Gas turbine combustion chamber device and method for producing a combustion component

Abstract

A gas turbine combustor device (7) comprising a burner component (12, 14) formed by additive 3D manufacturing, the burner component (12, 14) comprising: a first part (61, 90, 92) used in a first temperature range and / or in a first load range, and a second part (60, 91) used in a second temperature range lower than the first temperature range and / or in a second load range lower than the first load range, and characterized in that a layer formation speed at which a metal material has been layered in the first part (61, 90, 92) by the additive 3D manufacturing is lower than a layer formation speed at which the metal material has been layered in the second part (60, 91), wherein the burner component is a perforated plate (12) that mixes fuel with air, wherein the first part (61) is located on the flame side of the perforated plate (12), and the second part (60) is located on the side opposite the flame side of the perforated plate (12).

Description

BACKGROUND OF THE INVENTION

[0001] The present invention relates to a structure of a gas turbine combustor device and a method for manufacturing the gas turbine combustor device, and more particularly, to a technology effectively applied to a structure and a manufacturing method of a combustor component formed by a 3D metal additive manufacturing technology.

[0002] In a gas turbine, strict environmental standards are set for the NOx emitted during operation to reduce the impact of exhaust gases on the environment. Since the amount of NOx emitted increases with increasing flame temperatures, it is necessary to locally suppress the formation of high-temperature flames and thereby achieve uniform combustion. To achieve uniform fuel combustion, a complex burner structure is required to ensure high fuel dispersion.

[0003] A 3D additive manufacturing technology is proposed for the production of the complex burner structure. According to 3D additive manufacturing technology, it is possible to produce a complex structure by irradiating metal powders with lasers and thereby sintering the metal powders. By applying 3D additive manufacturing technology to the production of the burner structure (burner component), it is possible to realize the complex structure, which leads to improved fuel dispersion.

[0004] As a prior art of the technical field of 3D additive manufacturing, there is a field such as that described in, for example, Japanese Unexamined Patent Application Publication JP 2017-15326 A.JP 2017-15326 A discloses “a gas turbine combustor device including a combustion chamber into which fuel and air are supplied, a perforated plate located on the inlet side of the combustion chamber and in which a plurality of nozzle holes are formed in a state of being concentrically arranged, a plurality of fuel nozzles arranged in the perforated plate on the inlet sides of the respective nozzle holes and supplying the fuel to the combustion chamber, a fuel nozzle plate supporting the fuel nozzles and distributing the fuel flowing into the fuel nozzles from the inlet side, and a fuel nozzle unit for integrally supporting the plurality of fuel nozzles on a common base in which the fuel nozzle unit is connected to the fuel nozzle plate.”

[0005] Furthermore, JP 2017-15326 A (paragraph

[0028] ) describes that “the fuel nozzle unit 40 is manufactured by cutting, investment casting, additive 3D manufacturing, etc.”

[0006] PTL 2 relates to a system containing a layered structure. The layered structure includes first and second coalesced layers and an intermediate layer disposed between the first and second coalesced layers. The first and second coalesced layers have a higher degree of coalescence than the intermediate layer.

[0007] PTL 3 relates to a gas turbine combustor to which fuel and air are supplied; an air hole plate positioned at an upstream side of the combustor and formed with a plurality of air holes arranged in concentric rows; a plurality of fuel nozzles arranged at an upstream side of each of the air holes in the air hole plate to supply fuel; a fuel nozzle plate for supporting the fuel nozzles and distributing fuel flowing from the upstream side to the fuel nozzles; and a fuel nozzle unit having a plurality of fuel nozzles integrally supported on a common base, the fuel nozzle unit being connected to the fuel nozzle plate.

[0008] PTL 4 relates to a tube-and-pipe fuel injector comprising a fuel plenum disposed within the tube-and-pipe fuel injector and a plurality of premixing pipes extending parallel to each other downstream of the fuel plenum. Each premixing pipe includes an end portion and a radially extending end surface. An additively manufactured pipe tip is fixedly connected to the end portion of a corresponding premixing pipe.

[0009] PTL 5 relates to a method for manufacturing a component, in particular for gas turbines and other thermal machines, comprising the steps of: providing a data set defining the component for use in an additive manufacturing process, manufacturing the component by means of the additive manufacturing process according to the data set, and subjecting the manufactured component to a heat treatment in order to change the microstructure of the manufactured component.

[0010] PTL 6 relates to a method for the additive manufacturing of at least one component region of a component. The method comprises the steps of a) applying at least one powder layer of a powdered component material layer by layer to a component platform in the region of a build-up and joining zone, b) locally solidifying the powder layer by selective exposure by means of at least one high-energy beam in the region of the build-up and joining zone to form a component layer, c) lowering the component platform by a predefined layer thickness and d) repeating steps a) to c) until the component region or the component is completed. Citation listPatent literature PTL 1: JP 2017-15326 PTL 2: DE 10 2015 102 397 A1 PTL 3: JP 2017- 15 326 A PTL 4: US 2015 / 0 167 983 A1 PTL 5: EP 3 025 809 B1 PTL 6: DE 10 2016 209 084 A1 SUMMARY OF THE INVENTION

[0011] Although 3D additive manufacturing enables the production of complex structures, it has problems such as increased film formation time and increased costs. Although it is possible to reduce the film formation time by increasing the laser scanning speed and laser output power when sintering metal powders, a problem arises in this case that the relative density of the material decreases. Since decreasing the relative density also decreases the material strength, a film formation condition for sufficiently increasing the relative density is generally adopted, so the film formation time is increased.

[0012] In a burner structure, there is a part that has a high temperature and / or load applied to it, so it is required to have high material strength, and a part that has a low temperature and / or load applied to it, so it is not required to have high material strength. Accordingly, it is not necessary for the entire burner to have high strength, and it is possible to optimize the strength per part.

[0013] Japanese Unexamined Patent Application Publication No. 2017-15326 does not describe the problems of 3D additive manufacturing such as the above and solutions to these problems.

[0014] Accordingly, in the gas turbine combustor device including the burner component formed by 3D additive manufacturing, the present invention is intended to provide a gas turbine combustor device including a burner component in which the material strength per part is optimized.

[0015] Furthermore, the present invention is also intended to provide a method for producing a burner component which makes it possible to produce the burner component in which the material strength per part is optimized in the process for producing the burner component by additive 3D manufacturing in a relatively short period of time.

[0016] To solve the above-mentioned problems, according to one aspect of the present invention, there is provided a gas turbine combustor device including a burner component formed by 3D additive manufacturing, in which the burner component includes a first part used in a first temperature range and / or in a first load range, and a second part used in a second temperature range lower than the first temperature range and / or in a second load range lower than the first load range, and in which a layer formation speed at which a metal material has been layered in the first part by the 3D additive manufacturing is lower than a layer formation speed at which the metal material has been layered in the second part, wherein the burner component is a perforated plate that mixes fuel with air,and the first part is located on the flame side of the perforated plate (12), and the second part (60) is located on the side opposite the flame side of the perforated plate (12).

[0017] According to another aspect of the present invention, a method for manufacturing a burner component by 3D additive manufacturing is provided, comprising the steps of (a) layering a metal material in a first part used in a high-temperature region and / or in a high-stress region of the burner component at a first layer formation rate and (b) layering the metal material in a second part used in a temperature range and / or in a stress range that is / are lower than the temperature range and / or the stress range of the first part at a second layer formation rate that is higher than the first layer formation rate, wherein the burner component is a perforated plate that mixes fuel with air, and the first part is located on the flame side of the perforated plate (12), and the second part (60) is located on the side,which is opposite the flame side of the perforated plate (12).

[0018] According to the present invention, in the gas turbine combustor device including the burner component formed by the 3D additive manufacturing, it becomes possible to realize the gas turbine combustor device including the burner component in which the material strength per part is optimized.

[0019] In addition, it is also possible to realize the process for manufacturing the burner component by additive 3D manufacturing, which makes it possible to manufacture the burner component in which the material strength per part is increased in the relatively short period of time.

[0020] Accordingly, it becomes possible to create the gas turbine combustor device which has high environmental performance and cost advantage.

[0021] Problems, configurations, and effects other than the above will become apparent from the following description of embodiments. BRIEF DESCRIPTION OF THE DRAWINGS Fig. 1 is a sectional view showing an example of a schematic configuration of a gas turbine combustor apparatus according to an embodiment of the present invention; Fig. 2 is an enlarged view showing an example of a burner 17 in Fig. 1 represents; Fig. 3 is a diagram conceptually showing an example of a relative density distribution of metal material on a perforated plate according to a first embodiment of the present invention; Fig. 4 is a diagram illustrating an example of a relationship between an axial direction position and a film forming speed of the orifice plate according to the first embodiment of the present invention; Fig. 5 is a diagram conceptually illustrating an example of another relative density distribution of metal material on a perforated plate according to a second embodiment of the present invention; Fig. 6 is a diagram illustrating an example of another relationship between the axial direction position and the film forming speed of the orifice plate according to the second embodiment of the present invention; Fig. 7 is a diagram conceptually illustrating an example of still another relative density distribution of metal material at an adjacent part of a nozzle hole in the orifice plate according to a third embodiment of the present invention; Fig. 8 is a diagram conceptually illustrating an example of yet another relative density distribution of metal material at the fuel nozzle according to a fourth embodiment of the present invention; and Fig. 9 is a diagram illustrating an example of a relationship between the position and the film formation speed of the fuel nozzle according to the fourth embodiment of the present invention. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0022] Embodiments of the present invention will be described below with reference to the accompanying drawings. Incidentally, the same reference numerals are assigned to components with the same configurations, and detailed descriptions of duplicated parts are omitted.

[0023] First, based on Fig. 1 and Fig. 2 describes a gas turbine combustor device which becomes the subject of the present invention. Fig.1 is a sectional view showing an example of a schematic configuration of a gas turbine combustor apparatus according to an embodiment of the present invention. Fig. 1, the gas turbine combustor device is shown as a gas turbine plant 1 containing a compressor 3, a gas turbine 8 and a generator 9. Fig. 2 is an enlarged view showing an example of a burner 17 in Fig. 1 represents.

[0024] As in Fig.1, the gas turbine plant 1 includes the compressor 3 which draws in air 2 from the atmosphere and compresses the air 2, a combustor 7 which mixes compressed air 4 compressed in the compressor 3 with fuel 5, combusts the fuel 5 with the compressed air 3 and produces a high-temperature and high-pressure combustion gas 6, the gas turbine 8 which is driven by the combustion gas 6 produced in the combustor 7 and extracts energy of the combustion gas 6 as rotational power, and the generator 9 which generates electricity using the rotational power of the gas turbine 8.

[0025] In Fig. 1, as an example of the combustion chamber device 7, a structure is shown which is shown in Fig.1 includes an end flange 10, an outer cylinder 11, a perforated plate 12, a fuel nozzle plate 13, fuel nozzles 14 and a liner 15. However, the present invention is also applicable to combustion chamber devices with different structures, not to the combustion chamber device 7 in Fig. 1 limited, applicable.

[0026] The compressed air 4, which is compressed by the compressor 3, passes through a flow path 16 formed between the outer cylinder 11 and the liner 15 and flows into the burner 17. A portion of the compressed air 4 flows into the liner 15 as cooling air 18 for cooling the liner 15.

[0027] The fuel 5 passes through a fuel supply pipe 19 in an end flange 10, flows into the fuel nozzle plate 13, passes through the respective fuel nozzles 14, and is injected into the perforated plate 12. The fuel 5 injected by the fuel nozzles 14 and the compressed air 4 are mixed at the inlet openings on the fuel nozzle side of the nozzle holes 20 in the perforated plate 12, and an air-fuel mixture 21 of the fuel 5 and the compressed air 4 is injected into a combustion chamber 22, forming flames 23.

[0028] Incidentally, it is possible for the combustor device 7 according to the present invention to use fuels such as coke oven gas, refinery off-gas, coal gasification gas, etc., not limited to natural gas.

[0029] Fig. Figure 2 is an enlarged view showing an example of the burner 17 in Fig. 1 represents. Fig.Figure 2 shows an enlarged view of the upper half portion of the burner 17. The burner 17 includes the orifice plate 12, the fuel nozzle plate 13, and the fuel nozzles 14. The center axes 40 of the orifice plate 12 and the fuel nozzle plate 13 are aligned. An inlet end 30 of each fuel nozzle 14 is metallurgically bonded to the fuel nozzle plate 13, and a bonded portion between the inlet end 30 and the fuel nozzle plate 13 is sealed to prevent leakage of the fuel 5.

[0030] A front end 52 of each fuel nozzle is not in contact with each nozzle hole 20 in the orifice plate 12, allowing the compressed air 4 to flow freely into the nozzle holes 20. As a method for joining the inlet-side ends 30 of the nozzle holes 14 to the fuel nozzle plate 13, welding, brazing, etc. are generally used. [First embodiment]

[0031] The following are based on Fig. 3 and Fig. 4 describes a structure and manufacturing method of a burner component according to the first embodiment of the present invention. In the first embodiment, the perforated plate 12 is described as an example of the burner component.

[0032] Fig. 3 illustrates an example of the relative density distribution of a metal material in the perforated plate 12 in the first embodiment. Fig. 3 is an enlarged view showing an example of a part 54 of the perforated plate 12 shown in Fig.2. Since an outlet-side end face 50 of the orifice plate 12 is heated by radiant heat, etc., from the flames 23, a region 61 near the outlet-side end face 50 of the orifice plate 12 reaches a high temperature. On the other hand, an inlet-side end face 51 of the orifice plate 12 and an inner surface 62 of each nozzle hole 20 are cooled with the compressed air 4, so that they reach a lower temperature than the outlet-side end face 50.

[0033] Due to a temperature difference between the outlet-side end surface 50 and the inlet-side end surface 51, and a temperature difference between the outlet-side end surface 50 and the inner surface 62 of each nozzle hole 20, a thermal stress is generated in the region 61. Accordingly, the region 61 has a high temperature, and the thermal stress is generated in the region 61, so that the region 61 is required to have high material strength. On the other hand, a region 60 that is close to the inlet-side end surface 51 of the orifice plate 12 has a low temperature and stress, and the region 60 is not required to have high material strength.

[0034] Accordingly, the perforated plate 12 in the first embodiment is manufactured in a manner that the relative density of the metal material of the region 61 of the perforated plate 12 is increased by reducing a layer formation speed at which the metal material is layered in the region 61 by the 3D additive manufacturing, and thereby, as shown in Fig. 4, priority is given to material strength. On the other hand, the perforated plate 12 is also manufactured in such a way that the layer formation speed at which the metal material is layered is increased in the region 60, so that priority is given to manufacturing time and manufacturing costs. This makes it possible to realize a manufacturing process in which the material strength and the manufacturing cost per part of the perforated plate 12 are optimized.

[0035] A selection example of the film formation rate of a part for low temperature and low load is shown in Table 1. An allowable stress achieved when the film formation rate is low (about 0.1 kg / h) is about 600 MPa. On the other hand, if the film formation rate is high (about 0.2 kg / h), the allowable stress is reduced to about 400 MPa as the specific gravity of the metal material decreases. However, an applied stress is about 300 MPa, and it is lower than the allowable stress (about 400 MPa) achieved when the film formation rate is high. Accordingly, manufacturing by increasing the film formation rate while giving priority to production time and production cost becomes possible. [Table 1] Table 1 Layer formation rate Relative density Metal temperature permissible load Applied load Result of the evaluation high (0.2 kg / h) 95 % 400 °C 400 MPa 300 MPa 0 (strength is established) low (0.1 kg / h) 99 % 400 °C 600 MPa 300 MPa x (production costs are high)

[0036] Table 2 shows a selection example of the film formation rate of a part for high temperature and high load. If the film formation rate is low (about 0.1 kg / h), the allowable stress is about 500 MPa. On the other hand, if the film formation rate is high (0.2 kg / h), the allowable stress is reduced to about 300 MPa as the relative density of the metal material decreases. Since the metal temperature is about 600 °C, which is higher than about 400 °C of the metal temperature of the part for low temperature and low load, the allowable stresses corresponding to the high and low film formation rates are lower than the allowable stresses in Table 1. The applied stress is about 400 MPa, which is higher than the allowable stress (about 300 MPa) achieved if the film formation rate is high.Accordingly, it is necessary to carry out the manufacturing in which the layer formation rate is reduced and thereby giving priority to the material strength. [Table 2] Layer formation rate Relative density Metal temperature permissible load Applied load Result of the evaluation high (0.2 kg / h) 95 % 600 °C 300 MPa 400 MPa x(strength is not established) low (0.1 kg / h) 99 % 600 °C 500 MPa 400 MPa 0 (strength is established)

[0037] However, each relationship between each film formation rate and each property shown in Table 1 and Table 2 is a representative example, and the present invention is also applicable to examples other than the above-mentioned representative examples.

[0038] Although a high-temperature material such as a nickel (Ni), chromium (Cr), iron (Fe) alloy registered under the name of Inconel 718 (registered trademark) or the like is conceivable as the metal material to be layered by 3D additive manufacturing, the present invention is also applicable to a wide range of metal materials.

[0039] As described above, the burner component of the first embodiment includes the first part (region 61) used in the first temperature range (high-temperature range) and / or the first stress range (high-stress range), and the second part (region 60) used in the second temperature range (low-temperature range) lower than the first temperature range (high-temperature range) and / or the second stress range (low-stress range) lower than the first stress range (high-stress range). The film formation rate at which the metal material is layered in the first part (region 61) by 3D additive manufacturing is lower than the film formation rate at which the metal material is layered in the second part (second region 60).

[0040] The relative density of the metal material in the first part (the region 61) is then higher than the relative density of the metal material in the second part (the region 60),

[0041] This makes it possible to realize the gas turbine combustor device including the burner component formed by 3D additive manufacturing, the gas turbine combustor device including the burner component whose material strength in the gas turbine combustor device is optimized per part.

[0042] Furthermore, a method for manufacturing the burner component according to the first embodiment includes, in the method for manufacturing the burner component by the 3D additive manufacturing, the steps of (a) laminating the metal material in the first part used in the high-temperature region and / or the high-stress region of the burner component at the first laminating speed and (b) laminating the metal material in the second part used in the region with a lower temperature and / or stress than the region of the first part at the second laminating speed that is higher than the first laminating speed.

[0043] This makes it possible to implement the burner component manufacturing process by additive 3D manufacturing, which makes it possible to produce the burner component for which the material strength per part is optimized in a relatively short period of time. [Second embodiment]

[0044] Based on Fig. 5 and Fig. 6, a structure and manufacturing method of the burner component according to the second embodiment of the present invention are described. In the second embodiment, similarly to the first embodiment, the perforated plate 12 is described as an example of the burner component.

[0045] Fig. 5 illustrates an example of another relative density distribution of metal material of the perforated plate 12 in the second embodiment. Fig. 5 is a representation in which the representation in Fig.3, a layer formation rate transition region 70 is added. In the manufacturing method according to the first embodiment in Fig. 4, the film formation speeds of the region 60 and the region 61 are discontinuously switched into each other. On the other hand, in a case where the discontinuous switching of the film formation speeds is impossible due to a control of a manufacturing device, or in a case where the material strength is reduced by discontinuous switching of the film formation speeds, it is possible to use a manufacturing method which is Fig. 6, the transition region 70 is arranged.

[0046] That is, as in Fig. 6, it becomes possible to continuously alternate the layer formation rates by arranging the transition region 70. [Third Embodiment]

[0047] Based on Fig.7, a structure and manufacturing method of the burner component according to the third embodiment of the present invention are described. In the third embodiment, the perforated plate 12 is described as an example of the burner component similar to the first embodiment and the second embodiment.

[0048] Fig. Fig. 7 illustrates an example of yet another relative density distribution of metal material in a portion 80 adjacent to the inner surface 62 of each nozzle hole 20 in the orifice plate 12 in the third embodiment. Fig. 7 a sectional view along the line AA in Fig. 3 or Fig. 5. Since the inner surface 62 of each nozzle 20 is cooled with the compressed air 4, a thermal stress is generated in the adjacent part 80 of the inner surface 62 of each nozzle hole 20.

[0049] Accordingly, in the third embodiment, the perforated plate 12 is manufactured in such a manner that the film formation rate of the metal material in the adjacent part 80 of the inner surface 62 is made lower than the film formation rate of the metal material in a region 81 where the thermal stress is reduced, thereby giving priority to the material strength of the adjacent part 80 of the inner surface 62. Furthermore, the perforated plate 12 is manufactured in such a manner that, on the other hand, in the region 81 where the thermal stress is reduced, the film formation rate of the metal material is made higher than the film formation rate of the metal material in the adjacent part 80 of the inner surface 62, thereby reducing the manufacturing time and the manufacturing cost.

[0050] That is, the film formation rate of the metal material in the adjacent part 80 of the inner surface 62 of each nozzle hole 20 formed in the orifice plate 12 is lower than the film formation rate of the metal material in the area 81 located outside the adjacent part 80. [Fourth Embodiment]

[0051] Based on Fig. 8 and Fig. 9, a structure and manufacturing method of the combustor component according to the fourth embodiment of the present invention are described. In the fourth embodiment, one of the fuel nozzles 14 is described as an example of the combustor component.

[0052] Fig. 8 illustrates an example of yet another relative density distribution of metal material of the fuel nozzle 14 in the fourth embodiment. Fig. Fig. 8 is an enlarged view showing an example of a part 55 of the fuel nozzle 14 in Fig.2. The fuel nozzle 14 has a cantilevered structure in which the fuel nozzle 14 is supported on a base 53 on the fuel nozzle 13.

[0053] There are cases where vibration is generated in the fuel nozzle 14 under the influence of the compressed air 4 flowing around the fuel nozzle 14 and the vibration of the fuel nozzle plate 13. Generally, the vibration load is maximized at the base 53. Furthermore, there are cases where the temperature at the front end 52 of the fuel nozzle 14 is increased under the influence of the radiant heat of the flames 23.

[0054] Accordingly, it is necessary to increase the material strength of a region 90 and a region 92 of the fuel nozzle 14, taking into account the vibration load and the radiant heat of the flames 23. On the other hand, since the region 91 has low vibration load and temperature, no problem occurs in the region 91 even if its material strength is low.

[0055] Accordingly, in the fourth embodiment, the fuel nozzle 14 is manufactured in such a way that the film formation speeds of the metal material in the region 90 and in the region 92 of the fuel nozzle 14, as shown in Fig.9, thereby giving priority to material strength. On the other hand, the fuel nozzle 14 is also manufactured by increasing the film formation rate of the metal material in the region 91, thereby giving priority to manufacturing time and cost. This makes it possible to implement the manufacturing process in which the material strength and the manufacturing cost per part of the fuel nozzle 14 are optimized.

[0056] That is, the film formation speeds of the metal material at the root side part (the region 90) and at the front end side part (the region 92) of the fuel nozzle 14 are lower than the film formation speed of the metal material in the region 91 between the root side part (the region 90) and the front end side part (the region 92).

[0057] Incidentally, the present invention is not limited to the above-mentioned embodiments, and various modified examples are included. For example, the above-mentioned embodiments have been described in detail to assist in a better understanding of the present invention, and the present invention is not necessarily limited to the embodiment including all the configurations described above. In addition, it is also possible to replace a configuration of one embodiment with a configuration of another embodiment. In addition, it is also possible to add a configuration of another embodiment to a configuration of one embodiment. In addition, it is possible to add, remove, or replace a configuration of each embodiment with another configuration of each embodiment. 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 outer cylinders 12 hole plate 13 Fuel nozzle plate 14 Fuel nozzle 15 lining 16 Flow path 17 burners 18 Cooling air 19 Fuel supply pipe 20 nozzle holes 21 Air-fuel mixture 22 Combustion chamber 23 Flame 30 outlet end of the (fuel nozzle 14) 40 center axes 40 (of the perforated plate 12 and the fuel nozzle plate 13) 50 outlet-side face (of the perforated plate 12) 51 inlet-side face (of the perforated plate 12) 52 front end (of the fuel nozzle 14) 53 feet (of fuel nozzle 14) 54 Part 54 of the perforated plate 12 55 Part 55 of the fuel nozzle 14 60 area (where the layer formation speed of the perforated plate 12 is high) 61 Area (where the layer formation speed of the perforated plate 12 is low) 62 inner surface (of the nozzle hole 20) 70 (layer formation velocity) transition region 80 part which is adjacent to the inner surface 62 (of the nozzle hole 20) 81 Area (where thermal stress is reduced) 90 area (where the film formation speed of the fuel nozzle 14 is low) 91 Area (where the film formation speed of the fuel nozzle 14 is high) 92 Area (where the film formation speed of the fuel nozzle 14 is low)

Claims

[1] Gas turbine combustion chamber device (7) comprising a burner component (12, 14) formed by additive 3D manufacturing, wherein the burner component (12, 14) contains: a first part (61, 90, 92) that is used in a first temperature range and / or in a first load range, and a second part (60, 91) which is used in a second temperature range lower than the first temperature range and / or in a second load range lower than the first load range, and characterized by , that a layer formation rate at which a metal material in the first part (61, 90, 92) has been layered by additive 3D manufacturing is lower than a layer formation rate at which the metal material in the second part (60, 91) has been layered, wherein the burner component is a perforated plate (12) that mixes fuel with air, wherein the first part (61) is located on the flame side of the perforated plate (12), and the second part (60) is located on the side opposite the flame side of the perforated plate (12). [2] Gas turbine combustion chamber device according to claim 1, wherein the layer formation rate at which the metal material in the first part (61) has been layered and the layer formation rate at which the metal material in the second part (60) has been layered have been continuously alternated between each other. [3] Gas turbine combustion chamber device according to claim 1, wherein a layer formation rate with which the metal material has been layered in a part adjacent to an inner surface (62) of a nozzle hole (20) formed in the perforated plate (12) is lower than a layer formation rate with which the metal material has been layered in an area outside the part adjacent to the inner surface (62) of the nozzle hole (20). [4] Gas turbine combustion chamber device according to claim 1, wherein the relative density of the metal material in the first part (61, 90, 92) is higher than the relative density of the metal material in the second part (60, 91). [5] Method for manufacturing a burner component (12, 14) by additive 3D manufacturing, the method comprising the following steps: (a) Layers of a metallic material in a first part (61, 90, 92) used in a high-temperature and / or high-stress area of ​​the burner component (12, 14), with a first layer formation rate; and (b) Layers of the metal material in a second part (60, 91) which is used in a temperature range and / or load range which is / are lower than the temperature range and / or load range of the first part (61, 90, 92), with a second layer formation rate which is higher than the first layer formation rate, wherein the burner component is a perforated plate (12) which mixes fuel with air, wherein the first part (61) is located on the flame side of the perforated plate (12), and the second part (60) is located on the side opposite the flame side of the perforated plate (12). [6] Method for producing a burner component according to claim 5, wherein the first layer formation rate in step (a) and the second layer formation rate in step (b) are continuously alternated between each other. [7] Method for producing a burner component according to claim 5, wherein a layer formation rate at which the metal material is layered in a part adjacent to an inner surface (62) of a nozzle hole (20) formed in the perforated plate (12) is lower than a layer formation rate at which the metal material is layered in an area outside the part adjacent to the inner surface (62) of the nozzle hole (20).

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