Layout structure of combustion chamber of gas turbine

Abstract

The invention relates to the technical field of gas turbine combustion chambers, in particular to a gas turbine combustion chamber layout structure which comprises a gas inlet section, a combustion section is arranged on the gas inlet section, five sets of combustors are arranged in the gas inlet section, and each combustor comprises an outer shell, a middle shell and an inner shell which are sequentially arranged in a sleeving mode and coaxially arranged. A head cyclone is arranged at the air outlet end of the middle shell; a first guide vane; a second guide vane; a rotational flow assembly; and an assembling mechanism. Mixing of different components between air and fuel gas flow can be promoted, the reaction efficiency is improved, the uniformity of gas is improved, dead zones in the gas flow are effectively reduced, the gas flow is more uniform in the whole system, local accumulation or retention is avoided, the inlet direction of fluid can be optimized, the rotation effect of the fluid can be enhanced, and the service life of the fluid is prolonged. And rotational flow fluid is guided to be smoothly discharged, a certain flow speed is maintained, various combustion organizations such as diffusion, diffusion and premixing, premixing and the like are achieved, and therefore air organization and fuel distribution of each combustor are controllable.

Description

Technical Field

[0001] The invention relates to the technical field of gas turbine combustion chambers, and in particular to a layout structure of a gas turbine combustion chamber. Background Art

[0002] The combustion chamber is one of the important components of the gas turbine generator. Its function is to convert the chemical energy in the fuel into heat energy through chemical reaction combustion. There are many factors that affect the working performance of the combustion chamber, including the combustion chamber structure, the properties of the fuel and air, and the air distribution of the combustion chamber. The combustion chamber is in a high temperature and high pressure environment for a long time due to the combustion of the fuel. It is easy to have excessive temperature or even ablation of the combustion chamber components, which not only affects the service life of the combustion chamber, but also makes the gas turbine unable to work normally.

[0003] In order to ensure the normal operation of the combustion chamber under various working conditions, it is necessary to carry out structural design for the factors that affect the operation of the combustion chamber. The head and flame tube of the combustion chamber are easily eroded by high-temperature combustion gas during use. Therefore, the design and protection of these two components are particularly important. At present, the erosion of the combustion chamber can be avoided by the circulation and distribution of fuel and air in the combustion chamber; in addition, the internal combustion of the combustion chamber is a dynamic process when it is working, that is, the combustion inside the combustion chamber will change with factors such as temperature, pressure and the concentration of fuel components. The existing combustion chamber structure has a poor premixing effect on the inlet fuel, which leads to incomplete combustion of the fuel during combustion. In severe cases, it may even cause flameout, head flashback and excessive NOx emissions.

[0004] The above contents are only used to assist in understanding the technical solution of the present invention, and do not constitute an admission that the above contents are the closest prior art. Summary of the invention

[0005] The object of the present invention is to solve the above-mentioned deficiencies and provide a layout structure of a gas turbine combustion chamber.

[0006] In order to solve the above technical problems, the present invention adopts the following technical solutions: a layout structure of a gas turbine combustion chamber, comprising an air intake section, the air intake section is provided with a combustion section composed of a combustion zone, a transition zone and a turbine zone in sequence, five groups of burners distributed along the circumferential direction are evenly arranged in the air intake section, the burner comprises an outer shell, a middle shell and an inner shell which are sequentially sleeved and coaxially arranged, and a head swirler for evenly mixing air and fuel is provided at the air outlet end of the middle shell;

[0007] A first guide vane, arranged at the air inlet end of the outer shell and located between the outer shell and the middle shell;

[0008] A second guide vane is arranged between the middle shell and the inner shell and is arranged with the same length as the inner shell;

[0009] A swirl assembly, swirl-arranged on the middle shell, for mixing air and fuel entering the burner;

[0010] An assembly mechanism is arranged on one end of the middle shell close to the head cyclone and is used for installing the head cyclone.

[0011] Furthermore, the swirl assembly includes a rotating ring rotatably arranged on the outer supporting surface of the middle shell, and a plurality of swirl blades distributed along the circumferential direction are evenly arranged on the rotating ring.

[0012] Furthermore, an annular air port 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] Further, the assembly mechanism includes a support groove rotatably arranged at the end of the middle shell, an inner gear ring arranged on the inner circumference of the support groove, and the meshing surface of the inner gear ring is evenly provided with four gears for transmitting the force, and one side of a single gear is meshed with a rack horizontally guided on the support groove, and the head of the rack is fixed with a positioning pin for fixing the head cyclone with a pin;

[0014] An electric drive is arranged at the center of the end surface of one of the four gears.

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

[0016] Furthermore, a connection assembly for linkage use of the assembly mechanism is provided on the outlet side of the plurality of swirl blades;

[0017] The connection assembly comprises a fixing ring arranged on the outlet surfaces of a plurality of evenly distributed swirl blades, and a plurality of connecting rods for connecting the supporting grooves are evenly arranged on a side of the fixing ring close to the assembly mechanism.

[0018] Furthermore, the center line of the positioning pin points to the center of the head swirler along a radial line.

[0019] Compared with the prior art, the present invention has the following beneficial effects: the head swirler, the first guide vane, the second guide vane and the swirl assembly provided in the present invention can promote the mixing of different components between the air and fuel airflows, improve the reaction efficiency, increase the uniformity of the gas, effectively reduce the dead zone in the airflow, make the airflow more uniform in the whole system, avoid local accumulation or retention, optimize the entry direction of the fluid, enhance the rotation effect of the fluid, and guide the swirl fluid to discharge smoothly and maintain a certain flow rate, so as to realize diffusion, diffusion + premixing, premixing and other combustion organizations, thereby realizing the controllable air organization and fuel distribution of each burner; the assembly mechanism provided can conveniently assemble the combined head swirler, which is convenient for later maintenance and simple to operate; the connecting assembly provided between the swirl assembly and the assembly mechanism can also drive the head swirler assembled on the assembly mechanism to rotate by transmitting the force through the connecting assembly when the swirl assembly is driven to rotate by the airflow, thereby increasing the vortex effect of the head swirler, further preventing the particulate matter in the fluid from being deposited on the inner wall of the equipment, and helping to maintain the normal operation of the equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The drawings constituting a part of the present application are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0021] Figure 1 It is a cross-sectional three-dimensional structural diagram of an overall embodiment of the present invention;

[0022] Figure 2 It is a side plan view of the overall structure of an embodiment of the present invention;

[0023] Figure 3 A perspective sectional structural diagram of a single burner according to an embodiment of the present invention;

[0024] Figure 4 It is a cross-sectional three-dimensional structural diagram of a single burner in one embodiment of the present invention from another perspective;

[0025] Figure 5 A cross-sectional perspective structural diagram of a single burner without a head swirler assembled on an embodiment of the present invention;

[0026] Figure 6 for Figure 5 The enlarged structural diagram at A in the middle;

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

[0028] In the figure: 1, air intake section; 2, combustion section; 3, burner; 31, outer shell; 32, middle shell; 321, annular air port; 33, inner shell; 34, head swirler; 35, first guide vane; 36, second guide vane; 37, swirl assembly; 371, swirl ring; 372, swirl blade; 38, assembly mechanism; 381, support groove; 382, ​​inner ring; 383, gear; 384, rack; 385, positioning pin; 386, connecting section; 39, connecting assembly; 391, fixing ring; 392, connecting rod. DETAILED DESCRIPTION

[0029] The technical solutions in the embodiments of the present invention are described clearly and completely below. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all of the embodiments. In the absence of conflict, the embodiments in this application and the features in the embodiments can be combined with each other. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without creative work belong to 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 position relationship, movement status, etc. between the components in a certain specific posture. If the specific posture changes, the directional indication will also change accordingly.

[0031] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the present invention, the descriptions of "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, the meaning of "and / or" appearing in the full text includes three parallel schemes. Taking "A and / or B" as an example, it includes scheme A, or scheme B, or schemes that A and B meet at the same time. In addition, "multiple" refers to more than two. In addition, the technical solutions between the various embodiments can be combined with each other, but it must be based on the ability of ordinary technicians in this field to implement. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such a combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0032] like Figure 1-7As shown, a combustion chamber layout structure of the present invention is applied to a gas turbine, comprising an air intake section 1, on which a combustion section 2 composed of a combustion zone, a transition zone and a turbine zone is arranged in sequence, and five groups of burners 3 distributed along the circumferential direction are evenly arranged in the air intake section 1, and the burner 3 comprises an outer shell 31, a middle shell 32 and an inner shell 33 which are sequentially sleeved and coaxially arranged, and a head swirler 34 for evenly mixing air and fuel is arranged at the outlet end of the middle shell 32;

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

[0034] A second guide vane 36 is disposed between the middle shell 32 and the inner shell 33 and is equal in length to the inner shell 33;

[0035] A swirl assembly 37, swirl-arranged on the middle shell 32, for mixing the air and fuel entering the burner 3;

[0036] The assembly mechanism 38 is disposed on one end of the middle shell 32 close to the head cyclone 34 and is used for installing the head cyclone 34 .

[0037] In a specific implementation, the five groups of burners 3 are evenly arranged in the front inner cavity of the combustion chamber integrally formed with the air intake section 1 and the combustion section 2 and are installed along the circumferential direction, so that the air and fuel airflow entering the combustion chamber can be dispersed. The first guide vanes 35 welded between the outer shell 31 and the middle shell 32 and located at the air intake part of the outer shell 31 inside the five groups of burners 3 can increase the uniformity of the airflow of the incoming air, thereby achieving the air diffusion effect. The second guide vanes 36 welded between the middle shell 32 and the inner shell 33 can make the incoming fuel airflow evenly dispersed inside the middle shell 32, thereby also achieving the airflow diffusion effect. When the air entering through the first guide vanes 35 mentioned above will Cooperating with the blade structure of the swirl assembly 37, the swirl assembly 37 rotatably installed on the outer support surface of the middle shell 32 is driven to rotate, balance the movement of the airflow, and mix and react with the fuel airflow entering through the second guide blade 36, thereby achieving the diffusion + premixing effect. Finally, the head swirler 34, which is conveniently assembled by the assembly mechanism 38, utilizes the internal structure of the head swirler 34 to achieve sufficient premixing of the air-fuel airflow after uniform reaction, and ensures sufficient reaction of air and fuel before entering the combustion zone on the combustion section 2. The mixed mixture will enter the combustion zone from the inside of the five groups of burners 3 for combustion, and enter the turbine zone through the transition zone exhaust for work, and then enter 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, and the vortex flow can effectively reduce the dead zone in the airflow, making the airflow more uniform in the entire system and avoiding local accumulation or retention.

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

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

[0041] In one embodiment, the swirl assembly 37 includes a rotating ring 371 rotatably arranged on the outer support surface of the middle shell 32, and a plurality of swirl blades 372 evenly arranged along the circumferential direction on the rotating ring 371. With such a design, through the annular guide groove installed on both sides of a groove machined on the middle shell 32 and the annular guide rails on both sides of the rotating ring 371 that match the annular guide groove, the plurality of swirl blades 372 evenly welded along the circumferential direction on the outer surface of the rotating ring 371 are subjected to the disturbance of air, and the swirl assembly 37 composed of the swirl blades 372 and the rotating ring 371 will be driven to rotate on the outer support surface of the middle shell 32, so that the air entering through the first guide vane 35 is evenly diffused between the outer shell 31 and the middle shell 32 inside the burner 3, which effectively increases the uniformity of the airflow.

[0042] In one embodiment, an annular air port 321 for introducing air into the middle shell 32 is provided on the middle shell 32 and on the outlet side of the swirl blade 372. With this design, the annular air port 321 is formed by turning at a location on the middle shell 32 adjacent to the swirl blade 372 and away from the first guide blade 35, so that the air forming a rotating flow can enter the middle shell 32 through the annular air port 321 and achieve a premixing effect with the fuel airflow uniformly diffused by the second guide blade 36.

[0043] In one embodiment, the support groove 381 is rotatably arranged at the end of the middle shell 32, and an inner gear ring 382 is arranged on the inner circumference of the support groove 381. The meshing surface of the inner gear ring 382 is evenly provided with four gears 383 for transmitting the force. One side of each gear 383 is meshed with a rack 384 horizontally guided on the support groove 381. The head of the rack 384 is fixed with a positioning pin 385 for fixing the head cyclone 34 with a latch.

[0044] The center of the end face of one of the four gears 383 is provided with an electric drive. In this design, by using the support groove 381 connected by the annular guide rail and the annular guide rail groove at the end of the middle shell 32, and the inner gear ring 382 connected to the inner circumference of the support groove 381, when one of the four gears 383 evenly distributed on the meshing surface of the inner gear ring 382 is driven, it will mesh with the corresponding rack 384, driving the positioning pin 385 welded on the head of the rack 384 to move inward along the radial line, at this time, the inner gear ring 382 meshed with the outer teeth on the gear 383 will rotate synchronously to transmit the force to the remaining three gears 383 respectively, so that the corresponding meshing racks 384 on the sides of the remaining three gears 383 move inward along the radial line synchronously, and then the positioning pins 385 welded on the heads of the remaining three racks 384 are synchronously plugged and fixed to the head cyclone 34, so as to achieve the effect of convenient assembly of the head cyclone 34, and the operation is simple and fast.

[0045] It should be noted that a motor is installed at the center of the end surface of one of the four gears 383 to provide initial power for the assembly mechanism 38 to combine the head cyclone 34 .

[0046] In one embodiment, a connecting section 386 is provided at the center of the support groove 381 for allowing the mixed air and fuel to enter the head swirler 34. With this design, the connecting section 386 machined at the center of the support groove 381 can allow the air-fuel airflow premixed by the swirling assembly 37 to smoothly enter the head swirler 34 for further mixing reaction.

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

[0048] The connecting assembly 39 includes a fixing ring 391 arranged on the outlet surface of several uniformly distributed swirl blades 372, and several connecting rods 392 for connecting the support groove 381 are uniformly arranged on one side of the fixing ring 391 close to the assembly mechanism 38. In this design, the fixing ring 391 is welded on one side of several swirl blades 372, and several connecting rods 392 are uniformly welded on the fixing ring 391 along the circumferential direction, and the other ends of the several connecting rods 392 are welded to the outer surface of the support groove 381, so that the head swirler 34 fixedly assembled in the support groove 381 will rotate synchronously with the rotation of the swirl assembly 37, thereby increasing the vortex effect of the head swirler 34, further preventing the particulate matter in the fluid from being deposited on the inner wall of the equipment, and helping to maintain the normal operation of the equipment.

[0049] In one embodiment, the center line of the positioning pin 385 points to the center of the head cyclone 34 along the radial line. This design can ensure that the outer periphery of the head cyclone 34 fixed in the support groove 381 is evenly stressed and has a good clamping effect.

[0050] It should be noted that four positioning holes cooperating with the positioning pins 385 are evenly opened through the mounting portion of the head cyclone 34 by turning.

[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 present invention can be implemented in other specific forms without departing from the spirit or essential features of the present invention. Therefore, the embodiments should be considered exemplary and non-restrictive in all respects, and the scope of the present invention is defined by the appended claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims be included in the present invention.

Claims

1. A layout structure of a gas turbine combustion chamber, comprising an air intake section (1), wherein the air intake section (1) is provided with a combustion section (2) which is sequentially composed of a combustion zone, a transition zone and a turbine zone, and wherein five groups of burners (3) are evenly arranged in the air intake section (1) and distributed along the circumferential direction, and characterized in that: The burner (3) comprises an outer shell (31), a middle shell (32) and an inner shell (33) which are sequentially sleeved and coaxially arranged, and a head swirler (34) for uniformly mixing air and fuel is arranged at the gas outlet end of the middle shell (32); A first guide vane (35) is arranged at the air inlet end of the outer shell (31) and is located between the outer shell (31) and the middle shell (32); A second guide vane (36) is arranged between the middle shell (32) and the inner shell (33) and is arranged to be equal in length to the inner shell (33); a swirl assembly (37) swirlably disposed on the middle shell (32) and used for mixing air and fuel entering the burner (3); An assembly mechanism (38) is arranged on one end of the middle shell (32) close to the head cyclone (34) and is used for installing the head cyclone (34).

2. The layout structure of a gas turbine combustion chamber according to claim 1, characterized in that: The swirl assembly (37) comprises a rotating ring (371) rotatably arranged on the outer supporting surface of the middle shell (32), and a plurality of swirl blades (372) distributed along the circumferential direction are evenly arranged on the rotating ring (371).

3. The layout structure of a gas turbine combustion chamber according to claim 2, characterized in that: An annular air port (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).

4. The layout structure of a gas turbine combustion chamber according to claim 2, characterized in that: The assembly mechanism (38) comprises a support groove (381) rotatably arranged at the end of the middle shell (32), an inner gear ring (382) arranged on the inner circumference of the support groove (381), the meshing surface of the inner gear ring (382) being evenly provided with four gears (383) for transmitting force, one side of each gear (383) being meshed with a rack (384) horizontally guided on the support groove (381), and a positioning pin (385) for latching and fixing the head cyclone (34) is fixed to the head of the rack (384); An electric drive is provided at the center of the end surface of one of the four gears (383).

5. The layout structure of a gas turbine combustion chamber according to claim 4, characterized in that: A connecting section (386) for allowing mixed air and fuel to enter the head swirler (34) is provided at the center of the supporting groove (381).

6. The layout structure of a gas turbine combustion chamber according to claim 5, characterized in that: A connecting assembly (39) for linkage with the assembly mechanism (38) is provided on the air outlet side of the plurality of swirl blades (372); The connecting assembly (39) comprises a fixing ring (391) arranged on the outlet surfaces of a plurality of evenly distributed swirl blades (372), and a plurality of connecting rods (392) for connecting the supporting grooves (381) are evenly arranged on a surface of the fixing ring (391) close to the assembly mechanism (38).

7. The layout structure of a gas turbine combustion chamber according to claim 4, characterized in that: The center line of the positioning pin (385) points to the center of the head swirler (34) along a radial line.

Images