JP2013245598A - Gas turbine combustor - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a gas turbine combustor capable of achieving improvement of combustion performance of the gas turbine combustor and reduction of NOx emission while avoiding complication of operation control and increase of a manufacturing cost.SOLUTION: A gas turbine combustor includes: a burner plate in which a plurality of air holes are formed; and a burner in which a plurality of fuel nozzles are provided for injecting fuel towards the air holes of the burner plate and the fuel nozzles and the air holes are disposed coaxially so as to inject the fuel and air to a combustion chamber as a plurality of coaxial jet streams. In the gas turbine combustor, two systems of a burner central part fuel system and a burner outer peripheral part fuel system are disposed as a fuel supply system. The burner central part fuel system supplies the fuel to a burner central part that becomes a burner axial center side, and the burner outer peripheral part fuel system supplies the fuel to a burner outer peripheral part that becomes the outer peripheral side of the burner central part. In the burner outer peripheral part fuel system, a pressure regulation valve for regulating the pressure of the fuel and a flow control valve for controlling the flow of the fuel are installed. The burner central part fuel system is configured by being branched from the burner outer peripheral part fuel system in the upstream part of the pressure regulation valve and further installing a throttle part in the burner central part fuel system.

Description

  The present invention relates to a gas turbine combustor, and more particularly to a gas turbine combustor that improves the combustion performance of a gas turbine combustor by suppressing the complexity of operation controllability of the gas turbine combustor and the increase in gas turbine manufacturing cost. Is.

  In recent years, regulations on the emission of air pollutants have become stricter from the viewpoint of global environmental protection, and various kinds of gas turbine combustors have been developed to reduce the amount of nitrogen oxide (NOx) contained in exhaust gas. Combustion methods are being studied.

  Among them, as disclosed in JP-A-2006-17381, in a coaxial jet combustion system (hereinafter referred to as a cluster burner) in which fuel and air are supplied to a combustion chamber as a coaxial jet and burned, air and fuel are used. Compared with the conventional premixed combustion method in which the fuel is premixed and then burned, the mixing can be effectively promoted at a very short distance, and the NOx emission amount can be kept low.

JP 2006-17381 A

  In the gas turbine combustor technology disclosed in Japanese Patent Application Laid-Open No. 2006-17381, the NOx emission amount is reduced and the combustion stability is improved by improving the fuel nozzle and air hole structure of the cluster burner.

  However, due to the recent trend of further NOx reduction, there is a need to further reduce NOx emissions by reducing the ratio of the fuel flow rate to the air flow rate (hereinafter referred to as the fuel-air ratio) in the combustion field. .

  In general, when the fuel-air ratio is lowered, the stability of the flame is lowered. Therefore, a measure for improving the flame stability as well as reducing the NOx emission amount is required.

  By the way, as one of the measures for reducing NOx emissions and improving the stability of the flame, the fuel supplied to the cluster burner is divided into two systems, the central part and the outer peripheral part of the cluster burner, For example, a method can be considered in which a stable flame with a high fuel-air ratio is formed, and the fuel flame-air ratio at the outer peripheral portion is lowered to reduce the NOx emission amount by using the stable flame at the center as the type of fire.

  However, in the above-described method, it is necessary to increase the number of fuel systems that supply fuel to the cluster burner, and the operation control of the gas turbine combustor is only complicated by adding a fuel valve to the increased fuel system. However, the manufacturing cost of the gas turbine combustor increases.

  SUMMARY OF THE INVENTION An object of the present invention is to avoid a complicated operation control of a gas turbine combustor and an increase in manufacturing cost of the gas turbine combustor, and improve the combustion performance of the gas turbine combustor and reduce NOx emissions. It is to provide a combustor.

  A gas turbine combustor according to the present invention includes a combustion chamber that generates a combustion gas by mixing and burning fuel and air, a burner plate that has a plurality of air holes for ejecting air into the combustion chamber, and the burner plate A burner having a plurality of fuel nozzles that are ejected toward the air holes, wherein the fuel nozzles and the air holes are arranged coaxially so that the fuel and air are ejected into the combustion chamber as a plurality of coaxial jets A burner center fuel system for supplying a fuel supply system for supplying fuel to the burner to a burner center portion on the burner shaft center side, and a burner outer periphery portion on the outer periphery side of the burner center portion A burner outer peripheral fuel system for supplying fuel to the burner outer peripheral fuel system is disposed, and the burner outer peripheral fuel system has a pressure adjusting valve for adjusting the fuel pressure and a flow adjusting valve for adjusting the fuel flow rate. Each of the burner central fuel systems is configured to branch from the burner outer peripheral fuel system upstream of the pressure regulating valve, and a throttle unit for reducing the fuel flow rate is installed in the burner central fuel system. It is characterized by that.

  The gas turbine combustor according to the present invention includes a combustion chamber that generates a combustion gas by mixing and burning fuel and air, a burner plate that has a plurality of air holes for ejecting air into the combustion chamber, and fuel that is supplied to the burner. A plurality of fuel nozzles ejected toward the air holes of the plate, wherein the fuel nozzles and the air holes are arranged coaxially so that fuel and air are ejected into the combustion chamber as a plurality of coaxial jets; In a gas turbine combustor equipped with a burner, a fuel supply system for supplying fuel to the burner is supplied to a burner central portion on the burner shaft center side, and a burner outer periphery on the outer peripheral side of the burner central portion The burner outer periphery fuel system to be supplied to the fuel system is arranged in two systems, and the burner outer periphery fuel system has a pressure adjustment valve for adjusting the fuel pressure and a flow rate adjustment for adjusting the fuel flow rate. A valve is installed, and the burner central fuel system is configured to branch from the burner outer peripheral fuel system upstream of the pressure regulating valve, and a three-way valve is installed in the burner central fuel system. A plurality of throttle portions that throttle the flow rate of fuel are provided on the downstream side of the valve, and a fuel system that passes through the plurality of throttle portions is switched by switching the three-way valve. To do.

  The gas turbine combustor according to the present invention includes a combustion chamber that generates a combustion gas by mixing and burning fuel and air, a burner plate that has a plurality of air holes for ejecting air into the combustion chamber, and fuel that is supplied to the burner. A plurality of fuel nozzles ejected toward the air holes of the plate, wherein the fuel nozzles and the air holes are arranged coaxially so that fuel and air are ejected into the combustion chamber as a plurality of coaxial jets; The fuel is supplied to the cluster burner in a gas turbine combustor having a cluster burner and a premixed combustion burner that forms a flame by premixing and burning fuel and air on the outer periphery of the gas turbine combustor. The fuel supply system to be supplied is supplied to the burner center fuel system that supplies the center of the burner on the cluster burner shaft center side, and to the outer periphery of the burner that is the outer periphery of the burner center. The burner outer peripheral fuel system is provided with two systems, and the burner outer peripheral fuel system is provided with a pressure adjusting valve for adjusting the fuel pressure and a flow rate adjusting valve for adjusting the fuel flow rate, respectively. The system is configured to diverge from the burner outer peripheral fuel system upstream of the pressure regulating valve, and a throttle unit for restricting the flow rate of fuel is installed in the central fuel system of the burner to supply the fuel to the premix burner The premixed fuel supply system is branched from the burner outer peripheral fuel system downstream of the pressure regulating valve, and another pressure regulating valve for adjusting the fuel pressure is installed in the premixed fuel supplying system. It is characterized by that.

  The gas turbine combustor according to the present invention includes a combustion chamber that generates a combustion gas by mixing and burning fuel and air, a burner plate that has a plurality of air holes for ejecting air into the combustion chamber, and fuel that is supplied to the burner. A plurality of fuel nozzles ejected toward the air holes of the plate, wherein the fuel nozzles and the air holes are arranged coaxially so that fuel and air are ejected into the combustion chamber as a plurality of coaxial jets; A fuel for supplying fuel to the cluster burner in a gas turbine combustor having a plurality of cluster burners arranged in a central portion on the axial center side of the gas turbine combustor and an outer peripheral portion of the gas turbine combustor. Two systems are provided: a burner center fuel system that supplies the supply system to the burner center of the cluster burner and a burner outer periphery fuel system that supplies the burner outer periphery; -A pressure regulating valve for adjusting the fuel pressure is installed in the fuel system at the outer periphery of the burner, and the fuel is branched from the fuel system at the outer periphery of the burner downstream of the pressure regulating valve and supplied to the outer periphery of the burner of the cluster burner. A plurality of first fuel systems are arranged, and a flow rate adjusting valve for adjusting the flow rate of the fuel is installed in each of the plurality of fuel systems that supply fuel to the outer periphery of the burner of the cluster burner. A plurality of second fuel systems are configured to branch from the burner outer peripheral fuel system upstream of the pressure regulating valve, and supply fuel to the burner central part of the cluster burner by branching from the burner central fuel system. It is arranged, and a throttle part for restricting the flow rate of fuel is installed in the second fuel system.

  According to the present invention, it is possible to avoid the complicated operation control of the gas turbine combustor and the increase in the manufacturing cost of the gas turbine combustor, and to improve the combustion performance of the gas turbine combustor and reduce the NOx emission amount. A combustor can be realized.

BRIEF DESCRIPTION OF THE DRAWINGS Schematic which shows the structure of the gas turbine provided with the gas turbine combustor of the Example of this invention. The partial view which shows the cluster burner structure and fuel system of the gas turbine combustor which are 1st Examples of this invention. The partial view which shows the cluster burner structure and fuel system of the gas turbine combustor which are 2nd Examples of this invention. The partial view which shows the cluster burner structure and fuel system of the gas turbine combustor which are 3rd Example of this invention. The fragmentary figure which shows the multi-cluster burner structure and fuel system of the gas turbine combustor which are 4th Example of this invention. The arrow line view which looked at the multi-cluster burner structure of the gas turbine combustor which is the 4th example shown in Drawing 5 from the BB direction.

  An embodiment of a gas turbine combustor according to the present invention will be described with reference to the drawings.

  The gas turbine combustor which is 1st Example of this invention is demonstrated using FIG.1 and FIG.2.

  FIG. 1 shows a schematic configuration of a gas turbine equipped with a gas turbine combustor according to a first embodiment of the present invention. In the gas turbine shown in FIG. 1, high-pressure air 120 discharged from an air compressor 110 is diffuser. From the air introduction hole 151 introduced into the passenger compartment 140 from 130 and provided in the transition tube flow sleeve 150 of the gas turbine combustor 100, the tail tube flow sleeve 150 and the tail disposed inside the transition tube flow sleeve 150 are provided. It flows into the flow path formed in the gap with the cylinder 152.

  The high-pressure air 120 that has flowed into the flow path formed in the gap is then contacted between the liner 153 of the gas turbine combustor 100 and the liner flow sleeve 154 disposed concentrically with the liner 153 on the outer peripheral side of the liner 153. After flowing through the flow path formed in the gap, the flow is reversed and mixed with fuel injected from the plurality of fuel nozzles 31, 32 introduced from the fuel supply system 1 and constituting the cluster nozzle, and the combustion chamber inside the liner 153 It burns at 160 to form a flame 156 and generates a high temperature and pressure combustion gas 170.

  Thus, the high-temperature and high-pressure combustion gas 170 generated in the gas turbine combustor 100 flows down the tail cylinder 152 and is introduced into the turbine 180.

  In the turbine 180 constituting the gas turbine, the amount of work generated when the high-temperature and high-pressure combustion gas 170 introduced into the turbine 180 undergoes adiabatic expansion is converted into an axial rotational force by the turbine 180, so that A generator 190 connected by a shaft is driven to obtain an output from the generator 190.

  The air compressor 110 and the generator 190 constituting the gas turbine are connected to the turbine 180 by the turbine shaft. However, the air compressor 110, the turbine 180, and the generator 190 may not be configured with one turbine shaft but may be configured with two or more turbine shafts.

  In general, a gas turbine widely used in a thermal power plant or the like has a configuration in which a plurality of gas turbine combustors are arranged radially with respect to a turbine shaft.

  FIG. 2 is a partial view showing a cluster burner structure and a fuel system in the gas turbine combustor 100 according to the first embodiment of the present invention provided in the gas turbine shown in FIG. The fuel supplied to the cluster burner at 100 is branched and supplied from the fuel system 1 to the burner central part fuel system 10 and the burner outer peripheral part fuel system 20 at the downstream part of the fuel cutoff valve 2 installed in the fuel system 1. It is the composition which becomes.

  The fuel supplied through one of the branched burner center fuel systems 10 passes through an orifice 11 installed in the burner center fuel system 10 and is then introduced into the center burner center of the cluster burner.

  In addition, the fuel supplied through the other branched burner outer peripheral fuel system 20 passes through the pressure adjusting valve 21 and the flow rate adjusting valve 22 installed in the burner outer peripheral fuel system 20, respectively, and then the outer periphery constituting the cluster burner. Is introduced into the outer periphery of the burner on the side.

  The cluster burner is provided with a plurality of fuel nozzles 32 in the center of the burner located on the axial center side, and a plurality of fuel nozzles 31 in the outer periphery of the burner located on the outer periphery of the fuel nozzle 32 in the center of the burner. The plurality of fuel nozzles 32 and the plurality of fuel nozzles 31 have a one-to-one correspondence with the plurality of air holes 34 formed in the air hole plate 33 disposed close to the downstream side of the fuel nozzles 31 and 32. The plurality of air holes 34 are arranged so as to be coaxial with each other.

  The fuel injected from the plurality of fuel nozzles 32 at the center of the burner and the plurality of fuel nozzles 31 at the outer periphery of the burner toward the plurality of air holes 34 formed in the air hole plate 33 is supplied from the air compressor 110. Along with the combustion air, it is ejected into the combustion chamber 160 and rapidly mixed and combusted to form a flame and generate a high-temperature and high-pressure combustion gas 170.

  In the gas turbine combustor 100 of the present embodiment, the fuel pressure in the downstream portion of the shutoff valve 2 installed in the fuel system 1 is usually 2 to 3 MPa, and the pressure in the combustion chamber 160 of the gas turbine combustor 100 is 1 to 3. Since the pressure is 2 MPa, the pressure difference before and after the orifice 11 installed in the burner center fuel system 10 branched from the fuel system 1 downstream from the shutoff valve 2 can be increased. The fuel supplied to the plurality of fuel nozzles 32 is choked by the orifice 11, and a predetermined flow rate of fuel is always supplied through the burner center fuel system 10 regardless of the pressure in the combustion chamber 160 of the gas turbine combustor 100. A plurality of fuel nozzles 32 in the center can be supplied.

  Therefore, in the gas turbine combustor 100 of the present embodiment having the configuration shown in FIG. 1, in order to improve the flame stability of the cluster burner and reduce the NOx emission amount, two fuel systems are supplied to the gas turbine combustor. Even when the system is divided into systems, it is not necessary to add a fuel adjustment valve to the fuel system that is installed separately, which complicates operation control of the gas turbine combustor and increases the manufacturing cost of the gas turbine combustor. A gas turbine combustor capable of avoiding the above can be realized.

  Further, in the gas turbine combustor 100 according to the present embodiment, the fuel flow rate of the fuel supplied by the orifice 11 installed in the fuel system divided and arranged is choked so that a predetermined flow rate is always applied to the central portion of the burner of the cluster burner. A stable supply is possible.

  Further, in the gas turbine combustor 100 of the present embodiment, a stable flame with a high fuel-air ratio is formed in the central part of the burner of the cluster burner, and the stable flame in the central part of the burner of the cluster burner is used as a fire type. Since the fuel-air ratio can be lowered, NOx emission can be reduced.

  According to the present embodiment, complicated operation control of the gas turbine combustor and an increase in the manufacturing cost of the gas turbine combustor are avoided, and the combustion performance of the gas turbine combustor can be improved and the NOx emission amount can be reduced. A gas turbine combustor can be realized.

  Next, a gas turbine combustor according to a second embodiment of the present invention will be described with reference to FIG.

  The cluster burner structure and fuel system of the gas turbine combustor 100 of this embodiment shown in FIG. 3 are the same in basic configuration as those of the gas turbine combustor 100 of the first embodiment shown in FIG. The description of the configuration common to both is omitted, and only the differences are described below.

  In the cluster burner structure and fuel system of the gas turbine combustor 100 of the present embodiment shown in FIG. 3, the burner central part fuel system 10 branched from the fuel system 1 at the downstream part of the fuel cutoff valve 2 installed in the fuel system 1. A three-way valve 12 is provided in the middle, and branch pipes branching from the burner center fuel system 10 are disposed downstream of the three-way valve 12, and the diameters of the orifice restricting portions of these branch pipes are different from each other. A plurality of orifices 13 and 14 are respectively installed, and further, these branch pipes are merged so that the fuel passing through the three-way valve 12 and the orifices 13 and 14 is a plurality of fuels in the center of the burner located on the axial center side of the cluster burner. The nozzle 32 is configured to inject toward a plurality of air holes 34 formed in the air hole plate 33.

  In the cluster burner structure and fuel supply system of the gas turbine combustor 100 according to the present embodiment, a pressure regulator valve 21 and a flow rate regulator valve 22 are installed in the burner outer peripheral fuel system 20 branched from the fuel system 1, and the cluster burner is installed. The flow rate of fuel supplied to the outer peripheral portion of the outer peripheral burner is controlled.

  Furthermore, in the cluster burner structure and fuel supply system of the gas turbine combustor 100 of this embodiment, a three-way valve 12 is provided in the fuel system 10 at the center of the burner branched from the fuel system 1, and an orifice is provided downstream of the three-way valve 12. The diameters of the throttle parts of the branch pipes are different from each other, and are provided with two orifices 13, 14, that is, a small-diameter orifice 13 used at start-up and a low load and a large-diameter orifice 14 used at a high load. Is provided, so that the fuel is supplied through one branch pipe in which the small-diameter orifice 13 is installed by switching operation of the three-way valve 12 or through the other branch pipe in which the large-pore orifice 14 is installed. It is possible to supply the fuel by switching the gas, and by changing the hole diameter of the throttle portion by the orifice 13 and the orifice 14, the gas It is possible to flow the fuel flow rate supplied to the burner central portion of the gas turbine combustor 100 alters the flow rate of the different two kinds according to the operating state of the over bottle plant.

  Further, by providing another three-way valve downstream of the three-way valve, it is possible to change the flow rate of the fuel supplied to the burner central portion of the gas turbine combustor 100 into three different flow rates.

  In the gas turbine combustor 100 of the present embodiment, a three-way valve 12 is provided in a burner central fuel system 10 branched from a downstream part of a fuel cutoff valve 2 installed in the fuel system 1, and an orifice is provided downstream of the three-way valve 12. Even when the fuel supply is controlled in accordance with the output of the gas turbine plant by arranging the branch pipe provided with two orifices 13 and 14 having different diameters of the throttle portions, the gas of this embodiment is used. In the turbine combustor 100, so-called ON / OFF control is possible in which the flow rate of fuel corresponding to the output of the gas turbine plant can be controlled only by simple switching control of the three-way valve 12 and the small-bore orifice 13 or the large-bore orifice 14. Therefore, the fuel control of the gas turbine combustor can be greatly simplified.

  As described above, in the gas turbine combustor of the present embodiment, the fuel system that supplies the fuel system supplied to the gas turbine combustor to the burner central portion in order to improve the flame stability of the cluster burner and reduce the NOx emission amount. Even if the fuel system is divided into two fuel systems, that is, the fuel system supplied to the outer periphery of the burner, it is not necessary to add a fuel adjustment valve to the divided fuel supply system, and the operation control of the gas turbine combustor is complicated. It is possible to avoid an increase in manufacturing cost of the gas turbine.

  According to the present embodiment, complicated operation control of the gas turbine combustor and an increase in the manufacturing cost of the gas turbine combustor are avoided, and the combustion performance of the gas turbine combustor can be improved and the NOx emission amount can be reduced. A gas turbine combustor can be realized.

  Next, a gas turbine combustor according to a third embodiment of the present invention will be described with reference to FIG.

  The cluster burner structure and fuel system of the gas turbine combustor 100 of the present embodiment shown in FIG. 4 are the same in basic configuration as those of the gas turbine combustor 100 of the first embodiment shown in FIG. The description of the configuration common to both is omitted, and only the differences are described below.

  In the cluster burner structure and fuel system of the gas turbine combustor 100 of this embodiment shown in FIG. 4, the gas turbine combustor 100 of this embodiment has a cluster burner 50 disposed at the center of the burner. On the outer periphery of the burner, which is the outer peripheral side, the fuel and air injected from the premixing nozzle 155 are premixed, and the premixed premixed gas is installed downstream of the premixing nozzle 155. The gas turbine combustor has a configuration in which a plurality of premix burners 157 are disposed in the combustion chamber 160 provided inside the liner 153 of the gas turbine combustor 100 to flow downstream and burn to form a premixed flame.

  The fuel supply system for the fuel supplied to the cluster burner 50 at the center of the burner of the gas turbine combustor 100 and the premix burner 157 at the outer periphery of the burner is installed in the fuel system 1 with the fuel supplied from the fuel system 1. The cluster burner outer periphery fuel system 70 is connected to the fuel system 1 at the downstream portion of the fuel shut-off valve 2 and supplies fuel to the burner outer periphery, and the cluster burner outer periphery fuel system 70 is branched from the cluster burner outer periphery fuel system 70 A cluster burner central fuel system 60 that supplies fuel and a premixed burner fuel system 75 that further branches from the cluster burner outer peripheral fuel system 70 and supplies premixed fuel to the premixed burner 157 are configured.

  The cluster burner outer periphery fuel system 70 downstream of the fuel shut-off valve 2 installed in the fuel system 1 is provided with a pressure adjusting valve 71, and the fuel whose pressure is adjusted by the pressure adjusting valve 71 is the outer periphery of the cluster burner. The fuel adjusting valve 73 installed in the partial fuel system 70 and the fuel adjusting valve 74 installed in the premixed burner fuel system 75 branched from the cluster burner outer peripheral fuel system 70, the premixed fuel of the cluster burner outer peripheral portion and the premixed burner 157 The fuel flow rate supplied to each nozzle 155 is configured to be adjusted.

  On the other hand, the cluster burner center fuel system 60 branched from the cluster burner outer periphery fuel system 70 downstream of the fuel shut-off valve 2 is provided with an orifice 61, and the fuel installed in the cluster burner outer periphery fuel system 70. Fuel supplied to the outer peripheral portion of the cluster burner and the premixed fuel nozzle 155 of the premixed burner 157 by the fuel adjusting valve 74 installed in the premixed burner fuel system 75 branched from the adjusting valve 73 and the outer peripheral fuel system 70 of the cluster burner. Since the flow rate is adjusted, the fuel system supplied to the gas turbine combustor is supplied to the center of the burner in order to improve the flame stability of the cluster burner and reduce the NOx emissions. Even when the fuel system is divided into two fuel systems, the divided fuel supply system The fuel adjusting valve need not be additionally provided, it is possible to avoid the complication, and gas turbine manufacturing cost increase in the operation control of the gas turbine combustor.

  Further, even when the fuel supply is controlled in accordance with the output of the gas turbine plant, the gas turbine combustor 100 according to the present embodiment can control the output of the gas turbine plant only by controlling the orifice 61 and the fuel adjustment valves 73 and 74. Since the corresponding fuel flow rate can be controlled, the fuel control of the gas turbine combustor can be greatly simplified. Further, the fuel flow rate is choked at the orifice 61, so that the predetermined flow rate is always kept at the center of the burner. Can be supplied stably.

  According to the present embodiment, complicated operation control of the gas turbine combustor and an increase in the manufacturing cost of the gas turbine combustor are avoided, and the combustion performance of the gas turbine combustor can be improved and the NOx emission amount can be reduced. A gas turbine combustor can be realized.

  Next, a gas turbine combustor according to a fourth embodiment of the present invention will be described with reference to FIGS.

  The cluster burner structure and fuel system of the gas turbine combustor 100 of the present embodiment shown in FIGS. 5 and 6 have the same basic configuration as those of the gas turbine combustor 100 of the first embodiment shown in FIG. Therefore, the description of the configuration common to both is omitted, and only the differences are described below.

  The gas turbine combustor 100 of the present embodiment shown in FIGS. 5 and 6 has a configuration in which one cluster burner is arranged in the center of the center of the burner axis and a plurality of multi burners are arranged on the outer periphery of the burner. ing.

  6 is an arrow view of the gas turbine combustor 100 shown in FIG. 5 as viewed from the BB direction in the combustion chamber.

  In the cluster burner structure and fuel system of the gas turbine combustor 100 of this embodiment shown in FIG. 6, the gas turbine combustor 100 of this embodiment has one cluster burner 51 arranged at the center of the burner. This gas turbine combustor has a multi-cluster structure in which a total of six cluster burners 52 are arranged on the outer periphery of the burner 51 on the outer peripheral side.

  The fuel supply system that supplies fuel to the cluster burner 51 at the center of the burner of the gas turbine combustor 100 and the six cluster burners 52 at the outer periphery of the burner is configured such that the fuel supplied from the fuel supply system 1 is the fuel system 1. The fuel is branched from the fuel system 1 at the downstream portion of the fuel shut-off valve 2 installed in the fuel supply to the central portion of the cluster burner 51 at the central portion of the burner and the central portion of the six cluster burners 52 at the outer peripheral portion of the burner. A plurality of cluster burner center fuel systems 80 are arranged.

  In the fuel supply system, a pressure adjustment valve 94 is provided in the fuel system 90 in the cluster burner outer peripheral portion connected to the fuel supply system 1 at a downstream portion of the fuel cutoff valve 2 installed in the fuel system 1. The fuel whose pressure is adjusted by 94 is further branched from the outer peripheral fuel system 90 of the cluster burner, and a fuel regulating valve 91 installed in a fuel system 90a for supplying fuel to the outer peripheral part of the cluster burner in the cluster burner 51 in the central part of the burner, In addition, each of the cluster burner 51 and the six cluster burners 52 at the outer peripheral portion of the burner is provided by the fuel regulating valves 92 installed in the plurality of fuel systems 90b for supplying fuel to the outer peripheral portion of the cluster burner in the six cluster burners 52 at the outer peripheral portion of the burner It is configured so that the fuel flow rate supplied to the outer periphery of the cluster burner is adjusted respectively. That.

  Further, the fuel supply system further branches from the cluster burner outer peripheral fuel system 90 at the downstream portion of the fuel shutoff valve 2 installed in the fuel supply system 1, and further from the cluster burner central fuel system 80 arranged in a plurality of systems. The branched fuel systems 80a and 80b are provided with orifices 81, 82 and 83, respectively.

  Further, in the cluster burner outer periphery fuel system 90 that is branched from the fuel supply system 1 at the downstream portion of the fuel shutoff valve 2 and arranged in a plurality of systems, the outer periphery of one cluster burner 51 in the center of the burner is provided. A fuel adjustment valve 91 is installed in the fuel system 90 for supplying fuel to the outer periphery of the cluster burner 90. Since the valves 92 are respectively installed, a cluster of one cluster burner 51 and six cluster burners 52 is provided by the fuel regulating valves 91 and 92 installed in the plurality of cluster burner outer peripheral fuel systems 90. Since the fuel flow rate supplied to the outer periphery of the burner is adjusted, the flame stability of the cluster burner is improved and NOx emissions are reduced. In order to reduce the amount, the fuel supply system supplied to the gas turbine combustor is divided into two fuel supply systems, a fuel supply system that supplies the burner center and a fuel supply system that supplies the burner outer periphery. However, it is possible to perform fuel control of the gas turbine combustor while avoiding complicated operation control of the gas turbine combustor and an increase in manufacturing cost of the gas turbine combustor.

  The fuel supply system of the gas turbine combustor of this embodiment is configured such that the fuel supplied from the fuel supply system 1 is divided into a central fuel system 80 of the cluster burner and a cluster burner peripheral fuel system 90 in the downstream portion of the fuel cutoff valve 2. A fuel regulating valve 91 installed in a fuel system 90a branched from the cluster burner outer peripheral fuel system 90 is provided after adjusting the fuel pressure by providing a pressure regulating valve 94 downstream of the cluster burner outer peripheral fuel system 90. Thus, the fuel supplied to the cluster burner outer periphery of the cluster burner 51 at the center of the burner is adjusted.

  Further, fuel supplied to the cluster burner outer periphery of the six cluster burners 52 on the outer periphery of the burner is adjusted by a fuel adjustment valve 92 installed in a plurality of fuel systems 90 b branched from the cluster burner outer periphery fuel system 90.

  On the other hand, an orifice 81 is provided in the fuel system 80a branched from the cluster burner center fuel system 80 and supplying fuel to the cluster burner center of the cluster burner 51 in the center of the burner, and the six cluster burners 52 in the outer periphery of the burner. A plurality of fuel systems 80b for supplying fuel to the central portion of the cluster burner are provided with orifices 82, respectively. As in the gas turbine combustor of the first embodiment, a stable fuel is always supplied regardless of the plant load. It becomes possible to supply to the central part.

  In the gas turbine combustor of the present embodiment in which the cluster burners having the above-described configuration are arranged in a multi-form, when the fuel supply system is divided into two systems in order to improve the flame stability of each cluster burner and reduce the NOx emission amount. However, it is not necessary to additionally install a fuel adjustment valve in the divided fuel supply system, and it becomes possible to avoid complication of operation control of the gas turbine combustor and increase in gas turbine manufacturing cost.

  Further, even when the fuel supply is controlled in accordance with the output of the gas turbine plant, the gas turbine combustor 100 of this embodiment can control the gas turbine plant only by controlling the orifices 81 and 82 and the fuel adjustment valves 91 and 92. Since it is possible to control the fuel flow rate corresponding to the output, the fuel control of the gas turbine combustor can be greatly simplified, and the fuel flow rate is choked by the orifices 81 and 82 installed in the divided fuel supply system. By doing so, it becomes possible to always stably supply a predetermined flow rate to the center of each cluster burner.

  According to the present embodiment, complicated operation control of the gas turbine combustor and an increase in the manufacturing cost of the gas turbine combustor are avoided, and the combustion performance of the gas turbine combustor can be improved and the NOx emission amount can be reduced. A gas turbine combustor can be realized.

  1: fuel supply system, 2: fuel cutoff valve, 10: burner center fuel system, 11, 13, 14: orifice, 12: three-way valve, 20: burner outer periphery fuel system, 21: pressure regulating valve, 22, 23 , 24: Fuel adjustment valve, 30, 31, 32: Fuel nozzle, 33: Burner plate, 34: Air hole, 40: Diffusion burner, 41: Flame holder, 42: Diffusion fuel flow, 50, 51, 52: Cluster Burner, 60: Cluster burner central fuel system, 61: Orifice, 71: Pressure regulating valve, 72: Cluster burner outer peripheral fuel system, 73: Fuel regulating valve, 80: Cluster burner central fuel system, 80a, 80b: Fuel System, 81, 82: Orifice, 90a, 90b: Fuel system, 90: Cluster burner outer peripheral fuel system, 91, 92: Fuel adjustment valve, 94: Pressure adjustment valve, 110: 120: high pressure air, 130: diffuser, 140: passenger compartment, 150: tail tube flow sleeve, 151: air introduction hole, 152: tail tube, 153: liner, 154: liner flow sleeve, 155: premixing Fuel nozzle, 156: premixed flame, 160: combustion chamber, 170: hot combustion gas flow, 180: turbine, 190: generator.

Claims (4)

A combustion chamber in which fuel and air are mixed and burned to generate combustion gas;
A burner plate having a plurality of air holes for injecting air into the combustion chamber, and a plurality of fuel nozzles for injecting fuel toward the air holes of the burner plate, wherein the fuel and the air are burned as a plurality of coaxial jets. In a gas turbine combustor including a burner having a configuration in which the fuel nozzle and the air hole are arranged coaxially so as to be jetted into a chamber,
A fuel supply system for supplying fuel to the burner is supplied to a burner central portion on the burner shaft center side, and a burner outer peripheral fuel system is supplied to a burner outer periphery on the outer peripheral side of the burner central portion. The two systems are arranged,
The burner outer peripheral fuel system is provided with a pressure adjusting valve for adjusting the pressure of the fuel and a flow rate adjusting valve for adjusting the flow rate of the fuel, respectively.
The burner central fuel system is configured to branch from the burner outer peripheral fuel system upstream of the pressure regulating valve,
A gas turbine combustor characterized in that a throttle portion for reducing the flow rate of fuel is installed in the burner central fuel system. A combustion chamber in which fuel and air are mixed and burned to generate combustion gas;
A burner plate having a plurality of air holes for injecting air into the combustion chamber, and a plurality of fuel nozzles for injecting fuel toward the air holes of the burner plate, wherein the fuel and the air are burned as a plurality of coaxial jets. In a gas turbine combustor including a burner having a configuration in which the fuel nozzle and the air hole are arranged coaxially so as to be jetted into a chamber,
A fuel supply system for supplying fuel to the burner is supplied to a burner central portion on the burner shaft center side, and a burner outer peripheral fuel system is supplied to a burner outer periphery on the outer peripheral side of the burner central portion. The two systems are arranged,
The burner outer peripheral fuel system is provided with a pressure adjusting valve for adjusting the pressure of the fuel and a flow rate adjusting valve for adjusting the flow rate of the fuel, respectively.
The burner central fuel system is configured to branch from the burner outer peripheral fuel system upstream of the pressure regulating valve,
A three-way valve is installed in the fuel system in the center of the burner, and a plurality of throttle parts that throttle the flow rate of fuel are installed on the downstream side of the three-way valve. A gas turbine combustor configured to switch a fuel system passing through a section. A combustion chamber in which fuel and air are mixed and burned to generate combustion gas;
A burner plate having a plurality of air holes for injecting air into the combustion chamber, and a plurality of fuel nozzles for injecting fuel toward the air holes of the burner plate, wherein the fuel and the air are burned as a plurality of coaxial jets. A cluster-burner having a configuration in which the fuel nozzle and the air hole are arranged coaxially so as to be ejected into a chamber;
In a gas turbine combustor having a premixed combustion burner that preliminarily mixes and burns fuel and air to form a flame on the outer peripheral side of the gas turbine combustor,
Burner center fuel system for supplying a fuel supply system for supplying fuel to the cluster burner to the burner center portion on the cluster burner axial center side, and burner outer periphery fuel to be supplied to the burner outer periphery portion on the outer periphery side of the burner center portion Two systems are arranged with the system,
A pressure adjusting valve for adjusting the fuel pressure and a flow rate adjusting valve for adjusting the fuel flow rate are installed in the burner outer peripheral fuel system,
The burner central fuel system is configured to branch from the burner outer peripheral fuel system upstream of the pressure regulating valve,
Install a throttle to throttle the fuel flow rate in the burner center fuel system,
A premix fuel supply system for supplying fuel to the premix burner is branched from the burner outer peripheral fuel system downstream of the pressure regulating valve;
A gas turbine combustor, wherein another pressure regulating valve for regulating fuel pressure is installed in the premixed fuel supply system. A combustion chamber in which fuel and air are mixed and burned to generate combustion gas;
A burner plate having a plurality of air holes for injecting air into the combustion chamber, and a plurality of fuel nozzles for injecting fuel toward the air holes of the burner plate, wherein the fuel and the air are burned as a plurality of coaxial jets. A cluster burner having a configuration in which the fuel nozzle and the air hole are arranged coaxially so as to be ejected into the chamber is formed in a multi-shape at the central portion on the axial center side of the gas turbine combustor and the outer peripheral portion of the gas turbine combustor. In the gas turbine combustor having a plurality of
A fuel supply system for supplying fuel to the cluster burner is arranged in two systems, a burner center fuel system for supplying to the burner center of the cluster burner and a burner outer periphery fuel system for supplying to the burner outer periphery,
A pressure regulating valve for adjusting the fuel pressure is installed in the burner outer peripheral fuel system,
A plurality of first fuel systems that branch from the burner outer periphery fuel system downstream of the pressure regulating valve and supply fuel to the burner outer periphery of the cluster burner;
A flow rate adjusting valve for adjusting the flow rate of the fuel is installed in each of a plurality of fuel systems that supply fuel to the outer periphery of the cluster burner,
The burner central fuel system is configured to branch from the burner outer peripheral fuel system upstream of the pressure regulating valve,
A plurality of second fuel systems that branch from the burner center fuel system and supply fuel to the burner center of the cluster burner;
A gas turbine combustor characterized in that a throttle portion for restricting a flow rate of fuel is installed in the second fuel system.

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