JP2012037104A - Gas turbine combustor - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a gas turbine combustor suppressing pressure fluctuation due to fluctuation of a flame position formed in a combustion chamber, reducing an emission amount of NOx, and improving reliability of the gas turbine combustor.SOLUTION: The gas turbine combustor includes: a plurality of fuel nozzles disposed at a head of the gas turbine combustor and injecting fuel to a combustion chamber on a downstream side; a plurality of air holes respectively disposed approximately coaxially with the plurality of fuel nozzles on a downstream side of the fuel nozzles, to introduce air to the combustion chamber; and an air hole plate having air holes formed therein and disposed between the fuel nozzles and the combustion chamber. The gas turbine combustor is provided with: a center burner positioned at the axial center of the gas turbine combustor; and a plurality of outer peripheral burners positioned on an outer periphery side of the center burner; wherein each burner is composed of a plurality of fuel nozzles and a plurality of air holes. On the surface of the air hole plate on a combustion chamber side, projections are formed enclosing the center burner and the plurality of outer peripheral burners adjacent to the center burner.

Description

  The present invention relates to the structure of a gas turbine combustor.

In a gas turbine power plant that uses fossil resources as a fuel, an improvement in power generation efficiency can be cited as a means for reducing the amount of carbon dioxide (CO ₂ ) that causes global warming. In order to improve the power generation efficiency, it is effective to increase the temperature of the combustion gas generated by the gas turbine combustor.

  However, since the emission amount of nitrogen oxide (NOx), which is an environmental pollutant, increases as the combustion gas becomes higher in temperature, it is an important technical problem to improve the power generation efficiency and reduce the NOx emission amount.

In recent years, the use of hydrogen-containing fuel has been considered from the viewpoint of preventing global warming. Since hydrogen-containing fuels emit a small amount of CO ₂ during combustion, it has been studied to effectively use coke oven gas produced as a by-product at steelworks or off-gas produced as a by-product at refineries. In addition, in an integrated coal gasification combined cycle (IGCC) that generates electricity by gasifying oxygen, which is an abundant resource, from the viewpoint of global warming prevention, Systems for separating, collecting and storing carbon are being studied both at home and abroad.

  The by-product gas as described above contains 30% to 60% of hydrogen, and the coal gasification gas that is the fuel of the IGCC plant contains 25% to 90% of hydrogen. Thus, there is an increasing demand for using hydrogen-containing fuel in gas turbine combustors.

  Since the hydrogen contained in the fuel as described above has a wide flammable range and a high combustion speed, there is a concern that a high-temperature flame is formed near the wall surface in the combustion chamber and the reliability of the combustor is impaired. Therefore, as a means for preventing the formation of a high-temperature flame locally, a method of dispersing the fuel and burning it uniformly in the combustion chamber is effective.

  JP 2003-148734 A includes a plurality of fuel nozzles and a plurality of air holes as a method for increasing the dispersibility of fuel with respect to air and reducing NOx emissions, and is formed on the fuel flow and the outer peripheral side of the fuel flow. A technique of a gas turbine combustor in which a plurality of burners for injecting the air flow into a combustion chamber is arranged is disclosed.

  In JP 2010-065963 A, a plurality of burners having a structure in which the arrangement of air holes provided in the air plate of the gas turbine combustor disclosed in JP 2003-148734 A is improved are arranged. A gas turbine combustor is disclosed, and a technique for suppressing the adhesion of a flame to an air hole plate provided with air holes is disclosed.

JP 2003-148734 A JP 2010-065963 A

  In the technology related to the gas turbine combustor described in Japanese Patent Application Laid-Open No. 2003-148734 and Japanese Patent Application Laid-Open No. 2010-065963, the flame position formed in the combustion chamber of the combustor fluctuates due to a certain kind of disturbance. Pressure fluctuations can occur. When this pressure fluctuation occurs, it becomes a cause of reducing the reliability of the gas turbine combustor.

  An object of the present invention is to provide a gas turbine combustor that suppresses pressure fluctuation due to fluctuation of a flame position formed in a combustion chamber, reduces NOx emissions, and improves the reliability of the gas turbine combustor. is there.

  The gas turbine combustor according to the present invention includes a plurality of fuel nozzles installed at the head of the gas turbine combustor for injecting fuel into a downstream combustion chamber, and the fuel nozzles so as to be substantially coaxial with the plurality of fuel nozzles. A plurality of air holes that are respectively arranged on the downstream side of the air to guide the air to the combustion chamber, and an air hole plate in which the air holes are formed and disposed between the fuel nozzle and the combustion chamber. A plurality of fuel nozzles and a plurality of air holes, each of which is provided with a central burner positioned at the axial center of the gas turbine combustor and a plurality of outer peripheral burners positioned on the outer peripheral side of the central burner. The chamber-side air hole plate is provided with a protrusion that surrounds or separates the central burner and a plurality of peripheral burners adjacent to the central burner.

  The gas turbine combustor according to the present invention includes a plurality of fuel nozzles installed at the head of the gas turbine combustor for injecting fuel into a downstream combustion chamber, and the fuel nozzles so as to be substantially coaxial with the plurality of fuel nozzles. A plurality of air holes respectively arranged on the downstream side of the nozzle to guide air to the combustion chamber, and an air hole plate in which the air holes are formed and disposed between the fuel nozzle and the combustion chamber. A plurality of fuel nozzles and a plurality of the air holes, and a central burner located at the axial center of the gas turbine combustor and a plurality of outer peripheral burners located on the outer peripheral side of the central burner, Protrusions surrounding the outer periphery of the central burner and a plurality of outer peripheral burners adjacent to the central burner are provided on the surface of the air hole plate on the combustion chamber side.

  The gas turbine combustor according to the present invention includes a plurality of fuel nozzles installed at the head of the gas turbine combustor for injecting fuel into a downstream combustion chamber, and the fuel nozzles so as to be substantially coaxial with the plurality of fuel nozzles. A plurality of air holes respectively arranged on the downstream side of the nozzle to guide air to the combustion chamber, and an air hole plate in which the air holes are formed and disposed between the fuel nozzle and the combustion chamber. A plurality of fuel nozzles and a plurality of the air holes, and a central burner located at the axial center of the gas turbine combustor and a plurality of outer peripheral burners located on the outer peripheral side of the central burner, The pilot burner has an inclined surface in which the surface of the air hole plate on the combustion chamber side is inclined concavely toward the axial center of the combustor, and an oil nozzle is provided at the center of the pilot burner, and the combustion Wherein the surface of the side of the air hole plate central burner, and encloses a plurality of outer circumferential burners adjacent to the central burner, or characterized in that a partition for projection.

ADVANTAGE OF THE INVENTION According to this invention, the gas turbine combustor which suppresses the pressure fluctuation | variation by the fluctuation | variation of the flame position formed in a combustion chamber, and improves the reliability of a gas turbine combustor is realizable.

The longitudinal cross-sectional view which shows the structure of the air hole plate installed in the gas turbine combustor which is 1st Example of this invention. The front view which looked at the air hole plate installed in the gas turbine combustor which is 1st Example of this invention from the combustion chamber side of the gas turbine combustor. BRIEF DESCRIPTION OF THE DRAWINGS The schematic block diagram of the gas turbine plant provided with the gas turbine combustor which is 1st Example of this invention. The schematic of the flow and flame which are formed in the combustion chamber downstream of the air hole plate installed in the gas turbine combustor which is 1st Example 1 of this invention. Flow direction fuel concentration distribution schematic of each burner (space average value of cross section perpendicular to the flow direction) The longitudinal cross-sectional view which shows the structure of the air hole plate installed in the gas turbine combustor which is 2nd Example of this invention. The longitudinal cross-sectional view which shows the structure of the air hole plate installed in the gas turbine combustor which is 3rd Example of this invention. The front view which looked at the air hole plate installed in the gas turbine combustor which is 3rd Example of this invention from the combustion chamber side of the gas turbine combustor. The schematic block diagram of the gas turbine plant provided with the gas turbine combustor which is 3rd Example of this invention.

  A gas turbine combustor which is an embodiment of the present invention will be described below with reference to the drawings.

  A gas turbine combustor according to a first embodiment of the present invention will be described with reference to FIGS.

  1 and 2 are a longitudinal sectional view and a front view showing the structure of an air hole plate installed in a gas turbine combustor according to a first embodiment of the present invention, and FIG. 3 is a gas turbine having the air hole plate. It is a schematic block diagram which shows the gas turbine plant provided with the combustor.

  First, the gas turbine plant 1 having the gas turbine combustor 3 according to the first embodiment of the present invention will be described with reference to FIG. 3. The gas turbine plant 1 takes in the intake air 101 from the atmosphere and compresses it. The compressor 2, the gas turbine combustor 3 that generates the high-temperature combustion gas 110 by burning the compressed air 102 compressed by the air compressor 2 and the gas fuel 200 in the combustion chamber 5, and the combustion of the gas turbine combustor 3 A turbine 4 that guides and drives the high-temperature combustion gas 110 generated in the chamber 5, a generator 6 that rotates by driving the turbine 4 to generate electric power, and a gas turbine activation motor 7 that activates the air compressor 2 when the gas turbine is activated. It has.

  The combustion gas 110 after driving the turbine 4 becomes exhaust gas 111 and is exhausted from the turbine 4.

  The head of the gas turbine combustor 3 has one central burner 32 positioned at the axial center of the combustor 3 and a plurality of outer peripherals (six in the embodiment shown in FIG. 2) positioned on the outer peripheral side of the central burner 32. A burner 33 is provided, and an air hole plate 20 provided with a plurality of air holes 21 for guiding the compressed air 102 a to the combustion chamber 5 in the central burner 32 and the outer peripheral burner 33, and upstream of the air hole plate 20. The plurality of fuel nozzles 22 are arranged on the side and inject the gas fuel 200 into the plurality of air holes 21 of the air hole plate 20.

  A plurality of air holes 21 provided in the air hole plate 20 and a plurality of fuel nozzles 22 provided in the air hole plate 20 are arranged substantially coaxially so as to correspond to each other. It is provided through the hole plate 20.

  In addition, the central burner 32 and the six outer peripheral burners 33 include a first row air hole group 41 in which four air holes 21 are arranged in an annular shape, and eight outer air holes 21 on the outer peripheral side of the first row air hole group 41. Three rows of air hole groups 41, 42, 43, each comprising a second row air hole group 42 arranged and 12 third row air hole groups 43 arranged on the outer peripheral side of the second row air hole group 42, respectively. It is arranged.

  The upstream side of the air hole groups 41, 42, 43 in the row provided in the central burner 32 and the outer peripheral burner 33 is associated with the air holes 21 of these air hole groups 41, 42, 43. The fuel nozzles 22 are arranged so as to be substantially coaxial with the fuel nozzles 21. The fuel is sprayed into the air flow flowing down from the fuel nozzles 22 through the air holes 21, thereby mixing the fuel and air mixture. It is configured to form.

  The center axis of the air hole constituting each air hole group 41, 42, 43 disposed on the air hole plate 20 is formed to be inclined in the circumferential direction of the pitch circle of the air hole group 41, 42, 43, respectively. Therefore, the flow of air that passes through the air holes 21 of the air hole groups 41, 42, 43 and flows down to the combustion chamber 5 forms a swirl flow that spirally swirls at a position downstream of the air holes 21.

  In order to improve the dispersibility of the fuel supplied to the combustion chamber 5, the number of outer peripheral burners 33 is two or more, the number of air hole groups arranged in the central burner 32 and the outer peripheral burner 33 is two or more, and stable. In order to create a swirl flow, the number of air holes 21 in each air hole group is preferably four or more.

As described above, the gas turbine combustor 3 is constituted by a plurality of burners including the central burner 32 and the outer peripheral burner 33 installed on the outer peripheral side of the central burner 32, so that the turbine combustion corresponding to a wide range of gas turbine loads can be achieved. A vessel 3 is obtained.
Next, a fuel system for supplying the gas fuel 200 to the central burner 32 of the gas turbine combustor 3 and the plurality of outer peripheral burners 33 located outside the central burner 32 will be described.
The plurality of fuel nozzles 22 provided in the gas turbine combustor 3 are connected to a fuel header 23 provided at the head of the gas turbine combustor 3 with a fuel system that supplies the gas fuel 200 to the gas turbine combustor 3. The fuel header 23 is configured to distribute the gas fuel 200 supplied to the fuel nozzle 22 through the fuel system to a plurality of fuel nozzles 22 provided in the gas turbine combustor 3.

  The gas turbine combustor 3 used in the gas turbine plant 1 of the present embodiment uses hydrogen-containing fuel such as coke oven gas, refinery off-gas, coal gasification gas, or natural gas as the gas fuel 200.

  Next, the fuel system in the case where the gas fuel 200 is divided into three to be supplied to the plurality of fuel nozzles 22 of the gas turbine combustor 3 provided in the gas turbine plant 1 of the present embodiment will be described with reference to FIG.

  In the gas turbine combustor 3 of the present embodiment shown in FIG. 3, a fuel system 200 a that supplies the gas fuel 200 to the gas turbine combustor 3 is branched into three fuel systems downstream of the fuel cutoff valve 60. One of the fuel systems 203 a branched into three is divided into a central burner 32 installed at the center of the axis of the gas turbine combustor 3, and the remaining two fuel systems 201 a and 205 a branched into three are connected to the central burner 32. The fuel 200 is supplied by connecting to six outer peripheral burners 33 installed on the outer peripheral side.

  Among the fuel systems branched into three, one fuel system 203a further has a fuel system 204a branched from the middle thereof, and the fuel system 203a is a first row air hole group provided in the central burner 32. The gas fuel 203 is connected to the fuel nozzles 22 corresponding to the air holes 21 of 41 and supplied to the fuel nozzles 22.

  The fuel system 204a branched from the fuel system 203a is connected to the fuel nozzles 22 corresponding to the air holes 21 of the second and third air hole groups 42 and 43 provided in the central burner 32, so that the gas fuel 204 is supplied to the fuel nozzle 22.

  Similarly, among the two fuel systems branched into three, the remaining two fuel systems 201a and 205a are further branched from the middle of the fuel systems 202a and 206a, respectively. The gas fuels 201 and 205 are connected to the fuel nozzles 22 corresponding to the air holes 21 of the first-row air hole group 41 provided in 33 and supplied to the fuel nozzles 22 respectively.

  The fuel systems 202a and 206a branched from the fuel systems 201a and 205a are respectively connected to the fuel nozzles 22 corresponding to the air holes 21 of the second and third air hole groups 42 and 43 provided on the outer peripheral burner 33. Connected to supply gas fuels 202 and 206 to the fuel nozzle 22, respectively.

  Each fuel system 201a, 202a, 203a, 204a, 205a, 206a has a fuel pressure adjustment valve 61a, 62a, 63a, 64a, 65a, 66a for adjusting the pressure of the fuel 200, and a fuel flow rate for adjusting the flow rate of the fuel 200. Regulating valves 61b, 62b, 63b, 64b, 65b, 66b are respectively provided, and the fuel pressure regulating valve and the fuel flow regulating valve are controlled by an operation signal according to the load of the gas turbine device output from the control device 100. The opening degree is controlled, and the pressure and flow rate of the gas fuels 201, 202, 203, 204, 205, 206 supplied to the fuel nozzles 22 are respectively adjusted.

As described above, in the gas turbine combustor 3 of the present embodiment, the degree of freedom of operation of the gas turbine combustor 3 is increased by configuring the fuel system that supplies gas fuel to the fuel nozzle 22 with a plurality of branched fuel systems. Can be enlarged.
Next, the structure of the air hole plate 20 of the gas turbine combustor 3 of the present embodiment will be described in more detail with reference to FIGS. 1 to 3.
In the gas turbine combustor 3 of this embodiment, the combustion chamber side surface 301 of the air hole plate 20 installed in the gas turbine combustor 3 has a combustion chamber of the air hole plate 20 as shown in FIGS. An annular central protrusion 310 is provided between the central burner 32 and the outer peripheral burner 33 on the side surface 301 so as to surround the outer periphery of the central burner 32, and the adjacent outer peripheral burner 33 is interposed between the adjacent outer peripheral burners 33. The outer peripheral projection 311 that is divided and connected to the central projection 310 is provided.

  An annular central protrusion 310 disposed so as to surround the outer periphery of the central burner 32 is a flame of a flame formed by the central burner 32 and a flame formed by each of the plurality of outer peripheral burners 33 disposed on the outer periphery of the central burner 32. It functions to prevent interference.

  Further, the outer peripheral projections 311 that are installed between the adjacent outer peripheral burners 33 arranged on the outer periphery of the central burner 32 and that separate the adjacent outer peripheral burners 33 interfere with each other with the flames formed by the adjacent outer peripheral burners 33. It functions to prevent flame interference.

  The cross-sectional shapes of the central protrusion 310 and the outer peripheral protrusion 311 provided on the combustion chamber side surface 301 of the air hole plate 20 are each formed in a rectangular shape as shown in FIG.

  The size of the cross-sectional shape of the central protrusion 310 and the outer peripheral protrusion 311 is as follows. The length in the direction perpendicular to the air hole plate 20 is H, the length in the parallel direction is L, and the air hole diameter of the air hole 21 is da. The range of the length H in the direction perpendicular to the air hole plate 20 of the central protrusion 310 and the outer peripheral protrusion 311 can be defined as H ≦ 5da.

  In each air hole group 41, 42, 43 of the air hole 21 of the air hole 21 provided in the central burner 32 and the outer peripheral burner 33 of the air hole plate 20, the air on the combustion chamber side surface 301 of the air hole plate 20. The inter-hole distances Dc2 and Do2 (the pitch circle diameter of each air hole group) are smaller than the air-hole distances Dc1 and Do1 on the surface 300 on the air hole plate end cover 13 side, as shown in FIG. ing. That is, Dc1 <Dc2, Do1 <Do2.

  Next, the operation and effect of the air hole plate 20 provided in the gas turbine combustor 3 of the present embodiment will be described with reference to FIG.

  FIG. 4 shows the combustion downstream of the air hole plate 20 in the gas turbine combustor 3 provided with a protrusion protruding into the combustion chamber 5 on the combustion chamber side surface of the air hole plate 20 provided in the gas turbine combustor 3 according to this embodiment. FIG. 2 shows a schematic view of the flow of flow formed in the chamber 5 and the flame formed.

  In the gas turbine combustor 3 of the present embodiment, the swirl flow formed by the air holes 21 arranged in each row is downstream of the central burner 32 and the outer peripheral burner 33 arranged around the central burner 32. Since the swirl axis is at the center of the burner, the swirl flows merge with each other to form one swirl flow having the rotation axis at the center of the burner.

  In the gas turbine combustor 3 according to the present embodiment, a swirl flow is formed downstream of each of the central burner 32 installed and the six outer peripheral burners 33 installed around the central burner 32. A total of seven swirling flows are formed. In each swirl flow, since the distance between the air holes on the combustion chamber side 301 of each air hole group is smaller than the distance between the air holes on the end cover side 300, the swirl radius is gradually reduced to the point P shown in the figure. While erupting.

The swirl flow proceeds further downstream in the combustion chamber 5, and from the point P, the swirl radius increases. The swirl flow envelope flowing in this way is shown as a flow line 80. The flow line 80 shows the envelope of the swirl flow mainstream component in the cross section of the combustor in a cross section including the burner center. is there.
Due to the swirling flow, the flame is held with the point P at a position away from the air hole plate 20 as a flame holding point 81, and a flame floating from the air hole plate 20 is formed. The flame formed by the central burner 32 is referred to as a central burner flame 82, and the flame formed by the outer peripheral burner 33 is referred to as an outer peripheral burner flame 83.

  By the formation of the floating flame, it is possible to reduce the adhesion of the flame to the air hole plate 20 particularly for the hydrogen-containing fuel having a high combustion speed. Furthermore, since the distance from the outlet of the air hole plate 20 to the flame surface 84 where the fuel and air are mixed is extended, the mixing is promoted and the NOx emission amount is reduced.

  In the gas turbine combustor 3 of the present embodiment, an annular central protrusion 310 is provided between the central burner 32 and the outer peripheral burner 33 on the combustion chamber side surface 301 of the air hole plate 20 so as to surround the outer periphery of the central burner 32. In addition, since the adjacent outer peripheral burner 33 is divided between the adjacent outer peripheral burners 33 and the outer peripheral protrusion 311 connected to the central protrusion 310 is provided, the combustion gas 90 is generated in the outer peripheral wake 85. Inflow can be prevented.

  That is, in order to cope with a wide range of gas turbine loads, in the gas turbine combustor 3 in which the burner provided in the gas turbine combustor 3 is composed of a central burner 32 and a plurality of outer peripheral burners 33 on the outer peripheral side thereof, There is a possibility that the combustion gas 90 flows from the central burner flame 82 formed in the wake of the central burner 32 into the wake of the second and third row air holes of the outer burner 33 (outer wake 85). .

  Since an air-fuel mixture in the combustible range exists in the outer peripheral wake 85, if a high-temperature fluid (combustion gas 90) serving as an ignition source flows into the outer wake 85, the air-fuel mixture is ignited and pressure is increased. A wave will be emitted.

  That is, a pressure fluctuation occurs due to a change in the flame position, and this pressure fluctuation causes a decrease in the reliability of the gas turbine combustor. Such flame interference between the burners may occur also between the adjacent outer peripheral burners 33.

  On the other hand, in the gas turbine combustor 3 of the present embodiment, the central protrusion 310 is provided on the combustion chamber side surface 301 of the air hole plate 20, so that the combustion gas 90 serving as an ignition source is on the outer peripheral side wake. As a result, the air-fuel mixture in the outer peripheral side wake 85 can be accelerated without mixing and flow downstream to reach the flame surface 84 and perform lean combustion. The flame propagates from the flame holding point P and extends along the flame surface 84.

  Next, referring to FIG. 4, the flow of the mixture of fuel and air formed in the combustion chamber 5 downstream of the air hole plate 20 provided in the gas turbine combustor 3 of the present embodiment and the flame formed. Explain the situation.

  As shown in FIGS. 1 to 3, the gas turbine combustor 3 of the present embodiment has a center on the combustion chamber side surface 301 of the air hole plate 20 in order to prevent flame interference between the burners of the gas turbine combustor 3. An annular central protrusion 310 is provided between the burner 32 and the outer peripheral burner 33 disposed on the outer peripheral side of the central burner 32, and an outer peripheral protrusion 311 is provided between the adjacent outer peripheral burners 33. It has a configuration.

  By providing the central protrusion 310 on the combustion chamber side surface 301 of the air hole plate 20, the combustion gas 90 of the central burner flame 82 formed in the combustion chamber 5 on the downstream side of the central burner 32 is It is possible to prevent the outer peripheral burner 33 formed in the downstream combustion chamber 5 from flowing into the wake of the second and third rows of air holes (outer peripheral wake 85).

  As a result, the amount of NOx discharged from the gas turbine combustor is reduced, and the fuel in the outer peripheral wake 85 formed in the vicinity of the air plate 20 on the downstream side of the outer peripheral burner 33 provided in the gas turbine combustor. Turbine combustion with improved reliability of the gas turbine combustor by preventing the ignition of the mixture of air and air and preventing the pressure fluctuation of the gas turbine combustor caused by the ignition of this mixture Can be realized.

  In addition, the outer peripheral projection 311 located between the adjacent outer peripheral burners 33 provided on the combustion chamber side surface 301 of the air hole plate 20 provided in the gas turbine combustor 3 of the present embodiment is connected to the downstream side of the central burner 32. Since the combustion gas 90 of the central burner flame 82 formed in the combustion chamber 5 is prevented from flowing between the adjacent outer burners 33, pressure fluctuations generated in the outer burners 33 can be prevented.

  Further, a central burner flame 82 formed in the combustion chamber 5 on the downstream side of the central burner 32 and an outer peripheral burner flame 83 formed in the combustion chamber 5 on the downstream side of the outer peripheral burner 33 are arranged in the combustion chamber 5. Therefore, the fuel and air mixture spouted from the air hole plate 20 is promoted to the point P and discharged from the gas turbine combustor 3. NOx emissions can be reduced.

Next, in each rectangular cross section of the central protrusion 310 and the outer peripheral protrusion 311 provided on the combustion chamber side surface 301 of the air hole plate 20 provided in the gas turbine combustor 3 of the present embodiment, it is perpendicular to the surface of the air hole plate 20. When the length in the direction is H, the length in the parallel direction is L, and the air hole diameter of the air hole 21 is da, the length in the direction perpendicular to the air hole plate 20 that defines each rectangular cross section of the central protrusion 310 and the outer peripheral protrusion 311 The range of the height H can be defined as H ≦ 5da.
That is, the reason why the length H of the protrusion in the direction perpendicular to the air hole plate 20 defining the rectangular cross sections of the central protrusion 310 and the outer peripheral protrusion 311 is determined as H ≦ 5da is as follows.

  FIG. 5 is a schematic view of the fuel concentration distribution in the flow direction of the air-fuel mixture (space average value in a cross section perpendicular to the flow direction) in each burner of the central burner 32 and the outer peripheral burner 33 provided in the gas turbine combustor 3 of the present embodiment. Indicates.

  As shown in FIG. 5, the fuel and air are gradually mixed in the air holes 21 (from the air hole inlet to the air hole outlet) of the air plate 20, and the fuel concentration decreases. The jet of fuel and air rapidly expands at the air hole outlet, and the fuel and air rapidly mix, so the fuel concentration decreases rapidly.

  The fuel concentration becomes a substantially constant value downstream of the air hole plate 20 at a position 5 da away from the combustion chamber side surface 301 into the combustion chamber 5. In this way, in the region where the fuel concentration is almost constant, there is no portion where the fuel concentration is locally high, and the combustion speed does not increase rapidly, so the flame does not return upstream.

  Therefore, it is preferable to adopt a value of 5 da or less for the length H of one side of the rectangular cross section of the protrusions of the central protrusion 310 and the outer peripheral protrusion 311.

  According to the gas turbine combustor of the present embodiment, a gas turbine combustor that improves the reliability of the gas turbine combustor by suppressing the pressure fluctuation due to the fluctuation of the flame position formed in the combustion chamber can be realized.

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

Since the basic configuration of the gas turbine combustor 3 of the present embodiment is the same as that of the gas turbine combustor of the first embodiment described in FIGS. 1 to 5, the description of the configuration common to both is omitted. Only the differences will be described.
FIG. 6 shows a longitudinal sectional view of the air hole plate 20 provided in the gas turbine combustor 3 according to the second embodiment of the present invention.
In the gas turbine combustor 3 of this embodiment, the corners of the projections of the central projection 310 and the outer circumferential projection 311 provided on the combustion chamber side surface 301 of the air plate 20 are formed in a curved shape.
The range of the length H of the protrusion in the direction perpendicular to the air hole plate 20 that defines the shape of each rectangular cross section of the central protrusion 310 and the outer peripheral protrusion 311 provided on the combustion chamber side surface 301 of the air plate 20 of this embodiment. Is defined as H ≦ 5da, which is the same as the case of the central protrusion 310 and the outer peripheral protrusion 311 provided on the combustion chamber side surface 301 of the air plate 20 in the gas turbine combustor 3 of the first embodiment.

  In the air plate 20 of the gas turbine combustor 3 of the first embodiment, the corners of the tip portions of the central protrusion 310 and the outer peripheral protrusion 311 are formed in an edge shape. When heated by being exposed to a high-temperature combustion gas, there is a possibility that the structural reliability of the corners of the protrusions is lowered.

Therefore, in the air plate 20 of the gas turbine combustor 3 of the present embodiment, the corners of the projections of the central projection 310 and the outer circumferential projection 311 are formed in a curved shape, and therefore the effect of suppressing the above-described deterioration in structural reliability There is.
Regarding the effect of preventing the pressure fluctuation of the gas turbine combustor 3, if the range of the length H of the protrusions of the central protrusion 310 and the outer peripheral protrusion 311 of the air plate 20 is H ≦ 5da, For the reason explained in the case of the gas turbine combustor 3, pressure fluctuation caused by flame interference between burners of the gas turbine combustor 3 can be prevented, NOx emission amount can be reduced, and the reliability of the gas turbine combustor can be improved. .

  In the gas turbine combustor 3 of the present embodiment, the corners of the protrusions of the rectangular cross section of the central protrusion 310 and the outer peripheral protrusion 311 of the air plate 20 provided in the gas turbine combustor 3 are formed in a curved shape to form the protrusions. Since the corners that are easily subjected to heat transfer are eliminated, it is possible to avoid the occurrence of thermal deformation or melting in the protrusions, and thus the reliability of the gas turbine combustor 3 can be improved.

  According to the gas turbine combustor of the present embodiment, a gas turbine combustor that improves the reliability of the gas turbine combustor by suppressing the pressure fluctuation due to the fluctuation of the flame position formed in the combustion chamber can be realized.

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

Since the basic configuration of the gas turbine combustor 3 of the present embodiment is the same as that of the gas turbine combustor of the first embodiment described in FIGS. 1 to 5, the description of the configuration common to both is omitted. Only the differences will be described.
7 and 8 are structural views of the air hole plate 20 provided in the gas turbine combustor 3 according to the third embodiment of the present invention. FIG. 7 shows the air hole plate 20 of the gas turbine combustor 3. FIG. 8 is a longitudinal sectional view, and FIG. 8 is a front view of the air hole plate 20 of the gas turbine combustor 3.
In the gas turbine combustor 3 of the present embodiment, a ring-shaped central protrusion 310 surrounding the central burner 32 and a ring-shaped outer peripheral protrusion surrounding the outer peripheral burner 33 on the combustion chamber side surface 301 of the air hole plate 20. 311 is installed.

  The cross-sectional shapes of the central protrusion 310 and the outer peripheral protrusion 311 provided on the combustion chamber side surface 301 of the air hole plate 20 are on the combustion chamber side surface 301 of the air hole plate 20 provided in the gas turbine combustor 3 of the first embodiment. The projections have the same rectangle as the central projection 310 and the outer peripheral projection 311, and the length H of the projection in which the central projection 310 and the outer peripheral projection 311 extend in the direction perpendicular to the surface of the air hole plate 20 is also the first range. As in the case of the gas turbine combustor 3 of the embodiment, H ≦ 5da is set.

  In the central projection 310 and the outer peripheral projection 311 of the air hole plate 20 provided in the gas turbine combustor 3 of the present embodiment, as shown in FIG. 7, cooling holes 320 that pass through the air hole plate 20 are provided. Each has.

  The cooling holes 320 provided in the ring-shaped central protrusion 310 and the outer peripheral protrusion 311 are formed so that air flows from the air hole plate end cover side surface 300 toward the air hole plate combustion chamber side surface 301. Yes.

  Also in the gas turbine combustor 3 of the present embodiment, the central protrusion 310 provided on the combustion chamber side surface 301 of the air hole plate 20 includes a flame formed by the central burner 32 and a plurality of peripheral protrusions disposed on the outer periphery of the central burner 32. The outer peripheral burner 33 functions to prevent flame interference with the flames formed respectively.

  Further, the outer peripheral projection 311 provided on the combustion chamber side surface 301 of the air hole plate 20 is a flame interference in which flames formed by a plurality of adjacent outer peripheral burners 33 provided on the outer peripheral side of the central burner 32 interfere with each other. It functions to prevent.

Therefore, for the same reason as described in the gas turbine combustor 3 of the first embodiment, in the gas turbine combustor 3 of the present embodiment, it is possible to prevent the pressure fluctuation caused by the flame interference between the burners of the gas turbine combustor 3. Therefore, it is possible to improve the reliability of the combustor while reducing the NOx emission amount.
Further, since the central protrusion 310 and the outer peripheral protrusion 311 have a ring shape, the degree of stress concentration due to heating by the approaching flame is reduced.

  Since the central protrusion 310 and the outer peripheral protrusion 311 of the air plate 20 provided in the gas turbine combustor 3 of the present embodiment are provided with cooling holes 320 that pass through the protrusions 310 and 311, The central protrusion 310 and the outer peripheral protrusion 311 can be cooled by the air flowing through the cooling holes 320 provided in the central protrusion 310 and the outer peripheral protrusion 311.

  As a result, in the gas turbine combustor 3 of the present embodiment, the structural reliability of the protrusions of the central protrusion 310 and the outer peripheral protrusion 311 can be ensured.

  According to the gas turbine combustor of the present embodiment, a gas turbine combustor that improves the reliability of the gas turbine combustor by suppressing the pressure fluctuation due to the fluctuation of the flame position formed in the combustion chamber can be realized.

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

Since the basic configuration of the gas turbine combustor 3 of the present embodiment is the same as that of the gas turbine combustor of the first embodiment described in FIGS. 1 to 5, the description of the configuration common to both is omitted. Only the differences will be described.
FIG. 9 shows a schematic configuration of a gas turbine plant 1 including a gas turbine combustor 3 according to a fourth embodiment of the present invention. In the gas turbine combustor 3 of the present embodiment, a pilot burner 34 having an inclined surface in which the combustion chamber side surface 301 of the air hole plate 20 is inclined concavely toward the central axis is provided at the axial center of the gas turbine combustor 3. An oil nozzle 40 mainly used at the time of ignition / acceleration is disposed at the center of the pilot burner 34. A plurality of outer peripheral burners 33 are arranged around the outer periphery of the pilot burner 34.

  On the combustion chamber side surface 301 of the air hole plate 20 provided on the downstream side of the fuel nozzle 22 of the gas turbine combustor 3, an annular ring is disposed between the pilot burner 34 and the outer peripheral burner 33 so as to surround the pilot burner 34. The central protrusion 310 is installed, and an outer peripheral protrusion 311 that separates the adjacent outer peripheral burners 33 is installed between the adjacent outer peripheral burners 33.

  The structure and arrangement of the central protrusion 310, the outer peripheral protrusion 311 and the outer peripheral burner 33 installed on the combustion chamber side surface 301 of the air hole plate 20 provided in the gas turbine combustor 3 are the same as those in the gas turbine combustor 3 of the first embodiment. Is the same as

  The surface on the combustion chamber side of the pilot burner 34 provided in the gas turbine combustor 3 of the present embodiment has an inclined surface that is concavely inclined toward the central axis. This is sometimes to facilitate ignition of the outer peripheral burner 33.

  In the gas turbine combustor 3 of the present embodiment, as with the gas turbine combustor 3 of the first embodiment, each fuel system 201a, 202a, 203a, 204a, 205a, 206a has a fuel pressure that adjusts the pressure of the fuel 200. Adjusting valves 61 a, 62 a, 63 a, 64 a, 65 a, 66 a and fuel flow rate adjusting valves 61 b, 62 b, 63 b, 64 b, 65 b, 66 b for adjusting the flow rate of the fuel 200 are respectively provided and output from the control device 100. The gas fuels 201, 202, 203, 204, 205, which are supplied to the fuel nozzles 22 by controlling the valve openings of the fuel pressure adjusting valve and the fuel flow rate adjusting valve according to an operation signal corresponding to the load of the gas turbine device. It is comprised so that the pressure and flow volume of 206 may each be adjusted.

  In the gas turbine combustor 3 of the present embodiment, a fuel system 210a that supplies the starting fuel 210 to the oil nozzle 40 provided in the pilot burner 34, a fuel shut-off valve 59, a fuel pressure adjustment valve to the fuel system 210a. 67a and a fuel flow rate adjustment valve 67b. The fuel cutoff valve 59, the fuel pressure adjustment valve 67a, and the fuel flow rate adjustment valve 67b are also controlled so that the valve opening degree is controlled by an operation signal output from the control device 100. It is configured.

  As the starting fuel 210 supplied to the oil nozzle 40 of the pilot burner 34 through the fuel system 210a, oil fuel such as kerosene or A heavy oil is used.

  The gas turbine combustor 3 of the present embodiment is operated from the start up to the rated load by the following method. First, the starter fuel 210 is combusted by the pilot burner 34 to ignite / increase the speed, and the engine is operated by fueling the starter fuel to a low load condition.

  When the operation of the gas turbine device is under a low load condition, the combustion mode of the pilot burner 34 of the gas turbine combustor 3 is switched from oil burning to gas burning. And after switching to gas-only burning, the load of a gas turbine apparatus is raised by supplying gas fuel to three of the outer periphery burners 33 further. Then, all the burners of the six outer peripheral main burners 33 are burned up to the rated load condition of the gas turbine device by supplying gas fuel to the remaining three outer peripheral main burners 33.

  In order to facilitate ignition of the outer peripheral burner 33, the combustion chamber side surface of the pilot burner 34 is inclined toward the burner central axis to facilitate flame propagation. For this purpose, the second and third rows of the outer peripheral burner 33 are arranged. There is a concern that the combustion gas easily flows from the flame of the pilot burner 34 to the downstream of the air hole, and the air-fuel mixture in the combustible range existing in the downstream ignites to cause pressure fluctuation.

  Therefore, in the gas turbine combustor 3 of the present embodiment, the central protrusion 310 and the outer peripheral protrusion 311 are provided on the combustion chamber side surface 301 of the air hole plate 20 to prevent the inflow of the combustion gas to the wake. The pressure fluctuation is prevented from occurring in the turbine combustor 3.

  Moreover, the cross-sectional shape of the center protrusion 310 and the outer peripheral protrusion 311 provided on the combustion chamber side surface 301 of the air hole plate 20 is the combustion chamber side surface 301 of the air hole plate 20 provided in the gas turbine combustor 3 of the first embodiment. The upper projection has the same rectangular shape as the central projection 310 and the outer peripheral projection 311, and the range of the length H of the projection in which the central projection 310 and the outer peripheral projection 311 extend in the direction perpendicular to the surface of the air hole plate 20 is As in the case of the gas turbine combustor 3 of the first embodiment, H ≦ 5da is set.

  The protrusion length H of the central protrusion 310 and the outer peripheral protrusion 311 provided on the air hole plate 20 does not hinder ignition of the outer peripheral burner 33 by setting a value in a range of H ≦ 5da.

  In the gas turbine combustor 3 of the present embodiment, the formation of a flame is easy and it is difficult to be affected by a disturbance, so that it is possible to stably maintain low NOx combustion.

  According to the gas turbine combustor of the present embodiment, a gas turbine combustor that improves the reliability of the gas turbine combustor by suppressing the pressure fluctuation due to the fluctuation of the flame position formed in the combustion chamber can be realized.

  The present invention can be applied to a gas turbine combustor.

  1: gas turbine plant, 2: air compressor, 3: combustor, 4: turbine, 5: combustion chamber, 6: generator, 7: motor for starting gas turbine, 10: outer cylinder, 12: main chamber liner, 13: Combustor end cover, 20: Air hole plate, 21: Air hole, 22: Fuel nozzle, 23: Fuel header, 30: Burner central part, 31: Burner outer peripheral part, 32: Central burner, 33: Outer peripheral burner, 34: Pilot burner, 40: Oil nozzle, 41: First row air hole group, 42: Second row air hole group, 43: Third row air hole group, 59, 60: Fuel shut-off valve, 61a, 62a, 63a 64a, 65a, 66a, 67a: fuel pressure regulating valve, 61b, 62b, 63b, 64b, 65b, 66b, 67b: fuel flow regulating valve, 80: streamline of axial velocity of swirling flow in the cross section of the combustor, 81: Flame holding point 82: central burner flame, 83: outer burner flame, 84: flame surface, 85: outer wake, 90: combustion gas, 100: control device, 101: air, 102, 102a: compressed air, 103: cooling air, 110: Combustion gas, 111: Exhaust gas, 200, 201, 202, 203, 204, 205, 206a: Gas fuel, 200a, 201a, 202a, 203a, 204a, 205a, 206a, 210a: Fuel system, 210: For activation Fuel, 300: air hole plate end cover side surface, 301: air hole plate combustion chamber side surface, 310: central protrusion, 311: outer peripheral protrusion, 320: cooling hole.

Claims (10)

A plurality of fuel nozzles installed at the head of the gas turbine combustor for injecting fuel into a downstream combustion chamber, and disposed downstream of the fuel nozzles so as to be substantially coaxial with the plurality of fuel nozzles. A plurality of air holes for guiding air to the combustion chamber; and an air hole plate in which the air holes are formed and disposed between the fuel nozzle and the combustion chamber; A plurality of air holes, each of which is provided with a central burner positioned at the axial center of the gas turbine combustor and a plurality of outer peripheral burners positioned on the outer peripheral side of the central burner,
A gas turbine combustor characterized in that a projection that surrounds or separates the central burner and a plurality of peripheral burners adjacent to the central burner is provided on the surface of the air hole plate on the combustion chamber side. The gas turbine combustor according to claim 1.
The protrusion is installed on the outer periphery of the central burner and surrounds the central burner, and the second protrusion is installed between a plurality of adjacent outer peripheral burners and separates the outer peripheral burner. A gas turbine combustor comprising: The gas turbine combustor according to claim 2.
The cross sections of the first protrusion and the second protrusion are each formed in a rectangular shape, and the length H of each of the protrusions in the direction perpendicular to the surface of the air hole plate is the diameter da of the air hole. The gas turbine combustor is set to a length of 5 times or less. The gas turbine combustor according to claim 1.
The corners of the tip portions of the first protrusion and the second protrusion are formed in a curved shape, and the length H of each of the protrusions in the direction perpendicular to the surface of the air hole plate is the length of the air hole. A gas turbine combustor characterized in that the length is set to 5 times or less of the diameter da. A plurality of fuel nozzles installed at the head of the gas turbine combustor for injecting fuel into a downstream combustion chamber, and disposed downstream of the fuel nozzles so as to be substantially coaxial with the plurality of fuel nozzles. A plurality of air holes for guiding air to the combustion chamber; and an air hole plate in which the air holes are formed and disposed between the fuel nozzle and the combustion chamber; A plurality of air holes, each of which is provided with a central burner positioned at the axial center of the gas turbine combustor and a plurality of outer peripheral burners positioned on the outer peripheral side of the central burner,
A gas turbine combustor, wherein a protrusion surrounding the outer periphery of the central burner and a plurality of outer peripheral burners adjacent to the central burner is provided on the surface of the air hole plate on the combustion chamber side. The gas turbine combustor of claim 5.
The cross-sections of the protrusions are each formed in a rectangular shape, and the length H of the protrusions in the direction perpendicular to the surface of the air hole plate is set to be not more than 5 times the diameter da of the air holes. A gas turbine combustor. The gas turbine combustor according to claim 6.
The gas turbine combustor according to claim 1, wherein the protrusion includes a cooling hole through which air passes through the air hole plate. A plurality of fuel nozzles installed at the head of the gas turbine combustor for injecting fuel into a downstream combustion chamber, and disposed downstream of the fuel nozzles so as to be substantially coaxial with the plurality of fuel nozzles. A plurality of air holes for guiding air to the combustion chamber; and an air hole plate in which the air holes are formed and disposed between the fuel nozzle and the combustion chamber; A plurality of air holes, each of which is provided with a central burner positioned at the axial center of the gas turbine combustor and a plurality of outer peripheral burners positioned on the outer peripheral side of the central burner,
The pilot burner has an inclined surface in which the surface of the air hole plate on the combustion chamber side is inclined concavely toward the axial center of the combustor, and an oil nozzle is provided at the center of the pilot burner,
A gas turbine combustor characterized in that a projection that surrounds or separates the central burner and a plurality of peripheral burners adjacent to the central burner is provided on the surface of the air hole plate on the combustion chamber side. The gas turbine combustor according to claim 8.
The protrusion is installed on the outer periphery of the central burner and surrounds the central burner, and the second protrusion is installed between a plurality of adjacent outer peripheral burners and separates the outer peripheral burner. A gas turbine combustor comprising: The gas turbine combustor according to claim 9,
The cross sections of the first protrusion and the second protrusion are each formed in a rectangular shape, and the length H of each of the protrusions in the direction perpendicular to the surface of the air hole plate is the diameter da of the air hole. The gas turbine combustor is set to a length of 5 times or less.

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