Arrangement of a gas turbine combustion chamber

Abstract

The application relates to the technical field of gas turbine combustion chambers, in particular to a gas turbine combustion chamber layout structure which comprises an air inlet section, a combustion section is arranged on the air inlet section, five groups of burners are arranged in the air inlet section, the burners comprise an outer shell, a middle shell and an inner shell which are coaxially arranged in sequence, a head swirl generator is arranged at the air outlet end of the middle shell, first guide vanes, second guide vanes, a swirl assembly and an assembling mechanism are arranged in the air inlet section. The application can promote the mixing of different components between air and fuel gas flow, improve the reaction efficiency, increase the uniformity of the gas, effectively reduce the dead zone in the gas flow, make the gas flow more uniform in the whole system, avoid local accumulation or retention, optimize the entering direction of the fluid, enhance the rotation effect of the fluid, guide the smooth discharge of the swirl fluid and maintain a certain flow rate, realize multiple combustion organizations such as diffusion, diffusion+premixing and premixing, so that the air organization and fuel distribution of each burner are controllable.

Description

Technical Field

[0001] This invention relates to the field of gas turbine combustor technology, and more specifically to a gas turbine combustor layout structure. Background Technology

[0002] The combustion chamber is a crucial component of a gas turbine generator, its function being to convert the chemical energy of fuel into thermal energy through chemical reactions. Many factors influence the combustion chamber's performance, including its structure, the properties of the fuel and air, and the air distribution within the combustion chamber. Because of fuel combustion, the combustion chamber operates under high temperature and pressure for extended periods, making it prone to overheating and even component ablation. This not only affects the combustion chamber's lifespan but also prevents the gas turbine from functioning properly.

[0003] To ensure the combustion chamber operates normally under various conditions, structural design is necessary to address factors affecting its operation. The combustion chamber head and flame tube are susceptible to erosion from high-temperature combustion gases during use; therefore, the design and protection of these two components are particularly important. Currently, combustion chamber erosion can be prevented through proper fuel and air distribution. Furthermore, combustion within the combustion chamber is a dynamic process, meaning it changes with temperature, pressure, and fuel concentration. Existing combustion chamber structures often have poor fuel premixing at the inlet, leading to incomplete combustion, which can result in flameout, head backfire, and excessive NOx emissions in severe cases.

[0004] The above content is only used to help understand the technical solution of the present invention and does not represent an admission that the above content is the closest prior art. Summary of the Invention

[0005] The purpose of this invention is to overcome the above-mentioned shortcomings and provide a layout structure for a gas turbine combustion chamber.

[0006] To solve the above-mentioned technical problems, the present invention adopts the following technical solution: a gas turbine combustion chamber layout structure, including an intake section, wherein a combustion section consisting of a combustion zone, a transition zone and a turbine zone is arranged on the intake section, and five sets of burners are uniformly arranged in the intake section along the circumferential direction. Each burner includes an outer shell, a middle shell and an inner shell arranged coaxially and nested in sequence, and a head vortex for uniformly mixing air and fuel is provided at the outlet end of the middle shell.

[0007] The first guide vane is disposed at the air inlet end of the outer shell and located between the outer shell and the middle shell;

[0008] The second guide vane is disposed between the middle shell and the inner shell and is of the same length as the inner shell;

[0009] A swirl assembly, swirlingly mounted on the middle shell, is used to mix air and fuel entering the burner;

[0010] An assembly mechanism is provided on the middle shell at one end near the head cyclone, for mounting the head cyclone.

[0011] Furthermore, the swirl assembly includes a rotating ring that is swirled on the outer support surface of the middle shell, and several swirl blades are uniformly arranged on the rotating ring along the circumferential direction.

[0012] Furthermore, an annular air inlet for introducing air into the interior of the middle shell is provided on the middle shell and on the outlet side of the swirl blade.

[0013] Furthermore, the assembly mechanism includes a support groove that is rotatably disposed at the end of the middle shell and an internal gear ring disposed on the inner circumferential surface of the support groove. The meshing surface of the internal gear ring is evenly provided with four gears for transmitting force. A rack that is horizontally guided on the support groove is meshed on one side of each gear. A positioning pin for pin-fixing the head cyclone separator is fixed to the head of the rack.

[0014] One of the four gears has an electric drive at the center of its end face.

[0015] Furthermore, the center of the support groove is provided with a connecting section for allowing the mixed air and fuel to enter the head cyclone.

[0016] Furthermore, several of the swirl blades are provided with connecting components on the outlet side for linkage with the assembly mechanism;

[0017] The connecting assembly includes a fixing ring disposed on the air outlet surface of several evenly distributed swirl blades, and several connecting rods for connecting the support groove are evenly disposed on the side of the fixing ring near the assembly mechanism.

[0018] Furthermore, the center line of the positioning pin points radially toward the center of the head cyclone separator.

[0019] Compared with existing technologies, the present invention has the following beneficial effects: Through the configuration of the head cyclone separator, the first guide vane, the second guide vane, and the cyclone assembly, the present invention, in conjunction with these structures, can promote the mixing of different components between air and fuel gas flow, improve reaction efficiency, increase gas uniformity, effectively reduce dead zones in the gas flow, making the gas flow more uniform throughout the system, avoiding local accumulation or stagnation, optimizing the fluid entry direction, enhancing the fluid rotation effect, and guiding the cyclone fluid to smoothly exit and maintain a certain flow velocity, achieving various combustion structures such as diffusion, diffusion + premixing, and premixing, thereby enabling controllable air organization and fuel distribution for each burner. Furthermore, the assembly mechanism allows for convenient assembly and combination of the head cyclone separator, facilitating later maintenance and simplifying operation. Additionally, the connecting component between the cyclone assembly and the assembly mechanism, when the airflow drives the cyclone assembly to rotate, transmits force through the connecting component to drive the head cyclone separator mounted on the assembly mechanism to rotate, increasing the vortex effect of the head cyclone separator and further preventing particulate matter in the fluid from depositing on the inner wall of the equipment, thus helping to maintain the normal operation of the equipment. Attached Figure Description

[0020] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0021] Figure 1 This is a cross-sectional perspective view of an embodiment of the present invention;

[0022] Figure 2 This is a side view of the overall structure according to an embodiment of the present invention;

[0023] Figure 3 This is a perspective cross-sectional view of a single burner according to an embodiment of the present invention.

[0024] Figure 4 This is a three-dimensional cross-sectional view of a single burner according to an embodiment of the present invention.

[0025] Figure 5 This is a perspective cross-sectional view of a single burner without a head cyclone separator, according to an embodiment of the present invention.

[0026] Figure 6 for Figure 5 Enlarged structural diagram at point A in the middle;

[0027] Figure 7 This is a schematic diagram of the medium flow in a single burner according to an embodiment of the present invention.

[0028] In the diagram: 1. Inlet section; 2. Combustion section; 3. Burner; 31. Outer shell; 32. Middle shell; 321. Annular air inlet; 33. Inner shell; 34. Head swirler; 35. First guide vane; 36. Second guide vane; 37. Swirl assembly; 371. Rotary ring; 372. Swirl vane; 38. Assembly mechanism; 381. Support groove; 382. Internal gear ring; 383. Gear; 384. Rack; 385. Positioning pin; 386. Connecting section; 39. Connecting assembly; 391. Fixing ring; 392. Connecting rod. Detailed Implementation

[0029] The technical solutions in the embodiments of the present invention will be clearly and completely described below. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. Unless otherwise specified, the embodiments and features in the embodiments of this application can be combined with each other. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0030] It should be noted that if the embodiments of the present invention involve directional indications (such as up, down, left, right, front, back, etc.), the directional indications are only used to explain the relative positional relationship and movement of the components in a specific posture. If the specific posture changes, the directional indications will also change accordingly.

[0031] Furthermore, if the embodiments of this invention involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the meaning of "and / or" throughout the text includes three parallel solutions; for example, "A and / or B" includes solution A, solution B, or a solution where both A and B are satisfied simultaneously. Furthermore, "multiple" refers to two or more. Moreover, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this invention.

[0032] like Figure 1-7As shown, the present invention discloses a combustion chamber layout structure applied to a gas turbine, including an intake section 1. The intake section 1 is provided with a combustion section 2 consisting of a combustion zone, a transition zone, and a turbine zone arranged in sequence. Five sets of burners 3 are uniformly arranged in the intake section 1 along the circumferential direction. Each burner 3 includes an outer shell 31, a middle shell 32, and an inner shell 33 arranged coaxially and nested in sequence. The outlet end of the middle shell 32 is provided with a head vortex 34 for uniformly mixing air and fuel.

[0033] The first guide vane 35 is disposed at the air inlet end of the outer shell 31 and located between the outer shell 31 and the middle shell 32;

[0034] The second guide vane 36 is disposed between the middle shell 32 and the inner shell 33 and is of the same length as the inner shell 33;

[0035] The swirl assembly 37 is swirled on the middle shell 32 and is used to mix the air and fuel entering the burner 3;

[0036] An assembly mechanism 38 is disposed on the middle shell 32 at one end near the head cyclone separator 34, for mounting the head cyclone separator 34.

[0037] In specific implementation, five sets of burners 3, evenly and circumferentially installed in the front inner cavity of the combustion chamber integrally formed by the intake section 1 and the combustion section 2, can disperse the air and fuel flow entering the combustion chamber. Inside the five sets of burners 3, a first guide vane 35, welded between the outer shell 31 and the middle shell 32 and located at the air intake of the outer shell 31, increases the uniformity of the incoming airflow, achieving an air diffusion effect. A second guide vane 36, welded between the middle shell 32 and the inner shell 33, ensures that the incoming fuel flow is evenly dispersed within the middle shell 32, similarly achieving an air diffusion effect. When the air entering through the first guide vane 35... The blade structure of the swirl assembly 37, in conjunction with the blade structure of the swirl assembly 37, drives the swirl assembly 37, which is rotatably mounted on the outer support surface of the middle shell 32, to rotate, balancing the movement of the airflow. This airflow mixes and reacts with the fuel airflow that enters through the second guide vane 36, thereby achieving a diffusion + premixing effect. Finally, the head swirl 34, which is conveniently assembled through the assembly mechanism 38, utilizes the internal structure of the head swirl 34 to achieve full premixing of the air-fuel airflow after uniform reaction. This ensures that the air and fuel react fully before entering the combustion zone on the combustion section 2. The mixed gas will enter the combustion zone from inside the five sets of burners 3 for combustion, and after being exhausted through the transition zone, it will enter the turbine zone to perform work before entering the waste heat boiler.

[0038] It should be noted that the cross-sections of the first guide vane 35 and the second guide vane 36 are both vortex structures. Vortex flow can effectively reduce dead zones in the airflow, making the airflow more uniform throughout the system and avoiding local accumulation or stagnation.

[0039] It should be noted that the internal structure of the head cyclone separator 34 is a spiral channel structure, which helps to balance the movement of the fluid, reduce eddies and unstable areas, and make the flow smoother.

[0040] It should be noted that air can be introduced into the inner shell 33.

[0041] In one embodiment, the swirl assembly 37 includes a rotating ring 371 rotatably disposed on the outer support surface of the middle shell 32, and a plurality of swirl blades 372 uniformly disposed on the rotating ring 371 along the circumferential direction. This design, through the annular guide rail grooves installed on both sides of a machined groove on the middle shell 32 and the annular guide rails on both sides of the rotating ring 371 that cooperate with the annular guide rail grooves, allows the swirl blades 372 uniformly welded circumferentially on the outer surface of the rotating ring 371 to rotate on the outer support surface of the middle shell 32 under air disturbance. This effectively increases the uniformity of airflow between the outer shell 31 and the middle shell 32 inside the burner 3, allowing the air that is uniformly diffused into the burner through the first guide vane 35 to pass through.

[0042] In one embodiment, an annular air inlet 321 for introducing air into the interior of the middle shell 32 is provided on the middle shell 32 and on the outlet side of the swirl vane 372. This design allows the air forming a swirling flow to enter the interior of the middle shell 32 through the annular air inlet 321, which is machined through the middle shell 32 adjacent to the swirl vane 372 and away from the first guide vane 35, achieving a premixing effect with the fuel airflow uniformly diffused by the second guide vane 36.

[0043] In one embodiment, the device includes a support groove 381 rotatably disposed at the end of the middle shell 32, an internal gear ring 382 disposed on the inner circumferential surface of the support groove 381, four gears 383 for transmitting force are evenly disposed on the meshing surface of the internal gear ring 382, ​​and a rack 384 horizontally guided on the support groove 381 meshes with one side of each gear 383, and a positioning pin 385 for pin-fixing connection of the head cyclone separator 34 is fixed to the head of the rack 384.

[0044] One of the four gears 383 has an electric drive at its end face center. This design, using a support groove 381 connected to the end of the middle shell 32 by an annular guide rail and an annular guide rail groove, and an internal gear ring 382 rotatably connected to the inner circumferential surface of the support groove 381, allows one of the four gears 383, whose meshing surfaces are evenly distributed, to engage with a corresponding rack 384 when driven. This causes the positioning pin 385 welded to the head of the rack 384 to move inward along the radial line. Simultaneously, the internal gear ring 382, ​​connected to the external teeth of the gear 383, rotates synchronously, transmitting force to the remaining three gears 383. This causes the racks 384 correspondingly meshing on the sides of the remaining three gears 383 to move inward synchronously along the radial line. Consequently, the positioning pins 385 welded to the heads of the remaining three racks 384 are simultaneously inserted and fixed to the head cyclone separator 34, achieving convenient assembly of the head cyclone separator 34. The operation is simple and quick.

[0045] It should be noted that a motor is mounted on the center of the end face of one of the four gears 383 to provide initial power to the head cyclone separator 34 of the assembly mechanism 38.

[0046] In one embodiment, the support groove 381 has a connecting section 386 at its center for allowing the mixed air and fuel to enter the head cyclone separator 34. This design, through the connecting section 386 machined at the center of the support groove 381, allows the air-fuel gas flow, premixed by the cyclone assembly 37, to smoothly enter the head cyclone separator 34 for further mixing.

[0047] In one embodiment, a connecting component 39 for linkage use of the assembly mechanism 38 is provided on the outlet side of several of the swirl blades 372;

[0048] The connecting assembly 39 includes a fixing ring 391 disposed on the outlet surface of several evenly distributed swirl blades 372. Several connecting rods 392 for connecting the support groove 381 are evenly disposed on the side of the fixing ring 391 near the assembly mechanism 38. This design, by welding the fixing ring 391 to one side of the several swirl blades 372 and the several connecting rods 392 evenly welded circumferentially to the fixing ring 391, and welding the other ends of the connecting rods 392 to the outer surface of the support groove 381, ensures that the head swirler 34 fixedly assembled within the support groove 381 rotates synchronously with the rotation of the swirl assembly 37. This increases the vortex effect of the head swirler 34, further preventing particulate matter in the fluid from depositing on the inner wall of the equipment, and helps maintain the normal operation of the equipment.

[0049] In one embodiment, the centerline of the positioning pin 385 points radially toward the center of the head hydrocyclone 34. This design ensures that the head hydrocyclone 34, fixed in the support groove 381, experiences uniform force on its outer periphery, resulting in a good clamping effect.

[0050] It should be noted that the mounting part of the head cyclone separator 34 has four positioning holes that are uniformly machined around its perimeter and are used to mate with the positioning pins 385.

[0051] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within the present invention.

Claims

1. A gas turbine combustion chamber layout structure, comprising an intake section (1), wherein a combustion section (2) consisting of a combustion zone, a transition zone, and a turbine zone is arranged on the intake section (1), and five sets of burners (3) are uniformly arranged circumferentially within the intake section (1), characterized in that: The burner (3) includes an outer shell (31), a middle shell (32) and an inner shell (33) arranged in sequence and coaxially. The outlet end of the middle shell (32) is provided with a head cyclone separator (34) for uniformly mixing air and fuel. The first guide vane (35) is disposed at the air inlet end of the outer shell (31) and located between the outer shell (31) and the middle shell (32); The second guide vane (36) is disposed between the middle shell (32) and the inner shell (33) and is of the same length as the inner shell (33); A swirl assembly (37) is swirled on the middle shell (32) for mixing air and fuel entering the burner (3). The swirl assembly (37) includes a rotating ring (371) swirled on the outer support surface of the middle shell (32). Several swirl blades (372) are uniformly arranged on the rotating ring (371) along the circumferential direction. An assembly mechanism (38) is provided on the middle shell (32) near one end of the head cyclone separator (34) for installing the head cyclone separator (34). The assembly mechanism (38) includes a support groove (381) that is rotated at the end of the middle shell (32) and an internal gear ring (382) provided on the inner circumferential surface of the support groove (381). The meshing surface of the internal gear ring (382) is evenly provided with four gears (383) for transmitting force. A rack (384) that is horizontally guided on the support groove (381) meshes with one side of a single gear (383). The head of the rack (384) is fixed with a positioning pin (385) for pin-fixed connection to the head cyclone separator (34). One of the four gears (383) is provided with an electric drive at the center of its end face. The center of the support groove (381) is provided with a connecting section (386) for allowing the mixed air and fuel to enter the head cyclone (34). A connecting assembly (39) for linkage with the assembly mechanism (38) is provided on the air outlet side of several swirl blades (372). The connecting assembly (39) includes a fixing ring (391) disposed on the air outlet surface of several evenly distributed swirl blades (372). Several connecting rods (392) for connecting the support groove (381) are evenly disposed on the side of the fixing ring (391) near the assembly mechanism (38).

2. The layout structure of a gas turbine combustion chamber according to claim 1, characterized in that: An annular air inlet (321) for introducing air into the interior of the middle shell (32) is provided on the middle shell (32) and on the outlet side of the swirl blade (372).

3. The layout structure of a gas turbine combustion chamber according to claim 1, characterized in that: The centerline of the positioning pin (385) points radially toward the center of the head vortex (34).

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