Radial zoned combined combustor

Abstract

A radial partition type combined combustion chamber belongs to the technical field of combustion and aerodynamics of aero-engines and gas turbines. The existing gas-liquid dual-fuel combustion chamber adopts circumferential interval partition combustion, and the problems of local turbine air inlet, uneven turbine air inlet and low turbine efficiency are solved. The gas fuel distribution cavity and the second air distribution cavity are sequentially arranged in the radial direction of the combustion chamber between the cover plate assembly and the fuel pipe locator from outside to inside, the first gas separation plate is arranged in the inner part of the flame tube, the second gas separation plate is arranged between the turbine first stage static blades in the circumferential direction, and the first gas separation plate and the second gas separation plate are fixedly connected. By sequentially arranging the gas fuel distribution cavity and the second air distribution cavity in the radial direction of the combustion chamber from outside to inside, and arranging the first gas separation plate and the second gas separation plate, radial partition is realized, and gas-liquid dual-fuel combined combustion and partition combustion can be realized in one combustion chamber structure.

Description

Technical Field

[0001] This invention relates to a radially partitioned combined combustion chamber, belonging to the field of combustion and aerodynamic technology for aero engines and gas turbines. Background Technology

[0002] Gas turbines are widely used in aviation, aerospace, shipbuilding, power generation, natural gas transmission, and industrial drives. With the continuous development of gas turbine technology, the requirements for combustion performance in gas turbine combustors are becoming increasingly stringent. In traditional combustors, gas turbines were originally single-fuel (gas / liquid) systems; now, with upgrades to dual-fuel systems, their fuel applicability has been further broadened.

[0003] Currently, the engineering applications of dual-fuel gas turbines are mainly concentrated in offshore oil and gas development, vehicle-mounted power plants, liquefied natural gas (LNG) ships, and traditional gas turbine applications. Due to their excellent fuel adaptability, dual-fuel gas turbines have become a major development direction for future gas turbines.

[0004] In existing gas-liquid dual-fuel combustion chambers, combustion is generally carried out in a circumferentially spaced partitioned manner (e.g. Figure 12 As shown in the diagram, the nozzles are distributed according to sector, causing the turbine's intake method to change from circumferential intake to localized intake. This leads to uneven turbine intake, a significant reduction in turbine efficiency, biased force on the turbine shaft, and alternating heating and cooling of the turbine blades. Therefore, it is essential to propose a novel combined combustion chamber for gas-liquid dual fuel combustion. Summary of the Invention

[0005] The present invention aims to solve the above-mentioned technical problems and thereby provides a radially partitioned combined combustion chamber.

[0006] The technical solution adopted by the present invention to solve the above-mentioned technical problems is as follows:

[0007] A radially partitioned combined combustion chamber includes a casing and a flame tube. An air intake passage is provided between the inner wall of the casing and the outer wall of the flame tube. Several turbine first-stage stator vanes are arranged at the outlet end of the flame tube.

[0008] It also includes a fuel line positioner, an air distribution plate, a cover plate assembly, several gas fuel igniters, several liquid fuel igniters, several gas fuel nozzles, and several air swirl fuel nozzles. The cover plate assembly, fuel line positioner, and air distribution plate are arranged in parallel from front to back.

[0009] A first air distribution chamber is formed between the fuel line positioner and the air distribution plate, and the intake passage is connected to the first air distribution chamber.

[0010] A gas fuel distribution chamber and a second air distribution chamber are sequentially arranged between the cover plate assembly and the fuel pipe positioner along the radial direction of the combustion chamber from the outside to the inside. The cover plate assembly is correspondingly provided with a gas fuel inlet and an air inlet.

[0011] Several gaseous fuel igniters are arranged circumferentially along the gaseous fuel distribution chamber, and several liquid fuel igniters are arranged circumferentially along the second air distribution chamber. One end of each gaseous fuel igniter and one end of each liquid fuel igniter are inserted into the air distribution plate through a fuel pipe positioner.

[0012] The flame tube is equipped with a first gas separation plate, and a second gas separation plate is provided circumferentially between several turbine first-stage stator blades, with the first gas separation plate and the second gas separation plate being fixedly connected.

[0013] The front parts of several gas fuel nozzles are fixedly mounted on the fuel pipe positioners corresponding to the gas fuel distribution chamber, and the rear parts are inserted into the air distribution plate outside the first gas separation plate.

[0014] The front of several air cyclone fuel nozzles is fixed on the fuel pipe positioner corresponding to the second air distribution chamber, and the rear is fixed on the air distribution plate inside the first gas separator plate. Liquid fuel is introduced into each air cyclone fuel nozzle through an oil pipe.

[0015] Furthermore, the gas fuel distribution chamber includes a main gas fuel outer chamber, a secondary gas fuel chamber, and a main gas fuel inner chamber, which are sequentially separated from the outside to the inside along the radial direction of the combustion chamber. The gas fuel inlet includes a first main gas fuel inlet, a secondary gas fuel inlet, and a second main gas fuel inlet that are correspondingly connected to the main gas fuel outer chamber, the secondary gas fuel chamber, and the main gas fuel inner chamber.

[0016] Furthermore, the air cyclone fuel nozzle includes an air cyclone and a fuel nozzle body coaxially fixed inside the air cyclone, wherein the air cyclone includes a cylinder and a plurality of swirl blades circumferentially fixed between the cylinder and the fuel nozzle body.

[0017] Furthermore, the air distribution plate is provided with a plurality of air distribution holes, and the rear parts of a plurality of gas fuel nozzles are inserted into the plurality of air distribution holes one by one. There is a gap between the rear part of each gas fuel nozzle and its corresponding air distribution hole. The rear part of each gas fuel nozzle is provided with a plurality of fuel outlets along its circumference.

[0018] Furthermore, the cover plate assembly includes first to fourth cover plates, an inner baffle, an outer baffle, and three chamber partition plates. The first to fourth cover plates are all annular plates and are sequentially spliced ​​along the radial direction of the combustion chamber. The inner baffle, the three chamber partition plates, and the outer baffle are all cylindrical structures and are sequentially arranged along the radial direction of the combustion chamber. The inner baffle, the outer baffle, and the three chamber partition plates separate the first to fourth cover plates from the fuel pipe positioner into a main gas fuel outer chamber, a secondary gas fuel chamber, a main gas fuel inner chamber, and a second air distribution chamber.

[0019] Furthermore, the fuel pipe positioner is a circular ring plate, and a number of gas fuel nozzles are distributed in multiple circumferential arrays around the center of the fuel pipe positioner, with the multiple circumferential arrays arranged radially at equal intervals. A number of air cyclone fuel nozzles are distributed in multiple circumferential arrays around the center of the fuel pipe positioner, with the multiple circumferential arrays arranged radially at equal intervals.

[0020] Furthermore, several gas fuel igniters are evenly distributed around the secondary gas fuel chamber; several liquid fuel igniters are evenly distributed around the second air distribution chamber.

[0021] Furthermore, the number of the first main gas fuel inlet, the auxiliary gas fuel inlet, and the second main fuel inlet are all at least two and are evenly distributed along the circumference of their respective chambers.

[0022] Furthermore, the number of primary gas fuel imports, secondary gas fuel imports, and secondary primary fuel imports are all 2 to 6.

[0023] Furthermore, the top of the gas fuel igniter and the top of the liquid fuel igniter are located in the flame tube, respectively.

[0024] Compared with the prior art, the present invention has the following advantages:

[0025] For the outer ring gas fuel section, air enters the first air distribution chamber from the air intake channel in a counter-current manner, cooling the outer wall of the flame tube during the entry process, and then flows through the first air distribution chamber to premix with the gas fuel in the annular gap;

[0026] For the inner fuel section, air enters the air swirl fuel nozzle from the air inlet in a co-current manner through the second air distribution chamber, and liquid fuel enters from the fuel pipe and is injected through the air swirl fuel nozzle, and then enters the flame tube for combustion.

[0027] In this application, the gas fuel distribution chamber and the second air distribution chamber are sequentially separated from the outside to the inside along the radial direction of the combustion chamber. At the same time, a first gas separation plate and a second gas separation plate are provided to achieve radial partitioning. That is, the outer side of the first gas separation plate adopts a gas fuel nozzle and the inner side adopts a liquid fuel nozzle. Thus, gas-liquid dual-fuel combined combustion and partitioned combustion can be realized in one combustion chamber structure.

[0028] In this application, several gaseous fuel igniters, several liquid fuel igniters, several gaseous fuel nozzles, and several air swirl fuel nozzles are all arranged circumferentially. When burning a single gaseous fuel or a single liquid fuel, air or fuel is introduced in the entire circumference. The high-temperature gas mixture generated by the gaseous fuel and the liquid fuel is also separated by a first gas separator plate and a second gas separator plate, achieving radial zoning and better gas-liquid distribution. The turbine is introduced in the entire circumference, ensuring that every turbine blade is blown, effectively guaranteeing the combustion performance of the combustion chamber and the turbine's working efficiency.

[0029] The annular combustion chamber adopts a nozzle circumferential matrix distribution and a technical route of fuel and oxidant premixing under micro-scale conditions, which can improve the degree of fuel and oxidant premixing, further improve the average temperature and temperature ratio at the combustion chamber outlet, and thus reduce NOx emissions.

[0030] This invention features a high degree of structural integration, flexibility, and reliable operation. Different combustion characteristics and operating conditions can be achieved through different nozzle types (such as gaseous fuel nozzles and liquid fuel nozzles), different nozzle arrangement relationships (gase fuel nozzles working, liquid fuel nozzles working, or both gaseous and liquid fuel nozzles working simultaneously), different nozzle size combinations, and different nozzle spacing relationships. Furthermore, it has a wide operating range and strong fuel adaptability, enabling high-efficiency, low-emission combustion of gas-liquid combined fuels. Attached Figure Description

[0031] Figure 1 This is a schematic diagram of the first three-dimensional structure of one sector of a radially partitioned combined combustion chamber according to the present invention;

[0032] Figure 2 This is a schematic diagram of the second three-dimensional structure of one sector of a radially partitioned combined combustion chamber according to the present invention;

[0033] Figure 3 This is a first cross-sectional schematic diagram of a radially partitioned combined combustion chamber according to the present invention;

[0034] Figure 4 This is a second cross-sectional schematic diagram of a radially partitioned combined combustion chamber according to the present invention;

[0035] Figure 5 This is a third cross-sectional schematic diagram of a radially partitioned combined combustion chamber according to the present invention;

[0036] Figure 6 A schematic diagram (partial cross-section) showing the positional relationship between the gas fuel nozzle, air distribution plate, and fuel pipe positioner;

[0037] Figure 7 This is a three-dimensional structural diagram of a gas fuel nozzle;

[0038] Figure 8 This is a half-sectional schematic diagram of a gas fuel nozzle;

[0039] Figure 9 A three-dimensional structural diagram of the fuel nozzle of the air cyclone separator;

[0040] Figure 10 A schematic diagram (partial cross-section) showing the positional relationship between the fuel nozzle, air distribution plate, and fuel pipe positioner of the air swirl diffuser;

[0041] Figure 11 This is a schematic diagram of the oil pipeline distribution;

[0042] Figure 12 This is a schematic diagram showing the distribution of gas and liquid fuels in a gas-liquid dual-fuel combustion chamber in the prior art;

[0043] Figure 13 This is a schematic diagram of the distribution of gas-liquid fuel in a radially partitioned combined combustion chamber according to the present invention.

[0044] In the picture:

[0045] 1. Casing; 1-1. Inner Casing; 1-2. Outer Casing; 2. Flame Tube; 2-1. Inner Wall of Flame Tube; 2-2. Outer Wall of Flame Tube; 3. Intake Passage; 4. First Stage Turbine Stationary Blade; 5. First Stage Turbine Moving Blade; 6. Fuel Pipe Positioner; 7. Air Distribution Plate; 8-1. First Cover Plate; 8-2. Second Cover Plate; 8-3. Third Cover Plate; 8-4. Fourth Cover Plate; 8-5. Inner Baffle; 8-6. Outer Baffle; 8-7. Chamber Divider Plate; 9. Gaseous Fuel Igniter; 10. Liquid Fuel Igniter; 11. Gaseous Fuel Nozzle; 11-1. Fuel Outlet; 11-2. Fuel Inlet; 11-3. Outer Boss; 11-4. Gas nozzle body; 12. Air cyclone fuel nozzle; 12-1. Air cyclone; 12-11. Cylinder; 12-12. Cyclone blades; 12-2. Fuel nozzle body; 13. First air distribution chamber; 14-1. Main gas fuel outer chamber; 14-2. Secondary gas fuel chamber; 14-3. Main gas fuel inner chamber; 15. Second air distribution chamber; 16-1. First main gas fuel inlet; 16-2. Secondary gas fuel inlet; 16-3. Second main gas fuel inlet; 17. Air inlet; 18. First gas separator plate; 19. Second gas separator plate; 20. Oil pipe; 21. Screw. Detailed Implementation

[0046] Specific implementation method one: Combining Figures 1-11 and Figure 13This description of embodiments provides a clear and complete description of the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. 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.

[0047] It should be noted that the descriptions of "front," "rear," "left," "right," "inner," "outer," "left side," "right side," "upper part," "lower part," "top," and "bottom" in this invention are defined based on the orientation or positional relationships shown in the accompanying drawings. They are merely for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the described structure must be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0048] In the description of this invention, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0049] A radially partitioned combined combustion chamber includes a casing 1 and a flame tube 2. An air intake passage 3 is provided between the inner wall of the casing 1 and the outer wall 2-2 of the flame tube. Several turbine first-stage stator vanes 4 are arranged at the outlet end of the flame tube 2.

[0050] It also includes a fuel pipe positioner 6, an air distribution plate 7, a cover plate assembly, several gas fuel igniters 9, several liquid fuel igniters 10, several gas fuel nozzles 11, and several air swirl fuel nozzles 12, wherein the cover plate assembly, fuel pipe positioner 6, and air distribution plate 7 are arranged in parallel from front to back.

[0051] A first air distribution cavity 13 is formed between the fuel pipe positioner 6 and the air distribution plate 7, and the air intake channel 3 is connected to the first air distribution cavity 13.

[0052] A gas fuel distribution chamber and a second air distribution chamber 15 are sequentially arranged between the cover plate assembly and the fuel pipe positioner 6 along the radial direction of the combustion chamber from the outside to the inside. The cover plate assembly is correspondingly provided with a gas fuel inlet and an air inlet 17.

[0053] A plurality of gas fuel igniters 9 are arranged circumferentially along the gas fuel distribution chamber, and a plurality of liquid fuel igniters 10 are arranged circumferentially along the second air distribution chamber 15. One end of each gas fuel igniter 9 and one end of each liquid fuel igniter 10 are inserted into the air distribution plate 7 through the fuel pipe positioner 6.

[0054] The flame tube 2 is internally provided with a first gas separation plate 18, and a second gas separation plate 19 is provided circumferentially between several turbine first-stage stator blades 4, and the first gas separation plate 18 and the second gas separation plate 19 are fixedly connected.

[0055] The front parts of several gas fuel nozzles 11 are fixedly mounted on the fuel pipe positioner 6 corresponding to the gas fuel distribution chamber, and the rear parts are inserted into the air distribution plate 7 outside the first gas separation plate 18.

[0056] The front of several air cyclone fuel nozzles 12 are fixedly mounted on the fuel pipe positioner 6 corresponding to the second air distribution chamber 15, and the rear of each is fixedly mounted on the air distribution plate 7 inside the first gas separation plate 18. Liquid fuel is introduced into each air cyclone fuel nozzle 12 through the oil pipe 20.

[0057] The combustion chamber has an overall annular structure. The casing 1 is located outside the flame tube 2.

[0058] The gas fuel distribution chamber and the second air distribution chamber 15 are not connected to each other. The flame tube 2 is divided into two unconnected combustion zones by the first gas separation plate 18.

[0059] The cover assembly, casing 1, and fuel line positioner 6 are fastened together by a number of screws 21. The screws 21 are evenly distributed around the circumference of the combustion chamber.

[0060] The rear parts of several gas fuel nozzles 11 are evenly distributed on the air distribution plate 7 outside the first gas separation plate 18 to make the high-temperature gas formed in this area more evenly distributed.

[0061] The fuel pipe positioner 6 corresponding to the second air distribution chamber 15 has several first cyclone distribution holes evenly distributed on it for installing the front part of the air cyclone fuel nozzle 12; the air distribution plate 7 inside the first gas separator plate 18 has several second cyclone distribution holes evenly distributed on it for installing the rear part of the air cyclone fuel nozzle 12. Air flows into the air cyclone fuel nozzle 12 from the air inlet 17, and liquid fuel is injected into the air cyclone fuel nozzle 12 through the oil pipe 20 and enters the flame tube 2 for combustion.

[0062] The oil pipe 20 includes a main pipe and several branch pipes, wherein the main pipe is fixedly inserted into the cover plate assembly, and the several branch pipes are distributed in the second air distribution chamber 15 and their outlet ends are connected to the air cyclone fuel nozzle 12 to provide liquid fuel to the air cyclone fuel nozzle 12.

[0063] The cover plate assembly is fitted with several first igniter positioning tubes and several second igniter positioning tubes, which are used to insert gas fuel igniters 9 and liquid fuel igniters 10 respectively.

[0064] In this application, "inner" and "outer" refer to the side facing the central axis of the combustion chamber, with the side facing the central axis being the inner side and the side away from the central axis being the outer side.

[0065] The casing 1 includes an outer casing 1-2 and an inner casing 1-1 arranged coaxially. The flame tube 2 includes an inner wall 2-1 and an outer wall 2-2 arranged coaxially. The air intake channel 3 is opened between the outer casing 1-2 and the outer wall 2-2 of the flame tube, and between the inner casing 1-1 and the inner wall 2-1 of the flame tube.

[0066] The first gas separator 18 and the second gas separator 19 serve as the dividing line, with the portion located outside the two separators being the outer ring and the portion located inside the two separators being the inner ring.

[0067] For the outer ring gas fuel section, air enters the air distribution chamber from the air intake channel 3 in a counter-current manner, cooling the outer wall 2-2 of the flame tube during the entry process, and then flows through the first air distribution chamber 13, where it is premixed with the gas fuel in the annular gap.

[0068] For the inner fuel section, air enters the air swirl fuel nozzle 12 from the air inlet 17 in a co-current manner through the second air distribution chamber, and liquid fuel enters from the oil pipe 20 and is injected through the air swirl fuel nozzle, and then enters the flame tube 2 for combustion.

[0069] In this application, the gas fuel distribution chamber and the second air distribution chamber 15 are sequentially separated from the outside to the inside along the radial direction of the combustion chamber. At the same time, the first gas separation plate 18 and the second gas separation plate 19 are provided to achieve radial partitioning. That is, the outer side of the first gas separation plate 18 adopts the gas fuel nozzle 11 and the inner side adopts the liquid fuel nozzle. Thus, gas-liquid dual fuel combination combustion and partitioned combustion can be realized in one combustion chamber structure.

[0070] In this application, several gaseous fuel igniters 9, several liquid fuel igniters 10, several gaseous fuel nozzles 11, and several air swirl fuel nozzles 12 are all arranged circumferentially. When burning a single gaseous fuel or a single liquid fuel, air or fuel is introduced in the entire circumference. The high-temperature gas generated by the gaseous fuel and the liquid fuel is also separated by the first gas separation plate 18 and the second gas separation plate 19, realizing radial partitioning and better gas-liquid distribution. The turbine is introduced in the entire circumference, ensuring that every turbine blade can be blown, effectively ensuring the combustion performance of the combustion chamber and the working efficiency of the turbine.

[0071] The annular combustion chamber adopts a nozzle circumferential matrix distribution and a technical route of fuel and oxidant premixing under micro-scale conditions, which can improve the degree of fuel and oxidant premixing, further improve the average temperature and temperature ratio at the combustion chamber outlet, and thus reduce NOx emissions.

[0072] This invention features a high degree of structural integration, flexibility, and reliable operation. Different combustion characteristics and operating conditions can be achieved through different nozzle types (such as gaseous fuel nozzle 11 and liquid fuel nozzle 11), different nozzle arrangement relationships (gaseous fuel nozzle 11 working, liquid fuel nozzle working, or both gaseous fuel nozzle 11 and liquid fuel nozzle working simultaneously), different nozzle size combinations, and different nozzle spacing relationships. Furthermore, it has a wide operating range and strong fuel adaptability, enabling high-efficiency, low-emission combustion of gas-liquid combined fuels.

[0073] The gas fuel distribution chamber includes a main gas fuel outer chamber 14-1, a secondary gas fuel chamber 14-2, and a main gas fuel inner chamber 14-3, which are sequentially separated from the outside to the inside along the radial direction of the combustion chamber. The gas fuel inlets include a first main gas fuel inlet 16-1, a secondary gas fuel inlet 16-2, and a second main gas fuel inlet 16-3, which are correspondingly connected to the main gas fuel outer chamber 14-1, the secondary gas fuel chamber 14-2, and the main gas fuel inner chamber 14-3. The main gas fuel outer chamber 14-1, the secondary gas fuel chamber 14-2, and the main gas fuel inner chamber 14-3 are not interconnected.

[0074] The air cyclone fuel nozzle 12 includes an air cyclone 12-1 and a fuel nozzle body 12-2 coaxially fixed inside the air cyclone 12-1. The air cyclone 12-1 includes a cylinder 12-11 and a plurality of swirl blades 12-12 circumferentially fixed between the cylinder 12-11 and the fuel nozzle body 12-2. This design ensures that the swirl blades 12-12 are circumferentially evenly distributed, and each swirl blade 12-12 is obliquely arranged in the same direction, causing the air passing through the air cyclone 12-1 to form a swirling flow, thus improving the mixing of air and fuel. The fuel nozzle body 12-2 can be any existing nozzle capable of spraying liquid fuel, preferably a nozzle with atomizing function to ensure more complete combustion of the liquid fuel. The diameter of the fuel orifice inside the fuel nozzle body 12-2 is preferably 0.2–4 mm. The inner diameter of the swirl blades 12-12 is preferably 20–25 mm, and the outer diameter is preferably 50–70 mm.

[0075] The air distribution plate 7 has several air distribution holes, and the rear ends of several gas fuel nozzles 11 are inserted into the air distribution holes one by one, with a gap between the rear end of each gas fuel nozzle 11 and its corresponding air distribution hole. Each gas fuel nozzle 11 has several fuel outlets 11-1 circumferentially arranged on its rear end. With this design, the gas fuel nozzle 11 is a tubular structure with an open front end and a closed rear end. Each gas fuel nozzle 11 has a fuel inlet hole 11-2 axially arranged inside, and several fuel outlets 11-1 are located near the closed end. The front end of the gas fuel nozzle 11 is machined with an external boss 11-3 for fixing to the fuel pipe positioner 6. The structure of the gas fuel nozzle 11 other than the external boss 11-3 is the gas nozzle body 11-4, and the wall thickness of the gas nozzle body 11-4 is 1-3 mm. The number of fuel outlets 11-1 is preferably 2-10. The diameter of fuel outlet 11-1 is preferably 0.5–2 mm, and the inner diameter of fuel inlet 11-2 is preferably 3–12 mm. The vertical distance between the plane of fuel outlet 11-1 and the front end face of air distribution plate 7 is 10–50 mm, and the vertical distance between the plane of fuel outlet 11-1 and the rear end face of air distribution plate 7 is 9–36 mm. Gaseous fuel enters through fuel inlet 11-2, exits through fuel outlet 11-1, enters air distribution hole, and is premixed with air flowing in the opposite direction from intake channel 3 in an internal cross-jet manner before entering flame tube 2 for combustion, generating high-temperature gas. This gas contacts the turbine first-stage stationary blade 4 located outside the second gas separator plate 19. After being rectified by turbine first-stage stationary blade 4, the high-temperature gas enters turbine first-stage moving blade 5. Fuel pipe positioner 6 has several nozzle distribution holes, and these nozzle distribution holes are arranged one-to-one with several air distribution holes to correspond to the fixed gaseous fuel nozzles 11.

[0076] The cover plate assembly includes first to fourth cover plates, inner baffle 8-5, outer baffle 8-6, and three chamber partition plates 8-7. The first to fourth cover plates are all annular plates and are sequentially spliced ​​along the radial direction of the combustion chamber. The inner baffle 8-5, the three chamber partition plates 8-7, and the outer baffle 8-6 are all cylindrical structures and are sequentially arranged along the radial direction of the combustion chamber. The inner baffle 8-5, the outer baffle 8-6, and the three chamber partition plates 8-7 separate the first to fourth cover plates and the fuel pipe positioner 6 into a main gas fuel outer chamber 14-1, a secondary gas fuel chamber 14-2, a main gas fuel inner chamber 14-3, and a second air distribution chamber 15. With this design, the inner baffle 8-5 is fixed between the inner side of the fourth cover plate 8-4 and the inner side of the fuel pipe positioner 6, and the outer baffle 8-6 is fixed between the outer side of the first cover plate 8-1 and the outer side of the fuel pipe positioner 6. The outer baffle 8-6, the first cover plate 8-1, a chamber partition plate 8-7, and the fuel pipe positioner 6 form the main gas fuel outer cavity 14-1; the second cover plate 8-2, the fuel pipe positioner 6, and two radially adjacent chamber partition plates 8-7 form the secondary gas fuel cavity 14-2; the third cover plate 8-3, the fuel pipe positioner 6, and two radially adjacent chamber partition plates 8-7 form the main gas fuel inner cavity 14-3; and the fourth cover plate 8-4, the fuel pipe positioner 6, the inner baffle 8-5, and an adjacent chamber partition plate 8-7 form the second air distribution cavity 15.

[0077] The fuel pipe positioner 6 is a circular ring plate. A plurality of gas fuel nozzles 11 are arranged in multiple circumferential arrays around the center of the fuel pipe positioner 6, with these arrays arranged radially at equal intervals. Similarly, a plurality of air cyclone fuel nozzles 12 are also arranged in multiple circumferential arrays around the center of the fuel pipe positioner 6, with these arrays also arranged radially at equal intervals. This design effectively improves the uniformity of fuel distribution.

[0078] Several gas fuel igniters 9 are evenly distributed around the secondary gas fuel chamber 14-2; several liquid fuel igniters 10 are evenly distributed around the second air distribution chamber 15.

[0079] The number of the first main gas fuel inlet 16-1, the auxiliary gas fuel inlet 16-2, and the second main gas fuel inlet 16-3 are all at least two, and they are evenly distributed along the circumference of their respective chambers. This design effectively improves the uniformity of fuel distribution along the circumference of the combustion chamber.

[0080] The number of primary gas fuel inlets 16-1, secondary gas fuel inlets 16-2, and secondary gas fuel inlets 16-3 are all between 2 and 6.

[0081] The top of the gas fuel igniter 9 and the top of the liquid fuel igniter 10 are located in the flame tube 2.

[0082] Specific Implementation Method Two: Combining Figures 1-11 and Figure 13 In this embodiment, there are three auxiliary gas fuel inlets, and three primary gas fuel inlets and three secondary gas fuel inlets.

[0083] The fuel orifice diameter inside the fuel nozzle body is 4mm. The inner diameter of the swirl vane is 20mm, and the outer diameter is 64mm.

[0084] The gas nozzle body has a wall thickness of 3mm and six fuel outlets. The fuel outlet diameter is 1mm, and the fuel inlet diameter is 6mm. The vertical distance between the fuel outlet plane and the front face of the air distribution plate is 40mm, and the vertical distance between the fuel outlet plane and the rear face of the air distribution plate is 10mm. The inner diameter of the air distribution hole is 10mm.

[0085] Other components and connections are the same as in Specific Implementation Method 1.

[0086] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A radially partitioned combined combustion chamber, comprising a casing (1) and a flame tube (2), wherein an air intake passage (3) is provided between the inner wall of the casing (1) and the outer wall (2-2) of the flame tube, and a plurality of turbine first-stage stator vanes (4) are arranged at the outlet end of the flame tube (2), characterized in that: It also includes a fuel pipe positioner (6), an air distribution plate (7), a cover plate assembly, several gas fuel igniters (9), several liquid fuel igniters (10), several gas fuel nozzles (11), and several air swirl fuel nozzles (12), wherein the cover plate assembly, the fuel pipe positioner (6), and the air distribution plate (7) are arranged in parallel from front to back. A first air distribution cavity (13) is formed between the fuel pipe positioner (6) and the air distribution plate (7), and the air intake channel (3) is connected to the first air distribution cavity (13). A gas fuel distribution chamber and a second air distribution chamber (15) are sequentially arranged between the cover plate assembly and the fuel pipe positioner (6) along the radial direction of the combustion chamber from the outside to the inside. A gas fuel inlet and an air inlet (17) are correspondingly provided on the cover plate assembly. Several gas fuel igniters (9) are arranged circumferentially along the gas fuel distribution chamber, and several liquid fuel igniters (10) are arranged circumferentially along the second air distribution chamber (15). One end of each gas fuel igniter (9) and one end of each liquid fuel igniter (10) are inserted into the air distribution plate (7) through the fuel pipe positioner (6). The flame tube (2) is internally separated by a first gas separation plate (18), and a second gas separation plate (19) is provided circumferentially between several turbine first-stage stator blades (4), and the first gas separation plate (18) and the second gas separation plate (19) are fixedly connected. The front parts of several gas fuel nozzles (11) are fixed on the fuel pipe positioner (6) corresponding to the gas fuel distribution chamber, and the rear parts are inserted into the air distribution plate (7) outside the first gas separation plate (18). The front of several air cyclone fuel nozzles (12) are fixed on the fuel pipe positioner (6) corresponding to the second air distribution chamber (15), and the rear is fixed on the air distribution plate (7) inside the first gas separation plate (18). Each air cyclone fuel nozzle (12) is supplied with liquid fuel through the oil pipe (20).

2. The radially partitioned combined combustion chamber according to claim 1, characterized in that: The gas fuel distribution chamber includes a main gas fuel outer chamber (14-1), a secondary gas fuel chamber (14-2), and a main gas fuel inner chamber (14-3) arranged sequentially from the outside to the inside along the radial direction of the combustion chamber. The gas fuel inlet includes a first main gas fuel inlet (16-1), a secondary gas fuel inlet (16-2), and a second main gas fuel inlet (16-3) that are correspondingly connected to the main gas fuel outer chamber (14-1), the secondary gas fuel chamber (14-2), and the main gas fuel inner chamber (14-3).

3. The radially partitioned combined combustion chamber according to claim 1, characterized in that: The air swirler fuel nozzle (12) includes an air swirler (12-1) and a fuel nozzle body (12-2) coaxially fixed inside the air swirler (12-1). The air swirler (12-1) includes a cylinder (12-11) and a plurality of swirling blades (12-12) circumferentially fixed between the cylinder (12-11) and the fuel nozzle body (12-2).

4. A radially partitioned combined combustion chamber according to claim 1, characterized in that: The air distribution plate (7) has several air distribution holes, and the rear parts of several gas fuel nozzles (11) are inserted into the several air distribution holes one by one. There is a gap between the rear part of each gas fuel nozzle (11) and its corresponding air distribution hole. The rear part of each gas fuel nozzle (11) has several fuel outlets (11-1) along its circumference.

5. A radially partitioned combined combustion chamber according to claim 2, characterized in that: The cover plate assembly includes a first to a fourth cover plate, an inner baffle (8-5), an outer baffle (8-6), and three chamber partition plates (8-7). The first to fourth cover plates are all annular plates and are sequentially spliced ​​along the radial direction of the combustion chamber. The inner baffle (8-5), the three chamber partition plates (8-7), and the outer baffle (8-6) are all cylindrical structures and are sequentially arranged along the radial direction of the combustion chamber. The inner baffle (8-5), the outer baffle (8-6), and the three chamber partition plates (8-7) separate the first to fourth cover plates from the fuel pipe positioner (6) into a main gas fuel outer chamber (14-1), a secondary gas fuel chamber (14-2), a main gas fuel inner chamber (14-3), and a second air distribution chamber (15).

6. A radially partitioned combined combustion chamber according to claim 1, characterized in that: The fuel pipe positioner (6) is a circular ring plate. Several gas fuel nozzles (11) are arranged in multiple circumferential arrays around the center of the fuel pipe positioner (6), and the multiple circumferential arrays are arranged radially at equal intervals. Several air cyclone fuel nozzles (12) are arranged in multiple circumferential arrays around the center of the fuel pipe positioner (6), and the multiple circumferential arrays are arranged radially at equal intervals.

7. A radially partitioned combined combustion chamber according to claim 2, characterized in that: Several gas fuel igniters (9) are evenly distributed around the secondary gas fuel chamber (14-2); several liquid fuel igniters (10) are evenly distributed around the second air distribution chamber (15).

8. A radially partitioned combined combustion chamber according to claim 2, characterized in that: The number of the first main gas fuel inlet (16-1), the auxiliary gas fuel inlet (16-2), and the second main gas fuel inlet (16-3) are all at least two and are evenly distributed along the circumference of their respective chambers.

9. A radially partitioned combined combustion chamber according to claim 8, characterized in that: The number of primary gas fuel imports (16-1), secondary gas fuel imports (16-2), and secondary gas fuel imports (16-3) are all between 2 and 6.

10. A radially partitioned combined combustion chamber according to claim 1, characterized in that: The top of the gas fuel igniter (9) and the top of the liquid fuel igniter (10) are located in the flame tube (2).

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