COMBUSTION CHAMBER AND COMBUSTION CHAMBER ARRANGEMENT

Abstract

A combustion chamber (1) with: a distal end portion (31) forming a nozzle (11, 11b) extending along an axis (O) and opening at a distal end (11T), an intermediate section (32) forming a mixing space (32V) behind the distal end section (31) which extends from the nozzle (11, 11b) in a direction intersecting the axis (O), a proximal end portion (33) forming a fuel chamber (33V) behind the intermediate portion (32) to which fuel is supplied from the outside, and a plurality of air introduction tubes (12, 12b, 12c) penetrating the proximal end portion (33) in a direction of the axis (O), having a distal end (11T) communicating with the mixing space (32V), and arranged in a circumferential direction of the axis (O) to surround the axis (O), wherein a fuel supply hole (40, 40b, 40c) through which the fuel chamber (33V) and the mixing chamber (32V) communicate with each other is formed on a surface facing the distal end side of a portion surrounded by the plurality of air introduction pipes (12, 12b, 12c) in the proximal end portion (33), and an extension cylinder part (33T) extending in the direction of the axis (O) to cover the fuel supply hole (40, 40b, 40c) from an outer peripheral side and having an air hole (50) formed to communicate with the mixing space (32V) provided on the surface facing the distal end side.

Description

Background of the inventionField of the invention

[0001] The present invention relates to a combustion chamber and a combustion chamber arrangement. Description of the related art

[0002] Generally, in a combustion chamber, fuel injected from a fuel nozzle is mixed and burned within a cylindrical body to form a flame within the cylindrical body. Specifically, the fuel nozzle includes a first nozzle arranged on a central axis of the combustion chamber and a plurality of second nozzles arranged around the first nozzle in a circumferential direction. Fuel is injected from the first nozzle. The fuel burns in the ambient air. Consequently, a diffusion flame is formed. On the other hand, a premixed gas in which fuel and air are premixed is jetted from the second nozzles. When the diffusion flame contacts the premixed gas, a premixed flame is formed.

[0003] In this case, a premixed flame extending in an axial direction is formed in the combustion chamber as described above, starting from the first nozzle. For this reason, the flame length tends to increase in the axial direction. As the flame length increases, the residence time of the flame in the combustion chamber also increases, which is likely to promote NOx generation. This creates an increased demand for a combustion chamber that can reduce the flame length while maintaining the same output.

[0004] In this way, as a combustion chamber capable of reducing flame size, a device described below in Patent Document 1 has been proposed. The device described in Patent Document 1 has a plurality of tubes all extending in the same direction. A fuel supply hole for injecting fuel is formed on an inner peripheral surface of each tube, and the air and fuel flowing from an upstream side are mixed and expelled from a distal end of the tube. By igniting the air-fuel mixture, a short flame is formed from the distal end of each tube.

[0005] Patent Document 2 discloses a lean premixed swirl nozzle of a low-emission combustor and a full-annular combustor. It adopts lean premixed combustion technology, with a fuel nozzle orifice located on the inner hub of a swirl, and fuel and air begin to meet and mix in a rotating flow channel, followed by further mixing in a premixing segment.

[0006] Patent Document 3 discloses a low-emission gas turbine combustor with a single-swirl head structure. First, the central swirling air and the central natural gas, as well as the non-swirling outer wall air and the outer wall natural gas, are mixed. Then, the swirling air, the non-swirling air, the central natural gas, and the outer wall natural gas are further mixed in a natural gas-air mixing cavity.

[0007] Patent Document 4 relates to fuel burners particularly suited to the needs of gas turbine engines and to improved fuel injectors for these burners. [Patent documents] [Patent Document 1] US 8,112,999 B2 [Patent Document 2] CN 1 08 716 694 A [Patent Document 3] CN 1 07 543 202 A [Patent document 4] DE 22 23 093 A Summary of the invention

[0008] However, the combustor described in Patent Document 1 employs a design in which fuel is supplied from the inner peripheral surface of the tube. Therefore, a region with a higher fuel concentration than other regions is formed along the inner peripheral surface of the tube. This may cause a phenomenon in which the flame flows back to an upstream side (flame flashback). Consequently, there is a risk of hindering stable operation of the combustor.

[0009] The present invention has been made to solve the problems described above, and an object of the present invention is to provide a combustor and a combustor assembly that can be operated more stably.

[0010] A combustor according to one aspect of the present invention is provided with a distal end portion forming a nozzle extending along an axis and open at a distal end, an intermediate portion forming a mixing space behind the distal end portion and extending from the nozzle in a direction intersecting the axis, a proximal end portion forming a fuel space behind the intermediate portion to which fuel is supplied from the outside, and a plurality of air introduction pipes penetrating the proximal end portion in a direction of the axis, having a distal end communicating with the mixing space, and arranged in a circumferential direction of the axis to surround the axis, wherein a fuel supply hole through which the fuel space and the mixing space communicate with each other is formed on a surface facing the distal end side of a portion,which is surrounded by the plurality of air introduction tubes, is formed in the proximal end portion, and an extension cylinder part extending in the direction of the axis to cover the fuel supply hole from an outer peripheral side and having an air hole formed to communicate with the mixing space is provided on the surface facing the distal end side.

[0011] According to the above-mentioned configuration, the air introduced into the mixing space through the air introduction pipe is mixed with fuel in the mixing space to form an air-fuel mixture. By igniting the air-fuel mixture, a flame is generated on a downstream side of the nozzle of the distal end portion. At this time, the fuel supply hole is formed on a surface facing the distal end side of the portion surrounded by the plurality of air introduction pipes in the proximal end portion. Thus, the fuel is injected from the fuel supply hole in the direction of the axis. Further, the fuel supply hole is covered with the extension cylinder part from the outer peripheral side. In addition, an air hole through which the mixing space communicates with the space is formed in the extension cylinder part on the inner peripheral side of the extension cylinder part.Therefore, after the fuel and air have been mixed to a certain extent in the space on the inner circumference side of the expansion cylinder part, the air-fuel mixture can be supplied to the mixing chamber. Thus, the mixing of fuel and air in the mixing chamber can be further promoted.

[0012] In addition, since the fuel supply part is provided along the axis, the fuel concentration in the mixing space increases as the portion is closer to the axis. Therefore, in a flame region formed on the downstream side of the nozzle, a fuel concentration becomes highest in a region through which the axis passes. In other words, the fuel concentration is relatively low on the inner peripheral surface of the nozzle, the inner surface of the mixing space, and a region along the surface on an outer side in the radial direction of each air introduction tube. Consequently, the probability of flashback occurring along these surfaces can be reduced.

[0013] A combustor assembly according to one aspect of the present invention has a plurality of combustion chambers according to the above aspect. The plurality of combustion chambers are arranged in a plane orthogonal to the axis.

[0014] According to the above configuration, a combustor assembly can be provided which has a high output and can be stably operated by arranging a plurality of combustion chambers in which the probability of occurrence of flashback is reduced.

[0015] In the combustion chamber arrangement, the plurality of combustion chambers may be arranged in a lattice shape in the plane orthogonal to the axis.

[0016] In the combustor assembly, each of the plurality of combustors may have a hexagonal shape when viewed from the direction of the axis, and they may be arranged in a honeycomb shape by connecting the end faces thereof to each other.

[0017] In the combustion chamber arrangement, the plurality of combustion chambers may be arranged in a ring shape.

[0018] In the combustion chamber arrangement, the plurality of combustion chambers may be arranged in a staggered manner such that positions of the axis differ from each other in the plane orthogonal to the axis.

[0019] In the combustor assembly, the plurality of combustion chambers may be arranged along a curved concave surface that is convex from one side to the other side.

[0020] According to the above configuration, the flame distribution is made uniform and a more stable flame can be obtained.

[0021] According to one aspect of the present invention, a combustor and a combustor assembly that can be operated more stably can be provided. Short description of the drawings Fig. 1 is a plan view showing a configuration of a combustor assembly according to a first embodiment of the present invention. Fig. 2 is a cross-sectional view showing the configuration of the combustion chamber according to the first embodiment of the present invention. Fig. 3 is a cross-sectional view showing a configuration of a combustion chamber according to a second embodiment of the present invention. Fig. 4 is a cross-sectional view showing a configuration of the combustion chamber according to a third embodiment of the present invention. Fig. 5 is a cross-sectional view showing a configuration of a combustion chamber according to a fourth embodiment of the present invention. Fig. 6 is a plan view showing the configuration of the combustion chamber according to the fourth embodiment of the invention. Fig. 7 is a cross-sectional view showing a configuration of a combustion chamber according to a fifth embodiment of the invention. Fig. 8 is a plan view showing a configuration of a combustion chamber according to a sixth embodiment of the present invention. Fig. 9 is a cross-sectional view showing a configuration of a combustion chamber according to a seventh embodiment of the invention. Fig. 10 is a plan view showing a first modified example of a combustor assembly according to an embodiment of the present invention. Fig. 11 is a plan view showing a second modified example of the combustor assembly according to an embodiment of the present invention. Fig. 12 is a plan view showing a third modified example of the combustor assembly according to the embodiment of the present invention. Fig. 13 is a plan view showing another modified example of the combustor assembly according to the embodiment of the present invention. Detailed Description of the Invention[First Embodiment]

[0022] A first embodiment of the present invention will be described with reference to the Fig. 1 and Fig. 2. A combustion chamber assembly 100 according to the present invention is equipped with a plurality of combustion chambers 1. Each combustion chamber 1 is a small device that forms a small flame. The combustion chamber assembly 100 is thus designed as a so-called micro-flame combustion chamber.

[0023] In particular, as in Fig. 1, the combustor assembly 100 is provided with a plurality of (9) combustion chambers 1 arranged in a lattice shape in a plane orthogonal to an axis O, which is a central axis of the combustion chamber 1. The combustion chamber 1 has a rectangular (square) cross-sectional shape when viewed from a direction of the axis O. Outer surfaces of a pair of adjacent combustion chambers 1 are arranged against each other without a gap.

[0024] Next, the design of the combustion chamber 1 with reference to Fig. 2 are described. Fig. 1 is a cross-sectional view taken along a line AA of Fig. 2. As in Fig. As shown in Figure 2, the combustion chamber 1 is equipped with a distal end portion 31, an intermediate portion 32, a proximal end portion 33 and an air introduction tube 12.

[0025] A nozzle 11 extending along the axis O and having a distal end 11T open to the outside is formed in the distal end portion 31. As shown in Fig. 1, the nozzle 11 has a circular cross-sectional shape centered on the axis O.

[0026] The intermediate portion 32 is integrally provided on a side opposite to the distal end 11T of the distal end portion 31 in a direction of the axis O (a rear end 11R). In the following description, a side where the distal end 11T is located when viewed from the rear end 11R in the direction of the axis O is referred to as a "front side" and "front side," and an opposite side thereto is referred to as a "rear side" and "rear side." A mixing space 32V communicating with the nozzle 11 is formed inside the intermediate portion 32. The mixing space 32V expands in a direction (a radial direction) intersecting the axis O.Specifically, the mixing space 32V is defined by a conical mixing space S1 having a diameter that progressively widens outward in the radial direction from a rear end 11R of the nozzle 11 to the rear side along the axis O, and a cylindrical surface S2 extending in a cylindrical shape from an end portion on a rear side of the mixing surface S1 along the axis O. The mixing space 32V is thus progressively reduced in diameter from the rear side to the nozzle 11.

[0027] The proximal end portion 33 is integrally provided on the rear side of the intermediate portion 32. A fuel space 33V is formed as a hollow part within the proximal end portion 33. Fuel supplied from the outside is stored in the fuel space 33V. A surface facing the front side of the proximal end portion 33 is configured by an annular surface S3 connected to the cylindrical surface S2 of the mixing space 33V and a central surface S4 located on the inner peripheral side of the annular surface S3. The annular surface S3 and the central surface S4 expand at the same position in the direction of the axis O. Further, both the annular surface S3 and the central surface S4 expand in a direction orthogonal to the axis O.

[0028] The air introduction tube 12 is a flow path that penetrates the proximal end portion 33 in the direction of the axis O. Air supplied from the outside is introduced into the aforementioned mixing space 32V through the air introduction tube 12. A plurality (four) of air introduction tubes 12 are provided to surround the axis O at intervals in the circumferential direction. Each air introduction tube 12 extends along an auxiliary axis O2 extending parallel to the axis O. An inner diameter of the air introduction tube 12 is constant over the entire range in the direction of the auxiliary axis O2. End portions at a front side of each air introduction tube 12 communicate with the above-described mixing space 32V. End portions at the rear side of each air introduction tube 12 communicate with an air supply source (not shown).

[0029] Each individual fuel supply hole 40 is formed on the inner side surface of the introduction tube 12A, which is a portion on the inner side in the radial direction of the axis O, in the inner peripheral surface of the plurality of air introduction tubes 12. The inner side surface of the introduction tube 12A is a region facing the axis O side when the air introduction tube 12 is viewed from the direction of the axis O. In the inner peripheral surface of the air introduction tube 12, a region excluding the inner side surface of the introduction tube 12A (i.e., a region facing a side opposite to the axis O) is an outer side surface of an introduction tube 12B. Each fuel supply hole 40 communicates with the fuel space 33V and the space inside the air introduction tube 12. The fuel stored in the fuel space 33V is introduced into the air introduction tube 12 through the fuel supply hole 40.

[0030] Next, the operation of the above-mentioned combustion chamber 1 will be described. In the operation of the combustion chamber 1, fuel and air are respectively supplied to the combustion chamber 1. Air flows from the back to the front through the plurality of air introduction tubes 12. Fuel is supplied (sprayed) into the air flow from the fuel space 33V through the aforementioned fuel supply hole 40. The fuel flows from the back to the front along the inner side surface of the introduction tube 12A into the air introduction tube 12. Thereafter, the fuel and air are mixed in the mixing space 32V to form a premixed gas. At this time, a region having a relatively high fuel concentration (a high-concentration region X) is formed to cover the inner side surface of the introduction tube 12A and the central surface S4 from the outside.The premixed gas is guided through the mixing surface S1 of the mixing chamber 32V to contract toward the inside in the radial direction of the axis O. The contracted premixed gas is guided to the outside through the nozzle 11. By igniting the premixed gas with an igniter (not shown), a premixed flame is formed extending forward from the nozzle 11. When such a phenomenon occurs simultaneously in each combustion chamber 1, the combustor assembly 100 operates a microflame combustion chamber that forms a plurality of small flames.

[0031] As described above, according to the aforementioned configuration, the air introduced into the mixing space 32V through the air introduction pipe 12 is mixed with the fuel in the mixing space 32V to form a premixed gas. By igniting the premixed gas, a flame is formed at a downstream side of the nozzle 11 of the distal end portion 31. Here, the fuel supply holes 40 are formed in each of the portions on the inside in the radial direction of the plurality of air introduction pipes 12, that is, portions close to the axis O (the inner side surface of the introduction pipe 12A). Accordingly, in the mixing space 32V, as the portion is closer to the axis O, the fuel concentration becomes higher (a high-concentration region X is formed).Furthermore, since the nozzle 11 extends around the axis O, the fuel concentration is highest in a region through which the axis O passes, in a flame region formed on the downstream side of the nozzle 11. In other words, the fuel concentration is relatively low in the inner peripheral surface of the nozzle 11, the inner surface of the mixing region 32V, and a region along the surface on an outer side in the radial direction (the outer side surface of the introduction pipe 12B) of each air introduction pipe 12. Consequently, a probability of flameback occurring along the surfaces can be reduced. Therefore, the combustor 1 and the combustor assembly 100 can be operated more stably.

[0032] Furthermore, according to the aforementioned configuration, the mixing surface S1 progressively expands toward the outside in the radial direction from the nozzle 11 to the back. In other words, the mixing surface S1 is progressively reduced in diameter toward the nozzle 11 from the outside to the inside in the radial direction. Therefore, for example, compared with a configuration in which the mixing surface S1 expands in the radial direction of the axis O, the fuel and air can be progressively contracted and directed toward the nozzle while promoting the mixing of the fuel and air. Consequently, the pressure loss in the mixing space 32V can be reduced. Therefore, the combustor 1 and the combustor assembly 100 can be operated more stably.

[0033] In addition, according to the above-mentioned configuration, by arranging a plurality of combustion chambers 1 in which the probability of flashback is reduced, a combustion chamber assembly 100 can be provided that has high output and can operate more stably. Specifically, according to the above-mentioned configuration, the plurality of combustion chambers 1 are arranged in a lattice pattern on a plane orthogonal to the axis O. Therefore, the flame distribution on the plane orthogonal to the axis O is made uniform, and a more stable flame can be obtained.

[0034] The first embodiment of the present invention has been described above. Furthermore, various changes and modifications can be made to the above embodiment without departing from the spirit of the present invention. [Second embodiment]

[0035] Next, a second embodiment of the present invention will be described with reference to Fig. 3. In addition, components similar to those of the first embodiment are designated by the same reference numerals and a repeated description is omitted. As shown in Fig. 3 shows a shape of a mixing surface S1b in a combustion chamber 1 according to the present embodiment, different from that of the first embodiment. The mixing surface S1b has a curved surface shape that is curved to be convex toward the outside in the radial direction of the axis O in a cross-sectional view including the axis O. The mixing surface S1b is smoothly connected to a cylindrical surface S2 located at the rear.

[0036] According to the above configuration, since the mixing surface S1b is curved to be convex toward the outside in the radial direction of the axis O, the fuel and air can be further progressively contracted. Therefore, a pressure loss in the mixing chamber 32V can be further reduced.

[0037] The second embodiment of the present invention has been described above. Furthermore, various changes and modifications can be made to the above embodiment without departing from the spirit of the present invention. [Third Embodiment]

[0038] Hereinafter, a third embodiment of the present invention will be described with reference to Fig. 4. In addition, configurations similar to those of each of the aforementioned embodiments are denoted by the same reference numerals, and a repeated description is omitted. As shown in Fig. 4, in a combustion chamber 1 according to the present embodiment, shapes of a nozzle 11b and an air introduction pipe 12b are shown different from each of the aforementioned embodiments. The nozzle 11b extends from the distal end 11T to the rear end 11R while being eccentric in the radial direction with respect to the axis O. Specifically, the nozzle 11b is formed by alternately connecting a portion eccentric with respect to the axis O (an eccentric portion E1) and a portion centered on the axis O (a centered portion C1). Further, the eccentric portion E1 and the centered portion C1 are connected in a smoothly curved surface shape.

[0039] Furthermore, the air introduction pipe 12b extends from the intermediate portion 32 side to the rear side while being eccentric in the radial direction with respect to the auxiliary axis O2. Specifically, the air introduction pipe 12b is formed by alternately connecting a portion eccentric with respect to the auxiliary axis O2 (an eccentric portion E2) and a portion centered on the auxiliary axis O2 (a centered portion C2). Furthermore, the eccentric portion E2 and the centered portion C2 are connected in a smooth curved surface shape.

[0040] According to the above-mentioned configuration, the nozzle 11b extends from the distal end 11T side to the rear side while being eccentric in the radial direction with respect to the axis O. Therefore, for example, compared with a case where the nozzle 11b extends linearly along the axis O, more turbulent flow components can be transmitted to the flow of fuel and air in the nozzle 11b. Consequently, the mixing of fuel and air in the nozzle 11b can be further promoted.

[0041] Furthermore, according to the aforementioned configuration, the air introduction pipe 12b extends from the intermediate portion 32 side to the rear side while being eccentric in the radial direction with respect to the auxiliary axis O2, which is the central axis of the air introduction pipe 12b. Therefore, compared with a case where the air introduction pipe 12b extends linearly along the auxiliary axis O2, more turbulent flow components can be transmitted to the air flow in the air introduction pipe 12b. Consequently, the mixing of fuel and air in the mixing space 32V can be further promoted.

[0042] The third embodiment of the present invention has been described above. Furthermore, various changes and modifications can be made to the above embodiment without departing from the spirit of the present invention. [Fourth Embodiment]

[0043] Next, a fourth embodiment of the present invention will be described with reference to the Fig. 5 and Fig. 6. In addition, configurations similar to those of each of the aforementioned embodiments will be denoted by the same reference numerals and will not be provided with a repeated description. As shown in the Fig. 5 and Fig. 6, in the present embodiment, a configuration of an air introduction pipe 12c is shown, different from those of each of the aforementioned embodiments. The air introduction pipe 12c has a flow section 12c1 extending along the aforementioned auxiliary axis O2, and a flow section 12c2 connected to a downstream side (a front side) of the flow section 12c1. As shown in Fig. As shown in Figure 6, the flow compartment 12c2 is progressively twisted from one side in the circumferential direction of the axis O to the other side, from the side of the intermediate portion 32 to the rear side. Thus, the flow compartment 12c2 is inclined with respect to the axis O in a cross-sectional view including the axis O.

[0044] According to the above-mentioned configuration, the air introduction pipe 12c is twisted to be directed from one side in the circumferential direction of the axis O to the other side from the side of the intermediate portion 32 to the rear side. Therefore, the swirl component directed from one side in the circumferential direction to the other side can be transmitted to the air flow passing through the air introduction pipe 12c. Consequently, the mixing of fuel and air in the mixing chamber 32V can be further promoted.

[0045] The fourth embodiment of the present invention has been described above. Furthermore, various changes and modifications can be made to the above embodiment without departing from the spirit of the present invention. [Fifth Embodiment]

[0046] Hereinafter, a fifth embodiment of the present invention will be described with reference to Fig. 7. In addition, configurations similar to those of each of the aforementioned embodiments will be denoted by the same reference numerals and will not be provided with a repeated description. As in Fig. As shown in Fig. 7, in the present embodiment, a relief part VL is formed as a hollow part in a portion of the distal end portion 31 on the outer peripheral side of the nozzle 11. The relief part VL has a cross-sectional shape along the outer shapes of the nozzle 11 and the mixing surface S1. The relief valley VL communicates with the outside. That is, air can circulate in the relief part VL.

[0047] According to the aforementioned configuration, the lightening part VL is formed as the hollow part in the portion closer to the outer peripheral side than the nozzle 11 at the distal end portion 31. Consequently, convection is generated in the air exposed to the high temperature of the flame in the lightening part VL. Since the uneven temperature distribution along the nozzle 11 is reduced by the convection, the flame formed by the nozzle 11 can be maintained more effectively.

[0048] The fifth embodiment of the present invention has been described above. Furthermore, various changes and modifications can be made to the above embodiment without departing from the spirit of the present invention. [Sixth Embodiment]

[0049] Next, a sixth embodiment of the present invention will be described with reference to Fig. 8. In addition, configurations similar to those of each of the aforementioned embodiments will be described by the same reference numerals and will not be provided with a repeated description. As in Fig. As shown in Fig. 8, in the present embodiment, a protrusion 33P protruding toward the mixing space 32V side along the axis O is provided on a surface facing the front side of the proximal end portion 33 (i.e., a central surface S4). The protrusion 33P has a columnar shape centered on the axis O, and a fuel supply hole 40b through which the fuel space 33V and the mixing space 32V communicate with each other is formed on the outer peripheral surface (an outer peripheral surface of a protrusion 33S). A plurality of fuel supply holes 40b are formed at intervals in the circumferential direction of the axis O. That is, the fuel guided through the fuel supply hole 40b is directly supplied (sprayed) into the mixing space 32V.

[0050] According to the above-mentioned configuration, the protrusion 33P, which protrudes into the mixing space 32V along the axis O, is provided at the front of the proximal end portion 33. Furthermore, the fuel supply hole 40b is formed on the outer peripheral surface (the outer peripheral surface of the protrusion 33S) of the protrusion 33P. Therefore, fuel can be supplied to a region in the mixing space 32V closer to the nozzle 11. Consequently, the mixing of fuel and air in the mixing space 32V can be further promoted.

[0051] The sixth embodiment of the present invention has been described above. Furthermore, various changes and modifications can be made to the above embodiment without departing from the spirit of the present invention. [Seventh Embodiment]

[0052] Hereinafter, a seventh embodiment of the present invention will be described with reference to Fig. 9. In addition, configurations similar to those of each of the aforementioned embodiments will be denoted by the same reference numerals and will not be provided with a repeated description. As in Fig. As shown in Fig. 9, in the present embodiment, a cylindrical extension cylinder part 33T centered on the axis O is provided on a central surface S4 of the proximal end portion 33. Furthermore, a cylindrical outer extension cylinder part 33U centered on the axis O is provided on an annular surface S3c of the proximal end portion 33. The fuel supply hole 40c is formed on the central surface S4. A fuel supply hole 40c is formed on the axis O. A plurality of air holes 50 penetrating the extension cylinder part 33T in the radial direction are formed in the extension cylinder part 33D. The mixing space 32V and the space on the inner peripheral side of the extension cylinder part 33T communicate with each other through the air hole 50.

[0053] According to the above-mentioned configuration, the air introduced into the mixing space 32V through the air introduction pipe 12 is mixed with fuel in the mixing space 32V to form a premixed gas. By igniting the premixed gas, a flame is formed on a downstream side of the nozzle 11 of the distal end portion 31. Here, the fuel supply hole 40c is formed in a surface located on the distal end 11T side of the portion surrounded by the plurality of air introduction pipes 12 in the proximal end portion 33 (a central surface S4). Thus, the fuel is injected from the fuel supply hole 40c in the direction of the axis O. Further, the fuel supply hole 40c is covered with the extension cylinder part 33T from the outer peripheral side.Additionally, the extension cylinder part 33T is formed with an air hole 50 through which the mixing chamber 32V communicates with the space on the inner peripheral side of the extension cylinder part. Therefore, after the fuel and air are mixed to a certain extent in the space on the inner peripheral side of the extension cylinder part 33T, the air-fuel mixture can be supplied to the mixing chamber 32V. Thus, the mixing of fuel and air in the mixing chamber 32V can be further promoted.

[0054] In addition, since the fuel supply hole 40c is provided on the axis O, the fuel concentration in the mixing space 32V will increase as the portion is closer to the axis O. Therefore, in the flame region formed on the downstream side of the nozzle 11, a fuel concentration becomes highest in the region through which the axis O passes. In other words, the fuel concentration in the inner peripheral surface of the nozzle 11, the inner peripheral surface of the mixing space 32V, and a region along the surface on an outer side in the radial direction of each air introduction pipe 12 (an outer side surface of an introduction pipe 12B) is relatively low. Consequently, the possibility of flameback occurring along these surfaces can be reduced. Therefore, the combustor 1 and the combustor assembly 100 can be operated more stably.

[0055] The seventh embodiment of the present invention has been described above. Furthermore, various changes and modifications can be made to the aforementioned embodiments without departing from the gist of the present invention. In a modified example common to the above embodiments, the number of combustion chambers 1 included in the combustor assembly 100 is not limited to nine, and may be eight or fewer, or ten or more. Furthermore, the number of air introduction pipes 12 in the combustion chamber 1 is not limited to four, and may be three or fewer, or five or more.

[0056] In addition, the combustion chambers 1 in the combustion chamber arrangement 100 described above can also be arranged in a stepped manner as in Fig. 10 (a first modified example). In particular, a plurality of combustion chambers 1 are arranged in a plane orthogonal to the axis O in a stepped manner so that the positions of the axis O are different from each other. In addition, as shown in Fig. 11, each combustion chamber 1 may be formed in a hexagonal shape when viewed from the direction of the axis O, and the combustion chambers may be arranged in a honeycomb shape whose end surfaces communicate with each other (a second modified example). In addition, as shown in Fig. 12, an annular combustor assembly 100 can be configured by forming an outer diameter of each of the combustion chambers 1 in an annular arc shape and connecting the combustion chambers 1 in the circumferential direction (a third modified example).

[0057] Furthermore, in each of the above-described embodiments and modified examples, examples have been described in which the combustion chamber 1 is arranged on a plane. However, as in Fig. 13, a configuration in which the combustion chamber 1 is arranged along a curved surface may be adapted (a fourth modified example). Specifically, these combustion chambers 1 are arranged along a curved concave surface that is convex from one side to the other. Note that such a curved surface may also be a continuous surface. It may be a polyhedron formed by a plurality of planes connected to one another.

[0058] While preferred embodiments of the invention have been described and illustrated above, it should be understood that these are exemplary of the invention and are not to be considered limiting. Additions, omissions, substitutions, and other modifications may be made without departing from the spirit or scope of the present invention. Accordingly, the invention is not to be considered limited by the foregoing description and is limited only by the scope of the appended claims. Explanation of reference symbols 100 Combustion chamber arrangement 1 combustion chamber 11,11b nozzle 11R rear end 11T distal end 12,12b,12c Air inlet pipe 12c1 power distribution 12c2 power compartment 12A Inner surface of the insertion tube 12B Outside surface of the insertion tube 31 distal end section 32 Intermediate section 32V mixing chamber 33 proximal end section 33P protrusion 33S Outer peripheral surface of the protrusion 33T extension cylinder part 33U outer extension cylinder part 33V fuel chamber 40,40b,40c fuel feed hole 50 air hole C1,C2 centered part E1,E2 eccentric part O axis O2 auxiliary axle S1,S1b mixed surface S2 cylindrical surface S3 annular surface S4 centered plane VL relief part X highly concentrated area

Claims

[1] A combustion chamber (1) with: a distal end portion (31) forming a nozzle (11, 11b) extending along an axis (O) and opening at a distal end (11T), an intermediate section (32) forming a mixing space (32V) behind the distal end section (31) which widens from the nozzle (11, 11b) in a direction intersecting the axis (O), a proximal end portion (33) forming a fuel chamber (33V) behind the intermediate portion (32) to which fuel is supplied from the outside, and a plurality of air introduction tubes (12, 12b, 12c) penetrating the proximal end portion (33) in a direction of the axis (O), having a distal end (11T) communicating with the mixing space (32V), and arranged in a circumferential direction of the axis (O) to surround the axis (O), wherein a fuel supply hole (40, 40b, 40c) through which the fuel chamber (33V) and the mixing chamber (32V) communicate with each other is formed on a surface facing the distal end side of a portion surrounded by the plurality of air introduction pipes (12, 12b, 12c) in the proximal end portion (33), and an extension cylinder part (33T) extending in the direction of the axis (O) to cover the fuel supply hole (40, 40b, 40c) from an outer peripheral side and having an air hole (50) formed to communicate with the mixing space (32V) provided on the surface facing the distal end side. [2] A combustion chamber arrangement (100) comprising: a plurality of combustion chambers (1) according to claim 1, wherein the plurality of combustion chambers (1) are arranged in a plane orthogonal to the axis (O). [3] The combustor assembly (100) according to claim 2, wherein the plurality of combustors (1) are arranged in a lattice shape at equal intervals in the plane orthogonal to the axis (O). [4] The combustor assembly (100) according to claim 2, wherein each of the plurality of combustors (1) has a hexagonal shape when viewed from the direction of the axis (O) and is arranged in a honeycomb shape by contacting the end surfaces thereof. [5] The combustion chamber assembly (100) according to claim 2, wherein the plurality of combustion chambers (1) are arranged in a ring shape. [6] The combustor assembly (100) according to claim 2, wherein the plurality of combustion chambers (1) are arranged in a staggered manner such that positions of the axis (O) differ from each other in the plane orthogonal to the axis (O). [7] A combustion chamber arrangement (100) comprising: a plurality of combustion chambers (1) according to claim 1, wherein the plurality of combustion chambers (1) are arranged along a curved concave surface which is convex from one to the other.

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