JP2007147125A - Gas turbine combustor - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To suppress generation of flashbacks by increasing a combustor wall surface vicinity flow velocity of premixed gas flowing from a combustor inner tube to a combustor tail pipe in a gas turbine combustor. <P>SOLUTION: The gas turbine combustor is composed by connecting the combustor tail pipe 33 to a tip of the combustor inner tube 32, arranging a pilot nozzle 34 in a center part of the combustor inner tube 32, and arranging a plurality of premix nozzles 35 so as to surround the pilot nozzle 34 along a circumferential direction in an inner circumference face. A restriction part 43 comprising a curved shape reducing a gas passage cross-sectional area is provided on the tip of the combustor inner tube 32. <P>COPYRIGHT: (C)2007,JPO&INPIT

Description

  The present invention provides a pilot diffusion flame for stable combustion of a lean premixed fuel in a gas turbine which supplies fuel to compressed compressed air and burns it, and supplies the generated combustion gas to the turbine to obtain rotational power. The present invention relates to a gas turbine combustor that performs flame holding.

  For example, a gas turbine is composed of a compressor, a combustor, and a turbine. The air taken in from the air intake port is compressed by the compressor to become high-temperature / high-pressure compressed air. Fuel is supplied to the compressed air and burned, and high-temperature and high-pressure combustion gas drives a turbine and a generator connected to the turbine. In this case, the turbine is configured by alternately arranging a plurality of stationary blades and moving blades in the vehicle interior, and rotationally drives an output shaft connected to the generator by driving the moving blades with combustion gas. ing. The combustion gas that has driven the turbine is converted to static pressure by the diffuser in the exhaust casing and then released to the atmosphere.

  FIG. 10 is a main part schematic diagram showing a conventional gas turbine combustor. In the conventional gas turbine combustor, as shown in FIG. 10, a combustor inner cylinder 001 is supported by a combustor outer cylinder (not shown), and a combustor tail cylinder 002 is connected to a tip portion of the combustor inner cylinder 001. A casing is constructed. In this combustor inner cylinder 001, a pilot nozzle 003 is disposed at the center thereof, and a plurality of premixes are provided on the inner peripheral surface of the combustor inner cylinder 001 so as to surround the pilot nozzle 003 along the circumferential direction. A nozzle 004 is provided. A pilot fuel rod 005 is disposed in the pilot nozzle 003, a main fuel rod 006 is disposed in each premixing nozzle 004, and the pilot fuel rod 005 and the main fuel rod 006 are not shown at the base end. Fuel is supplied from the supply device, and fuel can be injected from the tip. A pilot swirl vane 007 is disposed in the pilot nozzle 003 and a premixing swirl vane 008 is disposed in each premixing nozzle 004.

  Accordingly, when an air flow of high-temperature and high-pressure compressed air compressed by the compressor flows into the gas turbine combustor, this air flow is mixed with the fuel injected from the main fuel rod 006 in each premixing nozzle 004. The swirl flow of the premixed gas flows into the tail cylinder 002. On the other hand, in the pilot nozzle 003, the air flow of the compressed air is mixed with the fuel injected from the pilot fuel rod 005, and this air-fuel mixture is ignited and burned by a seed fire (not shown) to become a combustion gas and the tail cylinder 002. Erupts inside. At this time, a part of the combustion gas is injected into the tail cylinder 002 so as to diffuse to the surroundings with a flame, so that the premixed gas flowing into the tail cylinder 002 from each premix nozzle 004 is ignited and burned. To do. That is, flame holding for stable combustion of the lean premixed fuel from the premixing nozzle 004 can be performed by the diffusion flame by the pilot fuel injected from the pilot fuel rod 005.

  As such a gas turbine, there are those described in Patent Documents 1 and 2 below.

JP 2002-372238 A Japanese Patent Application Laid-Open No. 06-347040

  In the conventional gas turbine described above, the air flow of the high-temperature and high-pressure compressed air is mixed with the fuel injected from the main fuel rod 006 in each premixing nozzle 004, and becomes a swirling flow of the premixed air and the tail cylinder 002. Then, it is ignited by a part of the combustion gas from the pilot nozzle 003 and burned. At this time, the premixed gas ejected from each premixing nozzle 004 flows into the combustor tail cylinder 002 along the inner wall surface of the combustor inner cylinder 001, but its inner diameter extends from the combustor inner cylinder 001 to the combustor tail cylinder 002. And a low flow rate region or a separation region of the premixed gas is generated here. That is, the inner diameter is widened so that the premixed gas smoothly flows from the combustor inner cylinder 001 to the combustor tail cylinder 002, but is formed between the combustor inner cylinder 001 and the combustor tail cylinder 002. Due to the level difference, a part of the premixed gas flowing along the wall surface of the combustor inner cylinder 001 does not flow smoothly to the combustor tail cylinder 002, and a vortex is formed here to generate a low flow velocity region or a separation region. End up. Then, here, the flow rate of the premixed gas becomes slower than the predetermined combustion speed, so-called flashback occurs in which the flame after ignition returns, so that the combustion becomes unstable and the combustion efficiency is lowered.

  In the gas turbine disclosed in Patent Document 2, a container 15 is connected to the tip of the casing, and three concentric annular passages formed in the casing are curved toward the center to form a step between the container and the container. Here, a vortex of the recirculation flow is formed to prevent the flame from being blown out, but flashback occurs due to the vortex of the recirculation flow.

  The present invention solves the above-described problems, and is a gas turbine combustion capable of suppressing the occurrence of flashback by increasing the velocity near the combustor wall surface of the premixed gas flowing from the combustor inner cylinder to the combustor tail cylinder. The purpose is to provide a vessel.

  In order to achieve the above object, a gas turbine combustor according to a first aspect of the present invention includes a combustor inner cylinder, a combustor tail cylinder connected to a tip portion of the combustor inner cylinder, and the combustor inner cylinder. A gas turbine combustor comprising a pilot nozzle disposed in the center and a plurality of premixing nozzles disposed on the inner circumferential surface of the combustor inner cylinder so as to surround the pilot nozzle along the circumferential direction In the above, a throttle portion having a curved surface shape in which a gas passage cross-sectional area is reduced is provided at a tip portion of the inner cylinder of the combustor.

  In the gas turbine combustor according to a second aspect of the present invention, the throttle portion is provided on the downstream side in the gas flow direction with respect to the tip portion of the premixing nozzle.

  In the gas turbine combustor according to a third aspect of the present invention, a bent portion along the throttle portion provided in the inner cylinder of the combustor is provided at a tip portion of the premixing nozzle.

  In a gas turbine combustor according to a fourth aspect of the present invention, the throttle portion is formed in a shape along a trajectory of a swirling flow of the gas flowing in the inner cylinder of the combustor.

  In the gas turbine combustor according to the fifth aspect of the present invention, a flat surface portion that has a gas passage cross-sectional area enlarged from the throttle portion and smoothly continues to the combustor tail tube is provided at the tip of the combustor inner tube. It is characterized by that.

  In the gas turbine combustor according to the invention of claim 6, the ratio of the inner diameter of the throttle portion to the inner diameter of the inner cylinder of the combustor is set to 0.8 or more and less than 1.0, and from the tip of the premixing nozzle. The ratio of the length from the tip of the premixing nozzle to the minimum inner diameter position of the throttle portion relative to the length to the tip of the combustor inner cylinder is set to 0.05 or more and 0.3 or less. Yes.

  In the gas turbine combustor according to the seventh aspect of the present invention, a guide is formed on the inner peripheral surface of the inner cylinder of the combustor that has a substantially uniform width along the circumferential direction with the outer peripheral surfaces of the plurality of premixing nozzles. It is characterized by the provision of a section.

  The gas turbine combustor according to claim 8 is characterized in that an air inflow hole through which air flows from the outside to the inner peripheral surface of the combustor tail cylinder is provided at the tip of the combustor inner cylinder. .

  According to a ninth aspect of the present invention, there is provided a gas turbine combustor including a combustor inner cylinder, a combustor tail cylinder connected to a tip portion of the combustor inner cylinder, and an inner circumferential surface of the combustor inner cylinder in a circumferential direction. A gas turbine combustor comprising: a plurality of premixing nozzles disposed along a plurality of premixing nozzles; and a pilot nozzle disposed in a central portion of the combustor inner cylinder so as to be surrounded by the plurality of premixing nozzles In addition, the tip of the combustor inner cylinder is provided with a curved portion whose gas passage cross-sectional area expands along the trajectory of the swirling flow of the gas flowing in the combustor inner cylinder.

  The gas turbine combustor according to the invention of claim 10 is characterized in that a flat portion smoothly extending from the curved portion to the combustor tail tube is provided at a tip portion of the combustor inner tube.

  According to the gas turbine combustor of the first aspect of the present invention, the combustor tail cylinder is connected to the tip of the combustor inner cylinder, the pilot nozzle is disposed at the center of the combustor inner cylinder, and the inner peripheral surface. A plurality of premixing nozzles are arranged so as to surround the pilot nozzle along the circumferential direction, and a throttle part having a curved surface shape in which the gas passage cross-sectional area is reduced is provided at the tip of the combustor inner cylinder. The premixed gas jetted from the premixing nozzle to the combustor inner cylinder increases its flow velocity due to the constricted portion having a curved surface, and therefore flows smoothly from the combustor inner cylinder to the combustor tail cylinder. Suppresses the occurrence of flashback by suppressing the occurrence of a low velocity region or separation region of the air-fuel mixture and increasing the flow velocity in the vicinity of the combustor wall surface of the premixed gas flowing from the so-called combustor inner cylinder to the combustor tail cylinder. Can do.

  According to the gas turbine combustor of the second aspect of the present invention, since the throttle portion is provided on the downstream side in the gas flow direction from the tip portion of the premixing nozzle, the premixing jetted from the premixing nozzle to the combustor inner cylinder The flow velocity of the gas can be reliably increased by the throttle portion, and the increased premixed gas can be smoothly poured into the combustor tail cylinder.

  According to the gas turbine combustor of the invention of claim 3, since the bent portion along the throttle portion provided in the combustor inner cylinder is provided at the tip of the premix nozzle, the combustor inner cylinder and the premix nozzle The air flowing between the premixed gas and the premixed gas jetted from the premixing nozzle smoothly joins and is accelerated at the throttle, and the premixed gas at the connection between the combustor inner cylinder and the combustor tail cylinder is increased. Generation of a low flow rate region or a separation region can be reliably suppressed.

  In the gas turbine combustor according to the fourth aspect of the present invention, since the throttle portion is formed in a shape along the swirl flow trajectory of the gas flowing in the combustor inner cylinder, the pre-jet ejected from the premixing nozzle to the combustor inner cylinder is formed. Since the air-fuel mixture is a swirling flow, it can be smoothly increased by the throttle, and it is ensured that a low flow velocity region or a separation region of the pre-mixed gas is generated at the connection between the combustor inner cylinder and the combustor tail cylinder. Can be suppressed.

  According to the gas turbine combustor of the invention of claim 5, since the gas passage cross-sectional area is enlarged from the constricted portion and the flat portion that is smoothly continuous to the combustor tail tube is provided at the tip of the combustor inner tube. The premixed gas increased in speed at the throttle portion flows smoothly into the combustor tail cylinder by the flat portion, and the generation of a low flow velocity region or a separation region can be reliably suppressed.

  According to the gas turbine combustor of the sixth aspect of the invention, the ratio of the inner diameter of the throttle portion to the inner diameter of the inner cylinder of the combustor is set to 0.8 or more and less than 1.0, and from the tip of the premixing nozzle to the inside of the combustor. Since the ratio of the length from the tip of the premixing nozzle to the minimum inner diameter position in the throttle portion to the length to the tip of the cylinder is set to 0.05 or more and 0.3 or less, the size and position of the throttle portion are set to appropriate values. By setting, generation | occurrence | production of the low flow velocity area or peeling area | region of a premixed gas can be suppressed, and generation | occurrence | production of flashback can be suppressed reliably.

  According to the gas turbine combustor of the seventh aspect of the present invention, the guide portion that forms the flow path having a substantially uniform width along the outer peripheral surface of the plurality of premix nozzles and the circumferential direction on the inner peripheral surface of the combustor inner cylinder. Therefore, the air flowing between the combustor inner cylinder and the premixing nozzle is accelerated by the guide part, and the premixed gas ejected from the premixing nozzle and smoothly join, and the combustor inner cylinder and the combustion are combusted. Generation | occurrence | production of the low-flow-rate area | region or peeling area | region of the premixed gas in a connection part with a breech cylinder can be suppressed reliably.

  According to the gas turbine combustor of the eighth aspect of the present invention, since the air inlet hole through which air flows from the outside to the inner peripheral surface of the combustor tail cylinder is provided at the tip of the combustor inner cylinder, the combustion from the air inlet hole The premixed gas at the connecting portion between the combustor inner cylinder and the combustor tail cylinder is accelerated by increasing the premixed gas flowing from the combustor inner cylinder into the combustor tail cylinder by the air flowing into the inner peripheral surface of the combustor tail cylinder. The generation of a low flow velocity region or a separation region can be reliably suppressed.

  According to the gas turbine combustor of the ninth aspect of the invention, the combustor tail cylinder is connected to the tip of the combustor inner cylinder, the pilot nozzle is disposed at the center of the combustor inner cylinder, A plurality of premixing nozzles are arranged on the peripheral surface so as to surround the pilot nozzle along the circumferential direction, and along the swirl flow trajectory of the gas flowing in the combustor inner cylinder at the tip of the combustor inner cylinder. Since the gas passage cross-sectional area is enlarged, the premixed gas ejected from the premixing nozzle to the combustor inner cylinder is separated from the combustor inner cylinder by the curved section along the gas swirl flow trajectory. Slowly flows into the cylinder, suppresses the generation of a low flow velocity region or separation region of the premixed gas, and increases the flow velocity near the combustor wall surface of the premixed gas flowing from the combustor inner cylinder to the combustor tail cylinder. Thus, the occurrence of flashback can be suppressed.

  According to the gas turbine combustor of the tenth aspect of the present invention, since the flat portion that smoothly continues from the curved portion to the combustor tail tube is provided at the tip portion of the combustor inner cylinder, the premixed gas stabilized by the curved portion is provided. Smoothly flows into the combustor tail cylinder by the flat portion, and the generation of a low flow velocity region or a separation region can be reliably suppressed.

  Exemplary embodiments of a gas turbine combustor according to the present invention will be described below in detail with reference to the accompanying drawings. Note that the present invention is not limited to the embodiments.

  FIG. 1 is a schematic diagram illustrating a main part of a gas turbine combustor according to a first embodiment of the present invention. FIG. 2-1 is an explanatory diagram of a swirl flow locus shape of a throttle portion in the gas turbine combustor according to the first embodiment. 2-2 is an explanatory diagram of a premixed swirl vane in the gas turbine combustor of the first embodiment, FIG. 3 is a schematic configuration diagram of the gas turbine of the first embodiment, and FIG. 4 is a diagram of the gas turbine combustor of the first embodiment. It is a schematic block diagram.

  As shown in FIG. 3, the gas turbine according to the first embodiment includes a compressor 11, a combustor (gas turbine combustor) 12, a turbine 13, and an exhaust chamber 14, and a generator (not shown) is connected to the turbine 13. ing. The compressor 11 has an air intake port 15 for taking in air, a plurality of stationary blades 17 and moving blades 18 are alternately arranged in a compressor casing 16, and a bleed manifold 19 is provided on the outside thereof. ing. The combustor 12 is combustible by supplying fuel to the compressed air compressed by the compressor 11 and igniting it with a burner. In the turbine 13, a plurality of stationary blades 21 and moving blades 22 are alternately arranged in a turbine casing 20. The exhaust chamber 14 has an exhaust diffuser 23 that is continuous with the turbine 13. A rotor (turbine shaft) 24 is positioned so as to pass through the center of the compressor 11, the combustor 12, the turbine 13, and the exhaust chamber 14, and an end portion on the compressor 11 side is freely rotatable by a bearing portion 25. On the other hand, the end portion on the exhaust chamber 14 side is rotatably supported by the bearing portion 26. A plurality of disk plates are fixed to the rotor 24, the rotor blades 18 and 22 are connected, and a drive shaft of a generator (not shown) is connected to the end on the exhaust chamber 14 side.

  Therefore, the air taken in from the air intake port 15 of the compressor 11 passes through the plurality of stationary blades 21 and the moving blades 22 and is compressed to become high-temperature and high-pressure compressed air. Combustion occurs when a predetermined fuel is supplied to the compressed air. The high-temperature and high-pressure combustion gas that is the working fluid generated in the combustor 12 passes through the plurality of stationary blades 21 and the moving blades 22 constituting the turbine 13 to drive and rotate the rotor 24. While the generator connected to 24 is driven, the exhaust gas is converted into static pressure by the exhaust diffuser 23 in the exhaust chamber 14 and then released to the atmosphere.

  In the above-described combustor 12, as shown in FIG. 4, the combustor inner cylinder 32 is supported by the combustor outer cylinder 31, and the combustor tail cylinder 33 is connected to the tip of the combustor inner cylinder 32 to combust the combustor. A casing is constructed. In the combustor inner cylinder 32, a pilot nozzle 34 is disposed at the center thereof, and a plurality of premixing nozzles are disposed on the inner peripheral surface of the combustor inner cylinder 32 so as to surround the pilot nozzle 34 along the circumferential direction. 35 is disposed, and a pilot cone 36 is attached to the tip of the pilot nozzle 34.

  More specifically, as shown in FIG. 1, the combustor inner cylinder 32 has a distal end portion, that is, a base end portion of the combustor tail cylinder 33, that is, a mixing portion on the outer peripheral surface of the downstream end portion in the flow direction of the mixture. The inner peripheral surface of the upstream end in the gas flow direction is connected via a connecting member 37. A plurality of premixing nozzles 35 are disposed on the inner peripheral side of the combustor inner cylinder 32 via a predetermined air flow path 38, and a pilot nozzle 34 is disposed at the center thereof. Pilot fuel rods 39 are disposed in the pilot nozzles 34, main fuel rods 40 are disposed in the respective premixing nozzles 35, and the pilot fuel rods 39 and the main fuel rods 40 are not shown at the base end. The fuel from the supply device is supplied, and the fuel can be injected from the tip portion. A pilot swirl vane 41 is disposed in the pilot nozzle 34, and a premixing swirl vane 42 is disposed in each premixing nozzle 35.

  In the present embodiment, a throttle portion 43 having a curved shape whose gas passage cross-sectional area is reduced is provided at the tip of the combustor inner cylinder 32. The throttle portion 43 is provided on the downstream side in the gas flow direction with respect to the tip portion of the premixing nozzle 35, and is formed in a shape along the swirl flow locus of the gas flowing in the combustor inner cylinder 32. Further, a bent portion 44 that is substantially parallel to the leading end portion of the premixing nozzle 35 is provided along the throttle portion 43.

従って、下記数式（４）（５）（６）を満たす旋回流軌跡形状を得ることができる。

A swirl flow locus shape in the throttle portion 43 will be described. As shown in FIGS. 2A and 2B, the diameter from the center of the combustor inner cylinder 32 to the minimum inner diameter position of the throttle portion 43 is R1, and from the tip of the premixing nozzle 35 to the tip of the combustor inner cylinder 32. Is the distance L1, the tip angle of the bent portion 44 of the mixing nozzle 35 is θ, and the swirler angle of the premixed swirl vane 42 is α, the following equations (1), (2), and (3) hold.

Therefore, a swirl flow locus shape satisfying the following mathematical formulas (4), (5), and (6) can be obtained.

  That is, in the premixing nozzle 35, a swirling flow of air is generated by the premixing swirl vane 42, and fuel is injected from the main fuel rod 40 into the swirling flow of air to be mixed and burned as a premixed gas. It flows into the inner cylinder 32. At this time, the flow rate of the premixed gas along the inner wall surface of the combustor inner cylinder 32 is reduced by making the shape of the throttle portion 43 into a swirl flow locus shape in which the swirling flow of the premixed gas naturally spreads outward. It can be made to flow smoothly to the combustor tail cylinder 33 without being peeled off or peeling off.

  Therefore, as shown in FIG. 1, when an air flow of high-temperature and high-pressure compressed air flows into the combustor 12, this air flow is mixed with the fuel injected from the main fuel rod 40 in each premixing nozzle 35. The swirl flow of the premixed gas flows into the combustor inner cylinder 32. At this time, since the flow velocity of the premixed gas flowing from the premixing nozzle 35 into the combustor inner cylinder 32 is increased by the curved throttle portion 43, the combustor inner cylinder 32 smoothly moves to the combustor tail cylinder 33. It will flow in, and generation | occurrence | production of the low flow-rate area | region or peeling area | region of a premixed gas can be suppressed.

  On the other hand, in the pilot nozzle 34, the air flow of compressed air is mixed with the fuel injected from the pilot fuel rod 39, and this air-fuel mixture is ignited and burned by a seed flame (not shown) to become combustion gas and become a combustion gas. It ejects into the cylinder 32. Then, a part of the combustion gas is injected into the combustor inner cylinder 32 so as to diffuse to the surroundings with a flame, so that it flows from each premix nozzle 35 into the combustor inner cylinder 32 and the combustor tail cylinder 33. It is ignited by the premixed gas and burns.

  As described above, in the gas turbine combustor according to the first embodiment, the combustor tail cylinder 33 is connected to the tip of the combustor inner cylinder 32, and the pilot nozzle 34 is disposed at the center of the combustor inner cylinder 32. In addition, a plurality of premix nozzles 35 are disposed on the inner peripheral surface so as to surround the pilot nozzle 34 along the circumferential direction, and a curved surface whose gas passage cross-sectional area is reduced at the tip of the combustor inner cylinder 32. An aperture 43 having a shape is provided.

  Accordingly, the flow rate of the premixed gas jetted from the premixing nozzle 35 to the combustor inner cylinder 32 is increased by the throttle portion 43 having a curved surface shape, so that the smoothness from the combustor inner cylinder 32 to the combustor tail cylinder 33 is smooth. The flow velocity of the premixed gas flowing from the combustor inner cylinder 32 to the combustor tail cylinder 33 is increased, and the flow velocity in the vicinity of the combustor wall surface is increased. The occurrence of flashback can be suppressed.

  Further, in the gas turbine combustor according to the first embodiment, the throttle portion 43 is provided on the downstream side in the gas flow direction with respect to the tip portion of the premixing nozzle 35, and is ejected from the premixing nozzle 35 to the combustor inner cylinder 32. The flow rate of the premixed gas can be reliably increased by the throttle portion 43, and the increased premixed gas can be smoothly poured into the combustor tail cylinder 32. A bent portion 44 is provided at the tip of the premixing nozzle 35 along the throttle portion 43, so that air flowing through the air flow path 38 between the combustor inner cylinder 32 and the premixing nozzle 35 flows from the premixing nozzle 35. The spouted premixed gas is smoothly merged and accelerated by the throttle 43, and the premixed gas low flow velocity region or separation region at the connecting portion between the combustor inner cylinder 32 and the combustor tail cylinder 33 is obtained. Can be reliably suppressed.

  Furthermore, in the gas turbine combustor of the first embodiment, the throttle portion 43 is formed in a shape along the trajectory of the swirling flow of the gas flowing in the combustor inner cylinder 32. Accordingly, a swirling flow of air is generated by the premixing swirl vane 42 in the premixing nozzle 35, fuel is injected from the main fuel rod 40 and mixed with the swirling flow of air, and the combustor is used as a premixed gas. The premixed gas along the inner wall surface of the combustor inner tube 32 is formed by making the shape of the throttle portion 43 into a swirl flow locus shape in which the swirl flow of the premixed gas naturally spreads outward when flowing into the inner tube 32. It is possible to smoothly flow through the combustor tail cylinder 33 without lowering the flow rate of the gas and without peeling.

  FIG. 5 is a main part schematic diagram showing a gas turbine combustor according to a second embodiment of the present invention. In addition, the same code | symbol is attached | subjected to the member which has the same function as what was demonstrated in the Example mentioned above, and the overlapping description is abbreviate | omitted.

  In the gas turbine combustor according to the second embodiment, as shown in FIG. 5, a combustor tail cylinder 33 is connected to the tip of the combustor inner cylinder 32, and a pilot nozzle 34 is provided at the center of the combustor inner cylinder 32. A plurality of premixing nozzles 35 are disposed on the inner peripheral surface of the combustor inner cylinder 32 so as to surround the pilot nozzle 34 along the circumferential direction. An air flow path 38 is provided between the mixing nozzles 35. A pilot fuel rod 39 is disposed in the pilot nozzle 34, a main fuel rod 40 is disposed in each premix nozzle 35, and a pilot swirl vane 41 is disposed in the pilot nozzle 34. A premixed swirl vane 42 is disposed therein.

  In the present embodiment, a constriction portion 43 having a swirl flow locus shape in which the gas passage cross-sectional area is reduced is provided at the tip of the combustor inner cylinder 32, and the gas passage cross-sectional area is enlarged from the constriction portion 43. A flat portion 45 that is smoothly continuous is provided on the inner wall surface of the combustor tail cylinder 33. Further, a bent portion 44 that is substantially parallel to the leading end portion of the premixing nozzle 35 is provided along the throttle portion 43.

  In the shape of the throttle portion 43 and the flat portion 45, the ratio of the inner diameter d of the throttle portion 43 to the inner diameter D of the combustor inner cylinder 32 is 0.8 or more and less than 1.0, that is, 0.8 ≦ d / D <. It is desirable to set 1.0, and it is optimal to set 0.8 ≦ d / D <0.9. Further, the ratio of the length x from the front end of the premixing nozzle 35 to the minimum inner diameter position of the throttle portion 43 with respect to the length X from the front end of the premixing nozzle 35 to the front end of the combustor inner cylinder 32 is 0.05 or more and 0.00. It is desirable to set 3 or less, that is, 0.05 ≦ x / X ≦ 0.3, and it is optimal to set x / X = 0.2.

  Accordingly, when an air flow of high-temperature and high-pressure compressed air flows into the combustor 12, this air flow is mixed with the fuel injected from the main fuel rod 40 in each premixing nozzle 35, and the swirling of the premixed air is performed. As a flow, it flows into the combustor inner cylinder 32. At this time, the premixed gas flowing from the premixing nozzle 35 into the combustor inner cylinder 32 is smoothly diffused by the flat surface portion 45 after the flow velocity is increased by the throttle portion 43 having a curved surface shape. 32 flows smoothly into the combustor tail cylinder 33, and generation of a low flow velocity region or a separation region of the premixed gas can be suppressed.

  On the other hand, in the pilot nozzle 34, the air flow of compressed air is mixed with the fuel injected from the pilot fuel rod 39, and this air-fuel mixture is ignited and burned by a seed flame (not shown) to become combustion gas and become a combustion gas. It ejects into the cylinder 32. Then, a part of the combustion gas is injected into the combustor inner cylinder 32 so as to diffuse to the surroundings with a flame, so that it flows from each premix nozzle 35 into the combustor inner cylinder 32 and the combustor tail cylinder 33. It is ignited by the premixed gas and burns.

  As described above, in the gas turbine combustor according to the second embodiment, the combustor tail cylinder 33 is connected to the tip of the combustor inner cylinder 32, and the pilot nozzle 34 is disposed at the center of the combustor inner cylinder 32. In addition, a plurality of premix nozzles 35 are disposed on the inner peripheral surface so as to surround the pilot nozzle 34 along the circumferential direction, and a curved surface whose gas passage cross-sectional area is reduced at the tip of the combustor inner cylinder 32. A throttle portion 43 having a shape is provided, and a plane portion 45 having a gas passage cross-sectional area extending from the throttle portion 43 and smoothly continuing to the inner wall surface of the combustor tail cylinder 33 is provided.

  Accordingly, the premixed gas jetted from the premixing nozzle 35 to the combustor inner cylinder 32 has its flow velocity increased by the throttle portion 43 having a curved surface shape and flows along the flat portion 45. The smooth flow from the inner cylinder 32 to the combustor tail cylinder 33 suppresses the generation of a low flow velocity region or a separation region of the premixed gas, and combustion of the premixed gas flowing from the combustor inner cylinder 32 to the combustor tail cylinder 33 occurs. By increasing the near-surface flow velocity, so-called flashback can be suppressed.

  In the gas turbine combustor according to the second embodiment, the ratio of the inner diameter d of the throttle portion 43 to the inner diameter D of the combustor inner cylinder 32 is 0.8 or more and 1.0 in the shape of the throttle portion 43 and the flat portion 45. And the ratio of the length x from the front end of the premixing nozzle 35 to the minimum inner diameter position of the throttle portion 43 with respect to the length X from the front end of the premixing nozzle 35 to the front end of the combustor inner cylinder 32 is set to 0. 0. It is set to 05 or more and 0.3 or less. Therefore, by setting the size and position of the throttle portion 43 to appropriate values, it is possible to suppress the occurrence of a low flow velocity region or a separation region of the premixed gas and reliably suppress the occurrence of flashback.

  In the first and second embodiments described above, the throttle 43 is provided at the tip of the combustor inner cylinder 32, or the throttle 43 and the flat part 45 are provided at the tip of the combustor inner cylinder 32. The container inner cylinder 32 is formed of an outer cylinder and an inner cylinder, and an outlet outer ring having a throttle portion 43 and a flat portion 45 is formed, and a base end portion of the outlet outer ring is welded to a distal end portion of the inner cylinder. While fixing, you may make it fix a front-end | tip part to the front-end | tip part of an outer cylinder by welding.

  FIG. 6 is a cross-sectional view of the main part broken at the tip of the premixing nozzle in the gas turbine combustor according to the third embodiment of the present invention. In addition, the same code | symbol is attached | subjected to the member which has the same function as what was demonstrated in the Example mentioned above, and the overlapping description is abbreviate | omitted.

  In the gas turbine combustor according to the third embodiment, as shown in FIG. 6, a pilot nozzle (not shown) is disposed at the center of the combustor inner cylinder 32, and is provided on the inner peripheral surface of the combustor inner cylinder 32. A plurality of premixing nozzles 35 are disposed so as to surround the pilot nozzles along the circumferential direction, a main fuel rod 40 is disposed in each premixing nozzle 35, and a premixing swirl vane 42 is disposed. Yes. And by attaching the guide part 51 along the outer peripheral surface of each premixing nozzle to the inner peripheral surface of the combustor inner cylinder 32, between the outer peripheral surface of each premixing nozzle 35 and this guide part 51, An air flow path 38 having a substantially uniform width W is provided along the circumferential direction of each premixing nozzle 35. Note that the mounting position of the guide portion 51 is desirably provided in the entire longitudinal direction of each premixing nozzle 35, but the position where the air flow is jetted from the air flow path 38 to the combustor inner cylinder 32, that is, in the combustor You may provide only in the front-end | tip part of the pipe | tube 32. FIG.

  Accordingly, when an air flow of high-temperature and high-pressure compressed air flows into the combustor 12, this air flow is mixed with the fuel injected from the main fuel rod 40 in each premixing nozzle 35, and the swirling of the premixed air is performed. As a flow, it flows into the combustor inner cylinder 32. At this time, the air flow flowing through the air flow path 38 is accelerated by the guide portion 51 and flows along the inner wall surface of the combustor inner cylinder 32, so that the premixed gas flowing into the combustor inner cylinder 32 from the premixing nozzle 35. Slowing and peeling are prevented. The premixed gas is ignited by the combustion gas from the pilot nozzle and burned.

  As described above, in the gas turbine combustor according to the third embodiment, the pilot nozzle is disposed in the central portion of the combustor inner cylinder 32, and a plurality of pilot nozzles are surrounded on the inner peripheral surface along the circumferential direction. The premixing nozzle 35 is disposed and formed, and an air flow path 38 having a substantially uniform width along the circumferential direction and the outer circumferential surface of the plurality of premixing nozzles 35 is formed on the inner circumferential surface of the combustor inner cylinder 32. A guide part 51 is provided.

  Accordingly, the swirling flow of the premixed gas is ejected from the premixing nozzle 35 into the combustor inner cylinder 32, while the air flow flowing through the air flow path 38 is accelerated by the guide portion 51, By flowing along the wall surface, the premixed gas is smoothly merged with the accelerated air flow and flows from the combustor inner cylinder 32 to the combustor tail cylinder 33, so that the premixed gas has a low flow velocity region or a separation region. The generation of so-called flashback can be suppressed by increasing the flow velocity in the vicinity of the combustor wall surface of the premixed gas flowing from the combustor inner cylinder 32 to the combustor tail cylinder 33.

  FIG. 7 is a schematic diagram of a main part illustrating a gas turbine combustor according to a fourth embodiment of the present invention. In addition, the same code | symbol is attached | subjected to the member which has the same function as what was demonstrated in the Example mentioned above, and the overlapping description is abbreviate | omitted.

  In the gas turbine combustor of the fourth embodiment, as shown in FIG. 7, a combustor tail cylinder 33 is connected to the tip of the combustor inner cylinder 32, and a pilot nozzle 34 is provided at the center of the combustor inner cylinder 32. A plurality of premixing nozzles 35 are disposed so as to surround the pilot nozzle 34. A pilot fuel rod 39 is disposed in the pilot nozzle 34, a main fuel rod 40 is disposed in each premix nozzle 35, and a pilot swirl vane 41 is disposed in the pilot nozzle 34. A premixed swirl vane 42 is disposed therein.

  In this embodiment, a constriction portion 43 having a swirl flow locus shape in which the gas passage cross-sectional area is reduced is provided at the tip of the combustor inner cylinder 32, and the gas passage cross-sectional area is enlarged from the constriction portion 43. A flat portion 45 that is smoothly continuous is provided on the inner wall surface of the combustor tail cylinder 33. Further, a bent portion 44 that is substantially parallel to the leading end portion of the premixing nozzle 35 is provided along the throttle portion 43. Furthermore, an air inflow hole 61 is provided at the tip of the combustor inner cylinder 32 to allow air to flow into the inner peripheral surface of the tip from the outside.

  Accordingly, when an air flow of high-temperature and high-pressure compressed air flows into the combustor 12, this air flow is mixed with the fuel injected from the main fuel rod 40 in each premixing nozzle 35, and the swirling of the premixed air is performed. As a flow, it flows into the combustor inner cylinder 32. The premixed gas flowing into the combustor inner cylinder 32 from the premixing nozzle 35 is increased in flow rate by the throttle portion 43 and flows along the flat portion 45 toward the combustor tail cylinder 33. At this time, external air is sucked into the inner peripheral surface of the distal end portion of the inner cylinder 32 through the air inflow hole 61 due to the pressure difference between the inner and outer sides of the combustor inner cylinder 32, and thus flows along the inner wall surface of the distal end portion. The flow velocity in the vicinity of the wall surface of the premixed gas flowing from the combustor inner cylinder 32 to the combustor tail cylinder 33 is increased by the air, and generation of a low flow velocity region or a separation region of the premixed gas can be suppressed.

  On the other hand, in the pilot nozzle 34, the air flow of compressed air is mixed with the fuel injected from the pilot fuel rod 39, and this air-fuel mixture is ignited and burned by a seed flame (not shown) to become combustion gas and become a combustion gas. It ejects into the cylinder 32. Then, a part of the combustion gas is injected into the combustor inner cylinder 32 so as to diffuse to the surroundings with a flame, so that it flows from each premix nozzle 35 into the combustor inner cylinder 32 and the combustor tail cylinder 33. It is ignited by the premixed gas and burns.

  As described above, in the gas turbine combustor according to the fourth embodiment, the combustor tail cylinder 33 is connected to the tip of the combustor inner cylinder 32, and the pilot nozzle 34 is disposed at the center of the combustor inner cylinder 32. In addition, a plurality of premix nozzles 35 are disposed on the inner peripheral surface so as to surround the pilot nozzle 34 along the circumferential direction, and a curved surface whose gas passage cross-sectional area is reduced at the tip of the combustor inner cylinder 32. A throttle portion 43 having a shape is provided, a gas passage cross-sectional area is enlarged from the throttle portion 43, and a flat portion 45 is provided smoothly on the inner wall surface of the combustor tail cylinder 33. An air inflow hole 61 through which air flows from the outside to the inner peripheral surface of the tip is provided at the tip.

  Therefore, the premixed gas ejected from the premixing nozzle 35 to the combustor inner cylinder 32 has its flow velocity increased by the throttle portion 43 having a curved surface shape, and flows along the flat portion 45, and the external air Flows from the air inflow hole 61 into the inner peripheral surface of the tip of the combustor inner cylinder 32 to increase the flow velocity in the vicinity of the wall surface of the premixed air, so that the combustor inner cylinder 32 moves to the combustor tail cylinder 33. By flowing smoothly, suppressing the occurrence of a low flow velocity region or separation region of the premixed gas, and increasing the flow velocity in the vicinity of the combustor wall surface of the premixed gas flowing from the combustor inner cylinder 32 to the combustor tail cylinder 33, The occurrence of so-called flashback can be suppressed.

  FIG. 8 is a schematic diagram of a main part illustrating a gas turbine combustor according to a fifth embodiment of the present invention. In addition, the same code | symbol is attached | subjected to the member which has the same function as what was demonstrated in the Example mentioned above, and the overlapping description is abbreviate | omitted.

  In the gas turbine combustor of the fifth embodiment, as shown in FIG. 8, a combustor tail cylinder 33 is connected to the tip of the combustor inner cylinder 32, and a pilot nozzle 34 is provided at the center of the combustor inner cylinder 32. A plurality of premixing nozzles 35 are disposed on the inner peripheral surface of the combustor inner cylinder 32 so as to surround the pilot nozzle 34 along the circumferential direction. An air flow path 38 is provided between the mixing nozzles 35. A pilot fuel rod 39 is disposed in the pilot nozzle 34, a main fuel rod 40 is disposed in each premix nozzle 35, and a pilot swirl vane 41 is disposed in the pilot nozzle 34. A premixed swirl vane 42 is disposed therein. In this embodiment, a curved portion 71 having a swirl flow locus shape in which the gas passage cross-sectional area is enlarged is provided at the tip of the combustor inner cylinder 32.

  That is, in the premixing nozzle 35, a swirling flow of air is generated by the premixing swirl vane 42, and fuel is injected from the main fuel rod 40 into the swirling flow of air to be mixed and burned as a premixed gas. It flows into the inner cylinder 32. At this time, the flow velocity of the premixed gas along the inner wall surface of the combustor inner cylinder 32 is reduced by making the curved portion 71 a swirl flow locus shape in which the swirling flow of the premixed gas naturally spreads outward. It can be made to flow smoothly to the combustor tail cylinder 33 without being peeled off or peeling off.

  Accordingly, when an air flow of high-temperature and high-pressure compressed air flows into the combustor 12, this air flow is mixed with the fuel injected from the main fuel rod 40 in each premixing nozzle 35, and the swirling of the premixed air is performed. As a flow, it flows into the combustor inner cylinder 32. At this time, since the premixed gas flowing from the premixing nozzle 35 into the combustor inner cylinder 32 is smoothly diffused by the curved portion 71 having a swirl flow locus shape, the premixed gas smoothly flows from the combustor inner cylinder 32 to the combustor tail cylinder 33. Thus, it is possible to suppress the generation of a low flow velocity region or a separation region of the premixed gas.

  On the other hand, in the pilot nozzle 34, the air flow of compressed air is mixed with the fuel injected from the pilot fuel rod 39, and this air-fuel mixture is ignited and burned by a seed flame (not shown) to become combustion gas and become a combustion gas. It ejects into the cylinder 32. Then, a part of the combustion gas is injected into the combustor inner cylinder 32 so as to diffuse to the surroundings with a flame, so that it flows from each premix nozzle 35 into the combustor inner cylinder 32 and the combustor tail cylinder 33. It is ignited by the premixed gas and burns.

  Thus, in the gas turbine combustor according to the fifth embodiment, the combustor tail cylinder 33 is connected to the tip of the combustor inner cylinder 32, and the pilot nozzle 34 is disposed at the center of the combustor inner cylinder 32. In addition, a plurality of premixing nozzles 35 are disposed on the inner peripheral surface so as to surround the pilot nozzle 34 along the circumferential direction, and the gas passage cross-sectional area is enlarged at the tip of the combustor inner cylinder 32. A curved portion 71 having a flow locus shape is provided.

  Accordingly, since the premixed gas ejected from the premixing nozzle 35 to the combustor inner cylinder 32 diffuses and flows along the curved portion 71 having a swirl flow locus shape, the premixed gas flows from the combustor inner cylinder 32 to the combustor tail. It will flow smoothly into the cylinder 33, suppress the generation of a low flow velocity region or separation region of the premixed gas, and increase the flow velocity in the vicinity of the combustor wall surface of the premixed gas flowing from the combustor inner tube 32 to the combustor tail tube 33. Thus, the occurrence of so-called flashback can be suppressed.

  FIG. 9 is a schematic view of the main part showing a gas turbine combustor according to Embodiment 6 of the present invention. In addition, the same code | symbol is attached | subjected to the member which has the same function as what was demonstrated in the Example mentioned above, and the overlapping description is abbreviate | omitted.

  In the gas turbine combustor according to the sixth embodiment, as shown in FIG. 9, a combustor tail cylinder 33 is connected to the tip of the combustor inner cylinder 32, and a pilot nozzle 34 is provided at the center of the combustor inner cylinder 32. A plurality of premixing nozzles 35 are disposed on the inner peripheral surface of the combustor inner cylinder 32 so as to surround the pilot nozzle 34 along the circumferential direction. An air flow path 38 is provided between the mixing nozzles 35. A pilot fuel rod 39 is disposed in the pilot nozzle 34, a main fuel rod 40 is disposed in each premixing nozzle 35, and a pilot swirl vane 41 is disposed in the pilot nozzle 34. A premixed swirl vane 42 is disposed therein. In this embodiment, a curved portion 71 having a swirl flow locus shape in which the gas passage cross-sectional area is enlarged is provided at the tip portion of the combustor inner cylinder 32, and the inside of the combustor tail cylinder 33 is formed from the curved portion 71. A flat portion 72 that is smoothly continuous with the wall surface is provided.

  That is, in the premixing nozzle 35, a swirling flow of air is generated by the premixing swirl vane 42, and fuel is injected from the main fuel rod 40 into the swirling flow of air to be mixed and burned as a premixed gas. It flows into the inner cylinder 32. At this time, the shape of the curved portion 71 is a swirl flow locus shape in which the swirling flow of the premixed gas naturally spreads outward, and a flat portion 72 following the curved portion 71 is provided, so that the inside of the combustor inner cylinder 32 is provided. The flow rate of the premixed gas along the wall surface can be smoothly flowed to the combustor tail cylinder 33 without decreasing and without peeling.

  Accordingly, when an air flow of high-temperature and high-pressure compressed air flows into the combustor 12, this air flow is mixed with the fuel injected from the main fuel rod 40 in each premixing nozzle 35, and the swirling of the premixed air is performed. As a flow, it flows into the combustor inner cylinder 32. At this time, the premixed gas flowing into the combustor inner cylinder 32 from the premixing nozzle 35 is smoothly diffused by the curved portion 71 having the swirl flow locus shape and flows smoothly along the flat portion 72. Generation | occurrence | production of the low flow velocity area or peeling area | region of air-fuel | gaseous mixture can be suppressed.

  On the other hand, in the pilot nozzle 34, the air flow of compressed air is mixed with the fuel injected from the pilot fuel rod 39, and this air-fuel mixture is ignited and burned by a seed flame (not shown) to become combustion gas and become a combustion gas. It ejects into the cylinder 32. Then, a part of the combustion gas is injected into the combustor inner cylinder 32 so as to diffuse to the surroundings with a flame, so that it flows from each premix nozzle 35 into the combustor inner cylinder 32 and the combustor tail cylinder 33. It is ignited by the premixed gas and burns.

  Thus, in the gas turbine combustor according to the sixth embodiment, the combustor tail cylinder 33 is connected to the tip of the combustor inner cylinder 32, and the pilot nozzle 34 is disposed at the center of the combustor inner cylinder 32. In addition, a plurality of premixing nozzles 35 are disposed on the inner peripheral surface so as to surround the pilot nozzle 34 along the circumferential direction, and the gas passage cross-sectional area is enlarged at the tip of the combustor inner cylinder 32. A curved portion 71 having a flow locus shape is provided, and a flat portion 72 continuous with the curved portion 71 is provided.

  Accordingly, the premixed gas ejected from the premixing nozzle 35 to the combustor inner cylinder 32 diffuses along the curved portion 71 having a swirl flow locus shape and flows along the flat portion 72. The combustor of the premixed gas that flows smoothly from the cylinder 32 to the combustor tail cylinder 33, suppresses the generation of a low flow velocity region or a separation region of the premixed gas, and flows from the combustor inner cylinder 32 to the combustor tail cylinder 33. By increasing the flow velocity in the vicinity of the wall surface, so-called flashback can be suppressed.

  The gas turbine combustor according to the present invention is capable of suppressing the occurrence of flashback by increasing the velocity near the combustor wall surface of the premixed gas flowing from the combustor inner cylinder to the combustor tail cylinder. It can also be applied to different types of gas turbines.

It is a principal part schematic showing the gas turbine combustor which concerns on Example 1 of this invention. It is explanatory drawing of the turning flow locus | trajectory shape of the throttle part in the gas turbine combustor of Example 1. FIG. It is explanatory drawing of the premixing swirl vane in the gas turbine combustor of Example 1. FIG. 1 is a schematic configuration diagram of a gas turbine according to Embodiment 1. FIG. It is a schematic block diagram of the gas turbine combustor of Example 1. FIG. It is a principal part schematic diagram showing the gas turbine combustor which concerns on Example 2 of this invention. It is principal part sectional drawing fractured | ruptured at the front-end | tip part of the premixing nozzle in the gas turbine combustor which concerns on Example 3 of this invention. It is a principal part schematic diagram showing the gas turbine combustor which concerns on Example 4 of this invention. It is a principal part schematic diagram showing the gas turbine combustor which concerns on Example 5 of this invention. It is a principal part schematic diagram showing the gas turbine combustor which concerns on Example 6 of this invention. It is a principal part schematic diagram showing the conventional gas turbine combustor.

Explanation of symbols

DESCRIPTION OF SYMBOLS 11 Compressor 12 Combustor 13 Turbine 14 Exhaust chamber 32 Combustor inner cylinder 33 Combustor tail cylinder 34 Pilot nozzle 35 Premix nozzle 38 Air flow path 39 Pilot fuel rod 40 Main fuel rod 41 Pilot swirl vane 42 Premix swirl vane 43 Restriction part 44 Bending part 45 Plane part 51 Guide part 61 Air inflow hole 71 Bending part 72 Plane part

Claims (10)

  A combustor inner cylinder, a combustor tail cylinder connected to the tip of the combustor inner cylinder, a pilot nozzle disposed in a central portion of the combustor inner cylinder, and an inner peripheral surface of the combustor inner cylinder A gas turbine combustor comprising a plurality of premixing nozzles disposed so as to surround the pilot nozzle along a circumferential direction, and a curved surface shape in which a gas passage cross-sectional area is reduced at a tip portion of the inner cylinder of the combustor A gas turbine combustor characterized in that a throttle portion is provided.   2. The gas turbine combustor according to claim 1, wherein the throttle portion is provided on a downstream side in a gas flow direction with respect to a tip portion of the premixing nozzle. 3.   3. The gas turbine combustor according to claim 1, wherein a bent portion along the throttle portion provided in the inner cylinder of the combustor is provided at a tip portion of the premixing nozzle. 4. Turbine combustor.   4. The gas turbine combustor according to claim 1, wherein the throttle portion is formed in a shape along a trajectory of a swirling flow of the gas flowing in the inner cylinder of the combustor. 5. Gas turbine combustor.   5. The gas turbine combustor according to claim 1, wherein a gas passage cross-sectional area is enlarged from the constricted portion at a tip portion of the inner cylinder of the combustor and is continuously continuous with the combustor tail cylinder. 6. A gas turbine combustor characterized in that a flat portion is provided.   6. The gas turbine combustor according to claim 5, wherein a ratio of an inner diameter of the throttle portion to an inner diameter of the inner cylinder of the combustor is set to 0.8 or more and less than 1.0, and from a tip of the premixing nozzle. The ratio of the length from the tip of the premixing nozzle to the minimum inner diameter position of the throttle portion to the length to the tip of the combustor inner cylinder is set to 0.05 or more and 0.3 or less. Gas turbine combustor.   7. The gas turbine combustor according to claim 1, wherein the inner peripheral surface of the inner cylinder of the combustor has a substantially uniform width along the outer peripheral surface and the circumferential direction of the plurality of premixing nozzles. A gas turbine combustor provided with a guide portion that forms a flow path.   The gas turbine combustor according to any one of claims 1 to 7, wherein an air inflow hole through which air flows from the outside to the inner peripheral surface of the combustor tail cylinder is provided at a tip portion of the combustor inner cylinder. A gas turbine combustor characterized by the above.   A combustor inner cylinder, a combustor tail cylinder connected to the tip of the combustor inner cylinder, and a plurality of premixing nozzles arranged along the circumferential direction on the inner peripheral surface of the combustor inner cylinder; A gas turbine combustor comprising a pilot nozzle disposed at a central portion of the combustor inner cylinder so as to be surrounded by the plurality of premixing nozzles, wherein the combustor is disposed at a tip portion of the combustor inner cylinder. A gas turbine combustor comprising a curved portion in which a gas passage cross-sectional area expands along a trajectory of a swirling flow of gas flowing in an inner cylinder.   The gas turbine combustor according to claim 9, wherein a flat portion that smoothly continues from the curved portion to the combustor tail tube is provided at a tip portion of the combustor inner tube. vessel.

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