JP2011058758A - Gas turbine combustor - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a gas turbine combustor which achieves reduction in NOx by rapidly mixing fuel with air when the size of the gas turbine combustor is increased and has a burner constituted to avoid flashback. <P>SOLUTION: In the gas turbine combustor including the burner for mixing fuel with air and injecting the mixed fuel and air to a combustion chamber for burning, the burner includes: a base plate having a plurality of first air holes for mixing fuel with air and making air fuel mixture of the air and fuel flow down; and a turning plate having a plurality of second air holes for injecting the air fuel mixture of the air and fuel made to flow down from the first air holes of the base plate to the combustion chamber. A plurality of fuel nozzle holes for injecting fuel to the first air holes of the base plate are installed on the wall face of the base plate facing the first air holes, and are arranged opposite to each other so that the fuels jetted from the fuel nozzle holes are collided with each other within the first air holes. <P>COPYRIGHT: (C)2011,JPO&INPIT

Description

  The present invention relates to a gas turbine combustor.

  Environmental regulations and social demands are increasing day by day, and even higher efficiency and lower NOx are required for gas turbines.

  As one measure for improving the efficiency of the gas turbine, it is conceivable to raise the gas temperature at the turbine inlet. In this case, however, there is a concern about an increase in NOx emissions as the flame temperature rises in the gas turbine combustor. Is done.

  In order to reduce NOx emissions, there is a gas turbine combustor that employs premixed combustion, which is a combustion method in which an air-fuel mixture in which fuel and air are mixed in advance is supplied to the gas turbine combustor for combustion.

  The gas turbine combustor adopting the premixed combustion burns a premixer that preliminarily mixes the fuel constituting the burner and air, and a fuel that is located downstream of the premixer and mixed with air. And a combustion chamber.

  Premixed combustion is effective in reducing NOx because the flame temperature is uniform, but when the flame temperature rises, the flame is unexpectedly unexpectedly reached the premixer that constitutes the burner located upstream from the combustion chamber of the gas turbine combustor. Therefore, there is an increasing demand for a gas turbine combustor that has both NOx emission suppression and backfire resistance.

  Concerning gas turbine combustors that combine NOx emission reduction and flashback resistance, a plurality of fuel nozzles and a plurality of air holes are arranged coaxially to supply a plurality of coaxial jets of fuel and air to the combustion chamber Japanese Patent No. 3960166 discloses a technique related to a gas turbine combustor that is burned.

  The gas turbine combustor for supplying a plurality of coaxial jets of fuel and air to the combustion chamber and burning it as disclosed in the above-mentioned Japanese Patent No. 3960166 is much more difficult than a conventional gas turbine combustor employing premixed combustion. In addition, fuel and air can be rapidly mixed at a short distance, so that it is possible not only to achieve both NOx emission reduction and flashback resistance, but also to cope with the conventional diffusion combustion method. It is a gas turbine combustor that can cope with fuels with high hydrogen content such as chemical gas and coke oven gas and high combustion speed.

Japanese Patent No. 3960166

  In general, in a gas turbine equipped with a gas turbine combustor, when increasing the rated output in a multi-can gas turbine combustor structure, the number of gas turbine combustors can be increased or the size of the gas turbine combustor can be increased. It is necessary to increase the size or both.

  Here, the case where the gas turbine combustor which is the latter method is enlarged and coped with when raising a rated output is considered.

  In the gas turbine combustor that supplies and burns a plurality of coaxial jets of fuel and air to the combustion chamber disclosed in Japanese Patent No. 3960166, both the air flow rate and the fuel flow rate are increased when the gas turbine combustor is enlarged. Will increase. In order to cope with the increase in both the air flow rate and the fuel flow rate, the number of coaxial jets of fuel and air is increased, that is, the method of increasing the number of fuel nozzles and air holes, and the size of the fuel nozzle and air holes are increased. A method can be considered.

  However, the former method of increasing the number of coaxial jets of fuel and air increases the number of fuel nozzles, leading to an increase in manufacturing cost. On the other hand, the latter method of enlarging the fuel nozzle and the air hole can avoid the increase in cost because the machining of the fuel nozzle and the air hole is easier than the conventional product, but the flame generated in the combustion chamber is burned in the burner. It is necessary to take measures to prevent backfire.

  Here, it is known that the small scale vortex generated during mixing greatly affects the mixing performance of fuel and air, and that the smaller the vortex scale is, the more effective the uniform mixing of fuel and air is.

  Therefore, simply increasing the size of the fuel nozzle and air holes increases the scale of the vortex generated during mixing compared to the large number of coaxial jets composed of fuel nozzles and air holes of the conventional size. It is considered that the mixing performance is reduced as compared with a large number of coaxial jets composed of a fuel nozzle of a conventional size and air holes, and it is difficult to reduce NOx.

  An object of the present invention is to provide a gas turbine combustor provided with a burner having a structure that achieves low NOx by rapidly mixing fuel and air and avoids backfire when the gas turbine combustor is enlarged. It is to provide.

  The gas turbine combustor according to the present invention is a gas turbine combustor provided with a burner that mixes fuel and air and jets and burns them into a combustion chamber. The burner mixes fuel and air to mix the fuel and air. A base plate having a plurality of first air holes flowing down the air-fuel mixture, and a plurality of fuel gas and air mixtures fixed to the base plate and flowing through the first air holes of the base plate to the combustion chamber A plurality of fuel injection holes for injecting fuel into the first air holes of the base plate are installed on the wall surface of the base plate facing the first air holes; The fuel injection holes are arranged to face each other so that the fuel injected from the fuel injection holes collides with each other inside the first air hole.

  According to the present invention, when a gas turbine combustor is increased in size, a gas turbine combustor having a burner configured to achieve low NOx by rapidly mixing fuel and air and avoid backfire is provided. realizable.

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 elements on larger scale of the fuel nozzle which comprises the burner with which the gas turbine combustor of 1st Example shown in FIG. 1 was equipped. FIG. 2 is a partial structural diagram showing details of a state of arrangement of a fuel nozzle hole of a fuel nozzle, a base plate and a swirl plate constituting a burner provided in the gas turbine combustor of the first embodiment shown in FIG. 1. AA direction sectional drawing of the fuel nozzle which comprises the burner with which the gas turbine combustor of 1st Example shown in FIG. 3 was equipped. FIG. 2 is a longitudinal sectional view of a burner provided in the gas turbine combustor of the first embodiment shown in FIG. 1. The longitudinal cross-sectional view of the burner with which the gas turbine combustor of 1st Example shown in FIG. 5 was equipped. The BB direction sectional drawing of the burner with which the gas turbine combustor of 1st Example shown in FIG. 5 was equipped. The longitudinal cross-sectional view of the burner with which the gas turbine combustor which is 2nd Example of this invention was equipped. The longitudinal cross-sectional view of the burner with which the gas turbine combustor of 2nd Example shown in FIG. 8 was equipped. CC sectional view of the burner with which the gas turbine combustor of 2nd Example shown in FIG. 8 was equipped. Schematic which shows the baseplate 1st layer which comprises the burner with which the gas turbine combustor of 2nd Example shown in FIG. 8 was equipped. Schematic which shows the baseplate 2nd layer which comprises the burner with which the gas turbine combustor of 2nd Example shown in FIG. 8 was equipped. The partial structure figure which shows the detail of the arrangement condition of the fuel injection hole of the fuel nozzle which comprises the burner with which the gas turbine combustor which is 3rd Example of this invention was equipped, a base plate, and a turning plate. FIG. 14 is a partial structural view showing a modification of the arrangement state of the fuel nozzle holes of the fuel nozzle, the base plate and the swirl plate constituting the burner provided in the gas turbine combustor which is the third embodiment of the present invention shown in FIG. 13.

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

  First, the gas turbine plant provided with the gas turbine combustor which is 1st Example of this invention is demonstrated using FIG.

  FIG. 1 shows an overall configuration of a gas turbine plant 1000 for power generation provided with a gas turbine combustor 2 according to a first embodiment of the present invention.

  A gas turbine plant 1000 for power generation shown in FIG. 1 is supplied through a compressor 1 that pressurizes intake air 100 to generate high-pressure air 101, high-pressure air 101 generated by the compressor 1, and a fuel system 200. A gas turbine combustor 2 that mixes and burns fuel to generate a high-temperature combustion gas 102, a turbine 3 that is driven by the high-temperature combustion gas 102 generated by the gas turbine combustor 2, A generator 20 that is rotated by driving to generate electric power.

  The compressor 1, the turbine 3 and the generator 20 are connected to each other by an integral shaft 21, and the driving force obtained by driving the turbine 3 is transmitted to the compressor 1 and the generator 20 through the shaft 21. It has a configuration that can be.

  The gas turbine combustor 2 is stored in a casing 4 of a gas turbine device.

  A burner 6 is installed at the head of the gas turbine combustor 2, and high-pressure air 101 supplied from the compressor 1 is placed inside the gas turbine combustor 2 on the downstream side of the burner 6. A substantially cylindrical combustor liner 10 is disposed to separate the high-temperature combustion gas 102 generated by the gas turbine combustor 2 from the high-temperature combustion gas 102.

  On the outer periphery of the combustor liner 10, a flow sleeve 11 serving as an outer peripheral wall forming an air flow path for allowing the high-pressure air 101 to flow from the compressor 1 to the gas turbine combustor 2 is disposed. The diameter of the combustor liner 10 is larger than that of the combustor liner 10, and the combustor liner 10 is arranged in a substantially concentric cylindrical shape.

  On the downstream side of the combustor liner 10, the high-pressure air 101 ejected from the burner 6 in the combustion chamber 50 formed inside the combustor liner 10 of the gas turbine combustor 2 and F 1 supplied through the fuel system 200, A tail cylinder inner cylinder 12 for guiding a high-temperature combustion gas 102 generated by burning an air-fuel mixture with F2 fuel to the turbine 3 is disposed. A tail cylinder outer cylinder 13 is provided on the outer periphery of the tail cylinder inner cylinder 12. Is arranged.

  The suction air 100 is compressed by the compressor 1 to become high-pressure air 101. This high-pressure air 101 is supplied into the casing 4 and filled, and then formed between the tail cylinder inner cylinder 12 and the tail cylinder outer cylinder 13. It flows in into the made space and cools the tail cylinder inner cylinder 12 from the outer wall surface.

  The high-pressure air 101 that has flowed down the space between the transition cylinder inner cylinder 12 and the transition cylinder outer cylinder 13 passes through the annular flow path formed between the flow sleeve 11 and the combustor liner 10 and burns the gas turbine. Although it flows down toward the head of the combustor 2, it is used for convection cooling of the combustor liner 10 installed inside the gas turbine combustor 2 during the flow down.

  In addition, a part of the high-pressure air 101 flowing down an annular flow path formed between the flow sleeve 11 and the combustor liner 10 passes through a number of cooling holes provided in the wall surface of the combustor liner 10. 10 is used to cool the combustor liner 10.

  The remaining high-pressure air 101 that has flowed down the annular flow path and was not used for film cooling of the combustor liner 10 is a large number of air holes 32 provided in the burner 6 provided at the head of the gas turbine combustor 2. To the combustor liner 10.

  FIG. 2 is an enlarged partial view showing a fuel nozzle constituting the burner 6 provided in the gas turbine combustor of the first embodiment shown in FIG.

  The burner 6 installed at the head of the gas turbine combustor 2 has an F1 fuel provided with an F1 fuel flow rate adjustment valve 211 branched from the fuel system 200 for supplying fuel through the fuel system 200 provided with a fuel cutoff valve 210. Two fuel systems, that is, a system 201 and an F2 fuel system 202 including an F2 fuel flow rate control valve 212 branched from the fuel system 200, are provided.

  The flow rate of F1 fuel supplied to the burner 6 through the F1 fuel system 201 is adjusted by the fuel flow rate adjustment valve 211, and the flow rate of F2 fuel supplied to the burner 6 through the F2 fuel system 202 is adjusted by the fuel flow rate adjustment valve 212. The

  The fuel flow rate adjusting valves 211 and 211 adjust the fuel flow rates of the F1 fuel and F2 fuel, respectively, to control the power generation amount of the gas turbine plant 1000.

  Next, a detailed configuration of the gas turbine combustor 2 will be described.

  FIG. 3 is a partial structural view showing details of the arrangement state of the fuel nozzle hole of the fuel nozzle, the base plate and the swirl plate constituting the burner 6 provided in the gas turbine combustor 2 of the first embodiment shown in FIG. FIG. 4 is a cross-sectional view in the AA direction of the fuel nozzle constituting the burner 6 provided in the gas turbine combustor 2 of the present embodiment shown in FIG.

  3 and 4, the burner 6 installed at the head of the gas turbine combustor 2 of the present embodiment has a base plate 33 having a plurality of air holes 32A having a multi-nozzle structure, and is fixed to the base plate 33. A swirl plate 38 having a plurality of air holes 32B serving as swirl air holes having a swirl angle is disposed. Of these, the swirl plate 38 is a combustion chamber 50 formed inside the combustor liner 10. It is arranged to face.

  The air holes 32A of the base plate 33 and the air holes 32B of the swivel plate 38 are disposed so as to communicate with each other.

  Further, on the outer peripheral side of the plurality of air holes 32A formed in the base plate 33, a sleeve 37 having an annular fuel header 40 formed so as to cover the air holes 32A is installed. The F1 fuel and F2 fuel supplied to the fuel header 40 through the F1 fuel system 201 and F2 fuel system 202 are ejected from the fuel header 40 into the air holes 32A through the plurality of fuel injection holes 31 provided in the sleeve 37. Is configured to do.

  The F1 fuel and the F2 fuel ejected from the plurality of fuel injection holes 31 provided on the side surface of the sleeve 37 provided on the outer peripheral side of the air hole 32A formed in the base plate 33 to the air hole 32A are shown in FIGS. The fuel jet 35 is supplied to the air hole 32A.

  A part of the high-pressure air 101 supplied to the head of the gas turbine combustor 2 through an annular flow path formed between the flow sleeve 11 of the gas turbine combustor 2 and the combustor liner 10 is The air holes 32A formed in the base plate 33 constituting the fuel nozzle of the burner 6 are supplied as air jets 36 as shown in FIGS. 3 and 4, and flow down the air holes 32A of the base plate 33. The air is swirled by an air hole 32 </ b> B formed in a swirl plate 38 fixed to the base plate 33 and supplied to the combustion chamber 50.

  In the gas turbine combustor 2 of the present embodiment, the plurality of fuel injection holes 31 provided on the side surface of the sleeve 37 provided on the outer peripheral side of the air holes 32A formed in the base plate 33 constituting the burner 6 are provided with these fuels. The two fuel injection holes 31 are arranged to face each other so that the axis of the injection hole 31 is located on the same line.

  The sleeve 37 is formed in a substantially cylindrical shape, and both end portions of the sleeve 37 adjacent to the fuel header 40 are formed thick, and the inner wall of the base plate 33 is formed at both end portions of the thickly formed sleeve 37. Fixed to.

  That is, since both ends of the sleeve 37 are thick on the outer peripheral side, a space is formed between the sleeve 37 and the base plate 33 at a portion other than both ends, and the fuel header 40 is formed in this space. Yes.

  The sleeve 37 disposed on the base plate 33 needs to be fixed so that fuel leakage does not occur in the base plate 33 at both ends that are thick. In order to reliably prevent fuel leakage, a cold fit or a shrink fit may be applied.

  However, if no fuel leakage occurs at the joint between the base plate 33 and the sleeve 37, other methods such as brazing and welding are not particularly problematic.

  As shown in FIG. 3, the swivel plate 38 is disposed downstream of the base plate 33 so that the central axis of the air hole 32A disposed in the base plate 33 and the central axis of the air hole 32B disposed in the swivel plate 38 are coaxial. Is arranged.

  The diameter of the air hole 32 </ b> B provided in the swivel plate 38 is made equal to the diameter of the air hole 32 </ b> A provided in the sleeve 37.

  Further, as shown in FIG. 3, the air hole 32 </ b> B provided in the swivel plate 38 is provided with a swivel angle of angle θ, and the air hole 32 </ b> B of the swivel plate 38 is provided with the swivel angle θ so Combustion stability is improved by forming a swirl flow in the jet of fuel and air supplied to the combustor 50 inside the combustor liner 10 through the 32B.

  The base plate 33 and the swivel plate 38 are fixed to each other with bolts or the like (not shown).

  Here, the outer diameter of the sleeve 37 fixed inside the air hole 32 </ b> A disposed in the base plate 33 is larger than the hole diameter of the air hole 32 </ b> B disposed in the swivel plate 38.

  Therefore, even when the sleeve 37 disposed on the base plate 33 is separated from the base plate 33, the swivel plate 38 serves to prevent the sleeve 37 from flowing downstream.

  On the other hand, as shown in FIG. 3, the fuel jets 35 ejected from the two fuel nozzles 31 disposed on the side surfaces of the sleeve 37 facing each other collide with each other inside the air hole 32 </ b> A.

  Then, the momentums of these fuel jets 35 are offset, the potential core of the fuel jets 35 disappears, and the residence time of the fuel inside the air holes 32A increases.

  Due to the turbulence component of the air jet 36 flowing down the air hole 32A, the fuel jet 35 and the air jet 36 are rapidly mixed inside the air hole 32A, and the fuel / air mixture is mixed in the combustor liner 10. It is supplied to the combustion chamber 50 formed inside and burns.

  Therefore, even when the gas turbine combustor is increased in size, the fuel jets 35 and the air jets 36 ejected from the fuel injection holes 31 are formed by opposing the plurality of fuel injection holes 31 provided in the base plate 33 of the burner. Since rapid mixing is performed in the hole 32A, the mixing performance of fuel and air is maintained.

  In the gas turbine combustor 2 of the above-described embodiment, the fuel and air are burned after being mixed well, so that the flame temperature is uniform throughout and the flame temperature does not rise locally, and low NOx combustion is performed. Realized.

  Further, in the gas turbine combustor 2 according to the above-described embodiment, it is possible to avoid the flashback phenomenon in which the flame generated in the combustion chamber flows back to the burner.

  In the gas turbine combustor 2 of the present embodiment, a pair of fuel injection holes 31 provided on the side surface of the sleeve 37 disposed on the base plate 33 are disposed opposite to the side surface of the sleeve 37. However, if the fuel jets 35 ejected from the fuel injection holes 31 collide with each other on the central axis of the air holes 32A, the same effect can be obtained even if three or more fuel injection holes 31 are provided on the side surface of the sleeve 37. can get.

  5 is an enlarged front view of the peripheral portion of the burner 6 of the gas turbine combustor 2 in the gas turbine plant 1000 of FIG. 1. FIG. 6 is a combustion chamber 50 in which the burner 6 is formed inside the combustor liner 10. It is the side view seen from.

  In the gas turbine combustor 2 of the present embodiment, as shown in FIGS. 5 and 6, the air holes 32 formed from the air holes 32 </ b> A and the air holes 32 </ b> B are concentrically arranged in the first row from the center side toward the outer peripheral side. The three air holes 32a, the second air holes 32b, and the third air holes 32c are arranged in four rows from the inner periphery of the burner 6, and four in the second row. 16 in total, 8 in the third row.

  FIG. 7 shows a cross-sectional view of the gas turbine combustor 2 which is a cross-section in the BB direction of FIG.

  In the gas turbine combustor 2 shown in FIG. 7, the F1 fuel supplied to the burner 6 through the F1 fuel system 201 is in the first row corresponding to the fuel injection holes 31 provided on the side surface of the sleeve 37 provided in the base plate 33. The F2 fuel supplied to the fuel injection holes 31a disposed on the inner side surface of the air holes 32a and supplied to the burner 6 through the F2 fuel system 202 is the second row of air holes 32b corresponding to the fuel injection holes 31. And the fuel injection holes 31b and 31c provided on the inner side surfaces of the third row of air holes 32c.

  As described above, the fuel system for supplying the F1 fuel and the F2 fuel to the burner of the gas turbine combustor is divided into two parts, the F1 fuel system 201 and the F2 fuel system 202, thereby changing the load fluctuation of the gas turbine. It is easy to adjust the flow rates of the F1 fuel and the F2 fuel by following the above.

  Further, in the gas turbine combustor 2 shown in FIG. 7, the flow rate of the F1 fuel is increased at the same time without changing the sum of the flow rates of the F1 fuel and the F2 fuel flowing through the F1 fuel system 201 and the F2 fuel system 202, respectively. By reducing the flow rate of the F2 fuel, the fuel concentration in the fuel / air mixture supplied to the combustor 50 formed inside the combustor liner 10 from the first row air holes 32a is increased.

  Therefore, the combustion stability is increased downstream of the first row air holes 32a, and the combustion stability can be ensured in a state where the entire combustion load of the gas turbine combustor 2 is kept constant.

  The F1 fuel supplied through the F1 fuel system 201 flows from the fuel port 42a provided in the outer peripheral portion of the base plate 33 into the fuel header 40a through the fuel flow path 44a disposed inside the base plate 33, The fuel is supplied to the fuel injection holes 31a provided inside the one row of air holes 32a.

  The fuel ports 42a are provided on the outer peripheral portion of the base plate 33 by the number of holes of the first row of air holes 32a.

  After the F2 fuel supplied through the F2 fuel system 202 is branched into two systems, the fuel ports 42b and 42c provided on the outer periphery of the base plate 33 are connected to the fuel flow paths 44b and 44b disposed inside the base plate 33. It flows into the fuel headers 40b and 40c through 44c.

  The F2 fuel that has flowed into the fuel header 40b from the fuel port 42b via the fuel flow path 44b is supplied to the fuel injection holes 31b provided on the inner side surface of the air holes 32b in the second row.

  The fuel ports 42b are provided on the outer peripheral portion of the base plate 33 by the number of holes of the second row of air holes 32b.

  On the other hand, the F2 fuel that has flowed into the fuel header 40c via the fuel flow path 44c is supplied to the fuel injection holes 31c provided inside the third row of air holes 32c.

  The fuel ports 42c are provided on the outer peripheral portion of the base plate 33 by the number of holes of the third row of air holes 32c.

  Thus, the F1 fuel supplied through the F1 fuel system 201 is supplied to the fuel injection holes 31a disposed in the first row of air holes 32a, and the F2 fuel supplied through the F2 fuel system 202 is supplied to the second row of air holes 32b. Can be supplied to the fuel injection holes 31b disposed inside the fuel injection holes 31b and the fuel injection holes 31c disposed inside the third row of air holes 32c.

  According to the present embodiment, when the gas turbine combustor is enlarged, the fuel and air are rapidly mixed to achieve low NOx, and the gas turbine combustor including a burner having a configuration that avoids backfire. Can be realized.

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

  The configuration of the gas turbine combustor of the present embodiment is the same as the configuration of the gas turbine combustor of the first embodiment shown in FIGS. Only the different configurations will be described below.

  FIG. 8 is a longitudinal sectional view of a burner provided in the gas turbine combustor of this embodiment in the gas turbine plant 1000 of FIG. 1, and FIG. 9 is provided in the gas turbine combustor of this embodiment shown in FIG. FIG.

  In the gas turbine combustor 2 of the present embodiment, the air holes 32 formed from the air holes 32A and the air holes 32B are formed in the base plate 33 and the turning plate 38 constituting the burner 6 as shown in FIGS. Are arranged in three rows of concentric circles from the center side toward the outer peripheral side, consisting of a first row of air holes 32a, a second row of air holes 32b, and a third row of air holes 32c. From the circumferential side, a total of 36 pieces are arranged, 6 in the first row, 12 in the second row, and 18 in the third row.

  FIG. 10 shows a cross-sectional view of the gas turbine combustor 2 which is a cross-section in the CC direction of FIG.

  In the gas turbine combustor 2 of the present embodiment, as in the gas turbine combustor of the first embodiment, the fuel system for supplying F1 fuel and F2 fuel is divided into two, each of which is F1 fuel. A system 201 and an F2 fuel system 202 are provided.

  The F1 fuel is supplied to the pair of fuel injection holes 31a disposed on the inner side surface of the first row of air holes 32a through the F1 fuel system 201, and the F2 fuel is supplied to the second row of air holes 32b and the third through the F2 fuel system 202. The fuel is supplied to a pair of fuel injection holes 31b and 31c disposed on the inner side surface of the air hole 32c in the row.

  The F1 fuel supplied through the F1 fuel system 201 is supplied from a fuel port 42a indicated by a dotted line in the drawing provided on the upstream surface of the base plate 33 to an annular fuel flow path 44a disposed inside the base plate. .

  The F1 fuel supplied to the fuel flow path 44a has a center of the air hole 32a from a pair of fuel injection holes 31a disposed on the inner side surface of the air holes 32a in the first row so that the axes thereof are on the same line. Supplied toward the shaft.

  F2 fuel supplied through the F2 fuel system 202 is supplied from fuel ports 42b and 42c provided on the outer periphery of the base plate 33 to annular fuel flow paths 44b and 44c disposed inside the base plate 33, respectively.

  The F2 fuel supplied to the fuel flow path 44b passes through the center of the air hole 32b from a pair of fuel injection holes 31b disposed on the inner side surface of the second row of air holes 32b so that their axes are located on the same line. Supplied toward the shaft.

  Further, the F2 fuel supplied to the fuel flow path 44c is supplied from the pair of fuel injection holes 31c disposed on the inner side surface of the third row of air holes 32c so that the axes thereof are on the same line. Supplied toward the central axis of the.

  Thus, one fuel port 42 for supplying the fuel 200 to the pair of fuel injection holes 31 provided inside the air holes 32 in each row is provided for each air hole 32. Instead, one is provided for each column, which is different from the first embodiment.

  The fuel flow path 44 and the fuel header 40 shown in the first embodiment are also integrated with the first embodiment.

  Next, the details of the fuel supply structure in the gas turbine combustor 2 of the present embodiment will be described.

  As shown in FIG. 8, the base plate 33 constituting the burner 6 in the gas turbine combustor 2 of the present embodiment is composed of two layers of a base plate first layer 33A and a base plate second layer 33B from the upstream side.

  Here, FIG. 11 shows a schematic diagram of the base plate first layer 33A, and FIG. 12 shows a schematic diagram of the base plate second layer 33B.

  As shown in FIG. 11, the base plate first layer 33 </ b> A is provided with a sleeve installation hole 45 </ b> A having a hole diameter equal to the outer diameter of the sleeve 37 in the phase of the air hole 32 provided in the base plate 33. The fuel port 42a for allowing the F1 fuel 201 to flow inside the base plate 33 is disposed at the center.

  In the base plate second layer 33B, similarly to the base plate first layer 33A, a sleeve installation hole 45B having a diameter equal to the outer diameter of the sleeve 37 in the phase of the air hole 32 provided in the base plate 33 is provided. Further, as shown in FIG. 12, fuel ports 42b to 42c are arranged on the outer periphery, and fuel flow paths 44a to 44c are arranged inside.

  Then, the sleeve 37 is placed in the sleeve installation holes 45A and 45B by cold fitting, shrink fitting or the like, and the base plate first layer 33A and the base plate second layer 33B are welded to maintain the cross section shown in FIG. A structural base plate 33 can be provided.

  Here, in the gas turbine combustor 2 of the present embodiment, the shape of the sleeve 37 is substantially cylindrical at both ends as in the first embodiment of the present invention, but the outer diameter is the base plate first layer 33A. And the structure of the gas turbine combustor 2 of the present embodiment can be realized even with a simple cylindrical shape having a uniform wall thickness as a whole, which is equal to the diameter of the air hole 32a disposed in the base plate second layer 33B.

  Thus, the F1 fuel supplied through the F1 fuel system 201 is supplied to the fuel injection holes 31a provided in the first row of air holes 32a, and the F2 fuel supplied through the F2 fuel system 202 is supplied to the second row of air holes 32b. Can be supplied to the fuel injection holes 31b disposed inside the fuel injection holes 31b and the fuel injection holes 31c disposed inside the third row of air holes 32c.

  Further, in the gas turbine combustor 2 of the present embodiment, since the F1 fuel and the F2 fuel flow through the base plate 33 constituting the burner 6, the base plate 33 and the swirl plate 38 are cooled by the cold heat of the F1 fuel and the F2 fuel. The

  Accordingly, overheating of the base plate 33 and the swirl plate 38 of the burner 6 is prevented and the thermal stress generated in the base plate 33 and the swirl plate 38 is reduced. The structural reliability can be increased.

  According to the present embodiment, when the gas turbine combustor is enlarged, the fuel and air are rapidly mixed to achieve low NOx, and the gas turbine combustor including a burner having a configuration that avoids backfire. Can be realized.

  Next, the gas turbine combustor which is the 3rd Example of this invention is demonstrated using FIG.13 and FIG.14.

  The configuration of the gas turbine combustor of the present embodiment is the same as the configuration of the gas turbine combustor of the first embodiment shown in FIGS. Only the different configurations will be described below.

  FIG. 13 is an enlarged schematic cross-sectional view of air holes 32A and peripheral portions of the air holes 32B formed in the base plate 33 and the swirl plate 38 constituting the burner 6 provided in the gas turbine combustor 2 of the present embodiment.

  13 and 14, the base plate 33 and the swirl plate 38 constituting the burner 6 provided in the gas turbine combustor 2 of the present embodiment are similar to the air turbine 32A and the air hole, as in the case of the turbine turbine combustor of the first embodiment. 32B is supplied with an air jet 36 from its upstream side and flows down.

  The plurality of fuel injection holes 31 provided on the side surface of the sleeve 37 disposed on the outer peripheral side of the air hole 32A formed in the base plate 33 are arranged so that the axes of the fuel injection holes 31 are on the same line. Two fuel injection holes 31 are arranged to face each other. The fuel jets 35 supplied from the two fuel nozzle holes 31 arranged opposite to each other collide on the central axis of the air hole 32A.

  And in the burner 6 in the gas turbine combustor 2 of the present embodiment, the air jets 36 are supplied to the air holes 32A of the base plate 33 by the turbulence of the air holes 36A, and the air holes 32A are formed in the air holes 32A. The fuel supplied to 32A and the air of the air jet 36 are more uniformly mixed and supplied to the combustion chamber 50.

  Furthermore, in the burner 6 in the gas turbine combustor 2 of the present embodiment, as shown in FIG. 13, in addition to the structure of the burner 6 in the gas turbine combustor 2 of the first embodiment shown in FIGS. 3 and 4, A vortex generator 39 is disposed on the side wall of the sleeve 37 facing the air hole 32 </ b> A and upstream of the position where the fuel injection hole 31 is disposed.

  In the burner 6 in the gas turbine combustor 2 of the present embodiment having the above-described configuration, as shown in FIG. 13, the burner 6 is installed at the upstream side of the fuel injection hole 31 on the side wall of the sleeve 37 facing the air hole 32A. The vortex generator 39 generates a vortex 43 in the air hole 32 </ b> A near the side wall of the sleeve 37 downstream of the vortex generator 39.

  For this reason, not only the turbulence of the air jet 36 supplied to the air holes 32A but also the vortex generator 39 positively generates turbulence so that the air holes 32A are supplied to the air holes 32A. Since the fuel and air of the air jet 36 are mixed more uniformly and supplied to the combustion chamber 50, the mixing of fuel and air is further promoted as compared with the burner of the gas turbine combustor of the first embodiment. .

  Here, as shown in FIG. 14 in the burner 6 of the gas turbine combustor 2 which is a modified example of the present embodiment, the side wall of the sleeve 37 facing the air hole 32 </ b> A is positioned downstream of the fuel injection hole 31. Even in the configuration in which the vortex generator 39 is installed, the flow is disturbed by the vortex 43 generated downstream of the vortex generator 39, so that the fuel and air jet supplied from the plurality of fuel injection holes 31 to the air holes 32A The 36 air is more uniformly mixed and supplied to the combustion chamber 50 to promote the mixing of fuel and air.

  Moreover, in the burner 6 in the gas turbine combustor 2 of the present embodiment, the vortex generator 39 has a rib-like structure with a uniform thickness in the circumferential direction and a uniform height in the radial direction for ease of processing. For example, even in a structure having a notch in a part of the vortex generator 39, the flow is disturbed downstream thereof, so that the mixing of fuel and air can be promoted.

  Thus, the burner 6 structure of the gas turbine combustor 2 that realizes further low NOx combustion can be obtained by further uniformly mixing the fuel and air as in the burner 6 in the gas turbine combustor 2 of the present embodiment. .

  According to the present embodiment, when the gas turbine combustor is enlarged, the fuel and air are rapidly mixed to achieve low NOx, and the gas turbine combustor including a burner having a configuration that avoids backfire. Can be realized.

  The present invention is applicable to gas turbine combustors.

  1: compressor, 2: gas turbine combustor, 3: turbine, 4: casing, 6: burner, 10: combustor liner, 11: flow sleeve, 12: combustor tail cylinder, 13: tail cylinder outer cylinder 20: generator, 21: shaft, 31: fuel injection hole, 32: air injection hole, 33: base plate, 34: spring seal, 35: fuel injection, 36: air injection, 37: sleeve, 38: swirl plate, 39 : Vortex generator, 40: fuel header, 42: fuel port, 43: vortex, 44: fuel flow path, 45: sleeve installation hole, 50: combustion chamber, 100: suction air, 101: high pressure air, 102: high temperature combustion Gas: 103: exhaust gas, 200: fuel, 201: F1 fuel, 202: F2 fuel, 210: fuel cutoff valve, 211: F1 fuel flow control valve, 212: F2 fuel flow control valve, 1000: gas turbine Cement.

Claims (6)

In a gas turbine combustor having a burner that mixes fuel and air and jets and burns them into a combustion chamber.
The burner mixes fuel and air to form a plurality of first air holes for flowing down the mixture of fuel and air, and is fixed to the base plate and flows down the first air holes of the base plate. A swirl plate having a plurality of second air holes for ejecting a fuel / air mixture into the combustion chamber,
A plurality of fuel injection holes for injecting fuel into the first air holes of the base plate are installed on the wall surface of the base plate facing the first air holes, and the plurality of fuel injection holes are fuel injected from the fuel injection holes. The gas turbine combustor is arranged so as to face each other so as to collide with each other inside the first air hole. The gas turbine combustor according to claim 1.
On the wall surface of the base plate facing the first air hole, a vortex generating member for generating an air vortex upstream or downstream of the fuel injection hole for injecting fuel into the first air hole is disposed. A gas turbine combustor. The gas turbine combustor according to claim 1 or 2,
The wall surface of the base plate facing the first air hole is formed by an annular sleeve member having a fuel header inside, and the fuel supplied from the fuel header to the sleeve member is jetted into the first air hole. A gas turbine combustor having an injection hole. The gas turbine combustor according to claim 1.
The gas turbine combustor, wherein the second air hole of the swirl plate is formed with a swirl angle that swirls the mixture of fuel and air flowing down the second air hole. The gas turbine combustor according to claim 1.
The first air hole of the base plate and the second air hole of the swivel plate are formed in communication with each other,
The gas turbine combustor, wherein the first air holes and the second air holes are arranged in a plurality of rows in the base plate and the swirl plate, respectively. The gas turbine combustor of claim 5.
A first fuel system for supplying fuel to a fuel injection hole for injecting fuel to a first air hole located in a central row of the first air holes arranged in a plurality of rows in an annular manner on the base plate; A gas turbine combustor characterized in that a second fuel system for supplying fuel to a fuel injection hole for injecting fuel to a first air hole located in a row on the outer peripheral side is separately provided.

Images