A gas turbine combustion chamber

Abstract

The present invention relates to the field of aerospace equipment technology, and in particular to a gas turbine combustion chamber. It solves the problem that the working range is not wide enough and the types of fuel options are narrow. It includes a casing, a rotating cylinder, an ignition nozzle and a flame tube. The two ends of the rotating cylinder pass through and are coaxially arranged at the smaller end opening of the casing. The ignition nozzle is coaxially arranged in the rotating cylinder. After one end of the rotating cylinder extends into the casing, a first-stage swirler and a second-stage swirler are sequentially arranged in the circumferential direction. The second-stage swirler is coaxially fixedly connected to the flame tube. The casing is provided with a first fuel channel, a second fuel channel, a third fuel channel, a fourth fuel channel and a fifth fuel channel which are sequentially arranged radially outward from the rotating cylinder. The working range of the combustion chamber of the present invention is significantly expanded, and a five-stage fuel channel supply scheme is adopted, which can adapt to gas and liquid fuels with large differences in density and atomization characteristics. By rationally selecting the fuel supply channel, the combustion efficiency and outlet temperature distribution of the combustion chamber are guaranteed.

Description

Technical Field

[0001] The present invention relates to the technical field of aerospace equipment, and in particular to a gas turbine combustion chamber. Background Art

[0002] Gas turbines are cutting-edge, highly technologically integrated equipment widely used in industries such as aerospace, power generation, and petrochemicals. Through the combustion chamber, a gas turbine releases the chemical energy of fuel and converts fresh air into high-speed combustion gas to generate power. Therefore, the combustion chamber is one of the core components of a gas turbine.

[0003] The combustion chamber head is the key structure of the combustion chamber. It is the carrier of combustion organization and fuel and air mixing. It is directly related to the performance indicators of gas turbine such as reliable ignition, stable and efficient combustion and outlet temperature distribution. Therefore, it is the essence of gas turbine combustion chamber design and requires special attention. The combustion chamber head structure is shown in the attached figure. Figure 1 As shown, a swirler is usually used to form a head reflux low-speed zone to stabilize combustion, a flame tube is used to form the outer boundary of the main combustion zone of the combustion chamber, a combustion chamber casing is used to provide a mounting carrier for various components and constitute the outer boundary of the combustion chamber, and the fuel and the ejection carrier are transported through the fuel main pipe, and finally the fuel is output to the combustion chamber.

[0004] At present, the gas turbine combustion chamber widely uses a two-stage fuel supply + multi-stage swirler combination to meet the requirements of wide working range and high performance. Figure 1 As shown, the middle fuel stage provides fuel under low-power conditions, ensuring sufficient fuel atomization and efficient combustion. Under high-power conditions, fuel is supplied through the outer fuel channel. This solution is mature and widely used. Currently, most military and civilian gas turbines use a similar structure. Although this solution has excellent performance in terms of stability, advanced performance, and operational reliability, it has the following problems:

[0005] 1) The operating range is not wide enough. Currently, the operating range of most fuels in the combustion chamber head is generally no more than 20 times. If it is installed on an aircraft, its maximum operating altitude and maximum speed will be limited. Therefore, if it is necessary to take into account both ground and higher altitude operations, the operating range of the fuel needs to be expanded.

[0006] 2) High pollutant emissions. Green development is a key theme of our time, and gas turbine pollutant emissions are receiving increasing attention. The currently widely used combustor head design provides excellent combustion under certain conditions, such as the design point. However, under other operating conditions, combustion is incomplete, particularly with uneven temperature distribution. This leads to high emissions of pollutants such as soot and nitrogen oxides, severely polluting the atmosphere and endangering climate safety.

[0007] 3) Limited fuel options. Most current combustion chamber head solutions utilize extremely sophisticated and complex nozzle structures, designed to accommodate either liquid fuels or gaseous fuels such as natural gas, but not both. This is because different fuel types have vastly different physical properties, such as density, volume, and atomization. Forcing the use of different fuel types will lead to serious consequences, such as unstable combustion, mismatched fuel mass flow rates, and substandard performance. Summary of the Invention

[0008] The present invention provides a gas turbine combustion chamber. By designing more fuel supply channels, the fuel quality working range can be more than 30 times, which is much wider than the current heads of most gas turbine combustion chambers. The working range of the combustion chamber is significantly expanded. If used in aerospace vehicles, the flight altitude of the aircraft can be significantly increased; the mixing quality of fuel and air is effectively improved to ensure sufficient and efficient combustion of the fuel. The double swirl air intake method without main combustion holes in the head also effectively reduces the average temperature of the combustion chamber head, thereby effectively reducing the emission of nitrogen oxides; a five-level fuel channel supply scheme is adopted, which can adapt to gas and liquid fuels with large differences in density and atomization characteristics, and through the reasonable selection of fuel supply channels, the combustion efficiency, outlet temperature distribution, etc. of the combustion chamber are guaranteed to meet the design requirements.

[0009] In order to solve the above technical problems, the present invention adopts the following technical solutions:

[0010] A gas turbine combustion chamber comprises a casing, a rotating cylinder, an ignition nozzle and a flame tube, wherein both ends of the rotating cylinder pass through and are coaxially arranged at the smaller end opening of the casing, the ignition nozzle is coaxially arranged in the rotating cylinder, and after one end of the rotating cylinder extends into the casing, a first-stage swirler and a second-stage swirler are sequentially arranged in the circumferential direction, and the second-stage swirler is coaxially fixedly connected to the flame tube, and the casing is provided with a first fuel channel, a second fuel channel, a third fuel channel, a fourth fuel channel and a fifth fuel channel which are sequentially arranged radially outward along the rotating cylinder, and the first fuel channel, the second fuel channel, the third fuel channel, the fourth fuel channel and the fifth fuel channel are all located on the inner side of the second-stage swirler.

[0011] Furthermore, the casing is a columnar structure.

[0012] Furthermore, the first-stage cyclone is composed of a plurality of circumferentially arranged first blades, and the second-stage cyclone is composed of a plurality of circumferentially arranged second blades.

[0013] Furthermore, the first blade and the second blade are both arc-shaped, and the inner sides of the first blade and the second blade face oppositely.

[0014] Furthermore, the first fuel channel is installed in the middle of the casing, and one end of the first fuel channel extends into the opening of the end of the rotating tube away from the flame tube.

[0015] Furthermore, the second fuel channel includes a second fuel pipe and a second feed pipe, the second fuel pipe is annular and coaxially located between the flame tube and the casing, the second fuel pipe is connected to a second opening, the projection of the second fuel pipe along the axial direction of the first-stage swirler is located inside the first-stage swirler, the second feed pipe is installed on the casing, the second feed pipe extends along the axial direction of the rotating cylinder, one end of the second feed pipe is connected to and docked with the second fuel pipe, and the other end of the second feed pipe is located outside the casing.

[0016] Furthermore, the third fuel channel includes a third fuel pipe and a third feed pipe. The third fuel pipe is annular and coaxially located between the flame tube and the casing. The third fuel pipe is connected to a third opening. The projection of the third fuel pipe along the axial direction of the first-stage swirler is located inside the first-stage swirler. The third feed pipe is installed on the casing. The third feed pipe extends along the axial direction of the rotating cylinder. One end of the third feed pipe is connected to and docked with the third fuel pipe, and the other end of the third feed pipe is located outside the casing. The third fuel pipe is located on the outside of the second fuel pipe.

[0017] Furthermore, the fourth fuel channel includes a fourth fuel pipe and a fourth feed pipe. The fourth fuel pipe is annular and coaxially located between the flame tube and the casing. The fourth fuel pipe is connected to a fourth opening. The projection of the fourth fuel pipe along the axial direction of the secondary swirler is located inside the secondary swirler. The fourth feed pipe is installed on the casing. The fourth feed pipe extends along the axial direction of the rotating cylinder. One end of the fourth feed pipe is connected to and docked with the fourth fuel pipe, and the other end of the fourth feed pipe is located outside the casing.

[0018] Furthermore, the fifth fuel channel includes a fifth fuel pipe and a fifth feed pipe. The fifth fuel pipe is annular and coaxially located between the flame tube and the casing. The fifth fuel pipe is connected to a fifth opening. The projection of the fifth fuel pipe along the axial direction of the secondary swirler is located inside the secondary swirler. The fifth feed pipe is installed on the casing. The fifth feed pipe extends along the axial direction of the rotating cylinder. One end of the fifth feed pipe is connected to and docked with the fifth fuel pipe, and the other end of the fifth feed pipe is located outside the casing. The fifth fuel pipe is located on the outside of the fourth fuel pipe.

[0019] Beneficial effects of the present invention:

[0020] By designing more fuel supply channels, the fuel quality working range can be increased by more than 30 times, which is much wider than the current combustion chamber heads of most gas turbines. The working range of the combustion chamber is significantly expanded. If used in aerospace vehicles, the flight altitude of the aircraft can be significantly increased; it effectively improves the mixing quality of fuel and air to ensure full and efficient combustion of the fuel. The double swirl air intake method without main combustion holes in the head also effectively reduces the average temperature of the combustion chamber head, thereby effectively reducing the emission of nitrogen oxides; a five-stage fuel channel supply scheme is adopted, which can adapt to gas and liquid fuels with large differences in density and atomization characteristics, and through the reasonable selection of fuel supply channels, it is ensured that the combustion efficiency and outlet temperature distribution of the combustion chamber meet the design requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a structural diagram of the combustion chamber head structure in the prior art;

[0022] Figure 2 This is a schematic structural diagram of the gas turbine combustion chamber of this application;

[0023] Figure 3 This is a cross-sectional view of the structure of the gas turbine combustion chamber of this application;

[0024] Figure 4 Schematic diagram of the three-dimensional structure of the fuel channel;

[0025] Figure 5 It is a structural front view of the fuel channel;

[0026] Figure 6 Schematic diagram of the three-dimensional structure of the first-stage cyclone and the second-stage cyclone;

[0027] Description of reference numerals:

[0028] 1. Receiver; 2. Rotating cylinder; 3. Ignition nozzle; 4. Flame tube; 5. First blade; 6. Second blade; 7. First fuel channel; 81. Second fuel pipe; 82. Second feed pipe; 83. Second opening; 91. Third fuel pipe; 92. Third feed pipe; 93. Third opening; 101. Fourth fuel pipe; 102. Fourth feed pipe; 103. Fourth opening; 111. Fifth fuel pipe; 112. Fifth feed pipe; 113. Fifth opening. DETAILED DESCRIPTION

[0029] In order to facilitate understanding by those skilled in the art, the present invention will be further described below with reference to embodiments and drawings. The contents mentioned in the embodiments are not intended to limit the present invention.

[0030] like Figure 2-6As shown, a gas turbine combustion chamber includes a casing 1, a rotating cylinder 2, an ignition nozzle 3 and a flame tube 4. Both ends of the rotating cylinder 2 pass through and are coaxially arranged at the smaller end opening of the casing 1. The ignition nozzle 3 is coaxially arranged in the rotating cylinder 2. After one end of the rotating cylinder 2 extends into the casing 1, a first-level swirler and a second-level swirler are sequentially arranged in the circumferential direction. The second-level swirler is coaxially fixedly connected to the flame tube 4. The casing 1 is provided with a first fuel channel 7, a second fuel channel, a third fuel channel, a fourth fuel channel and a fifth fuel channel which are sequentially arranged radially outward along the rotating cylinder 2. The first fuel channel 7, the second fuel channel, the third fuel channel, the fourth fuel channel and the fifth fuel channel are all located on the inner side of the second-level swirler.

[0031] In this embodiment, the casing 1 is a columnar structure.

[0032] like Figure 3 、 6 As shown, in this embodiment, the first-stage cyclone is composed of a plurality of circumferentially arranged first blades 5 , and the second-stage cyclone is composed of a plurality of circumferentially arranged second blades 6 .

[0033] In this embodiment, the first blade 5 and the second blade 6 are both arc-shaped, and the inner sides of the first blade 5 and the second blade 6 face opposite directions.

[0034] When the rotating cylinder 2 rotates, the first blade 5 and the second pressing piece cause the air at the two locations to rotate in different directions. The first blade 5 and the second blade 6 turbulently disturb the inflowing air, thereby improving the pre-mixing atomization quality of the fuel and increasing the combustion rate.

[0035] like Figure 4 、 5 As shown, in this embodiment, the first fuel channel 7 is installed in the middle of the casing 1, and one end of the first fuel channel 7 extends into the opening of the rotating cylinder 2 away from the flame cylinder 4.

[0036] Through the first fuel channel 7, the fuel flows from the outer side of the ignition nozzle 3 and the inner channel of the first-stage swirler into the head of the flame tube 4. Under the action of the first-stage swirler and the second-stage swirler, a recirculation zone is formed at the head of the flame tube 4. The fuel is sprayed into the center of the recirculation zone, close to the ignition nozzle 3. Its main function is to be used in small states such as ignition in the combustion chamber to ensure reliable ignition and stable combustion in the combustion chamber.

[0037] In this embodiment, the second fuel channel includes a second fuel pipe 81 and a second feed pipe 82. The second fuel pipe 81 is annular and coaxially located between the flame tube 4 and the casing 1. The second fuel pipe 81 is connected to a second opening 83. The projection of the second fuel pipe 81 along the axial direction of the first-stage swirler is located inside the first-stage swirler. The second feed pipe 82 is installed on the casing 1. The second feed pipe 82 extends along the axial direction of the rotating cylinder 2. One end of the second feed pipe 82 is connected to and docked with the second fuel pipe 81, and the other end of the second feed pipe 82 is located outside the casing 1.

[0038] In this embodiment, the third fuel channel includes a third fuel pipe 91 and a third feed pipe 92. The third fuel pipe 91 is annular and coaxially located between the flame tube 4 and the casing 1. The third fuel pipe 91 is connected to a third opening 93. The projection of the third fuel pipe 91 along the axial direction of the first-stage swirler is located inside the first-stage swirler. The third feed pipe 92 is installed on the casing 1. The third feed pipe 92 extends along the axial direction of the rotating cylinder 2. One end of the third feed pipe 92 is connected to and docked with the third fuel pipe 91. The other end of the third feed pipe 92 is located outside the casing 1. The third fuel pipe 91 is located on the outside of the second fuel pipe 81.

[0039] The second fuel channel and the third fuel channel are located at the front end of the first-stage swirler. When the gas turbine power increases and the required fuel flow rate is higher, the second fuel channel or the third fuel channel can be opened as needed. The output fuel is ejected through the second opening 83 or the third opening 93, and then mixed and assisted in atomization by the first-stage swirler before flowing into the head reflux area to participate in combustion.

[0040] In this embodiment, the fourth fuel channel includes a fourth fuel pipe 101 and a fourth feed pipe 102. The fourth fuel pipe 101 is annular and coaxially located between the flame tube 4 and the casing 1. The fourth fuel pipe 101 is connected to a fourth opening 103. The projection of the fourth fuel pipe 101 along the axial direction of the secondary swirler is located inside the secondary swirler. The fourth feed pipe 102 is installed on the casing 1. The fourth feed pipe 102 extends along the axial direction of the rotating cylinder 2. One end of the fourth feed pipe 102 is connected to and docked with the fourth fuel pipe 101, and the other end of the fourth feed pipe 102 is located outside the casing 1.

[0041] In this embodiment, the fifth fuel channel includes a fifth fuel pipe 111 and a fifth feed pipe 112. The fifth fuel pipe 111 is annular and coaxially located between the flame tube 4 and the casing 1. The fifth fuel pipe 111 is connected to a fifth opening 113. The projection of the fifth fuel pipe 111 along the axial direction of the secondary swirler is located inside the secondary swirler. The fifth feed pipe 112 is installed on the casing 1. The fifth feed pipe 112 extends along the axial direction of the rotating cylinder 2. One end of the fifth feed pipe 112 is connected to and docked with the fifth fuel pipe 111. The other end of the fifth feed pipe 112 is located outside the casing 1. The fifth fuel pipe 111 is located on the outside of the fourth fuel pipe 101.

[0042] The fourth fuel channel and the fifth fuel channel are located at the front end of the secondary swirler. When the gas turbine further increases its power (such as operating at maximum operating conditions), the corresponding channels are gradually opened to output fuel according to the fuel quality requirements. After the fuel is ejected through the fourth opening 103 or the fifth opening 113, it is mixed with the air in the secondary swirler and assisted in atomization, and then flows into the outside of the head recirculation area to participate in combustion.

[0043] After optimization, the selection order of the fuel channels can further reduce the pollutant emissions from the combustion chamber and improve combustion efficiency. In this solution, the first fuel channel 7 needs to be kept open at all times. Its main function is to stabilize the combustion in the combustion chamber and ensure the continued existence of the flame source. The fuel outputs of the other four fuel channels can be combined arbitrarily. For example, at certain operating points, only the second fuel channel, the third fuel channel or the fourth fuel channel can be opened. In this way, the fuel can be distributed as much as possible in the recirculation area of ​​the entire combustion chamber head, thereby minimizing the maximum temperature and reducing the emission of pollutants such as nitrogen oxides. In short, through experimental or numerical simulation optimization design results, the four fuel channels located outside the first fuel channel 7 can be selected and combined according to the operating fuel consumption of the gas turbine to maximize the fuel supply with high combustion efficiency, excellent temperature outlet distribution quality and low pollutant emissions.

[0044] The main advantages of the present invention are:

[0045] 1) The operating range of the combustor head is significantly expanded. By designing more fuel supply channels, the combustor head of this solution can achieve a fuel mass operating range of more than 30 times, significantly wider than the combustor heads of most current gas turbines. This significantly expands the operating range of the combustor. If used in aerospace vehicles, it can significantly increase the flight altitude of the aircraft.

[0046] 2) Lower combustion chamber pollutant emissions. This solution utilizes multi-stage fuel combustion chamber head air optimization matching and fuel pre-mixing to effectively improve the quality of fuel-air mixing and ensure sufficient and efficient combustion of the fuel. The dual swirl air intake method without a main combustion hole in the head also effectively reduces the average temperature of the combustion chamber head gas, thereby effectively reducing nitrogen oxide emissions. In summary, this solution can significantly improve the pollutant emissions of the combustion chamber under various operating conditions.

[0047] 3) This combustion chamber can simultaneously burn both gaseous and liquid fuels. This invention utilizes a five-stage fuel supply channel design, adapting to gaseous and liquid fuels with widely varying densities and atomization characteristics. By rationally selecting fuel supply channels, the combustion chamber's combustion efficiency and outlet temperature distribution meet design requirements.

[0048] Working principle:

[0049] like Figure 2 、 3 As shown in Figures 4, 5, and 6, the high-pressure gas flowing into the combustion chamber structure from the gas turbine compressor and other components flows into the inner cavity of the flame tube 4 through the gap between the flame tube 4 and the inner wall of the casing 1, and together with the fuel flowing in from the first fuel channel 7, the second fuel channel, the third fuel channel, the fourth fuel channel or the fifth fuel channel, after swirl treatment, a recirculation zone is formed inside the flame tube 4 to burn, and the chemical energy of the fuel is converted into thermal energy and kinetic energy of the air, and flows out of the flame tube 4 to drive the turbine and other components to do work. The flame tube 4, the first-stage swirler and the second-stage swirler are welded together and fixed to the casing 1 by pins, etc., to ensure the effective rotation of the rotating tube 2. The air flows along the flame tube 4 and The air flows into the gaps between the inner walls of the casing 1, and flows from the first-stage swirler and the second-stage swirler into the recirculation zone at the head of the flame tube 4 to participate in the combustion. The recirculation zone has the flame tube 4 as the outer boundary and has a large area, which can effectively ensure stable and efficient combustion, is beneficial to the full combustion of the fuel, reduces the formation of unburned hydrocarbons, and increases the air flow in the main combustion zone. It can not only reduce the average temperature of the gas at the head of the combustion chamber, but also increase the air flow rate, and minimize the possibility of the flame at the recirculation zone at the head of the combustion chamber to burn back to the air inlet. In addition, the high-speed airflow can also make the fuel flow in a concentrated manner under the action of the air pressure difference, improve the pre-mixing atomization quality of the fuel, thereby improving the combustion efficiency and preventing the occurrence of smoke.

[0050] All technical features in this embodiment can be freely combined according to actual needs.

[0051] It should be noted that, in this document, relational terms such as first and second, etc., are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "comprises," "comprising," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that includes a list of elements includes not only those elements but also other elements not explicitly listed, or elements inherent to such process, method, article, or apparatus.

[0052] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to these embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the appended claims and their equivalents.

[0053] The above embodiments are preferred implementation schemes of the present invention. In addition, other implementation schemes are also included. Any obvious replacement without departing from the concept of the present technical solution is within the protection scope of the present invention.

Claims

1. A gas turbine combustion chamber, comprising a casing (1), a rotating cylinder (2), an ignition nozzle (3) and a flame tube (4), characterized in that: The two ends of the rotating cylinder (2) pass through and are coaxially arranged at the smaller end opening of the casing (1); the ignition nozzle (3) is coaxially arranged in the rotating cylinder (2); after one end of the rotating cylinder (2) extends into the casing (1), a first-stage swirler and a second-stage swirler are sequentially arranged in the circumferential direction; the second-stage swirler is coaxially fixedly connected to the flame cylinder (4); the casing (1) is provided with a first fuel channel (7), a second fuel channel, a third fuel channel, a fourth fuel channel and a fifth fuel channel sequentially arranged radially outward along the rotating cylinder (2); the first fuel channel (7), the second fuel channel, the third fuel channel, the fourth fuel channel and the fifth fuel channel are all located on the inner side of the second-stage swirler; The first fuel channel (7) is installed in the middle of the casing (1), and one end of the first fuel channel (7) extends into the opening of the rotating cylinder (2) away from the flame cylinder (4); The second fuel channel includes a second fuel pipe (81) and a second feed pipe (82), the second fuel pipe (81) is annular and coaxially located between the flame tube (4) and the casing (1), the second fuel pipe (81) is connected to a second opening (83), the second fuel pipe (81) is projected along the axial direction of the first-stage swirler and is located inside the first-stage swirler, the second feed pipe (82) extends along the axial direction of the rotating cylinder (2), one end of the second feed pipe (82) is connected to and docked with the second fuel pipe (81), and the other end of the second feed pipe (82) is located outside the casing (1); The third fuel channel includes a third fuel pipe (91) and a third feed pipe (92), the third fuel pipe (91) is annular and coaxially located between the flame tube (4) and the casing (1), the third fuel pipe (91) is connected to a third opening (93), the projection of the third fuel pipe (91) along the axial direction of the first-stage swirler is located inside the first-stage swirler, one end of the third feed pipe (92) is connected to and docked with the third fuel pipe (91), and the third fuel pipe (91) is located outside the second fuel pipe (81); The fourth fuel channel comprises a fourth fuel pipe (101) and a fourth feed pipe (102); the fourth fuel pipe (101) is annular and coaxially located between the flame tube (4) and the casing (1); the fourth fuel pipe (101) is connected to a fourth opening (103); the projection of the fourth fuel pipe (101) along the axial direction of the secondary swirler is located inside the secondary swirler; one end of the fourth feed pipe (102) is connected to and docked with the fourth fuel pipe (101); The fifth fuel channel comprises a fifth fuel pipe (111) and a fifth feed pipe (112), the fifth fuel pipe (111) being annular and coaxially located between the flame tube (4) and the casing (1), the fifth fuel pipe (111) being connected to a fifth opening (113), the projection of the fifth fuel pipe (111) along the axial direction of the secondary swirler being located inside the secondary swirler, one end of the fifth feed pipe (112) being connected to and docked with the fifth fuel pipe (111), and the fifth fuel pipe (111) being located outside the fourth fuel pipe (101).

2. The gas turbine combustor according to claim 1, wherein: The casing (1) is a columnar structure.

3. The gas turbine combustor according to claim 2, wherein: The first-stage cyclone is composed of a plurality of circumferentially arranged first blades (5), and the second-stage cyclone is composed of a plurality of circumferentially arranged second blades (6).

4. The gas turbine combustor according to claim 3, wherein: The first blade (5) and the second blade (6) are both arc-shaped, and the inner sides of the first blade (5) and the second blade (6) face opposite directions.

5. The gas turbine combustor according to claim 1, wherein: The second feed pipe (82) is mounted on the casing (1).

6. The gas turbine combustor according to claim 1, wherein: The third feed pipe (92) is mounted on the casing (1), the third feed pipe (92) extends along the axial direction of the rotating cylinder (2), and the other end of the third feed pipe (92) is located outside the casing (1).

7. The gas turbine combustor according to claim 1, wherein: The fourth feed pipe (102) is mounted on the casing (1), the fourth feed pipe (102) extends along the axial direction of the rotating cylinder (2), and the other end of the fourth feed pipe (102) is located outside the casing (1).

8. The gas turbine combustor according to claim 1, wherein: The fifth feed pipe (112) is mounted on the casing (1), the fifth feed pipe (112) extends along the axial direction of the rotating cylinder (2), and the other end of the fifth feed pipe (112) is located outside the casing (1).

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