 4, a rectangular annular lid 29 having a substantially U-shaped cross section is installed so as to form an acoustic space 92 on the outer peripheral surface 12b of the liner 12, and the acoustic space is provided. A plurality of pressure wave introduction holes 90 are provided in the liner 12 forming the 92, and a plurality of purge air holes 91 are provided in the outer peripheral side wall of the rectangular annular lid 29. The combustor structure and fuel system of the conventional example are the same as those of the present embodiment except for the above features.

In both the combustors of this embodiment and the conventional example, when the amplitude of the pressure fluctuation due to the generation of combustion vibration increases due to the application of hydrogen-containing fuel or the like, the pressure wave generated by the combustion vibration from the pressure wave introduction hole 90 is generated in the acoustic space 92. It is possible to attenuate the pressure fluctuation in a specific frequency band according to the radial height L of the acoustic space 92.

In the conventional example of FIG. 4, a purge air hole 91 is provided in the rectangular annular lid 29, a part of the combustion air 104 is guided to the acoustic space 92 as the purge air 106, and the purge air 106 is sent to the combustion chamber 5 through the pressure wave introduction hole 90. The invasion of the flame into the acoustic space 92 is prevented by flowing the air.

In order to prevent the flame from entering the acoustic space 92, the purge air 106 must always flow at a constant flow velocity or higher. Therefore, the combustion air 104 flowing through the air holes 21 decreases, and the fuel concentration relatively increases, so that a local high temperature region is likely to be formed, and NOx emissions may increase.

Further, since the damping effect of the pressure fluctuation in the acoustic space 92 increases as the number of the pressure wave introduction holes 90 increases, it may be difficult to reduce the NOx emission amount when dealing with a larger pressure fluctuation. ..

On the other hand, in the present embodiment of FIG. 1, the acoustic space 92 is formed by the slot 27 and the burner 8 installed on the inner peripheral surface 12a of the liner 12 downstream of the spring seal 26, and the lip cooling air (leak) passing through the spring seal 26 is formed. By using the air) 105, the fuel 100 flowing from the air holes 21 located in the outermost outermost row of the air holes 21 provided concentrically in the burner 8, and the combustion air 104 as the purge air 106, the slot 27 is filled. Purge air 106 can be flowed from the provided pressure wave introduction hole 90 to prevent the flame from entering the acoustic space 92.

Therefore, the pressure fluctuation due to the combustion vibration can be attenuated in the acoustic space 92 without reducing the combustion air 104 by installing the purge air hole 91 as in the conventional example of FIG. 4, and the NOx emission amount can be reduced. It will be possible.

Further, the fuel 100 and the combustion air 104 injected from the air holes 21 in the outermost peripheral row into the acoustic space 92 are mixed with the lip cooling air (leak air) 105 that has passed through the spring seal 26, and a pressure wave is introduced as purge air 106. Since the air is ejected from the hole 90 into the combustion chamber 5, the fuel concentration is lower than that of the air-fuel mixture of the fuel 100 ejected from the other air holes 21 and the combustion air 104, which is relatively low when burning in the combustion chamber 5. NOx emissions can be reduced by forming a temperature range.

Further, in the operation of the gas turbine plant 1, the total flow rate of the combustion air 104 and the lip cooling air (leak air) 105 flowing into the acoustic space 92 is the purge air required to prevent the flame from entering the acoustic space 92. Purge required to prevent flames from entering the acoustic space 92 by controlling the fuel flow control valves 61b and 62b so as to increase the flow rate of the fuel 100 flowing into the acoustic space 92 even when the flow rate is less than 106. It is possible to increase the flow rate of air 106 or more.

Further, in this embodiment, by installing the annular partition plate 28 on the axial side wall portion of the slot 27, the radial height L of the acoustic space 92 is set from the wall surface provided with the pressure wave introduction hole 90 of the slot 27. The distance to the partition plate 28 can be specified, and the frequency band of the pressure fluctuation attenuated in the acoustic space 90 can be arbitrarily adjusted.

The axial length of the partition plate 28 is preferably long as long as it does not come into contact with other structures, and the lowest frequency band of pressure fluctuation attenuated in the acoustic space 92 that can be adjusted at the installation position of the partition plate 28 is a slot. It is from the position of the pressure wave introduction hole 90 of 27 to the frequency band defined by the distance of the inner peripheral wall surface of the plate lip 25.

As described above, the gas turbine combustor of the present embodiment has a combustion chamber 5 that burns a mixture of fuel 100 and air (combustor air 104), and a combustor liner (liner 12) that forms the combustion chamber 5. ), An air hole plate 20 located on the upstream side of the combustion chamber 5 and having a plurality of air holes 21 arranged in a plurality of concentric rows, and a plurality of fuel nozzles 22 arranged coaxially with the air holes 21. The plate lip 25 that covers the outer periphery of the air hole plate 20, and the outer peripheral surface of the plate lip 25 and the inner peripheral surface 12a of the combustor liner (liner 12) at the fitting portion between the plate lip 25 and the combustor liner (liner 12). The spring seal 26 arranged between the two and the inner peripheral surface 12a of the combustor liner (liner 12) located downstream of the spring seal 26 has a substantially L-shaped cross-sectional shape and has a combustor liner (liner 12). A slot 27 that is arranged so as to extend in the circumferential direction of 12) and forms an acoustic space 92, and a ring-shaped partition plate 28 that is arranged in the acoustic space 92 and on the axial side wall portion of the slot 27. , A plurality of pressure wave introduction holes 90 provided in the slot 27 and connecting the acoustic space 92 and the combustion chamber 5, and the slot 27 covers the air holes 21 in the outermost row of the air hole plate 20. It is arranged like this.

As described above, the present invention can attenuate the pressure fluctuation due to the generation of combustion vibration in the acoustic space 92 and can prevent the invasion of the flame into the acoustic space 92 without reducing the combustion air 104, so that the NOx emissions can be simultaneously increased. Can be reduced.

The gas turbine combustor according to the second embodiment of the present invention will be described with reference to FIG. FIG. 5 is a cross-sectional view showing a combustor burner portion of this embodiment. The configuration and operation method of the gas turbine plant having the gas turbine combustor of this embodiment is basically the same as that of the first embodiment.

However, the difference from the first embodiment is that the fuel pressure adjusting valve 63a and the fuel flow rate adjusting valve 63b are installed, and the purging fuel system 207 for individually controlling the fuel 100 flowing into the acoustic space 92 is provided. The gas turbine combustor of this embodiment has a fuel flow rate adjusting mechanism (purge fuel system 207) that individually controls the fuel supplied to the air holes 21 covered with the slots 27.

By installing the purging fuel system 207 in this way, in addition to the same effects as in Example 1, the following effects can be obtained.

In this embodiment, the pressure and flow rate of the fuel 100 flowing into the acoustic space 92 are individually controlled by the purging fuel system 207, so that the amount of change in the flow rate of the fuel 100 flowing through the other fuel supply systems 201 and 202 is small. Therefore, it is possible to control the flow rate of the fuel 100 flowing into the acoustic space 92. In particular, when the number of air holes 21 for guiding the fuel 100 and the combustion air 104 to the acoustic space 92 is smaller than the total number of air holes 21 installed in the burner 8, the characteristics of the flame 83 of the combustion chamber 5 are not changed. Since the purge air 106 can be increased, the effect is high.

The gas turbine combustor according to the third embodiment of the present invention will be described with reference to FIGS. 6 and 7. FIG. 6 is a cross-sectional view showing a combustor burner portion of this embodiment. Further, FIG. 7 is a front view of the air hole plate of this embodiment. The configuration and operation method of the gas turbine plant having the gas turbine combustor of this embodiment is basically the same as that of the first embodiment.

However, in order to support a larger power generation output and various operation modes, one burner 8 composed of three rows of air holes 21 and a fuel nozzle 22 arranged substantially coaxially shown in the first embodiment is provided in the center and around the burner 8. It has a structure in which six are arranged. Further, in the combustor shown in this embodiment, the starting fuel nozzle 24 is installed in the center of the burner 8 provided in the center, and the fuel (supply) system is divided for each burner 8 to form a gas turbine. The difference from the first embodiment is that the fuel distribution for each burner 8 can be controlled according to the operating state.

In this embodiment, as shown in the front view of the air hole plate 20 seen from the combustion chamber 5 side in FIG. 7, a plurality of the air hole plates 20 of the first embodiment are arranged to form one air hole plate 20. There is. That is, the combustor of this embodiment includes one central burner 32 located at the center of the combustor 3 and six outer peripheral burners 33 located outside the central burner 32.

The central axis of each air hole 21 is inclined in the pitch circumferential direction of each row, and the flow passing through the air hole 21 spirally swirls downstream of the air hole 21 to form a swirling flow. Further, as shown in FIG. 6, the central burner 32 and the outer peripheral burner 33 are connected to the three fuel systems 203, 204, and 205, and the fuel flow rate can be controlled independently of each other. In this embodiment, the number of outer peripheral burners 33 is 6, but it is desirable that the number of outer peripheral burners 33 is 3 or more concentrically with respect to the central burner 32.

The central burner fuel system 203 and the gas turbine starting fuel system 206 are connected to the central burner 32, and are mainly used for starting operation of the gas turbine and stable combustion of the entire combustor during load operation. Operate to ensure sex. In this embodiment, the fuel supplied to the gas turbine starting fuel system 206 is a liquid fuel such as light oil and heavy oil.

On the other hand, the outer peripheral burner 33 is connected to the outer peripheral burner inner peripheral fuel system 204 and the outer peripheral burner outer peripheral fuel system 205. The coaxial jet group arranged on the concentric circles in the first row of the outer burner 33 forms the starting point of the flame, and is particularly related to the combustion stability. Therefore, as in this embodiment, by independently controlling the fuel flow rate supplied to the first row (inner circumference) of the outer peripheral burner 33, the starting point of the flame is strengthened and stable combustion is performed over a wider load range. Can be maintained.

The feature of this embodiment is that the air hole plate 20 having one central burner 32 and a plurality of outer peripheral burners 33 has a slot having a substantially L-shaped cross section on the inner peripheral surface 12a of the liner 12 downstream of the spring seal 26. The acoustic space 92 is formed by arranging the 27 so as to extend (extend) in the circumferential direction and arranging the slot 27 so that the radial height of the slot 27 covers the air hole 21 of the outer peripheral burner 33 near the plate lip 25. In addition to this, a band-shaped partition plate 28 is provided on the axial side wall portion of the slot 27, and a plurality of pressure wave introduction holes 90 are provided in the slot 27.

That is, in the gas turbine combustor of the present embodiment, the air holes 21 arranged in a plurality of concentric rows and the burners in which a plurality of fuel nozzles 22 are arranged coaxially with the air holes 21 are placed on the central axis of the air hole plate 20. This is a multi-cluster burner in which one is arranged as a central burner 32, and a plurality of outer peripheral burners 33 and 112 are concentrically arranged around the central burner 32 to form one combustor.

Further, it has a fuel nozzle (starting fuel nozzle 24) for supplying liquid fuel to the central burner 32.

By arranging the air holes 21 of the outer peripheral burner 33 near the plate lip 25 so as to be covered with the slots 27, the following effects can be obtained in addition to the same effects as in the first embodiment.

In the combustor 3 of the present embodiment, the central burner fuel system 203 is used as the purge air 106 for preventing the flame from entering the acoustic space 92 when the fuel 100 is supplied from the air holes 21 communicating with the acoustic space 92. Since it can be controlled independently, it is possible to perform load operation while ensuring the combustion stability of the entire combustor.

Further, the fuel 100 and the combustion air 104 ejected from the air hole 21 near the plate lip 25 are mixed with the lip cooling air (leak air) 105 passing through the spring seal 26 and ejected from the pressure wave introduction hole 90 of the slot 27. Therefore, the flame 83 is not formed downstream of the air hole 21 near the plate lip 25, and the heating factor of the plate lip 25 can be removed, so that the reliability of the combustor can be improved.

Further, in this embodiment, when the outer peripheral burner outer peripheral fuel system 205 is divided as in the second embodiment and the fuel 100 flowing to the acoustic space 92 is used as the purging fuel system 207, the outer peripheral burner which is the starting point of the flame of the outer burner 33 While independently controlling the inner peripheral fuel system 204, it is possible to control the flow rate of the fuel 100 flowing into the acoustic space 92 while the amount of change in the flow rate of the outer peripheral burner outer peripheral fuel system 205 is small.

The gas turbine combustor according to the fourth embodiment of the present invention will be described with reference to FIG. FIG. 8 is a front view of the air hole plate and liner of this embodiment as viewed from the combustion chamber 5 side. The configuration of the combustor shown in this embodiment is basically the same as that of the third embodiment, but differs from the third embodiment in that the slot 27 installed on the inner peripheral surface 12a of the liner 12 is divided in the circumferential direction. ..

In the gas turbine combustor of the present embodiment, the slot 27 is divided into a plurality of slots 27 so as to be arranged only in the vicinity of the outer peripheral burners 33 and 112 in the circumferential direction of the combustor liner (liner 12).

As shown in FIG. 8, by dividing the slot 27 in the circumferential direction, the following effects can be obtained in addition to the same effects as in the third embodiment.

In the combustor 3 of the present embodiment, the slot 27 is divided in the circumferential direction, so that the distance L between the partition plate 28 provided on the axial side wall of the slot 27 and the installation position of the pressure wave introduction hole 90 is set. Since it can be set individually in the slot 27 of the above, the frequency band of the pressure fluctuation that can be attenuated in each acoustic space 92 can be changed, and it is possible to correspond to the combustion vibration in a wide band.

The present invention is not limited to the above-described examples, and includes various modifications. For example, the above-described embodiment has been described in detail in order to explain the present invention in an easy-to-understand manner, and is not necessarily limited to the one including all the described configurations. Further, it is possible to replace a part of the configuration of one embodiment with the configuration of another embodiment, and it is also possible to add the configuration of another embodiment to the configuration of one embodiment. Further, it is possible to add / delete / replace a part of the configuration of each embodiment with another configuration.

1 ... Gas turbine plant, 2 ... Compressor, 3 ... Combustor, 4 ... Turbine, 5 ... Combustion chamber, 6 ... Transition piece, 7 ... End cover, 8 ... Burner, 9 ... Diffuser, 10 ... Outer cylinder, 12 ... Liner, 12a ... (liner's) inner peripheral surface, 12b ... outer peripheral surface, 13 ... cabin, 14 ... flow sleeve, 20 ... air hole plate, 21 ... air hole, 22 ... fuel nozzle, 23 ... fuel header, 24 ... Starting fuel nozzle, 25 ... Plate lip, 26 ... Spring seal, 27 ... Slot, 28 ... Partition plate, 29 ... Rectangular annular lid, 32 ... Central burner, 33, 112 ... Outer burner, 51 ... First row air holes, 52 ... 2nd row air hole, 53 ... 3rd row air hole, 60 ... Fuel shutoff valve, 61a, 62a, 63a ... Fuel pressure regulating valve, 61b, 62b, 63b ... Fuel flow rate regulating valve, 80 ... Circulation flow (circulation) Vortex), 83 ... Flame, 90 ... Pressure wave introduction hole, 91 ... Purge air hole, 92 ... Acoustic space, 100 ... Fuel, 102 ... Compressed air, 103 ... Cooling air, 104 ... Combustion air, 105 ... Lip cooling air (Leak air), 106 ... Purge air, 110 ... Combustion gas, 200, 201, 202 ... Fuel supply system, 203 ... Central burner fuel system, 204 ... Outer burner inner peripheral fuel system, 205 ... Outer burner outer peripheral fuel system, 206 … Fuel system for starting gas turbine, 207… Fuel system for purging.

Claims (6)

A combustion chamber that burns a mixture of fuel and air,
With the combustor liner forming the combustion chamber,
An air hole plate located on the upstream side of the combustion chamber and provided with a plurality of air holes arranged in a plurality of concentric rows.
A plurality of fuel nozzles arranged coaxially with the air holes,
A plate lip that covers the outer circumference of the air hole plate and
A spring seal arranged between the outer peripheral surface of the plate lip and the inner peripheral surface of the combustor liner at the fitting portion between the plate lip and the combustor liner.
It has a substantially L-shaped cross-sectional shape on the inner peripheral surface of the combustor liner at a position downstream of the spring seal, and is arranged so as to extend in the circumferential direction of the combustor liner to form an acoustic space. Slots and
An annular partition plate arranged in the acoustic space and on the axial side wall portion of the slot, and
A plurality of pressure wave introduction holes provided in the slot and connecting the acoustic space and the combustion chamber are provided.
The slot is a gas turbine combustor arranged so as to cover the air holes in the outermost row of the air hole plates. The gas turbine combustor according to claim 1.
A gas turbine combustor having a fuel flow rate adjusting mechanism that individually controls the fuel supplied to the air holes covered with the slots. The gas turbine combustor according to claim 1.
A plurality of concentrically arranged air holes and a burner in which a plurality of fuel nozzles are arranged coaxially with the air holes are arranged as a central burner on the central axis of the air hole plate.
A gas turbine combustor which is a multi-cluster burner in which a plurality of outer peripheral burners are concentrically arranged around the central burner to form one combustor. The gas turbine combustor according to claim 3.
A gas turbine combustor having a fuel nozzle that supplies liquid fuel to the central burner. The gas turbine combustor according to claim 1.
A gas turbine combustor that burns fuel containing hydrogen in its fuel composition. The gas turbine combustor according to claim 3.
A gas turbine combustor in which the slots are divided into a plurality of slots so as to be arranged only in the vicinity of the outer peripheral burner in the circumferential direction of the combustor liner.

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