Gas turbine combustion chamber device

Abstract

Gas turbine combustion chamber device (7) which is equipped with a burner (17) wherein the burner (17) comprises the following: a fuel nozzle group with several fuel nozzles (14) for fuel supply; a fuel nozzle plate (13) which structurally supports the fuel nozzles (14) and serves to distribute the fuel (5) flowing from an upstream side to the fuel nozzles (14); and a perforated plate (12) arranged downstream of the fuel nozzles (14) and having nozzle holes (20) corresponding to the fuel nozzles (14), wherein the fuel nozzle group includes outer circumferential fuel nozzles and inner circumferential fuel nozzles, wherein an outer diameter of the outer circumferential fuel nozzles is larger than an outer diameter of the inner circumferential fuel nozzles, wherein fuel (5) supplied by the fuel nozzles (14) and compressed air (4) are caused to mix at inlets of the nozzle holes (20) of the perforated plate (12) on one side of the fuel nozzles, and wherein the fuel nozzle group comprises a central fuel nozzle group (50) whose fuel nozzles (14) each have the same outer diameter, and several outer circumferential fuel nozzle groups (51); in the burner (17) the central fuel nozzle group (50) is arranged in its center and the several outer circumferential fuel nozzle groups (51) are arranged such that they surround the central fuel nozzle group (50) when the fuel nozzle plate (13) and the fuel nozzles (14) are viewed from downstream of the burner (17), wherein Each of the multiple outer-circumference fuel nozzle groups (51) forms a circular arrangement of fuel nozzles (14); each of the outer-circumference fuel nozzle groups (51) contains at least two types of fuel nozzles (14) which differ from each other in their outer diameter; and Based on a boundary defined by a radial distance (100) from the center (40) of the burner (17), in each of the outer circumferential fuel nozzle groups (51) the fuel nozzles (53) with a large outer diameter are arranged in an outer circumferential region from the boundary on a side facing away from the central fuel nozzle group (50) and the fuel nozzles (54) with a small outer diameter are arranged in an inner circumferential region from the boundary on a side facing the central fuel nozzle group (50).

Description

Background of the invention

[0001] The present invention relates to a gas turbine combustion chamber device and in particular to a gas turbine combustion chamber device comprising many fuel nozzles and a fuel nozzle plate for structurally supporting the fuel nozzles.

[0002] Strict environmental standards have been introduced for NOx emissions from gas turbines in operation in order to reduce environmental pollution caused by exhaust gases.

[0003] NOx emissions increase with increasing flame temperature. Therefore, it is necessary to ensure uniform combustion by preventing the formation of a locally high-temperature flame. Uniform combustion requires numerous fuel injection nozzles to improve the fine distribution of the fuel.

[0004] JP 2011- 58 775 A discloses the generally used process of reducing NOx emissions.

[0005] JP 2011-58775A discloses the process of reducing NOx emissions by lowering the pressure drop of the coaxial nozzle and accelerating the fuel / air mixture, as described below. The element for creating turbulence in the airflow is provided either at the tip end of the fuel nozzle forming the coaxial nozzle or within the channel of the nozzle hole formed in the perforated plate, where the tip end of the fuel nozzle is located, thus defining the minimum channel cross-sectional area of ​​the coaxial nozzle hole. The minimum channel cross-sectional area of ​​the coaxial nozzle hole for the burner on the outer circumferential side, among those arranged in multiple rows, is larger than the minimum channel cross-sectional area of ​​the coaxial nozzle hole for the burner on the central side. Furthermore, US 2009 / 0031728A1 discloses a gas turbine combustion chamber device with a burner comprising a variety of fuel nozzles.The document describes a specific arrangement of fuel nozzles and a perforated plate, which together form a coaxial nozzle structure to optimize fuel supply and combustion. DE 10 2011055 472 A1 describes a multi-tube fuel nozzle for gas turbines with various flow control features. The nozzle comprises a fuel line, a fuel chamber, and several tubes arranged concentrically around a central axis. These tubes have different control features, including different fuel-air premix ratios, different tube diameters, or different outlet spacings. This arrangement enables improved flow control and fuel distribution in the gas turbine combustion chamber. Finally, US 2018 / 0003386 A1 describes a fuel nozzle for gas turbine combustion chambers with improved durability and strength reliability.The nozzle is metallurgically and integrally connected to a base plate, with the connection surface featuring both fused or brazed joints on the surface and press fits internally. This design thus increases mechanical strength and enables long-term reliable operation of the gas turbine combustion chamber. Summary of the invention

[0006] In the gas turbine combustion chamber device, which contains many fuel nozzles and the fuel nozzle plate for the structural support of the fuel nozzles, increasing the number of fuel nozzles to improve the fine distribution of the fuel can reduce the distance between the fuel nozzles.

[0007] As a result, the space around the fuel nozzle narrows. To ensure sufficient space for connecting the fuel nozzle to the fuel nozzle plate, or the space between the fuel nozzles which serves as the air channel, it is necessary to reduce the outer diameter of the fuel nozzle when increasing the number of fuel nozzles.

[0008] However, vibrations can occur in the fuel nozzles, which are located in the flow field of compressed air, due to the fluid force. The fluid force acting on the fuel nozzle varies depending on its position. If all fuel nozzles have the same outer diameter, the vibration load caused by the fluid force will also differ depending on the nozzle's position. Accordingly, increasing the outer diameter of the fuel nozzle can be one of the most effective approaches to reducing the vibration load.

[0009] However, in order to improve both the fine distribution of the fuel and reduce the vibration load, the inventors of the present invention have discovered that it is preferable to optimize each outer diameter of the respective fuel nozzles taking into account the fluid force, which differs according to the position of the fuel nozzle.

[0010] The present invention provides a gas turbine combustion chamber device with structural reliability with respect to vibrations under fluid force and high environmental performance due to uniform combustion, which is achieved by optimizing the outer diameter of the fuel nozzle under the fluid force, which varies according to the position of the fuel nozzle.

[0011] The present invention relates to a gas turbine combustion chamber device with the features of claims 1, 7, and 8. Advantageous embodiments are defined in the dependent claims. The gas turbine combustion chamber device according to the present invention comprises a burner equipped with a fuel nozzle assembly having multiple fuel nozzles for fuel supply, a fuel nozzle plate that structurally supports the fuel nozzles and serves to distribute the fuel flowing from an upstream side to the fuel nozzles, and a perforated plate arranged downstream of the fuel nozzles and having nozzle holes corresponding to the fuel nozzles. The fuel nozzle assembly comprises outer circumferential fuel nozzles and inner circumferential fuel nozzles. Each outer diameter of at least one proximal end section of the outer circumferential fuel nozzles is larger than each outer diameter of the inner circumferential fuel nozzles.

[0012] The gas turbine combustion chamber device according to the present invention comprises a burner equipped with a fuel nozzle assembly having multiple fuel nozzles for fuel supply, a fuel nozzle plate that structurally supports the fuel nozzles and serves to distribute the fuel flowing from an upstream side to the fuel nozzles, and a perforated plate arranged downstream of the fuel nozzles and having nozzle holes corresponding to the fuel nozzles. The fuel nozzle assembly comprises a central fuel nozzle assembly, the fuel nozzles of which each have the same outer diameter, and multiple outer circumferential fuel nozzle assemblies.In the burner, the central fuel nozzle assembly is arranged in its center, and the multiple outer-circumference fuel nozzle assemblies are arranged such that they surround the central fuel nozzle assembly when viewed from downstream of the burner, considering the fuel nozzle plate and the fuel nozzles. Each of the outer-circumference fuel nozzle assemblies contains at least two types of fuel nozzles that differ in their outer diameter, with the fuel nozzles with a large outer diameter being arranged on an outer circumferential side facing away from the central fuel nozzle assembly, and the fuel nozzles with a small outer diameter being arranged on an inner circumferential side facing the central fuel nozzle assembly.

[0013] The gas turbine combustion chamber device according to the present invention comprises a burner equipped with a fuel nozzle assembly having multiple fuel nozzles for fuel supply, a fuel nozzle plate that structurally supports the fuel nozzles and serves to distribute the fuel flowing from an upstream side to the fuel nozzles, and a perforated plate arranged downstream of the fuel nozzles and having nozzle holes corresponding to the fuel nozzles. The fuel nozzle assembly comprises a central fuel nozzle assembly, the fuel nozzles of which each have the same outer diameter, and multiple outer circumferential fuel nozzle assemblies.In the burner, the central fuel nozzle assembly is located at its center, and the multiple outer-circumference fuel nozzle assemblies are arranged to surround the central fuel nozzle assembly when viewed from downstream of the burner. Each of the outer-circumference fuel nozzle assemblies contains at least two types of fuel nozzles that differ in their outer diameter. Based on a boundary defined by a radial distance from the center of the burner, in each of the outer-circumference fuel nozzle assemblies, the fuel nozzles with a large outer diameter are arranged in an outer circumferential region from the boundary on a side facing away from the central fuel nozzle assembly, and the fuel nozzles with a small outer diameter are arranged in an inner circumferential region from the boundary on a side facing the central fuel nozzle assembly.

[0014] The gas turbine combustion chamber device according to the present invention comprises a burner equipped with a fuel nozzle assembly having multiple fuel nozzles for fuel supply, a fuel nozzle plate that structurally supports the fuel nozzles and serves to distribute the fuel flowing from an upstream side to the fuel nozzles, and a perforated plate arranged downstream of the fuel nozzles and having nozzle holes corresponding to the fuel nozzles. The fuel nozzle assembly comprises a central fuel nozzle assembly, the fuel nozzles of which each have the same outer diameter, and multiple outer circumferential fuel nozzle assemblies, the fuel nozzles of which each have the same outer diameter.In the burner, the central fuel nozzle assembly is located in its center, and the multiple outer-circumference fuel nozzle assemblies are arranged such that they surround the central fuel nozzle assembly when viewed from downstream of the burner, considering the fuel nozzle plate and the fuel nozzles. The outer diameter of the fuel nozzles of the central fuel nozzle assembly is smaller than the outer diameter of the fuel nozzles of the outer-circumference fuel nozzle assemblies.

[0015] The gas turbine combustion chamber device according to the present invention offers structural reliability with respect to vibrations under fluid force and high environmental performance due to uniform combustion, which is achieved by optimizing the outer diameter of the fuel nozzle under fluid force, which differs according to the position of the fuel nozzle. Brief description of the drawings Fig. Figure 1 is a sectional view of an exemplary gas turbine combustion chamber device according to the present invention, illustrating fuel and air flows and a combustion process in a schematic manner; Fig. Figure 2 is a sectional view of components forming a burner of a gas turbine combustion chamber device as a first embodiment according to the present invention; Fig. 3 represents a relationship between the vibration load occurring in a fuel nozzle and the distance from the center of a burner in a generally used structure; Fig. Figure 4 is a sectional view of the fuel nozzles of the gas turbine combustion chamber device as the first embodiment according to the present invention, which shows a distribution of the outer diameter of the fuel nozzles. Fig. Figure 5 illustrates the distribution of the outer diameter of the fuel nozzles of the gas turbine combustion chamber device as a second embodiment according to the present invention, when a fuel nozzle plate and the fuel nozzles are viewed from a downstream side of the burner without a perforated plate; Fig. Figure 6 illustrates the distribution of the outer diameter of the fuel nozzles in the generally used structure, which Fig. 5 corresponds to; Fig. Figure 7 illustrates the distribution of the outer diameter of the fuel nozzles of the gas turbine combustion chamber device as a third embodiment according to the present invention, which Fig. 5 corresponds to; Fig. Figure 8 represents the distribution of the outer diameter of the fuel nozzles of the gas turbine combustion chamber device as a fourth embodiment according to the present invention; and Fig. Figure 9 is a sectional view of each type of fuel nozzle of the gas turbine combustion chamber device as a fifth embodiment according to the present invention. Detailed description of the preferred embodiments

[0016] A gas turbine combustion chamber device according to the present invention is described below with reference to examples shown in the drawings. The same components in the respective examples are designated by the same reference numerals. First embodiment

[0017] An example of components that form a gas turbine plant 1 is given with reference to Fig. 1 described.

[0018] How Fig. Figure 1 shows that the gas turbine system 1 consists mainly of a compressor 3, which compresses air 2 taken from the environment, a combustion chamber device 7, which burns compressed air 4, which has been compressed by the compressor 3, and a fuel 5 at high temperature and high pressure to produce a combustion gas 6, a gas turbine 8, which is driven by the combustion gas 6 produced in the combustion chamber device 7 to extract energy from the combustion gas 6 in the form of rotational energy, and a generator 9, which generates energy using the rotational energy extracted by the gas turbine 8.

[0019] The combustion chamber device 7 consists of an end flange 10, an outer cylinder 11, a perforated plate 12, a fuel nozzle plate 13, fuel nozzles 14, and a lining 15. The compressed air 4, which has been compressed by the compressor 3, flows through a channel 16 formed by the outer cylinder 11 and the lining 15, and flows into a burner 17. Part of the compressed air 4 flows into the lining 15 as cooling air 18, thus cooling the lining 15.

[0020] The fuel 5 flows through a fuel supply pipe 19 of the end flange 10 into the fuel nozzle plate 13 and flows through the respective fuel nozzles 14 for injection into the perforated plate 12. At an inlet of a nozzle hole 20 of the perforated plate 12 on one side of the fuel nozzles, the fuel 5 injected through the fuel nozzles 14 and the compressed air 4 are mixed. A mixture 21 of the fuel 5 and the compressed air 4 is injected towards a combustion chamber 22 such that a flame 23 is formed.

[0021] The combustion chamber device 7 of the example is configured to use fuels such as coke oven gases, refinery exhaust gases and coal gasification gases in addition to natural gas.

[0022] Fig. Figure 2 illustrates components that form the burner 17 of the gas turbine combustion chamber device as the first embodiment according to the present invention.

[0023] How Fig. Figure 2 shows that the burner 17 consists of the perforated plate 12, the fuel nozzle plate 13 and the fuel nozzles 14.

[0024] An upstream end 30 of the fuel nozzle 14 is metallurgically connected to the fuel nozzle plate 13, and the connected section is sealed to prevent leakage of the fuel 5. A downstream end 31 of the fuel nozzle 14 is not in contact with the nozzle hole 20 of the nozzle plate 12 to allow the free flow of compressed air 4 into the nozzle hole 20. Typically, the upstream end 30 of the fuel nozzle 14 and the fuel nozzle plate 13 are joined by welding or brazing.

[0025] Fig. Figure 3 shows experimental data (a relationship between the vibration load in the fuel nozzle and the distance from the center of the burner in the generally used structure) as the basis of the present invention.

[0026] Fig. Figure 3 represents the relationship between the vibration load occurring in the fuel nozzle 14, which was measured in an airflow test for supplying compressed air at normal temperature to the combustion chamber device with an actual machine structure, and a distance 100 (see Figure 3). Fig. 2) between the fuel nozzle 14 and a center 40 of the burner.

[0027] Fig. 3 indicates that there is a tendency for the vibration load to increase when the dynamic pressure at an inlet of the burner 17 is higher and when the fuel nozzle is located on the outer circumferential side away from the center 40 of the burner 17.

[0028] The test results show that the fluid force acting on the outermost peripheral fuel nozzle 14, which is furthest from the center 40 of the burner 17, is highest and the vibration load in the outermost peripheral fuel nozzle 14 is highest when each fuel nozzle's outer diameter 14 is the same.

[0029] An explanation is given as described below with regard to the mechanism by which the fluid force acting on the outermost peripheral fuel nozzle 14 is increased.

[0030] As in Fig. As shown in Figure 1, the compressed air 4 flowing into the burner 17 flows through the perforated plate 12 into the combustion chamber 22. Accordingly, the flow rate of the compressed air 4 flowing around the fuel nozzle 14 decreases as the compressed air 4 flows towards the center of the burner 17. In conjunction with the reduction in flow rate, the flow velocity of the compressed air 4 flowing around the fuel nozzle 14 also decreases. Due to the positive correlation between the fluid force acting on the fuel nozzle 14 and the flow velocity of the compressed air, the fluid force acting on the outer peripheral fuel nozzle 14 is higher than the fluid force acting on the inner peripheral fuel nozzle 14.

[0031] With reference to Fig. 4 An explanation is given with regard to a structure of the burner 17 of the gas turbine combustion chamber device as an example according to the present invention.

[0032] How Fig. As shown in Figure 4, the burner 17 of the example consists of a fuel nozzle assembly containing the fuel nozzles 14 (described later), the fuel nozzle plate 13, which structurally supports the fuel nozzles 14 and serves to distribute the fuel flowing from an upstream side to the fuel nozzles 14, and the perforated plate 12 for mixing the fuel 5 injected by the fuel nozzles 14 with the compressed air 4.

[0033] The burner generally used has fuel nozzles 14, each with the same outer diameter. How Fig. As specified in Figure 4, the outer diameter of the fuel nozzle 14 in the burner 17 of the example according to the present invention becomes smaller when it is arranged closer to the center 40 of the burner 17 on the inner circumferential side, and the outer diameter of the fuel nozzle 14 becomes larger when it is arranged further away from the center 40 of the burner 17 on the outer circumferential side (the side facing away from the center 40 of the burner 17). The outer circumferential fuel nozzles 14 with a large outer diameter are arranged at intervals that are smaller than those of the inner circumferential fuel nozzles 14 with a small outer diameter.

[0034] In the burner generally used, the outer diameter of the fuel nozzle 14 is determined such that the vibration resistance for the outermost peripheral fuel nozzle 14 is set under the highest fluid force and the inner peripheral fuel nozzle 14 has the same outer diameter as that of the outer peripheral fuel nozzle 14.

[0035] In the burner 17 of the example according to the present invention, the outer diameter of the inner circumferential fuel nozzle 14 is manufactured to be smaller than that of the outer circumferential fuel nozzle 14 under the low fluid force. Therefore, it is possible to arrange the inner circumferential fuel nozzles 14 more densely than the outer circumferential fuel nozzles 14 need to be arranged, resulting in improved fine fuel distribution. Since the outer diameter of the inner circumferential fuel nozzle 14 is manufactured to be smaller than that of the outer circumferential fuel nozzle 14, the manufacturing costs for the fuel nozzles 14 can be reduced.

[0036] The outer circumferential fuel nozzles 14 can be shaped in different forms, that is, the fuel nozzles 14 have uniform outer diameters in the axial direction of the fuel nozzles 14 and have outer diameters that vary along the axial direction of the fuel nozzles 14.

[0037] If with reference to Fig. Since the outer diameters of the fuel nozzles 14 are manufactured uniformly in the axial direction, the inner diameter of the nozzle hole 20 of the perforated plate 12 will differ between the inner and outer circumferential sides. Therefore, the design must be carried out taking into account the difference in the inner diameter of the nozzle hole 20 between the inner and outer circumferential sides.

[0038] If only the outer diameter of a proximal end of the outer circumferential fuel nozzle 14 is manufactured larger, as described later in a fifth embodiment, the outer diameters of the tip ends of both the outer circumferential fuel nozzles 14 and the inner circumferential fuel nozzles 14 can be manufactured uniformly.

[0039] In the structure described above, the fuel nozzles 14 with a large outer diameter are located on the outer circumferential side of the burner 17, where they are subject to the stronger fluid force, while the fuel nozzles 14 with a small outer diameter are located on the inner circumferential side, where they are subject to the weaker fluid force. This makes it possible to optimize the outer diameter of the fuel nozzle 14 in accordance with the fluid force, which varies depending on the position of the fuel nozzle 14. This results in structural reliability with respect to vibrations under the fluid force and high environmental performance due to uniform combustion. Second embodiment

[0040] Fig. Figure 5 illustrates in detail the structure of the burner 17 of the gas turbine combustion chamber device as a second embodiment according to the present invention. Fig. Figure 5 shows the fuel nozzle plate 13 and the fuel nozzles 14 downstream of 41 of the burner (see Fig. 4) viewed without the perforated plate 12, as in Fig. 4 shown.

[0041] Typically, the burner 17 of the combustion chamber device 7 in the example according to the present invention contains several fuel supply systems, as shown in Fig. 5 is shown. With reference to Fig. 5 is a central fuel nozzle assembly 50, which contains fuel nozzles 14, each with the same outer diameter, arranged in the center of the burner 17. Several outer circumferential fuel nozzle assemblies 51 are arranged such that they surround the central fuel nozzle assembly 50. One of the outer circumferential fuel nozzle assemblies 51 contains at least two types of fuel nozzles 53, 54, which have different outer diameters. The fuel nozzles 53 with the large outer diameter of the outer circumferential fuel nozzle assembly 51 are arranged on the outer circumferential side (the radially outer side of the burner 17) on a side facing away from the central fuel nozzle assembly 50. The fuel nozzles 54 with the small outer diameter of the outer circumferential fuel nozzle assembly 51 are arranged on the inner circumferential section on a side facing the central fuel nozzle assembly 50.

[0042] A boundary is defined by an arbitrary radial distance from the center of the outer circumferential fuel nozzle group 51. The fuel nozzles 53 with a large outer diameter of the outer circumferential fuel nozzle group 51 are arranged in an outer circumferential region from the boundary on the side facing away from the central fuel nozzle group 50 (the radially outer side of the burner 17). The fuel nozzles 54 with a small outer diameter of the outer circumferential fuel nozzle group 51 are arranged in an inner circumferential region from the boundary on the side facing the central fuel nozzle group 50.

[0043] In burner 17, the fuel supply system differs between the central fuel nozzle group 50 and the outer-circumferential fuel nozzle groups 51 on the outer circumferential side. The fluid force acting on the fuel nozzles 14 is high when the fuel nozzle is oriented towards the outer circumferential side of the burner 17. Therefore, the fluid force acting on the outer-circumferential fuel nozzle group 51 is higher than the fluid force acting on the central fuel nozzle group 50. In particular, the fluid force acting on a fuel nozzle group 52, which consists of the large-diameter fuel nozzles 53 of the outer-circumferential fuel nozzle group 51, is higher.

[0044] In the generally used design approach, the outer diameter of the fuel nozzle 14, as in Fig. Figure 6 shows that the strength for an outermost circumferential fuel nozzle 60 is determined such that it withstands the highest fluid force. The determined outer diameter is set for all fuel nozzles 14.

[0045] However, in the second embodiment according to the present invention, the fuel nozzle group 52 contains, as in Fig. As shown in section 5, the fuel nozzles 53 have a large outer diameter under the high fluid force, each with the same outer diameter as the one shown in Fig. As shown in Figure 6, the fuel nozzles 54 on the inner circumferential side have no outer diameter. The outer diameter of each of the fuel nozzles of the central fuel nozzle group 50 is set such that it is the same as that of each of the fuel nozzles 54 of the outer circumferential fuel nozzle group 51 on the side facing the central fuel nozzle group 50. This makes it possible to arrange the fuel nozzles very close together and to reduce manufacturing costs.

[0046] The structure of the example described above according to the present invention provides similar effects to those derived from the first embodiment and ensures that the fuel nozzles are arranged very close together and that manufacturing costs are reduced. Third embodiment

[0047] Fig. Figure 7 illustrates in detail a structure of the burner 17 of the gas turbine combustion chamber device as a third embodiment according to the present invention.

[0048] In the same way as Fig. 5 illustrates Fig. 7 the fuel nozzle plate 13 and the fuel nozzles 14 viewed from downstream 41 of the burner without the perforated plate 12 as in Fig. 4 shown.

[0049] In the structure as in Fig. As shown in Figure 7, the fuel supply system differs in the central fuel nozzle group 50, which is located in the center of the burner 17, and the outer-circumference fuel nozzle groups 51, which are located on the outer circumference of the burner 17. The fluid force acting on the fuel nozzle 14 is higher when it is located towards the outer circumference of the burner 17. Accordingly, the fluid force acting on the outer-circumference fuel nozzle group 51 is higher than the fluid force acting on the central fuel nozzle group 50.

[0050] In the example according to the present invention, the outer circumferential fuel nozzle groups 51, which surround the central fuel nozzle group 50, use, under the higher fluid force, the fuel nozzles 53 with a large outer diameter, each having the same outer diameter as that which is in Fig. Figure 5 shows that the central fuel nozzle group 50, located in the middle, uses fuel nozzles 54 with a small outer diameter. This ensures that the fuel nozzles are very closely spaced and reduces manufacturing costs.

[0051] As in Fig. As shown in Figure 5, in the second embodiment according to the present invention, only the outer diameter of each fuel nozzle 53, which forms the fuel nozzle group 52 of the circumferential fuel nozzle group 51 under a particularly high fluid force, is manufactured larger. In this example according to the present invention, each outer diameter of the fuel nozzles 53 is manufactured uniformly for the respective fuel supply systems, such that a reduction in manufacturing costs is expected.

[0052] The example described above provides the same effects as those derived from the second embodiment. Fourth embodiment

[0053] Fig. Figure 8 represents the distribution of the outer diameter of the fuel nozzle of the gas turbine combustion chamber device as a fourth embodiment according to the present invention.

[0054] With reference to Fig. 8 provide experimental data as in Fig. Figure 3 shows that the fluid force acting on the fuel nozzle 14 is proportional to the radial distance of the fuel nozzle 14 from the center of the burner.

[0055] Assuming that the fluid force is defined as the uniformly distributed load and the fuel nozzle 14 is clamped on one side, the load is inversely proportional to the cube of the outside diameter of the fuel nozzle 14. If the vibration load occurring in the fuel nozzles 14 is caused to be uniform regardless of the radial distance, the outside diameter of the fuel nozzle 14 is proportional to the cube root of the radial distance, as determined by a minimum outside diameter 80 as shown in Fig. 8 is shown.

[0056] In addition to the fluid force associated with the flow of compressed air, the overall vibration of the combustion chamber device must be taken into account. Therefore, the outer diameter of the fuel nozzle 14 has a lower limit, such as a minimum outer diameter 81 as shown in Fig. 8 shown on.

[0057] In general, the outer diameter of the fuel nozzle 14 is determined by designing such that the strength for the fuel nozzle is set at the outermost circumference and the same outer diameter is set for all fuel nozzles regardless of the radial distance from the center of the burner.

[0058] However, in the second embodiment, the individual fuel nozzle group contains, as in Fig. Figure 5 shows two types of fuel nozzles with different outer diameters. As shown in Fig. As shown in Figure 7, in the third embodiment two types of fuel nozzles with different outer diameters are used for the central fuel nozzle group and the outer circumferential fuel nozzle groups, respectively. The outer diameter of the fuel nozzle is set such that it is greater than or equal to the minimum outer diameter as shown in Figure 7. Fig. 8 is shown.

[0059] In the example according to the present invention, the outer diameter of the fuel nozzle can be defined along the distribution of the minimum outer diameter. Since the outer diameters differ according to the radial distance from the center of the burner, the example is implemented under the assumption that the burner 17 is manufactured by a process such as three-dimensional layer formation.

[0060] In the structure of the example according to the present invention, the outer diameters of all fuel nozzles are reduced to the minimum outer diameter required to ensure strength. This example provides the same effects as those derived from the first embodiment and allows the fuel nozzles to be arranged with the highest density. Fifth embodiment

[0061] Fig. Figure 9 illustrates in detail a structure of the burner 17 of the gas turbine combustion chamber device as a fifth embodiment according to the present invention. Fig. Figure 9 is a sectional view of the burner 17, which consists of the fuel nozzle plate 13 and the fuel nozzles 14.

[0062] A proximal end 90 of the fuel nozzle 14 is a section where the highest vibration load occurs. In the example according to the present invention, the outer diameter of the proximal end 90 of the fuel nozzle 14 is manufactured larger on an outer circumferential side 91 to reduce the vibration load. An outer diameter 92 of a tip end of the fuel nozzle 14 is manufactured to be the same as an outer diameter 94 of the fuel nozzle 14 on an inner circumferential side 93 to reduce the pressure loss that occurs when the compressed air 4 flows through a region 95 between the fuel nozzles.

[0063] Since the fluid force acting on the fuel nozzles 14 on the inner circumferential side 93 is low, the outer diameter 94 is manufactured uniformly in the axial direction of the fuel nozzle. Because the fuel nozzles 14 with their small outer diameter are arranged very close together, the fine distribution of the fuel can be improved.

[0064] The example described above provides the same effects as those derived from the first embodiment and reduces the pressure loss that occurs when the compressed air 4 flows through the area 95 between the fuel nozzles.

[0065] The examples have been described in detail for the sake of clarity regarding the present invention. The present invention is not necessarily limited to the embodiment that incorporates all the structures described above. It is possible to partially replace a structure from one of the examples with a structure from another example, or to partially add a structure from one of the examples to the structure of another example. It is also possible to add, remove, or replace a section of the structure from one of the examples with a section of the structure from another example. List of reference symbols 1 gas turbine plant, 2 air, 3 compressor, 4 compressed air, 5 Fuel, 6 Combustion gas, 7 Combustion chamber device, 8 Gas turbine, 9 Generator, 10 End flange, 11 external cylinders, 12-hole plate, 13 Fuel nozzle plate, 14 Fuel nozzle, 15 Lining, 16 Channel between outer cylinder and lining, 17 burners, 18 Cooling air, 19; Fuel supply pipe, 20 nozzle holes of the perforated plate, 21 Mixture of fuel and compressed air, 22 Combustion chamber, 23 flames, 30 upstream end of the fuel nozzle, 31 Downstream end of the fuel nozzle, 40 Middle of the Brenner Pass, 41 downstream of the burner, 50 Central fuel nozzle group in the center of the burner, 51 Fuel nozzle group on the radial outside of the burner, 52 outermost peripheral fuel nozzle group of the burner, 53 Fuel nozzle with large outer diameter, 54 Fuel nozzle with small outer diameter, 60 outermost peripheral fuel nozzle, 90 proximal end of the fuel nozzle, 91 Outer circumference side, 92 Outer diameter of the tip end of the outer circumferential fuel nozzle, 93 inner circumference side, 94 Outer diameter of the tip end of the inner circumferential fuel nozzle, 95 area between fuel nozzles and 100 meters distance from the center of the burner

Claims

Gas turbine combustion chamber device (7) equipped with a burner (17), the burner (17) comprising: a fuel nozzle assembly with multiple fuel nozzles (14) for fuel supply; a fuel nozzle plate (13) structurally supporting the fuel nozzles (14) and serving to distribute the fuel (5) flowing from an upstream side to the fuel nozzles (14);and a perforated plate (12) arranged downstream of the fuel nozzles (14) and having nozzle holes (20) corresponding to the fuel nozzles (14), wherein the fuel nozzle group comprises outer circumferential fuel nozzles and inner circumferential fuel nozzles, wherein an outer diameter of the outer circumferential fuel nozzles is larger than an outer diameter of the inner circumferential fuel nozzles, wherein fuel (5) supplied by the fuel nozzles (14) and compressed air (4) are caused to mix at inlets of the nozzle holes (20) of the perforated plate (12) on one side of the fuel nozzles, and wherein the fuel nozzle group comprises a central fuel nozzle group (50) having fuel nozzles (14) of the same outer diameter, and several outer circumferential fuel nozzle groups (51);in the burner (17) the central fuel nozzle group (50) is arranged in its center and the multiple outer circumferential fuel nozzle groups (51) are arranged such that they surround the central fuel nozzle group (50) when the fuel nozzle plate (13) and the fuel nozzles (14) are viewed from downstream of the burner (17), each of the multiple outer circumferential fuel nozzle groups (51) forming a circular arrangement of fuel nozzles (14); each of the outer circumferential fuel nozzle groups (51) contains at least two types of fuel nozzles (14) which differ from each other with respect to their outer diameter;and based on a boundary defined by a radial distance (100) from the center (40) of the burner (17), in each of the outer circumferential fuel nozzle groups (51) the fuel nozzles (53) with a large outer diameter are arranged in an outer circumferential region from the boundary on a side facing away from the central fuel nozzle group (50) and the fuel nozzles (54) with a small outer diameter are arranged in an inner circumferential region from the boundary on a side facing the central fuel nozzle group (50). Gas turbine combustion chamber device (7) according to claim 1, wherein in the fuel nozzle group the outer circumferential fuel nozzles (52) are arranged with a distance (95) that is smaller than a distance of the inner circumferential fuel nozzles (54). Gas turbine combustion chamber device (7) according to claim 1 or 2, wherein only the outer diameter of a proximal end (90) of the fuel nozzles (53) is manufactured with a large outer diameter and the outer diameters of the tip ends of the fuel nozzles (53) with a large outer diameter and of the fuel nozzles (54) with a small outer diameter are the same. Gas turbine combustion chamber device (7) according to claim 1, wherein each outer diameter of the fuel nozzles (14) of the outer circumferential fuel nozzle groups (51) in the outer circumferential region is proportional to the cube root of the radial distance (100) from the center (40) of the burner (17) of the outer circumferential fuel nozzle groups (51) in the outer circumferential region from the limit on the side facing away from the central fuel nozzle group (50) and each outer diameter of the fuel nozzles (14) of the outer circumferential fuel nozzle groups (51) in the inner circumferential region from the limit on the side facing the central fuel nozzle group (50) corresponds to a minimum outer diameter of the fuel nozzles (14) in the outer circumferential region. Gas turbine combustion chamber device (7) according to claim 1, wherein the outer diameter of the fuel nozzles (14) of the central fuel nozzle group (50) is the same as the outer diameter of the fuel nozzles (14) of the outer circumferential fuel nozzle groups (51) on the side facing the central fuel nozzle group (50). Gas turbine combustion chamber device (7) according to one of claims 1, 2, 4 and 5, wherein the cross-sectional shapes of all fuel nozzles (14) are manufactured uniformly in an axial direction of the fuel nozzles (14). Gas turbine combustion chamber device (7) equipped with a burner (17), the burner (17) comprising: a fuel nozzle assembly with multiple fuel nozzles (14) for fuel supply; a fuel nozzle plate (13) structurally supporting the fuel nozzles (14) and serving to distribute the fuel (5) flowing from an upstream side to the fuel nozzles (14);and a perforated plate (12) arranged downstream of the fuel nozzles (14) and having nozzle holes (20) corresponding to the fuel nozzles (14), wherein the fuel nozzle assembly comprises outer circumferential fuel nozzles and inner circumferential fuel nozzles, wherein an outer diameter of the outer circumferential fuel nozzles is larger than an outer diameter of the inner circumferential fuel nozzles, wherein fuel (5) supplied by the fuel nozzles (14) and compressed air (4) are caused to mix at inlets of the nozzle holes (20) of the perforated plate (12) on one side of the fuel nozzles, and wherein the fuel nozzle assembly comprises a central fuel nozzle assembly (50) whose fuel nozzles (14) each have the same outer diameter, and several outer circumferential fuel nozzle assemblies (51) whose fuel nozzles (14) each have the same outer diameter;in the burner (17) the central fuel nozzle group (50) is arranged in its center and the multiple outer circumferential fuel nozzle groups (51) are arranged such that they surround the central fuel nozzle group (50) when the fuel nozzle plate (13) and the fuel nozzles (14) are viewed from downstream of the burner (17), each of the multiple outer circumferential fuel nozzle groups (51) forming a circular arrangement of fuel nozzles (14); and the outer diameter of the fuel nozzles (14) of the central fuel nozzle group (50) is smaller than the outer diameter of the fuel nozzles (14) of the outer circumferential fuel nozzle groups (51).

Images