Afterburner for jet propulsion units and self-adapting flame holder thereof

Abstract

The application relates to a thrust chamber of a jet propulsion device and an adaptive flame stabilizer thereof. The adaptive flame stabilizer comprises two side plates connected in rotation, an oil injection rod and a linkage mechanism. The oil injection rod is arranged between the two side plates, and a first nozzle is arranged on the oil injection rod. The linkage mechanism comprises an extension assembly and two linkage assemblies. One end of the extension assembly is communicated with the first nozzle, and the other end of the extension assembly is rotatably connected with the two linkage assemblies respectively. The ends of the two linkage assemblies away from the extension assembly are rotatably connected with the two side plates respectively. The adaptive flame stabilizer has a thrust state and a non-thrust state. In the thrust state, the oil injection rod sprays oil to the first nozzle, and the extension assembly is elongated to drive the two side plates to rotate to the side away from each other through the two linkage assemblies respectively. In the non-thrust state, the extension assembly is retracted to drive the two side plates to rotate to the side close to each other through the two linkage assemblies respectively.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of jet propulsion devices, in particular to a thrust chamber of a jet propulsion device and a self-adaptive flame stabilizer thereof. BACKGROUND

[0002] The thrust chamber is a key component in military aeroengines, which aims to support the aircraft to perform short take-off, in-flight maneuvering and supersonic cruise by instantaneously increasing the thrust. In order to achieve these goals, the thrust chamber must have low flow resistance loss and high reliable flame stability, which is the core of the technical development.

[0003] In the related art, the thrust chamber adopts a self-adaptive flame stabilizer with a fixed geometric structure design. Although this design meets the basic functional requirements to some extent, it also has significant limitations. Specifically, this self-adaptive flame stabilizer occupies a large space in the flow passage, which causes the engine to face significant flow resistance loss even when it does not need to work in the thrust mode. This problem not only affects the overall efficiency of the engine, but also limits the further improvement of its performance. SUMMARY

[0004] Therefore, it is necessary to provide a thrust chamber of a jet propulsion device and a self-adaptive flame stabilizer thereof in view of the problem that the self-adaptive flame stabilizer occupies a large space in the flow passage.

[0005] A self-adaptive flame stabilizer is used to be arranged in a thrust chamber, and the self-adaptive flame stabilizer comprises:

[0006] Two side plates connected in rotation;

[0007] An oil injection rod arranged between the two side plates, and a first nozzle is arranged on the oil injection rod;

[0008] A linkage mechanism comprising an extension assembly and two linkage assemblies, one end of the extension assembly is in communication with the first nozzle, the other end of the extension assembly is rotatably connected with the two linkage assemblies respectively, and the ends of the two linkage assemblies away from the extension assembly are rotatably connected with the two side plates respectively;

[0009] The self-adaptive flame stabilizer has a thrust state and a non-thrust state. In the thrust state, the oil injection rod sprays oil to the first nozzle, and the extension assembly is elongated to push the two side plates to rotate to the side away from each other through the two linkage assemblies respectively. In the non-thrust state, the extension assembly is retracted to drive the two side plates to rotate to the side close to each other through the two linkage assemblies respectively.

[0010] In some embodiments, the telescopic assembly comprises a cylinder, a piston arranged in the cylinder, and a piston rod connected to the piston at one end, one end of the cylinder is in communication with the first nozzle, the end of the piston rod away from the piston extends out of the cylinder, and the end of the piston rod extending out of the cylinder is rotatably connected to the two link assemblies.

[0011] In some embodiments, the telescopic assembly comprises an elastic member arranged in the cylinder and abutting against the inner wall of the cylinder at one end and against the piston at the other end.

[0012] In some embodiments, the oil injection rod is provided with a second nozzle, the second nozzle is provided with an injection port for injecting oil into the afterburner, and the second nozzle is arranged apart from the first nozzle along the rotation axis of the two side plates.

[0013] In some embodiments, the link assembly comprises a first link and a second link rotatably connected in sequence, the first link is rotatably connected to the telescopic assembly, and the end of the second link away from the first link is fixedly connected to the side plate.

[0014] An afterburner of a jet propulsion device, comprising a combustion chamber and self-adapting flame stabilizers, a plurality of the self-adapting flame stabilizers are arranged in the combustion chamber; the plurality of self-adapting flame stabilizers are arranged on the same circumference of the combustion chamber, one end of each of the self-adapting flame stabilizers is connected to the side wall of the combustion chamber, and the other end extends along the radial direction of the combustion chamber. In some embodiments,

[0015] In some embodiments, the self-adapting flame stabilizers are divided into first flame stabilizers and second flame stabilizers, the length of the first flame stabilizers is greater than the length of the second flame stabilizers, and the first flame stabilizers and the second flame stabilizers are arranged in sequence and staggered along the circumference of the combustion chamber.

[0016] In some embodiments, the side wall of the combustion chamber comprises a first side wall section and a second side wall section, the inner diameter of the first side wall section is smaller than the inner diameter of the second side wall section, the self-adapting flame stabilizers are arranged on the first side wall section, and the self-adapting flame stabilizers are inclined from the first side wall section toward the second side wall section.

[0017] In some embodiments, the difference between the inner diameter of the first side wall section and the inner diameter of the second side wall section is H, the radius of the second side wall section is R, and H is in the range of 0.01R-0.1R.

[0018] In some embodiments, the angle α between the self-adapting flame stabilizer and the side wall of the combustion chamber is in the range of 30°-80°.

[0019] The afterburner of the jet propulsion device and the adaptive flame stabilizer thereof, the adaptive flame stabilizer is arranged in the afterburner, when the afterburner works, the oil injection rod injects oil into the first nozzle, under the action of oil pressure, the telescopic assembly is elongated, and then the two side plates are pushed to rotate to the side away from each other through the two link assemblies, that is, the V-shaped groove is formed between the first side plate and the second side plate, which is beneficial to stabilize the flame and ensure the stability and reliability of the combustion process. When the afterburner does not need to work, the oil injection rod stops injecting oil, the telescopic assembly is retracted, and then the two side plates are pulled to rotate to the side close to each other through the two link assemblies, so that the two side plates are folded, and then the aerodynamic resistance of the afterburner can be effectively reduced, and the flow resistance loss in the non-afterburning state is reduced. BRIEF DESCRIPTION OF DRAWINGS

[0020] Figure 1 It is a structural schematic view of the adaptive flame stabilizer in an embodiment.

[0021] Figure 2 It is a sectional structural schematic view of the adaptive flame stabilizer in an embodiment.

[0022] Figure 3 It is a structural schematic view of the rotation connection structure of the two side plates in the adaptive flame stabilizer in another embodiment.

[0023] Figure 4 It is a structural schematic view of one of the views of the combustion chamber in an embodiment.

[0024] Figure 5 It is a structural schematic view of another view of the combustion chamber in an embodiment.

[0025] The adaptive flame stabilizer; 11, the first flame stabilizer; 12, the second flame stabilizer; 20, the side wall; 21, the first side wall section; 22, the second side wall section; 100, the side plate; 110, the first side plate; 120, the second side plate; 130, the arc-shaped end; 200, the nozzle; 210, the first nozzle; 220, the second nozzle; 300, the telescopic assembly; 310, the cylinder body; 320, the piston; 330, the elastic member; 400, the fixed support plate; 410, the first plate; 420, the second plate; 500, the oil injection rod; 600, the link assembly; 610, the first link; 620, the second link. DETAILED DESCRIPTION

[0026] In order to make the above objectives, features and advantages of the present application more clear and comprehensible, the specific embodiments of the present application will be described in detail below with reference to the accompanying drawings. In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present application. However, the present application can be practiced in a number of different ways beyond the specific embodiments described herein and with modifications thereof, without departing from the scope of the present application, and it is understood that these specific embodiments are given for purposes of example and exemplary description only and are not presented in a way of limitation to the present application.

[0027] In the description of the present application, it should be understood that, if these terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like appear, these terms indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation to the present application.

[0028] In addition, if these terms "first", "second" appear, these terms are only for the purpose of description, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features referred to. Therefore, the features defined with "first", "second" can explicitly or implicitly include at least one of the features. In the description of the present application, if the term "a plurality of" appears, the meaning of "a plurality of" is at least two, for example, two, three, etc., unless otherwise specifically limited.

[0029] In the present application, unless otherwise specifically defined and limited, if the terms "mounting", "connecting", "connecting", "fixing" and the like appear, these terms should be understood in a broad sense. For example, it can be fixedly connected, or it can be detachably connected, or it can be integrated; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the internal communication of two elements or the interaction relationship between two elements, unless otherwise specifically limited. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0030] In the present application, unless specifically defined otherwise, if there is a description of a first feature on a second feature, or similar descriptions, it can mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, the first feature can be above, above and above, and above the second feature, which can be directly above or obliquely above the first feature, or only means that the horizontal height of the first feature is higher than that of the second feature. The first feature below, below and below the second feature can be directly below or obliquely below the second feature, or only means that the horizontal height of the first feature is less than that of the second feature.

[0031] It should be noted that if an element is referred to as being "fixed" or "set" on another element, it can be directly on the other element or there can be an intermediate element. If an element is considered to be "connected" to another element, it can be directly connected to the other element or there can be an intermediate element. If present, the terms "vertical", "horizontal", "up", "down", "left", "right" and similar expressions used in the present application are only for illustrative purposes and do not mean the only embodiment.

[0032] In combination Figure 1 , Figure 2 And Figure 4 , an embodiment of the present application discloses a self-adaptive flame stabilizer 10 for being arranged in a afterburner, the self-adaptive flame stabilizer 10 comprises two side plates 100 connected in rotation, an oil injection rod 500 and a connecting rod mechanism. The oil injection rod 500 is arranged between the two side plates 100, and the oil injection rod 500 is provided with a first nozzle 210; the connecting rod mechanism comprises an extension assembly 300 and two connecting rod assemblies 600, one end of the extension assembly 300 is communicated with the first nozzle 210, the other end of the extension assembly 300 is rotatably connected with the two connecting rod assemblies 600 respectively, and the ends of the two connecting rod assemblies 600 away from the extension assembly 300 are rotatably connected with the two side plates 100 respectively; the self-adaptive flame stabilizer 10 has a afterburning state and a non-afterburning state, in the afterburning state, the oil injection rod 500 sprays oil to the first nozzle 210, and the extension assembly 300 is elongated to push the two side plates 100 to rotate to a side away from each other through the two connecting rod assemblies 600 respectively; in the non-afterburning state, the extension assembly 300 is retracted to drive the two side plates 100 to rotate to a side close to each other through the two connecting rod assemblies 600 respectively.

[0033] In the embodiment, the two side plates are respectively a first side plate 110 and a second side plate 120. The adaptive flame stabilizer 10 is arranged in the afterburner. When the afterburner works, the oil injection rod 500 injects oil into the first nozzle 210, and the telescopic assembly 300 is extended under the action of oil pressure, and then the two side plates 100 are pushed to rotate to the side away from each other by the two linkage assemblies 600, that is, a V-shaped groove is formed between the first side plate 110 and the second side plate 120, which is beneficial to stabilize the flame and ensure the stability and reliability of the combustion process. When the afterburner does not need to work, the oil injection rod 500 stops injecting oil, the telescopic assembly 300 is retracted, and then the two side plates 100 are pulled to rotate to the side close to each other by the two linkage assemblies 600, so that the two side plates 100 are folded, and the aerodynamic resistance of the afterburner can be effectively reduced, and the flow resistance loss in the non-afterburning state is reduced.

[0034] It should be noted that as long as the extension direction of the telescopic assembly 300 does not coincide with the rotation axis direction of the two side plates 100, the telescopic assembly 300 can drive the corresponding side plate 100 to rotate around the rotation axis when the telescopic assembly 300 is extended. Optionally, the extension direction of the telescopic assembly 300 is perpendicular to the rotation axis. Or the extension direction of the telescopic assembly 300 is perpendicular to the rotation axis and the second direction at the same time, and the second direction is from one side plate 100 to the other side plate 100.

[0035] In some other embodiments, at least a group of oil injection holes are formed in the first nozzle, and the injection direction of the same group of oil injection holes is inclined to one side plate. In the afterburning state, the oil injection nozzle injects oil, so that at least one side plate rotates to the side away from the other side plate; in the non-afterburning state, at least one side plate rotates to the side close to the other side plate under the action of high-speed airflow.

[0036] In some embodiments, the telescopic assembly 300 includes a cylinder body 310, a piston 320 arranged in the cylinder body 310, and a piston rod 340 connected to the piston 320 at one end. One end of the cylinder body 310 is in communication with the first nozzle 210, and the end of the piston rod 340 away from the piston 320 extends out of the cylinder body 310. The end of the piston rod 340 extending out of the cylinder body 310 is rotationally connected to the two linkage assemblies 600 at the same time.

[0037] In the embodiment, in the afterburning state, the first nozzle 210 injects oil, and then pushes the piston 320 to move in the cylinder body 310, so that the piston rod 340 gradually extends out of the cylinder body 310. At this time, the extended piston rod 340 can push the corresponding side plate 100 to rotate to the side away from each other through the linkage assembly 600. In the non-afterburning state, the first nozzle 210 stops injecting oil, and at this time, the two side plates 100 can rotate to the side close to each other under the action of high-speed airflow, and then push the piston rod 340 to retract into the cylinder body 310.

[0038] In some embodiments, the telescopic assembly 300 comprises an elastic member 330, which is arranged in the cylinder 310 and abuts against the inner wall of the cylinder 310 at one end and abuts against the piston 320 at the other end.

[0039] Specifically, the elastic member 330 is sleeved on a section of the piston rod 340 located in the cylinder 310. In the force-adding state, the first nozzle 210 sprays oil, and the piston 320 moves away from the first nozzle 210 in the cylinder 310 to compress the elastic member 330, so that the piston rod 340 gradually extends out of the cylinder 310, and then the elongated piston rod 340 drives the corresponding side plates 100 to rotate away from each other through the connecting rod assembly 600; in the non-force-adding state, the first nozzle 210 stops spraying oil, and at this time the piston rod 340 can be retracted into the cylinder 310 under the elastic force of the elastic member 330, and then the two side plates 100 rotate towards each other.

[0040] In some embodiments, the connecting rod assembly 600 comprises a first connecting rod 610 and a second connecting rod 620 connected in sequence, the first connecting rod 610 is rotationally connected with the piston rod 340, and the second connecting rod 620 is fixedly connected with the side plate 100 at an end away from the first connecting rod 610.

[0041] Specifically, the second connecting rod 620 is a V-shaped structure, that is, the second connecting rod 620 is fixedly connected with the side plate 100 through two connecting points, which can improve the connection stability of the second connecting rod 620 and the side plate 100 and the rotation stability of the side plate 100.

[0042] In some embodiments, the flame-adaptive flame holder 10 comprises a fixed support plate 400 for fixedly connecting with the combustion chamber, the fixed support plate 400 is an arc-shaped structure, and the fixed support plate 400 is rotationally connected with the two side plates 100 at the circumferential two ends.

[0043] Specifically, the two side plates 100 are rotationally connected with the fixed support plate 400 through hinges or shafts.

[0044] In combination Figure 3 In some other embodiments, the fixed support plate 400 comprises a first plate 410 and a second plate 420 arranged at intervals, the first plate 410 and the second plate 420 are coaxially arranged arc-shaped structures, the first plate 410 is located on the inner side of the second plate 420, and the circumferential two ends of the first plate 410 extend out of the second plate 420; the two side plates 100 each have an arc-shaped end 130, and the arc-shaped ends 130 of the two side plates 100 are respectively inserted between the first plate 410 and the second plate 420 from the circumferential two ends of the second plate 420.

[0045] Specifically, the first plate 410 and the second plate 420 can be connected to each other at the circumferential middle parts, and the first plate 410 and the second plate 420 can not be connected to each other at the circumferential end parts, i.e., the fixed support plate 400 is a double-layer structure arc structure connected at the middle part, so that the first side plate 110 and the second side plate 120 can be inserted between the double-layer structure from the circumferential two ends of the double-layer structure, respectively. At the same time, the first plate 410 is located at the inner side of the second plate 420, and the circumferential two ends of the first plate 410 extend to the outside of the second plate 420, so as to facilitate the rotation of the first side plate 110 and the second side plate 120 to the side away from each other or to the side close to each other.

[0046] In some embodiments, the second nozzle 220 is provided with a spray port for spraying oil into the afterburner, and the second nozzle 220 is arranged in the direction of the rotation axis and spaced apart from the first nozzle 210.

[0047] The first nozzle 210 and the second nozzle 220 can be arranged according to actual needs, for example, the number of the first nozzle 210 is two, two first nozzles 210 are arranged at the two ends of the oil injection rod 500 in the first direction, and a plurality of second nozzles 220 are arranged between the two first nozzles 210; or the first nozzle 210 and the second nozzle 220 are arranged alternately; or the number of the first nozzle 210 is three, two first nozzles 210 are arranged at the two ends of the oil injection rod 500 in the first direction, and the third first nozzle 210 is arranged at the middle part of the oil injection rod 500 in the first direction, and at least one second nozzle 220 is arranged between the two adjacent first nozzles 210.

[0048] In some embodiments, the adaptive flame stabilizer 10 comprises a side wall and a stabilizer body, the side wall comprises a first side wall section 21 and a second side wall section 22, the inner diameter of the first side wall section 21 is smaller than the inner diameter of the second side wall section 22, and the stabilizer body is arranged on the first side wall section 21.

[0049] In this embodiment, since the inner diameter of the second side wall section 22 is larger than the inner diameter of the first side wall section 21, a wall surface groove is formed on the side wall of the combustion chamber, a backflow area is forcedly formed in the combustion chamber airflow through the wall surface groove structure, the high-temperature flame is stabilized, and the high-speed airflow is prevented from being blown out; at the same time, the mixing time of fuel and air is prolonged, the turbulent mixing and evaporation are promoted, and the combustion efficiency is improved.

[0050] Specifically, the side wall can be the side wall of the combustion chamber, and the number of the stabilizer body can be multiple, and the multiple stabilizer bodies are arranged on the side wall in sequence along the circumference of the combustion chamber. Each stabilizer body comprises two side plates 100 connected in rotation, an oil injection rod 500, and a connecting rod mechanism.

[0051] In combination with Figure 4 andFigure 5 The embodiment of the present application also discloses a thrust chamber of a jet propulsion device, which comprises a combustion chamber and a plurality of adaptive flame stabilizers 10 arranged in the combustion chamber.

[0052] In the embodiment, the adaptive flame stabilizer 10 has a thrust state and a non-thrust state. In the thrust state, the two side plates 100 are opened, that is, the adaptive flame stabilizer 10 is in a V-shaped structure, at this time, the airflow speed in the thrust chamber is very high, the V-shaped structure helps to form a relatively stable recirculation zone in the airflow, facilitates continuous ignition of fresh combustible mixture in the recirculation zone, prevents the flame from being blown out by the high-speed airflow, and ensures that the thrust combustion can be continuously and stably carried out. In the non-thrust state, the two side plates 100 are folded to be in a rectangular structure or a V-shaped structure with a smaller opening angle, thereby effectively reducing the aerodynamic resistance of the thrust chamber and reducing the flow resistance loss in the non-thrust state.

[0053] In some embodiments, the adaptive flame stabilizer 10 is a linear adaptive flame stabilizer, one end of each linear adaptive flame stabilizer is connected with the side wall 20 of the combustion chamber, and the other end extends along the radial direction of the combustion chamber.

[0054] In the embodiment, on the one hand, one end of the linear adaptive flame stabilizer is connected with the side wall 20 of the combustion chamber, and the other end extends along the radial direction of the combustion chamber, and this structure can provide reliable support for the combustion chamber. When the engine is working, the combustion chamber bears a complex mechanical environment such as high temperature and high pressure, and the linear adaptive flame stabilizer 10 can help to disperse these forces, reduce the deformation and stress concentration of the wall surface of the combustion chamber, thereby enhancing the stability and reliability of the overall structure of the combustion chamber, improving the working safety and service life of the engine.

[0055] In other embodiments, the adaptive flame stabilizer 10 is an arc-shaped adaptive flame stabilizer, a plurality of arc-shaped adaptive flame stabilizers are arranged in a ring structure, and the axis of the ring structure coincides with the axis of the combustion chamber.

[0056] In the embodiment, the arc-shaped adaptive flame stabilizer is distributed in a ring shape around the axis of the combustion chamber, and a continuous stable flame area is formed in the entire combustion chamber, so that the combustion is more uniform, the local overheating or insufficient combustion is avoided, and the overall combustion stability and efficiency of the combustion chamber are improved.

[0057] In other embodiments, the plurality of adaptive flame stabilizers 10 are located on any cross section of the combustion chamber along the axial direction, the plurality of adaptive flame stabilizers 10 are divided into linear adaptive flame stabilizers and arc-shaped adaptive flame stabilizers, the linear adaptive flame stabilizers are located on the outer periphery of the arc-shaped adaptive flame stabilizers, the plurality of arc-shaped adaptive flame stabilizers are arranged in a ring structure, and the axis of the ring structure coincides with the axis of the combustion chamber, one end of each linear adaptive flame stabilizer is connected with the side wall 20 of the combustion chamber, and the other end extends along the radial direction of the combustion chamber to the side close to the ring structure.

[0058] In the present embodiment, the linear adaptive flame stabilizers and the arc-shaped adaptive flame stabilizers are combined, which can make the radial-to-circumferential airflow interact, and this interaction can lead to the formation of a more complex and highly turbulent flow field, which is conducive to the uniform mixing of oil and gas. In addition, in the part where the linear adaptive flame stabilizers and the arc-shaped adaptive flame stabilizers are close to each other, it is beneficial to better promote the growth of flame nuclei, so as to form a plurality of small high-temperature regions in the combustion chamber, which become the core of flame growth and propagation, and can further promote combustion and improve combustion efficiency.

[0059] In some embodiments, the adaptive 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, and the first flame stabilizer 11 and the second flame stabilizer 12 are arranged in turn along the circumferential direction of the combustion chamber.

[0060] In the present embodiment, the first flame stabilizer 11 and the second flame stabilizer 12 both extend along the radial direction of the combustion chamber, and the first flame stabilizer 11 and the second flame stabilizer 12 with different lengths are arranged in turn, which can avoid interference of the first flame stabilizer 11 and the second flame stabilizer 12 close to the center of the combustion chamber, facilitate the first flame stabilizer 11 to extend to the center of the combustion chamber, improve the flame stability of the center of the combustion chamber, improve the fuel utilization rate, and improve the combustion efficiency.

[0061] Further, along the direction from the outer periphery to the center of the combustion chamber, the distance between adjacent two nozzles 200 becomes larger and larger, which is conducive to the uniformity of oil and gas on the entire circumferential surface of the combustion chamber.

[0062] In some embodiments, the side wall 20 of the combustion chamber includes a first side wall section 21 and a second side wall section 22, the inner diameter of the first side wall section 21 is smaller than the inner diameter of the second side wall section 22, the adaptive flame stabilizer 10 is arranged on the first side wall section 21, the rotation axis is inclined from the first side wall section 21 to the second side wall section 22, and the injection direction of the nozzle is toward the second side wall section 22.

[0063] In the embodiment, the inner diameter of the second side wall segment 22 is larger than that of the first side wall segment 21, so that a wall surface groove is formed on the side wall of the combustion chamber, a backflow area is forcedly formed in the combustion chamber airflow through the wall surface groove structure, the high-temperature flame is stabilized, and the flame is prevented from being blown out by the high-speed airflow; at the same time, the mixing time of the fuel and air is prolonged, the turbulent mixing and evaporation are promoted, and the combustion efficiency is improved. The injection direction of the nozzle 200 is perpendicular to the direction of the rotation axis and the extension direction of the oil injection channel 211, that is, when the rotation axis is inclined from the first side wall segment 21 to the second side wall segment 22, that is, the nozzle 200 is inclined to the second side wall segment 22, so that the fuel injection is formed on the second side wall segment 22 to form a vortex, and the oil-gas mixing is further promoted.

[0064] Specifically, the difference between the inner diameter of the first side wall segment 21 and the inner diameter of the second side wall segment 22 is H, the radius of the second side wall segment 22 is R, and the range of H is 0.01R-0.1R. The above relationship between the radius and the difference can adapt to combustion chambers of different sizes and ensure that the combustion chambers of different sizes have good combustion efficiency.

[0065] Specifically, the angle α between the adaptive flame stabilizer 10 and the side wall 20 of the combustion chamber is 30°-80°.

[0066] The technical features of the above-described embodiments can be combined arbitrarily. To make the description concise, all possible combinations of the technical features in the above-described embodiments are not described, however, as long as the combinations of the technical features do not exist contradictory, they should be considered as the scope of the present application.

[0067] The above-described embodiments only express several implementation manners of the present application, the description is more specific and detailed, but it should not be understood as a limitation on the patent application scope. It should be noted that for ordinary skilled in the art, without departing from the concept of the present application, several modifications and improvements can be made, which are all within the protection scope of the present application. Therefore, the patent protection scope of the present application should be subject to the appended claims.

Claims

1. An adaptive flame holder, characterized by, The adaptive flame stabilizer is used for being arranged in a reheat combustor, and comprises: Two side plates connected in rotation; An oil injection rod arranged between the two side plates, and provided with a first nozzle; A linkage mechanism comprising an extension assembly and two linkage assemblies, one end of the extension assembly being communicated with the first nozzle, the other end of the extension assembly being rotatably connected with the two linkage assemblies respectively, and the ends of the two linkage assemblies away from the extension assembly being rotatably connected with the two side plates respectively; The extension assembly comprises a cylinder, a piston arranged in the cylinder, and a piston rod connected with the piston at one end, one end of the cylinder being communicated with the first nozzle, the end of the piston rod away from the piston extending out of the cylinder, and the end of the piston rod extending out of the cylinder being rotatably connected with the two linkage assemblies simultaneously; the extension assembly comprises an elastic member arranged in the cylinder and abutting against the inner wall of the cylinder at one end and the piston at the other end; The adaptive flame stabilizer has a reheat state and a non-reheat state, in the reheat state, the oil injection rod injects oil to the first nozzle, and the piston is pushed to move to make the extension assembly elongate to push the two side plates to rotate to the side away from each other through the two linkage assemblies respectively; in the non-reheat state, the first nozzle stops injecting oil, and the elastic member releases elastic energy to make the extension assembly retract to drive the two side plates to rotate to the side close to each other through the two linkage assemblies respectively.

2. The adaptive flame holder of claim 1, wherein, The oil injection rod is provided with a second nozzle, the second nozzle is provided with an injection port for injecting oil into the reheat combustor, and the second nozzle is arranged in the direction of the rotation axis of the two side plates and spaced apart from the first nozzle.

3. The adaptive flame holder of claim 1, wherein, The linkage assembly comprises a first linkage and a second linkage connected in rotation, the first linkage is rotatably connected with the extension assembly, and the second linkage is fixedly connected with the side plate at the end away from the first linkage.

4. A thrust chamber for a jet propulsion unit, characterized in that The adaptive flame stabilizer comprises a combustor and a plurality of adaptive flame stabilizers according to any one of claims 1-3, and the plurality of adaptive flame stabilizers are arranged in the combustor; The plurality of adaptive flame stabilizers are arranged on the same circumference of the combustor, one end of each adaptive flame stabilizer is connected with the side wall of the combustor, and the other end extends along the radial direction of the combustor.

5. The afterburner of a jet propulsion unit according to claim 4, characterized in that The adaptive flame stabilizer comprises a first flame stabilizer and a second flame stabilizer, the length of the first flame stabilizer is greater than the length of the second flame stabilizer, and the first flame stabilizer and the second flame stabilizer are arranged alternately along the circumference of the combustor.

6. The afterburner of a jet propulsion unit according to claim 4, characterized in that The side wall of the combustor comprises a first side wall section and a second side wall section, the inner diameter of the first side wall section is smaller than the inner diameter of the second side wall section, the adaptive flame stabilizer is arranged on the first side wall section, and the adaptive flame stabilizer is inclined from the first side wall section to the second side wall section.

7. The afterburner of a jet propulsion unit according to claim 6, characterized in that The difference between the inner diameter of the first side wall section and the inner diameter of the second side wall section is H, the radius of the second side wall section is R, and H is in the range of 0.01R-0.1R.

8. The afterburner of a jet propulsion unit according to claim 6, characterized in that An angle a between the self-adapting flame stabilizer and the side wall of the combustion chamber is 30°-80°.

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