JP2009074706A - Gas turbine combustor - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a gas turbine combustor further reduced in NOx exhaust amount. <P>SOLUTION: This gas turbine combustor includes: an inner cylinder 4 partitioning a combustion chamber; a plurality of fuel nozzles 5 provided at the upstream side of the inner cylinder 4 to inject fuel; and a plurality of porous plates having a plurality of air holes disposed between the fuel nozzle 5 and the inner cylinder, wherein the porous plates are constituted of a first porous plate 6 having air holes at positions opposite to the fuel nozzles and a second porous plate 7 provided at the downstream side through a gap with the first porous plate. The plurality of fuel nozzles 5 and the first porous plate 6 form a porous coaxial jet stream, and the porous coaxial jet stream is made to collide with the wall surface of the second porous plate 7 and diffused to thereby promote the mixing degree of fuel and combustion air, whereby on the downstream from the second porous plate 7, the fuel and the combustion air can be mixed at a moderate ratio to perform combustion. <P>COPYRIGHT: (C)2009,JPO&INPIT

Description

  The present invention relates to a gas turbine combustor.

  In recent years, with the demand for higher output and higher efficiency for gas turbine power plants, the temperature of combustion gas discharged from gas turbine combustors tends to increase year by year. When the temperature of the combustion gas increases, the amount of nitrogen oxide (hereinafter referred to as NOx) emission in the gas turbine exhaust gas also increases. In gas turbine combustors, reducing NOx emissions is a major issue from the viewpoint of global environmental conservation.

  From such a background, fuel is injected from the fuel nozzle into the combustion air, and the fuel and combustion air are uniformly mixed in advance by the premixer and burned in the combustion chamber, thereby generating local high-temperature combustion gas. A premixed combustion system that prevents NOx emissions and reduces NOx emissions is employed in gas turbine combustors. However, as a problem of the premixed combustion method, there is a possibility that a backfire occurs in which a flame flows backward in the premixer that mixes fuel and combustion air. When the flame flows back into the premixer, the premixer burns out and damages the turbine on the downstream side, so the backflow of flame to the premixer must be avoided. From such a background, a combustor structure that suppresses the occurrence of flashback has been proposed (see, for example, Patent Document 1).

  According to the gas turbine combustor of Patent Document 1, a plate-like member provided with a combustion chamber to which fuel and combustion air are supplied and provided with a plurality of air holes on the wall surface of the combustion chamber is disposed. A fuel nozzle that ejects fuel is disposed. By forming the combustion air flow around the fuel flow in the premix flow path in the air hole, the mixing distance can be shortened, and the NOx emission amount can be reduced.

JP 2003-148734 A

  However, environmental regulations tend to be stricter, and it is necessary to realize further lower NOx. In that case, the combustor structure becomes complicated and the cost can be increased.

  The present invention has been made in view of the above problems, and an object thereof is to provide a gas turbine combustor that further reduces NOx emission.

  The present invention includes a first porous plate provided with air holes at a position facing the fuel nozzle in the porous plate, and a second porous plate provided downstream of the first porous plate via a gap. And a board.

  According to the present invention, it is possible to provide a gas turbine combustor that further reduces NOx emissions.

  In the embodiment of the present invention, the fuel nozzles and the air holes are arranged so that the air flow wraps around the outer peripheral side of the fuel flow, and they are dispersed in a large number. Therefore, a plurality of fuel nozzles and a first perforated plate are used to form a perforated coaxial jet, and the perforated coaxial jet collides with the wall surface of the second perforated plate and diffuses to promote the mixing degree of fuel and combustion air. The fuel and combustion air are burned at an appropriate mixing ratio downstream of the porous plate 2. For this reason, further low NOx combustion becomes possible.

  Embodiments of a gas turbine combustor using the present invention will be described below with reference to the drawings.

  Example 1 of the present invention will be described below. FIG. 2 is a schematic configuration diagram illustrating the overall configuration of the gas turbine plant. As shown in FIG. 2, the gas turbine plant mainly combusts the compressor 1 that compresses air to generate high-pressure combustion air 13, and the combustion air 13 introduced from the compressor 1 and fuel. A combustor 3 that generates a gas 14 and a turbine 2 into which the combustion gas 14 generated by the combustor 3 is introduced. Note that the shafts of the compressor 1 and the turbine 2 are connected.

  The combustor 3 includes an inner cylinder 4 that generates combustion gas 14, a plurality of fuel nozzles 5 that eject fuel, a first perforated plate 6 and a second perforated plate 7 that mix combustion air 13 and fuel. , A pressure vessel in which the spark plug 8 is sealed with an outer cylinder 9 and an end cover 10.

  An end cover 10 is disposed on the upstream side of the combustor 3. The direction in which the combustion gas 14 flows is defined as the downstream direction. The end cover 10 is formed with a fuel manifold 15 that distributes fuel to the fuel nozzles. A plurality of protruding fuel nozzles 5 are formed from the downstream side wall surface of the end cover 10 that forms the fuel manifold 15, and the fuel in the fuel manifold 15 is ejected from the fuel nozzle 5. A first perforated plate 6 having a large number of air holes is installed downstream of the fuel nozzle 5 in order to primarily mix the fuel ejected from the fuel nozzle 5 and the combustion air 13. Further, a second perforated plate 7 in which a large number of air holes are formed is installed downstream of the first perforated plate 6 for secondary mixing of fuel and combustion air 13.

  According to the present embodiment configured as described above, the combustion air 13 from the compressor 1 passes through the annular air flow path constituted by the outer cylinder 9 and the inner cylinder 4 and is then cooled in the inner cylinder 4. While flowing into the combustion chamber 4 a from the hole, the air is introduced into the combustion chamber 4 a through the second porous plate 7 from the air hole of the first porous plate 6 installed at the upstream end of the inner cylinder 4. The air supplied to the combustion chamber 4a is mixed with fuel, and this mixed gas is ignited and burned by the spark plug 8 in the combustion chamber 4a. The combustion gas 14 generated by the combustion is supplied to the turbine 2 through the transition piece 11 to drive the turbine 2. Thereby, the generator 12 connected to the turbine 2 is driven to generate power.

  The fuel supply system 16 includes a fuel supply device 17 including a fuel tank, a pressure regulator, a fuel shut-off valve, a fuel flow meter, and the like, and a fuel pipe 18 that is installed downstream of the fuel supply device 17 and supplies fuel to the fuel nozzle 5. In the gas turbine combustor configured as described above, the purpose of the first embodiment is to place a plurality of perforated plates in the flow direction, which are located downstream of the fuel nozzle 5 and mix the fuel and the combustion air. Is to promote the mixing of the combustion air with the combustion air and reduce the NOx emission amount in the combustion gas.

  FIG. 1 is a partially enlarged view illustrating the structure of the end cover 10, the fuel nozzle 5, the first perforated plate 6, and the second perforated plate 7 of the combustor 3. FIG. 3 is a cross-sectional structural view (a) of the porous plate and a front view (b) viewed from the downstream side of the second porous plate 7, and FIG. 4 is a fuel nozzle for explaining the mixing mechanism of fuel and combustion air. FIG. 5 is a partially enlarged view in which the first porous plate 6 and the second porous plate 7 are enlarged.

  The plurality of fuel nozzles 5 shown in FIG. 1 are formed in a pipe shape, one of which is connected to a fuel manifold 15 formed in the end cover, and the other is connected to a plurality of air holes 19 formed in the first perforated plate 6. Opposed to open. A second porous plate 7 in which a plurality of air holes 20 are formed is installed at a downstream position of the first porous plate 6 with a gap G therebetween. A cover member 22 that covers the combustion air seal member 21 installed at the upstream end of the inner cylinder 4 is formed on the outer peripheral portion of the second porous plate 7, and from the connection portion between the inner cylinder 4 and the second porous plate 7. Reduce the amount of combustion air that leaks.

  Moreover, since the 2nd perforated plate 7 is overheated by the radiant heat from the combustion gas produced | generated inside the inner cylinder 4, the cooling hole 23 for cooling the 2nd perforated plate 7 is a 2nd perforated plate. 7 between the air holes 20.

  Further, two perforated plates for mixing fuel and combustion air are arranged in the axial direction of the combustor 3, and the formation positions of the air holes 20 formed in the second perforated plate 7 are formed in the first perforated plate 6. The air holes 19 are eccentric by a distance H in the radial direction of the perforated plate.

  FIG. 3 shows a front view of the second porous plate 7 as seen from the downstream side of the combustion chamber 4a. In the first embodiment, the air holes 19 (dotted lines) and the air holes 20 are formed so as not to overlap each other. The second porous plate 7 has a cooling hole 23 formed on the extension of the central axis of the air hole 19 formed in the first porous plate 6.

  FIG. 4 is an enlarged view showing the air holes 19 formed in the fuel nozzle 5 and the first porous plate 6 and the air holes 20 formed in the second porous plate 7. In the first embodiment, since the air holes 19 formed in the first porous plate 6 are installed on the ejection shaft of the fuel nozzle 5, the fuel flow ejected from the fuel nozzle 5 is converted into a combustion air flow inside the air holes 19. It will be in a state of being surrounded. Since the fuel nozzles 5 are distributed in a large number, the flow rate of fuel ejected from one fuel nozzle 5 is reduced. For this reason, the ratio of the combustion air flow rate to the small amount of fuel ejected from the fuel nozzle 5 increases in the air hole 19. Therefore, the primary mixing of fuel and combustion air is promoted inside the air hole 19. A second porous plate 7 is disposed downstream of the first porous plate 6 at a distance G, and the air holes 20 of the second porous plate 7 are air holes 19 formed in the first porous plate 6. And the phase is different. For this reason, the fuel and fuel air primarily mixed inside the air holes 19 of the first perforated plate 6 collide with the wall surface 24 of the second perforated plate 7 and diffuse, so that the contact area between the fuel and combustion air increases rapidly. Secondary mix. When the secondary mixed fuel and combustion air pass through the air holes 20 formed in the second perforated plate 7, they are tertiary mixed by small vortices formed inside the air holes 20. In addition, fuel and combustion air are quaternarily mixed by vortices generated when they are ejected from the air holes 20 to the combustion chamber 4a, so that mixing of fuel and combustion air is promoted and NOx emissions in the combustion gas are greatly reduced. It becomes possible to do.

  In the case of the configuration as in the first embodiment, the second porous plate 7 is heated by the radiant heat of the combustion gas 14 generated in the inner cylinder 4, so that the porous plate may need to be cooled. When cooling a perforated plate, a method of cooling by forming a cooling hole in the perforated plate is common, which is advantageous for cost reduction. However, when this cooling method is applied to a combustor composed of only one perforated plate, a part of the combustion air is ejected from the cooling hole to the combustion chamber 4a. For this reason, the fuel concentration increases with a decrease in the flow rate of the combustion air flowing into the combustion chamber together with the fuel from the air hole, and there has been a problem that the amount of NOx emission in the combustion gas increases.

  However, in the first embodiment, the gas ejected from the cooling hole 23 of the second porous plate 7 facing the combustion chamber 4 a of the inner cylinder 4 is combusted with the fuel sufficiently mixed on the upstream side of the second porous plate 7. It is an air-fuel mixture. Therefore, the fuel concentration of the entire air-fuel mixture ejected from the air holes 20 of the second porous plate 7 to the combustion chamber 4a can be reduced as compared with the case where one porous plate is used, and NOx in the combustion gas It becomes possible to reduce the discharge amount. Therefore, even if the cooling hole 23 is slightly deviated from the central axis of the air hole 19, the above-described effect can be obtained.

  Further, in the first embodiment, the low temperature air-fuel mixture resulting from the mixture of the fuel and the combustion air having a temperature lower than that of the combustion air rapidly collides with the wall surface of the second perforated plate 7 heated by the combustion gas. Cooling of the porous plate 7 is promoted, and the reliability of the second porous plate 7 is improved. In addition, the cooling hole 23 has a smaller diameter so that the cooling effect of the second perforated plate 7 can be improved as the diameter of the cooling hole 23 is smaller and within a range where the reliability of the second perforated plate 7 does not decrease. is there.

  The mixing mechanism of the fuel and the combustion air in the first embodiment is such that the fuel ejected from the fuel nozzle 5 and the combustion air flowing in from the air holes 19 of the first porous plate 6 pass through the air holes 20 of the second porous plate 7. This is considered to be determined by the flow state until it is ejected to the combustion chamber 4a. Influencing the flow state of fuel and combustion air, the number of air holes 19 and 20 formed in the first perforated plate 6 and the second perforated plate 7, the hole diameter and the ratio of the opening area of the air holes, Axial thickness, axial gap G between first porous plate 6 and second porous plate 7, eccentric distance H of air holes 19 and 20 formed in first porous plate 6 and second porous plate 7, etc. There is. These parameters are examined according to the purpose of the combustor to which the present invention is applied and the combustion conditions.

  5A and 5B show the magnitude relationship between the air hole diameter D1 of the first porous plate 6 and the air hole diameter D2 of the second porous plate 7. FIG. FIG. 5A shows an example where D1> D2, and FIG. 5B shows an example where D1 <D2.

  When the hole diameter of the air hole 20 of the downstream second porous plate 7 is made smaller than the air hole 19 of the upstream first porous plate 6 as shown in FIG. And the mixture of combustion air collide with the second porous plate 7 and diffuse. When the air holes 20 are ejected from the air holes 20 to the combustion chamber 4a, the number of air holes 20 is large and the air-fuel mixture is more dispersed and ejected to the combustion chamber 4a. It is possible to reduce the NOx emission amount. By making the air holes 20 of the second perforated plate 7 a large number of small diameters, a reduction in NOx emission can be expected. When cost is prioritized over NOx emission performance, it is possible to reduce the number of air holes 19 in the first porous plate 6 and the number of fuel nozzles 5 installed corresponding to the air holes 19. Is advantageous.

  FIG. 5B shows an example where D1 <D2. If the hole diameter D2 of the air hole 20 is larger than the hole diameter D1 of the air 19, the number of air holes 20 formed in the second porous plate 7 is reduced from the air holes 19 formed in the first porous plate 6, thereby reducing the cost. It will be advantageous. However, when the hole diameter D2 of the air hole 20 is increased, the ratio of the air-fuel mixture ejected from the air hole 19 directly flows into the combustion chamber 4a without colliding with the wall surface of the second porous plate 7 increases. It is considered that the hole diameter D2 of the air hole 20 is desirably equal to or smaller than the hole diameter D1 of the air hole 19 in order to reduce the mixing promoting effect.

  5C and 5D show examples in which the axial gap G between the first perforated plate 6 and the second perforated plate 7 is different. As shown in FIG. 5C, when the gap G between the first porous plate 6 and the second porous plate 7 is narrow, the jet velocity of the mixture of fuel and combustion air ejected from the air holes 19 is not attenuated. Since it collides with the wall surface of the 2nd perforated panel 7 as it is, the diffusion effect by collision increases and mixing is accelerated | stimulated. When the gap G is large as shown in FIG. 5 (d), the residence time until the air-fuel mixture ejected from the air holes 19 collides with the second porous plate 7 increases, so that the mixture of fuel and combustion air In any case, the effect of reducing the NOx emission amount in the exhaust gas can be expected. However, if the gap G is made too short, the pressure loss increases and the performance of the entire turbine deteriorates. Further, if the gap G is made too long, the flow velocity of the gap portion decreases, so that the flame easily flows back into the gap G. Therefore, it is desirable to set the gap G so as to have a flow rate comparable to the flow rate of the air-fuel mixture passing through the air holes 19 for the purpose of suppressing an increase in pressure loss and flame backflow.

  FIGS. 5E and 5F show examples in which the eccentric distance H of the air hole 19 formed in the first porous plate 6 and the air hole 20 formed in the second porous plate 7 are different. As shown in FIG. 5E, when the eccentric distance H at the axial center of the air holes 19 and 20 is large and the air holes 19 and 20 are arranged so as not to overlap when viewed from the downstream side of the combustion chamber 4a, the air holes Since almost the entire amount of the air-fuel mixture ejected from 19 collides with the wall surface 24 of the second porous plate 7, the diffusion effect due to the collision is maximized and the mixing of fuel and combustion air is promoted.

  As shown in FIG. 5F, when the eccentric distance H is small and the air holes 19 and 20 are arranged so as to overlap when viewed from the downstream side of the combustion chamber 4a, a part of the air-fuel mixture ejected from the air holes 19 is A component that flows from the air hole 20 to the combustion chamber 4a without colliding with the wall surface 24 of the second porous plate 7 is generated. Therefore, although the mixing promotion effect due to the collision of a part of the air-fuel mixture with the second porous plate 7 is reduced, the mixing is considered to be promoted by the effect of the separation vortex generated at the inlet portion of the air hole 20, The effect of reducing the NOx emission amount in the gas can be expected.

  Moreover, there exists a shape of the air hole formed in the 2nd perforated panel 7 as what affects the mixed state of a fuel and combustion air. Although the shape of the air holes of the second perforated plate 7 shown in FIGS. 1 to 5 is a cylindrical shape, the mixing characteristics are obtained when the shape of the air holes is reduced toward the downstream side as shown in FIG. 6A. And new effects on combustion characteristics.

  In the example of FIG. 6A, the mixture of fuel and combustion air ejected from the adjacent air holes 19 a and 19 b of the first porous plate 6 flows into the air holes 27 of the second porous plate 7. At that time, since the hole diameter of the inlet portion of the air hole 27 is formed larger than the hole diameter of the air hole 19, the ratio of the air-fuel mixture colliding with the wall surface of the second porous plate 7 is reduced and mixing by collision diffusion is performed. The promotion effect is considered to be reduced. However, since the air-fuel mixture from the air holes 19a and 19b collides with each other inside the air hole 27, the mixing of fuel and combustion air is promoted. Further, even when a large vortex is not generated in the gap between the first porous plate 6 and the second porous plate 7 and the flame formed in the combustion chamber 4a flows backward, there is a possibility that the flame is stagnated in the gap. Low potential for burning the combustor is reduced and reliability is improved.

  Further, FIG. 6B shows the air hole 28 formed in the second perforated plate having a conical shape and a plurality of small-diameter air holes 29 formed at the outlet portion. In addition to mixing inside the air holes 28, the outlets are formed in a large number of small-diameter holes 29, so that the air-fuel mixture is more dispersed and the NOx emission amount in the exhaust gas can be reduced.

  As described above, the structure of the first perforated plate 6 and the second perforated plate 7 and the number and shape of air holes formed in each of them are flexible according to the configuration and purpose of the combustor or the type of fuel. It is excellent in that it can be handled with a relatively simple structure.

  Further, by applying the above concept, it is possible to use a plurality of porous plates (for example, three porous plates 6a, 6b, 7) provided between the fuel nozzle and the inner cylinder as shown in FIG. Is possible.

  A second embodiment will be described with reference to FIG. In the second embodiment, as shown in FIG. 7, the cover member 32 covers the combustion air seal member 21 installed at the upstream end of the inner cylinder 4 on the outer peripheral portion of the first porous plate 30 located downstream of the fuel nozzle 5. Is formed. A second porous plate 31 having an outer diameter smaller than the inner diameter of the cover member 32 formed on the first porous plate 30 is installed on the downstream side of the first porous plate 30, and the cover member 32 of the first porous plate 30. A gap is formed between the two. The second embodiment is an example in which the positions of the air holes 34 formed in the second porous plate 31 are moved in the circumferential direction with reference to the positions of the air holes 33 formed in the first porous plate 30. Since the air holes 33 and 34 formed in the first perforated plate 30 and the second perforated plate 31 are formed to be shifted in the circumferential direction, the fuel and combustion air ejected from the air holes 33 of the first perforated plate 30 The air-fuel mixture collides with the wall surface of the second porous plate 31, and the mixing is promoted by the diffusion effect caused by the collision, so that it is expected that the amount of NOx emission in the exhaust gas is reduced.

  In Example 2, the specifications such as the hole diameter and the number of air holes formed in the first perforated plate 30 and the second perforated plate 31 are the same, and the second perforated plate 31 is compared with the first perforated plate 30. The mounting method is shifted in the circumferential direction. Since the air hole specifications of the first perforated plate 30 and the second perforated plate 31 are the same, it can be expected that the manufacturing cost is reduced.

  Further, in the second embodiment, even when the second porous plate 31 is heated by the combustion gas generated in the combustion chamber 4a and the second porous plate 31 is thermally expanded, the outer peripheral side portion of the second porous plate 31 and A gap is formed between the cover members 32 formed on the first porous plate 32. Therefore, it is not restrained by the cover member 32, and it is possible to avoid thermal deformation.

  As a method for promoting the mixing of fuel and combustion air, it is conceivable to increase the thickness of the first porous plate 30 and the second porous plate 31. However, there is a problem that the cost increases when the plate thickness is increased, and in particular, the thermal stress increases when the plate thickness of the second porous plate 31 is increased. Therefore, in the embodiment according to the present invention, it can be expected that the mixing of the fuel and the combustion air is further promoted and the NOx emission amount in the exhaust gas is reduced, so that the thickness of the perforated plate can be reduced and the cost can be reduced.

  In addition, since the second porous plate 31 is heated to a high temperature depending on the combustion conditions, the second porous plate 31 can be attached to and detached from the first porous plate 30 and the second porous plate is made of a heat-resistant alloy. It is possible to manufacture or apply a heat shielding shield material, and it is excellent in that it has a structure that can flexibly respond to combustion conditions.

  A third embodiment will be described with reference to FIG. In the third embodiment, the fuel nozzle is divided into a central fuel nozzle 35 and a surrounding fuel nozzle 36. On the downstream side of the fuel nozzle 35 and the fuel nozzle 36, a first perforated plate 39 having air holes 37 and air holes 38 facing each other is installed. On the downstream side of the first perforated plate 39, a second perforated plate having air holes 40 and air holes 41 formed at positions different from the air holes 37 and air holes 38 formed in the first perforated plate 39. 42 is installed. A fuel supply system 43 that supplies fuel to the fuel nozzle 35 and a fuel supply system 44 that supplies fuel to the fuel nozzle 36 are installed.

  In the third embodiment, the positions of the air holes 37 and 38 formed in the first porous plate 39 and the positions of the air holes 40 and 41 formed in the second porous plate 42 are different as in the first and second embodiments. The fuel ejected from the fuel nozzle is the first perforated plate, and the fuel flow is surrounded by the combustion air flow, and the contact area between the fuel and the combustion air is increased to promote mixing. Further, since the fuel and combustion air collide with the wall surface of the second porous plate disposed downstream of the first porous plate and diffuse to promote the degree of mixing, the fuel and combustion air can be set to a substantially complete premixed state. It becomes possible. Depending on the combustion conditions, the second porous plate 42 is overheated by the flame generated in the combustion chamber 4 a, but in Example 3, the low-temperature air-fuel mixture ejected from the first porous plate 39 enters the second porous plate 42. Because of the collision, the second porous plate 42 can be expected to be cooled.

  In the third embodiment, the air hole 40 formed in the second porous plate 42 corresponding to the central fuel nozzle 35 has an appropriate turning angle so that the air hole 40 is turned around the center axis of the combustion chamber 4a. Has been granted. By providing the swirl angle in the air hole 40 in this way, a stable recirculation region is formed by swirling of the air-fuel mixture ejected from the air hole 40, and combustion can be stabilized.

  Moreover, in Example 3, the remarkable effect can be expected with respect to the load condition of the gas turbine. The fuel supply system 43 and the fuel supply system 44 shown in FIG. 8 can be used to adjust the fuel flow rate to cope with various load conditions of the gas turbine.

  In other words, the fuel flow rate is small with respect to the total air flow rate under the condition where the gas turbine load is small. In this case, the fuel is supplied only from the central fuel nozzle 35, and the fuel concentration in the central region is stably formed. It can be operated to keep the concentration above a certain level. Further, under conditions where the load of the gas turbine is large, fuel can be supplied from both the central fuel nozzle 35 and the surrounding fuel nozzle 36 to perform low NOx combustion as a whole. Further, at an intermediate load, the amount of fuel ejected from the central fuel nozzle 35 is set so that the equivalence ratio exceeds 1 with respect to the air flow rate flowing from the air hole 37, and the ambient air is used for combustion. It is also possible to operate in a simple manner.

  Therefore, it can contribute to flame stabilization and low NOx combustion according to various gas turbine loads.

  The present invention can be widely applied to combustion apparatuses that reduce NOx emissions in exhaust gas.

It is the elements on larger scale of the fuel nozzle in Example 1, and a perforated board part. 1 is a diagram illustrating an overall configuration of a gas turbine in Embodiment 1. FIG. It is sectional drawing and the front view of the perforated board part in Example 1. FIG. Explanatory drawing of the mixing mechanism of the fuel and combustion air in Example 1. FIG. It is a comparison figure at the time of changing various arrangement | positioning of a perforated plate and a fuel nozzle. 2 is a diagram illustrating a structure of a porous plate in Example 1. FIG. It is a figure showing the detailed structure of the burner in Example 2. FIG. It is a figure showing the detailed structure of the burner in Example 3. FIG. It is a figure showing the detailed structure of the burner (modified example) in Example 1. FIG.

Explanation of symbols

1 Compressor 2 Turbine 3 Combustor 4 Inner cylinder 4a Combustion chamber 5 Fuel nozzle 6 First perforated plate 7 Second perforated plate 8 Spark plug 9 Outer cylinder 10 End cover 11 Transition piece 12 Generator 13 Combustion air 14 Combustion Gas 15 Manifold 16 Fuel supply system 17 Fuel supply device 18 Fuel piping

Claims (3)

An inner cylinder that defines a combustion chamber that mixes combustion air and fuel to generate combustion gas, a plurality of fuel nozzles that are located upstream of the inner cylinder and that ejects fuel, and between the fuel nozzle and the inner cylinder A gas turbine combustor having a plurality of perforated plates provided with a plurality of air holes,
A first porous plate provided with air holes at positions facing the fuel nozzles of the porous plate;
A gas turbine combustor comprising the first perforated plate and a second perforated plate provided downstream via a gap. The gas turbine combustor according to claim 1.
A gas turbine combustor, wherein a deviation occurs between a central axis of air holes arranged in the first perforated plate and a central axis of air holes arranged in the second perforated plate. An inner cylinder defining a combustion chamber for mixing combustion air and fuel to generate combustion gas;
A plurality of fuel nozzles which are located upstream of the inner cylinder and eject fuel;
A first perforated plate provided with air holes at positions facing the fuel nozzle;
A second perforated plate disposed downstream from the first perforated plate and provided with a plurality of air holes;
The fuel and combustion air ejected through the air holes in the first perforated plate collide with the wall surface of the second perforated plate, and are ejected from the air holes of the second perforated plate to the combustion chamber. A gas turbine combustor characterized by comprising.

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