Afterburner for jet propulsion units and variable-geometry flameholder thereof

Abstract

The application relates to a variable-geometry sudden-expansion flame stabilizer of a thrust chamber of a jet propulsion device. The variable-geometry sudden-expansion flame stabilizer comprises a first side plate and a second side plate connected in rotation, an oil injection rod and two telescopic assemblies. The oil injection rod is arranged between the first side plate and the second side plate, a plurality of nozzles are arranged on the oil injection rod, at least one nozzle is provided with an oil injection channel extending in a second direction, the two telescopic assemblies are arranged at two ends of the oil injection channel respectively, and the ends, away from the oil injection channel, of the two telescopic assemblies are connected with the first side plate and the second side plate respectively. The variable-geometry sudden-expansion flame stabilizer has a thrust state and a non-thrust state. In the thrust state, the oil injection rod injects oil into the oil injection channel, and the two telescopic assemblies are respectively elongated to sides, away from each other, so that the first side plate and the second side plate are rotated to sides, away from each other. In the non-thrust state, the two telescopic assemblies are retracted so that the first side plate and the second side plate are rotated to sides, close to each other.

Description

Technical Field

[0001] This application relates to the field of jet propulsion technology, and in particular to the afterburner of a jet propulsion device and its variable geometry burst flame stabilizer. Background Technology

[0002] The afterburner is a key component of military aero engines, designed to provide a significant, instantaneous thrust boost to support short takeoff, aerial maneuvering, and supersonic cruise. To achieve these goals, the afterburner must possess low flow drag loss and highly reliable flame stability, which are central to its technological development.

[0003] In related technologies, afterburners employ flame stabilizers with fixed geometric designs. While this design meets basic functional requirements to some extent, it also has significant limitations. Specifically, this flame stabilizer occupies a large space in the flow channel, leading to significant flow resistance losses in the engine even when afterburner operation is not required. This issue not only affects the overall efficiency of the engine but also limits further performance improvements. Summary of the Invention

[0004] Therefore, it is necessary to address the issue of flame stabilizers occupying a large space in the flow channel by providing an afterburner for a jet propulsion device and its variable geometry burst flame stabilizer.

[0005] A variable geometry sudden expansion flame stabilizer, the variable geometry sudden expansion flame stabilizer being disposed within an afterburner chamber, the variable geometry sudden expansion flame stabilizer comprising:

[0006] The first and second side plates are rotatably connected;

[0007] An injection rod is disposed between the first side plate and the second side plate. The injection rod has a plurality of nozzles sequentially opened along a first direction. At least one of the nozzles has an injection channel. The first direction is the direction of the rotation axis of the first side plate and the second side plate.

[0008] Two telescopic components are respectively disposed at both ends of the fuel injection channel along the second direction and are correspondingly connected to both ends of the fuel injection channel. The ends of the two telescopic components away from the fuel injection channel are respectively connected to the first side plate and the second side plate. The second direction is the direction from the first side plate to the second side plate.

[0009] The variable geometry burst flame stabilizer has an applied state and a non-applied state. In the applied state, the fuel injector injects fuel into the fuel injection channel, and the two telescopic components extend to opposite sides, causing the first side plate and the second side plate to rotate to opposite sides. In the non-applied state, the two telescopic components retract, causing the first side plate and the second side plate to rotate to opposite sides.

[0010] In one embodiment, one of the telescopic components includes a first cylinder disposed on the side of the nozzle near the first side plate, a first piston disposed within the first cylinder, and a piston rod of the first piston extending outside the first cylinder to connect with the first side plate.

[0011] Another of the telescopic components includes a second cylinder disposed on the side of the nozzle near the second side plate, a second piston disposed within the second cylinder, and a piston rod of the second piston extending out of the second cylinder to connect with the second side plate;

[0012] The first cylinder and the second cylinder are respectively connected to both ends of the fuel injection channel along the second direction.

[0013] In one embodiment, a first slide rail is provided on the side of the first side plate near the second side plate, the extension direction of the first slide rail is perpendicular to the rotation axis, and the piston rod of the first piston is slidably connected to the first slide rail.

[0014] The second side plate has a second slide rail on the side close to the first side plate. The extension direction of the second slide rail is perpendicular to the rotation axis. The piston rod of the second piston is slidably connected to the second slide rail.

[0015] In one embodiment, the telescopic component includes:

[0016] The first elastic element is sleeved on the piston rod of the first piston, with one end of the first elastic element abutting against the first piston and the other end abutting against the inner wall of the first cylinder.

[0017] The second elastic element is sleeved outside the piston rod of the second piston. One end of the second elastic element abuts against the second piston, and the other end abuts against the inner wall of the second cylinder.

[0018] In one embodiment, the flame stabilizer includes a fixed support plate for connection to the side wall of the combustion chamber, two side plates being rotatably connected to both sides of the fixed support plate along a second direction, the fuel injector rod and the fixed support plate both extending along a first direction, and the fuel injector rod being fixed to the fixed support plate.

[0019] In one embodiment, the fixed support plate includes a first plate and a second plate spaced apart. The first plate and the second plate are both coaxially arranged arc-shaped structures. The first plate is located inside the second plate, and both ends of the first plate extend out of the second plate in the circumferential direction.

[0020] The first side plate and the second side plate each have an arc-shaped end, and the arc-shaped ends of the first side plate and the second side plate are respectively inserted into the space between the first plate and the second plate from both ends of the second plate along the circumferential direction.

[0021] In one embodiment, the plurality of nozzles includes a first nozzle and a second nozzle, the first nozzle having a closed fuel injection channel, and the second nozzle having a first injection port for injecting fuel into the combustion chamber, the first injection port being a centrifugal injection port or a direct injection port.

[0022] In one embodiment, the plurality of nozzles includes a third nozzle, the third nozzle having a second injection port communicating with the fuel injection channel, the injection direction of the second injection port being perpendicular to the extension direction of the fuel injection channel, and the second injection port facing the direction of the high-speed incoming flow, the second injection port being a centrifugal injection port or a direct injection port.

[0023] In one embodiment, the spacing between two adjacent nozzles is 10mm-100mm.

[0024] An afterburner for a jet propulsion device includes a combustion chamber and a variable geometry burst-expansion flame stabilizer. The sidewall of the combustion chamber includes a first sidewall section and a second sidewall section. The inner diameter of the first sidewall section is smaller than the inner diameter of the second sidewall section. The variable geometry burst-expansion flame stabilizer is disposed on the first sidewall section.

[0025] The aforementioned jet propulsion device includes an afterburner and a variable geometry burst flame stabilizer. The variable geometry burst flame stabilizer is located within the afterburner. When the afterburner is operating, the fuel injector injects fuel into the injection channel. Under oil pressure, two telescopic components extend to opposite sides, causing the first and second side plates to rotate in the opposite direction. This forms a V-groove between the first and second side plates, which helps stabilize the flame and ensures the stability and reliability of the combustion process. When the afterburner is not in use, the telescopic components rotate the first and second side plates to the opposite direction, causing them to close together. This effectively reduces the aerodynamic drag of the afterburner and lowers flow resistance losses in the non-afterburning state. Attached Figure Description

[0026] Figure 1 This is a schematic diagram of the structure of a variable geometry sudden expansion flame stabilizer in one embodiment.

[0027] Figure 2 for Figure 1 Schematic diagram of the cross-sectional structure of the variable geometry sudden expansion flame stabilizer.

[0028] Figure 3 This is a schematic diagram of the variable geometry sudden expansion flame stabilizer in another embodiment.

[0029] Figure 4 for Figure 3 Schematic diagram of the cross-sectional structure of the variable geometry sudden expansion flame stabilizer.

[0030] Figure 5 This is a structural schematic diagram of the combustion chamber from one perspective in one embodiment.

[0031] Figure 6 This is a structural schematic diagram of the combustion chamber from another perspective in one embodiment.

[0032] Reference numerals: 10, Variable geometry burst flame stabilizer; 11, First flame stabilizer; 12, Second flame stabilizer; 20, Combustion chamber; 21, First sidewall section; 22, Second sidewall section; 110, First side plate; 111, First slide rail; 120, Second side plate; 121, Second slide rail; 130, Arc-shaped end; 200, Nozzle; 210, First nozzle; 211, Injection channel; 220, Second nozzle; 221, First injection port; 230, Third nozzle; 231, Second injection port; 300, Telescopic assembly; 310, First cylinder; 320, First piston; 330, First elastic element; 350, Second cylinder; 360, Second piston; 370, Second elastic element; 400, Fixed support plate; 410, First plate; 420, Second plate; 500, Injection rod. Detailed Implementation

[0033] To make the above-mentioned objectives, features, and advantages of this application more apparent and understandable, the specific embodiments of this application are described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a thorough understanding of this application. However, this application can be implemented in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of this application. Therefore, this application is not limited to the specific embodiments disclosed below.

[0034] In the description of this application, it should be understood that if terms such as "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential" appear, these terms indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application.

[0035] Furthermore, where the terms "first" and "second" appear, these terms are for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined with "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, where the term "multiple" appears, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0036] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0037] In this application, unless otherwise expressly specified and limited, the use of descriptions such as "above" or "below" the second feature indicates that the first and second features are in direct contact or indirect contact via an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. Similarly, "below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0038] It should be noted that if an element is referred to as being "fixed to" or "set on" another element, it can be directly on the other element or there may be an intervening element. If an element is considered to be "connected to" another element, it can be directly connected to the other element or there may be an intervening element. If so, the terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used in this application are for illustrative purposes only and do not represent the only possible implementation.

[0039] See Figures 1-3 In one embodiment of this application, a variable geometry burst flame stabilizer 10 is disposed within a combustion chamber 20. The variable geometry burst flame stabilizer 10 includes a first side plate 110 and a second side plate 120 rotatably connected, an injection rod 500, and two telescopic assemblies 300. The injection rod 500 is disposed between the first side plate 110 and the second side plate 120, and the injection rod 500 has a plurality of nozzles 200 sequentially arranged along a first direction. At least one nozzle 200 has an injection channel 211 extending along a second direction, which is from the first side plate 110 to the second side plate 120. The two telescopic assemblies 300 are respectively disposed at both ends of the injection channel 211 along the second direction, and the ends of the two telescopic assemblies 300 away from the injection channel 211 are respectively connected to the first side plate 110 and the second side plate 120. The variable geometry burst flame stabilizer 10 has an applied state and a non-applied state. In the applied state, the fuel injection rod 500 injects fuel into the fuel injection channel 211, and the two telescopic components 300 extend to the side away from each other, so that the first side plate 110 and the second side plate 120 rotate to the side away from each other. In the non-applied state, the two telescopic components 300 retract, so that the first side plate 110 and the second side plate 120 rotate to the side closer to each other.

[0040] In this embodiment, the variable geometry burst flame stabilizer 10 is disposed within the afterburner 20. When the afterburner 20 is operating, the fuel injection rod 500 injects fuel into the fuel injection channel 211. Under the action of oil pressure, the two telescopic components 300 extend to opposite sides, causing the first side plate 110 and the second side plate 120 to rotate to opposite sides, forming a V-groove between them. This V-groove helps stabilize the flame and ensures the stability and reliability of the combustion process. When the afterburner 20 is not required to operate, the telescopic components 300 drive the first side plate 110 and the second side plate 120 to rotate to opposite sides, causing them to close together. This effectively reduces the aerodynamic drag of the afterburner 20 and lowers the flow resistance loss in the non-afterburner state.

[0041] In some embodiments, one telescopic assembly 300 includes a first cylinder 310 disposed on the side of the nozzle 200 near the first side plate 110, and a first piston 320 disposed inside the first cylinder 310, with the piston rod of the first piston 320 extending out of the first cylinder 310 to connect with the first side plate 110; the other telescopic assembly 300 includes a second cylinder 350 disposed on the side of the nozzle 200 near the second side plate 120, and a second piston 360 disposed inside the second cylinder 350, with the piston rod of the second piston 360 extending out of the second cylinder 350 to connect with the second side plate 120; the first cylinder 310 and the second cylinder 350 are respectively connected to both ends of the fuel injection channel 211.

[0042] In some embodiments, when the fuel injector 500 supplies fuel to the nozzle 200, the pressure inside the fuel injection channel 211 increases under the action of the fuel pressure. Since the two ends of the fuel injection channel 211 are connected to the first cylinder 310 and the second cylinder 350 respectively, the first piston 320 in the first cylinder 310 can move closer to the first side plate 110 under the action of the fuel pressure. This allows the piston rod of the first piston 320 to push the first side plate 110 to rotate away from the second side plate 120. Similarly, under the action of the fuel pressure, the second piston 360 in the second cylinder 350 can also move closer to the second side plate 120. This allows the piston rod of the second piston 360 to push the second side plate 120 to rotate away from the first side plate 110. When the fuel injector 500 stops supplying fuel to the nozzle 200, the first side plate 110 and the second side plate 120 can rotate towards each other under the action of external airflow, thereby pushing the piston rod of the first piston 320 to retract into the first cylinder 310 and the piston rod of the second piston 360 to retract into the second cylinder 350, respectively.

[0043] In other embodiments, diaphragms may be respectively provided in the first cylinder block 310 and the second cylinder block 350. A push rod is provided at the end of the diaphragm away from the fuel injector, pushing the first side plate 110 and the second side plate 120. Specifically, when the oil pressure in the fuel injection channel 211 increases, the diaphragm deforms, pushing the first side plate 110 and the second side plate 120 through the push rod, causing them to rotate towards each other. When the oil pressure in the fuel injection channel 211 decreases, the diaphragm returns to its original shape, causing the push rod to retract, thus causing the first side plate 110 and the second side plate 120 to rotate towards each other.

[0044] In some embodiments, a first slide rail 111 is provided on the side of the first side plate 110 near the second side plate 120, the extension direction of the first slide rail 111 is perpendicular to the rotation axis, and the piston rod of the first piston 320 is slidably connected to the first slide rail 111; a second slide rail 121 is provided on the side of the second side plate 120 near the first side plate 110, the extension direction of the second slide rail 121 is perpendicular to the rotation axis, and the piston rod of the second piston 360 is slidably connected to the second slide rail 121.

[0045] In some embodiments, when the fuel injector 500 supplies fuel, the piston rod of the first piston 320 extends and slides within the first slide rail 111 towards the side closer to the rotation axis, allowing the first side plate 110 to rotate away from the second side plate 120. Similarly, when the fuel injector 500 supplies fuel, the piston rod of the second piston 360 extends and slides within the second slide rail 121 towards the side closer to the rotation axis, allowing the second side plate 120 to rotate away from the first side plate 110.

[0046] In another embodiment, the piston rod of the first piston 320 can rotate within the first cylinder 310, and the piston rod of the first piston 320 is rotatably connected to the first side plate 110; the piston rod of the second piston 360 can rotate within the second cylinder 350, and the piston rod of the second piston 360 is rotatably connected to the second side plate 120. Similarly, the first side plate 110 and the second side plate 120 can rotate when the fuel injector 500 supplies fuel.

[0047] In some embodiments, the telescopic assembly 300 includes a first elastic member 330 and a second elastic member 370. The first elastic member 330 is sleeved outside the piston rod of the first piston 320, with one end abutting against the first piston 320 and the other end abutting against the inner wall of the first cylinder 310; the second elastic member 370 is sleeved outside the piston rod of the second piston 360, with one end abutting against the second piston 360 and the other end abutting against the inner wall of the second cylinder 350.

[0048] In this embodiment, when the fuel injector 500 supplies fuel, the first piston 320 moves towards the end near the first side plate 110 within the first cylinder 310, compressing the first elastic element 330. Similarly, the second piston 360 moves towards the end near the second side plate 120 within the second cylinder 350, compressing the second elastic element 370. When the fuel injector 500 does not supply fuel, under the elastic force of the first elastic element 330, the first elastic element 330 pushes the first piston 320 towards the end near the nozzle 200, causing the piston rod of the first piston 320 to retract into the first cylinder 310. The second elastic element 370 pushes the second piston 360 towards the end near the nozzle 200, causing the piston rod of the second piston 360 to retract into the second cylinder 350, i.e., the first side plate 110 and the second side plate 120 close together.

[0049] Combination Figure 3 and Figure 4 In some embodiments, the plurality of nozzles 200 includes a first nozzle 210 and a second nozzle 220. The first nozzle 210 has a closed oil injection channel 211, and the second nozzle 220 has a first injection port 221 for injecting oil into the combustion chamber 20. The first injection port 221 is a centrifugal injection port or a direct injection port.

[0050] In this embodiment, the two ends of the fuel injection channel 211 along the second direction are respectively closed by the first piston 320 and the second piston 360. The first nozzle 210 has a closed fuel injection channel 211, and the two ends of the fuel injection channel 211 along the second direction are connected by two telescopic components 300, so that the two telescopic components 300 can respectively push the first side plate 110 and the second side plate 120 to rotate. Due to the closed fuel injection channel 211, the first nozzle 210 cannot be used for fuel injection, but only to provide rotational power for the first side plate 110 and the second side plate 120. The first injection port 221 on the second nozzle 220 injects fuel into the combustion chamber 20.

[0051] The first nozzle 210 and the second nozzle 220 can be arranged according to actual needs. For example, there can be two first nozzles 210, which are respectively located at both ends of the fuel injection rod 500 along the first direction, and multiple second nozzles 220 are arranged between the two first nozzles 210; or the first nozzles 210 and the second nozzles 220 can be arranged alternately; or there can be three first nozzles 210, where two first nozzles 210 are respectively located at both ends of the fuel injection rod 500 along the first direction, and the third first nozzle 210 is located in the middle of the fuel injection rod 500 along the first direction, and at least one second nozzle 220 is arranged between two adjacent first nozzles 210.

[0052] Combination Figure 1 and Figure 2In some embodiments, the plurality of nozzles 200 includes a third nozzle 230, which has a second injection port 231 communicating with the fuel injection channel 211. The injection direction of the second injection port 231 is perpendicular to the extension direction of the fuel injection channel 211, and the second injection port 231 faces the direction of the high-speed incoming flow. Specifically, the second injection port 231 is a centrifugal injection port or a direct injection port.

[0053] In this embodiment, a first piston 320 is provided at one end of the fuel injection channel 211, and a second piston 360 is provided at the other end. The first piston 320 and the second piston 360 respectively block the fuel injection channel 211, allowing fuel to be ejected from the second injection port 231 to achieve afterburning. The second injection port 231 is either a centrifugal injection port or a direct injection port, which not only improves the fuel atomization effect but also promotes a more uniform combustion process.

[0054] In some embodiments, the fuel injector 500 is provided with a plurality of nozzles 200 in sequence along the extension direction of the rotation axis, and the distance between two adjacent nozzles 200 is 10mm-100mm.

[0055] In this embodiment, the fuel injector 500 is provided with multiple nozzles 200, each nozzle 200 being connected to a telescopic assembly 300 to ensure the rotational power of the first side plate 110 and the second side plate 120. Furthermore, the multiple nozzles 200 facilitate uniform mixing of fuel and air, promoting complete combustion. The spacing between two adjacent nozzles 200 is 10mm-100mm. If the spacing is too small, the fuel ratio may be too high, hindering complete combustion; if the spacing is too large, it will impede flame propagation.

[0056] In some embodiments, the variable geometry burst flame stabilizer 10 includes a fixed support plate 400 for connection to the side wall of the combustion chamber 20, with two side plates rotatably connected to opposite sides of the fixed support plate, and an injection rod 500 extending in the same direction as the fixed support plate 400, and the injection rod 500 fixed on the fixed support plate 400.

[0057] In this embodiment, the fixed support plate 400 is used to connect the first side plate 110 and the second side plate 120 to the side wall of the combustion chamber 20 at the same time. The first side plate 110 can be rotatably connected relative to the fixed support plate 400, and the second side plate 120 can be rotatably connected relative to the fixed support plate 400. The fuel injection rod 500 is fixed on the fixed support plate 400, which can achieve a stable connection of the fuel injection rod 500.

[0058] Furthermore, the fixed support plate 400 includes a first plate 410 and a second plate 420 spaced apart. The first plate 410 and the second plate 420 are both coaxially arranged arc-shaped structures. The first plate 410 is located inside the second plate 420, and the two ends of the first plate 410 extend out of the second plate 420 along the circumferential direction. The two side plates each have an arc-shaped end 130, and the arc-shaped ends 130 of the two side plates are respectively inserted from the two ends of the second plate 420 along the circumferential direction between the first plate 410 and the second plate 420.

[0059] Specifically, the middle portions of the first plate 410 and the second plate 420 along the circumferential direction can be connected to each other, while the ends of the first plate 410 and the second plate 420 along the circumferential direction are not connected. That is, the fixed support plate 400 is a double-layered arc-shaped structure with a central connection, allowing the first side plate 110 and the second side plate 120 to be inserted into the double-layered structure from their respective circumferential ends. Simultaneously, the first plate 410 is located inside the second plate 420, with its circumferential ends extending outside the second plate 420, thus allowing the first side plate 110 and the second side plate 120 to rotate towards or away from each other.

[0060] In some other embodiments, the first side plate 110 and the second side plate 120 are rotatably connected by a hinge. The hinge includes a pivot and two blades disposed on the pivot, one blade being connected to the first side plate 110 and the other blade being connected to the second side plate 120.

[0061] In some other embodiments, the first side plate is fixedly connected to the combustion chamber sidewall, and the second side plate is rotatable relative to the first side plate. There is one telescopic assembly connected to the second side plate, used to push the second side plate to rotate relative to the first side plate.

[0062] In some embodiments, the variable geometry burst flame stabilizer 10 includes a sidewall and a stabilizer body. The sidewall includes a first sidewall segment 21 and a second sidewall segment 22. The inner diameter of the first sidewall segment 21 is smaller than the inner diameter of the second sidewall segment 22. The stabilizer body is disposed on the first sidewall segment 21.

[0063] In this embodiment, since the inner diameter of the second sidewall section 22 is larger than the inner diameter of the first sidewall section 21, a wall groove is formed on the sidewall of the combustion chamber 20. The wall groove structure forces a recirculation zone to be formed in the airflow of the combustion chamber, stabilizes the high-temperature flame, and prevents it from being blown out by the high-speed airflow. At the same time, it prolongs the mixing time of fuel and air, promotes turbulent mixing and evaporation, and improves combustion efficiency.

[0064] Specifically, the sidewall can be the sidewall of the combustion chamber, and there can be multiple stabilizer bodies arranged sequentially on the sidewall along the circumference of the combustion chamber. Each stabilizer body includes a first side plate 110 and a second side plate 120 rotatably connected, a fuel injection rod 500, and two telescopic components 300.

[0065] Combination Figure 5 and Figure 6 An embodiment of this application also provides an afterburner 20 for a jet propulsion device, including a combustion chamber 20 and a variable geometry burst flame stabilizer 10. The variable geometry burst flame stabilizer 10 is disposed in the combustion chamber 20, and a plurality of variable geometry burst flame stabilizers 10 are disposed on the same circumference of the combustion chamber 20. One end of each variable geometry burst flame stabilizer 10 is connected to the side wall of the combustion chamber 20, and the other end extends radially along the combustion chamber 20.

[0066] In this embodiment, a ring of variable geometry burst flame stabilizers 10 is arranged around the circumference of the combustion chamber 20, and each variable geometry burst flame stabilizer 10 extends radially along the combustion chamber 20. This increases the disturbance generated by the high-speed incoming flow in both the circumferential and radial directions, enhancing the mixing effect of fuel and air. Moreover, this arrangement is relatively simple and easy to manufacture and install.

[0067] In some embodiments, the variable geometry burst flame stabilizer 10 is divided into a first flame stabilizer 11 and a second flame stabilizer 12. The length of the first flame stabilizer 11 is greater than the length of the second flame stabilizer 12. Along the circumference of the combustion chamber 20, the first flame stabilizer 11 and the second flame stabilizer 12 are arranged alternately.

[0068] In this embodiment, both the first flame stabilizer 11 and the second flame stabilizer 12 extend radially along the combustion chamber 20. The first flame stabilizer 11 and the second flame stabilizer 12, which are of different lengths, are arranged alternately in sequence. This can avoid interference between the first flame stabilizer 11 and the second flame stabilizer 12 at positions close to the center of the combustion chamber 20, and make it easier for the first flame stabilizer 11 to extend into the center of the combustion chamber 20, thereby improving the flame stability at the center of the combustion chamber 20, increasing fuel utilization, and improving combustion efficiency.

[0069] Furthermore, along the direction from the outer periphery to the center of the combustion chamber 20, the distance between two adjacent nozzles 200 increases, which is beneficial to the uniformity of oil and gas on the entire circumferential surface of the combustion chamber 20.

[0070] In some embodiments, the combustion chamber 20 sidewall includes a first sidewall section 21 and a second sidewall section 22, the inner diameter of the first sidewall section 21 being smaller than the inner diameter of the second sidewall section 22, and the variable geometry burst flame stabilizer 10 being disposed on the first sidewall section 21.

[0071] In this embodiment, since the inner diameter of the second sidewall section 22 is larger than the inner diameter of the first sidewall section 21, a wall groove is formed on the sidewall of the combustion chamber 20. The wall groove structure forces a recirculation zone to be formed in the airflow of the combustion chamber, stabilizes the high-temperature flame, and prevents it from being blown out by the high-speed airflow. At the same time, it prolongs the mixing time of fuel and air, promotes turbulent mixing and evaporation, and improves combustion efficiency.

[0072] Furthermore, the axis of rotation is inclined from the first sidewall segment 21 toward the second sidewall segment 22.

[0073] In this embodiment, the injection direction of the nozzle 200 is perpendicular to both the direction of the rotation axis and the extension direction of the fuel injection channel 211. That is, when the rotation axis is inclined from the first sidewall section 21 toward the second sidewall section 22, the nozzle 200 is inclined toward the second sidewall section 22, so that the fuel is injected onto the second sidewall to form a vortex, further promoting fuel-air mixing and stabilizing the flame.

[0074] Specifically, the difference between the inner diameter of the first sidewall section 21 and the inner diameter of the second sidewall section 22 is H, the radius of the second sidewall section 22 is R, and the range of H is 0.01R-0.1R. The relationship between the radius and the difference can accommodate combustion chambers 20 of different sizes, ensuring that combustion chambers 20 of different sizes have good combustion efficiency.

[0075] Specifically, the angle α between the variable geometry burst flame stabilizer 10 and the sidewall of the combustion chamber 20 is 30°-80°.

[0076] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0077] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. A variable geometry sudden-expansion flame stabilizer, characterized in that, The variable geometry sudden expansion flame stabilizer is used in the afterburner chamber and includes: The first and second side plates are rotatably connected; An injection rod is disposed between the first side plate and the second side plate. The injection rod has a plurality of nozzles sequentially opened along a first direction. At least one of the nozzles has an injection channel. The first direction is the direction of the rotation axis of the first side plate and the second side plate. Two telescopic components are respectively disposed at both ends of the fuel injection channel along the second direction and are correspondingly connected to both ends of the fuel injection channel. The ends of the two telescopic components away from the fuel injection channel are respectively connected to the first side plate and the second side plate. The second direction is the direction from the first side plate to the second side plate. The variable geometry burst flame stabilizer has an applied state and a non-applied state. In the applied state, the fuel injector injects fuel into the fuel injection channel, and the two telescopic components extend to opposite sides, causing the first side plate and the second side plate to rotate to opposite sides. In the non-applied state, the two telescopic components retract, causing the first side plate and the second side plate to rotate to opposite sides.

2. The variable geometry sudden expansion flame stabilizer according to claim 1, characterized in that, One of the telescopic components includes a first cylinder body disposed on the side of the nozzle near the first side plate, a first piston disposed inside the first cylinder body, and the piston rod of the first piston extending outside the first cylinder body to connect with the first side plate. Another of the telescopic components includes a second cylinder disposed on the side of the nozzle near the second side plate, a second piston disposed within the second cylinder, and a piston rod of the second piston extending out of the second cylinder to connect with the second side plate; The first cylinder and the second cylinder are respectively connected to both ends of the fuel injection channel along the second direction.

3. The variable geometry sudden expansion flame stabilizer according to claim 2, characterized in that, A first slide rail is provided on the side of the first side plate near the second side plate. The extension direction of the first slide rail is perpendicular to the rotation axis. The piston rod of the first piston is slidably connected to the first slide rail. The second side plate has a second slide rail on the side close to the first side plate. The extension direction of the second slide rail is perpendicular to the rotation axis. The piston rod of the second piston is slidably connected to the second slide rail.

4. The variable geometry sudden expansion flame stabilizer according to claim 2, characterized in that, The telescopic component includes: The first elastic element is sleeved on the piston rod of the first piston, with one end of the first elastic element abutting against the first piston and the other end abutting against the inner wall of the first cylinder. The second elastic element is sleeved outside the piston rod of the second piston. One end of the second elastic element abuts against the second piston, and the other end abuts against the inner wall of the second cylinder.

5. The variable geometry sudden expansion flame stabilizer according to claim 4, characterized in that, The flame stabilizer includes a fixed support plate for connecting to the side wall of the combustion chamber. The first side plate and the second side plate are rotatably connected to both sides of the fixed support plate along a second direction. The fuel injector rod and the fixed support plate both extend along a first direction, and the fuel injector rod is fixed to the fixed support plate.

6. The variable geometry sudden expansion flame stabilizer according to claim 5, characterized in that, The fixed support plate includes a first plate and a second plate arranged at intervals. The first plate and the second plate are both coaxial arc-shaped structures. The first plate is located inside the second plate, and both ends of the first plate extend out of the second plate in the circumferential direction. The first side plate and the second side plate each have an arc-shaped end, and the arc-shaped ends of the first side plate and the second side plate are respectively inserted into the space between the first plate and the second plate from both ends of the second plate along the circumferential direction.

7. The variable geometry sudden expansion flame stabilizer according to claim 1, characterized in that, The plurality of nozzles include a first nozzle and a second nozzle. The first nozzle has a closed fuel injection channel, and the second nozzle has a first injection port for injecting fuel into the combustion chamber. The first injection port is a centrifugal injection port or a direct injection port.

8. The variable geometry sudden expansion flame stabilizer according to claim 1, characterized in that, The plurality of nozzles includes a third nozzle, wherein a second injection port is provided in the third nozzle and communicates with the fuel injection channel. The injection direction of the second injection port is perpendicular to the extension direction of the fuel injection channel and the second injection port faces the direction of the high-speed incoming flow. The second injection port is a centrifugal injection port or a direct injection port.

9. The variable geometry sudden expansion flame stabilizer according to claim 1, characterized in that, The distance between two adjacent nozzles is 10mm-100mm.

10. An afterburner chamber for a jet propulsion device, characterized in that, The device includes a combustion chamber and a variable geometry burst-expansion flame stabilizer as described in any one of claims 1-9. The sidewall of the combustion chamber includes a first sidewall section and a second sidewall section. The inner diameter of the first sidewall section is smaller than the inner diameter of the second sidewall section. The variable geometry burst-expansion flame stabilizer is disposed on the first sidewall section.

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