Multi-channel rich-burn gas panel stabilizer suitable for wide speed range combined power

Abstract

The present application relates to a kind of multi-channel rich combustion gas branch plate flame holder suitable for wide speed range combined power, belong to wide range combined engine technical field, including the branch plate being connected in the flow passage of combustion chamber, air flows through the two sides of branch plate, mixing component is set on branch plate, mixing component includes rich combustion gas passage, is set in the two sides of branch plate, the inside of branch plate is hollow and is communicated with rich combustion gas passage, the inside of branch plate is communicated with the output port of rocket engine, two stops are respectively set the two sides of branch plate, stop and branch plate abut, drive mechanism is set on branch plate, the output end of drive mechanism is connected with stop, the rich combustion gas passage of the branch plate in flow passage and mixing component, stop and drive mechanism are used in cooperation, when engine combustion chamber is in low temperature environment, utilize drive mechanism to open rich combustion gas passage, so that the high-temperature rich combustion gas of rocket engine output is ejected from the rich combustion gas passage of the two sides of branch plate, realize that high-temperature rich combustion gas is directly mixed with the air of the two sides of branch plate and efficiently, enhance the heating effect of high-temperature rich combustion gas and air contact and take place combustion reaction to engine, guarantee the combustion performance of engine, while avoiding the length, weight and volume of engine combustion chamber increase caused by longer combustion reaction distance.

Description

Technical Field

[0001] This invention belongs to the field of wide-range combined engine technology, specifically relating to a multi-channel fuel-rich gas support flame stabilizer suitable for wide-speed-range combined power. Background Technology

[0002] Traditional engines can only operate within a limited speed range. For example, turbojet and turbofan engines operate at speeds of around Mach 0-2, and ramjet engines operate at speeds of around Mach 2-10. Neither can achieve wide-range flight.

[0003] Currently, existing technologies combine the advantages of various traditional engines in each speed range to form combined propulsion systems in order to enable engines to operate across the entire speed range. For example, rockets and ramjet engines are combined into rocket-based combined propulsion systems (RBCCs), and rockets, turbines, and ramjet engines are combined into three-way combined engines. In engines that use chemical fuels as their energy source, combustion efficiency directly determines engine performance. In the combustion chamber of a wide-speed-range combined engine, the flame stabilizer, which exhibits excellent combustion performance at high speeds, experiences reduced combustion efficiency at low speeds and lower total temperatures due to the longer chemical reaction time. Combined propulsion systems utilize a rocket engine located inside the engine to eject high-temperature, fuel-rich gases. These gases react with the incoming air, releasing heat and increasing the engine's total operating temperature. This effectively shortens the combustion reaction time between the chemical fuels and air, significantly improving the engine's combustion performance.

[0004] However, the high-temperature, fuel-rich gas ejected by the rocket engine is located inside the incoming airflow. The incoming airflow and the high-temperature, fuel-rich gas flow in layers. The contact area between the high-temperature, fuel-rich gas and the air is small. It can only react and release heat through continuous diffusion and gradual mixing. This results in the air and the fuel-rich gas needing a long combustion reaction distance to achieve the heating effect. However, this increases the length of the engine's combustion chamber, which in turn increases the engine's weight and volume. Summary of the Invention

[0005] In view of this, the present invention provides a multi-channel fuel-rich gas support plate flame stabilizer suitable for wide speed range combined power, which can realize the combustion reaction between high temperature fuel-rich gas and air to raise the engine temperature, while avoiding the increase in the length, weight and volume of the engine combustion chamber due to the long combustion reaction distance, so as to solve the shortcomings of the prior art.

[0006] The technical solution of this invention is: a multi-channel fuel-rich gas support plate flame stabilizer suitable for wide-speed-range combined power, comprising a support plate connected in the combustion chamber flow channel, air flowing through both sides of the support plate, a mixing component disposed on the support plate, the mixing component comprising a fuel-rich gas channel opened on both sides of the support plate, the interior of the support plate being hollow and communicating with the fuel-rich gas channel, the interior of the support plate communicating with the output port of the rocket engine, the fuel-rich gas being ejected from the fuel-rich gas channel and mixing with the air flowing through both sides of the support plate, two baffles respectively disposed on both sides of the support plate, the baffles abutting against the support plate, a drive mechanism disposed on the support plate, the output end of the drive mechanism being connected to the baffles, used to drive the baffles to move towards or away from the side of the fuel-rich gas channel, using the baffles to close or open the fuel-rich gas channel.

[0007] Preferably, the driving mechanism includes: a translational slider, which is horizontally disposed on the side of the support plate near the inner wall of the flow channel, and is slidably connected to the support plate along its length direction. Two stops are respectively connected to the translational slider, and a linear displacement mechanism is connected to the support plate. The output end of the linear displacement mechanism is connected to the translational slider.

[0008] Preferably, the linear displacement mechanism includes: a screw, which passes through and is threadedly connected to the translational slider, the screw and the translational slider are parallel to each other, and a rotary power unit is connected to the support plate, the output end of the rotary power unit is connected to the screw, and is used to drive the screw to rotate.

[0009] Preferably, a sliding groove is provided in the inner wall of both sides of the support plate near the rich gas passage. The sliding groove is connected to the rich gas passage. The stop block is embedded in the sliding groove and slidably connected to it. The side of the sliding groove near the translation slider passes through the support plate. A stop block connecting section is connected to the stop block. The stop block connecting section extends out of the sliding groove and connects with the translation slider.

[0010] Preferably, the sliding groove is horizontally connected to the upper and lower sides of the fuel-rich gas passage, and the stop block moves along the track.

[0011] Preferably, a mounting plate is horizontally connected to the side of the support plate near the inner wall of the flow channel, and the drive mechanism is connected to the mounting plate.

[0012] Preferably, multiple fuel injection holes are equally spaced on both sides of the support plate along the radial direction of the flow channel. The fuel injection holes are located on the side of the fuel-rich gas passage away from the combustion chamber and are connected to the fuel tank through pipes.

[0013] Preferably, the support plate has a fuel passage inside, and multiple fuel injection holes are connected to the fuel passage. The fuel passage is connected to the fuel tank through a pipe.

[0014] Preferably, the support plate is connected to a vortex generator between the fuel injection hole and the fuel passage.

[0015] Preferably, the thickness of the support plate on the side away from the combustion chamber gradually decreases from the end closest to the vortex generator to the other end.

[0016] Compared with existing technologies, this invention provides a multi-channel fuel-rich gas support plate flame stabilizer suitable for wide-speed-range combined power systems. The support plate in the flow channel works in conjunction with the fuel-rich gas passages, baffles, and drive mechanism of the mixing component. When the engine combustion chamber is in a low-temperature environment, the drive mechanism opens the fuel-rich gas passages, allowing the high-temperature fuel-rich gas output from the rocket engine to be ejected from the fuel-rich gas passages on both sides of the support plate. This achieves efficient mixing of the high-temperature fuel-rich gas directly with the air flowing on both sides of the support plate, enhancing the engine's heating effect through the combustion reaction between the high-temperature fuel-rich gas and air, ensuring engine combustion performance, and avoiding an increase in the length, weight, and volume of the engine combustion chamber due to a longer combustion reaction distance. When the engine combustion chamber is in a high-temperature or low-temperature environment, the drive mechanism closes the fuel-rich gas passages to prevent them from obstructing the incoming airflow. This invention's support plate flame stabilizer has good mixing effect, is easy to use, and is highly practical, making it worthy of promotion. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the opening of the fuel-rich gas passage of the present invention;

[0018] Figure 2 This is a schematic diagram of the closure of the fuel-rich gas passage of the present invention;

[0019] Figure 3 This is a schematic diagram of the linear displacement mechanism of the present invention;

[0020] Figure 4 This is a schematic diagram of the sliding groove on the support plate of the present invention;

[0021] Figure 5 This is a cross-sectional view of the flame stabilizer of the support plate of the present invention;

[0022] Figure 6 This is a longitudinal sectional view of the flame stabilizer of the support plate of the present invention;

[0023] Figure 7 This is a schematic diagram of the stop block of the present invention;

[0024] Figure 8 This is a longitudinal sectional view of the flame stabilizer of the support plate of the present invention along the track;

[0025] Figure 9 This is a schematic diagram of the translational slider 3 of the present invention. Detailed Implementation

[0026] This invention provides a multi-channel fuel-rich gas support flame stabilizer suitable for wide-speed-range combined power systems, which is described below in conjunction with... Figures 1 to 9 The present invention is illustrated by the structural diagram shown below.

[0027] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the technical solution of this invention 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. Therefore, they should not be construed as limitations on this invention.

[0028] Currently, existing technologies combine the advantages of various traditional engines in each speed range to form combined propulsion systems in order to enable engines to operate across the entire speed range. For example, rockets and ramjet engines are combined into rocket-based combined propulsion systems (RBCCs), and rockets, turbines, and ramjet engines are combined into three-way combined engines. In engines that use chemical fuels as their energy source, combustion efficiency directly determines engine performance. In the combustion chamber of a wide-speed-range combined engine, the flame stabilizer, which exhibits excellent combustion performance at high speeds, experiences reduced combustion efficiency at low speeds and lower total temperatures due to the longer chemical reaction time. Combined propulsion systems utilize a rocket engine located inside the engine to eject high-temperature, fuel-rich gases. These gases react with the incoming air, releasing heat and increasing the engine's total operating temperature. This effectively shortens the combustion reaction time between the chemical fuels and air, significantly improving the engine's combustion performance.

[0029] However, the high-temperature, fuel-rich gas ejected by the rocket engine is located inside the incoming airflow. The incoming airflow and the high-temperature, fuel-rich gas flow in layers. The contact area between the high-temperature, fuel-rich gas and the air is small. It can only react and release heat through continuous diffusion and gradual mixing. This results in the air and the fuel-rich gas needing a long combustion reaction distance to achieve the heating effect. However, this increases the length of the engine's combustion chamber, which in turn increases the engine's weight and volume.

[0030] To address the aforementioned issues, this invention provides a multi-channel fuel-rich gas support plate flame stabilizer suitable for wide-speed-range combined propulsion systems. This stabilizer works in conjunction with the support plate in the flow channel, the fuel-rich gas passage of the mixing component, baffles, and a drive mechanism. When the engine combustion chamber is in a low-temperature environment, the drive mechanism opens the fuel-rich gas passage, allowing the high-temperature fuel-rich gas output from the rocket engine to be ejected from the fuel-rich gas passages on both sides of the support plate. This achieves efficient mixing of the high-temperature fuel-rich gas directly with the air flowing through both sides of the support plate, enhancing the engine's heating effect from the combustion reaction between the high-temperature fuel-rich gas and air, ensuring engine combustion performance, and avoiding an increase in the length, weight, and volume of the engine combustion chamber due to a longer combustion reaction distance. When the engine combustion chamber is in a high- or low-temperature environment, the drive mechanism closes the fuel-rich gas passage, preventing the fuel-rich gas passage from causing resistance to the incoming airflow and improving the engine's specific impulse performance.

[0031] A multi-channel fuel-rich gas support plate flame stabilizer suitable for wide-speed-range combined power includes a support plate 1 connected in the combustion chamber flow channel, with air flowing through both sides of the support plate 1. A mixing component is disposed on the support plate 1, including a fuel-rich gas channel 11, which is opened on both sides of the support plate 1. The support plate 1 is hollow and communicates with the fuel-rich gas channel 11. The interior of the support plate 1 is connected to the output port of the rocket engine. The fuel-rich gas is ejected from the fuel-rich gas channel 11 and mixes with the air flowing through both sides of the support plate 1. Two baffles 2 are respectively disposed on both sides of the support plate 1 and abut against the support plate 1. A drive mechanism is disposed on the support plate 1, and the output end of the drive mechanism is connected to the baffles 2 to drive the baffles 2 to move towards or away from the side of the fuel-rich gas channel 11, thereby using the baffles 2 to close or open the fuel-rich gas channel 11.

[0032] As shown in the figure Figure 1 This is a schematic diagram of the opening of the fuel-rich gas passage in this embodiment. In this embodiment, the fuel-rich gas passages 11 opened on both sides of the support plate 1 are used. When the engine combustion chamber is in a low-temperature environment, the fuel-rich gas passages are opened by the drive mechanism, which can guide the high-temperature fuel-rich gas output by the rocket engine into the incoming air. This allows the high-temperature fuel-rich gas to directly and efficiently mix with the air flowing through both sides of the support plate, improving the effect of the high-temperature fuel-rich gas reacting with the air to heat up the engine combustion chamber, ensuring the combustion performance of the engine, and avoiding an increase in the length, weight, and volume of the engine combustion chamber due to a longer combustion reaction distance.

[0033] When the flame stabilizer of the present invention is in operation, the high-temperature fuel-rich gas reacts with the air and flows into the combustion chamber. It is necessary to avoid uneven spraying of high-temperature fuel-rich gas from both sides of the support plate.

[0034] Therefore, this embodiment proposes a solution. Preferably, the driving mechanism includes: a translational slider 3, which is horizontally disposed on the side of the support plate 1 near the inner wall of the flow channel. The translational slider 3 is slidably connected to the support plate 1 along its length direction. Two stops 2 are respectively connected to the translational slider 3. A linear displacement mechanism is connected to the support plate 1, and the output end of the linear displacement mechanism is connected to the translational slider 3.

[0035] As a further optimization, in this embodiment of the present disclosure, a translational slider 3 is provided on the side of the support plate 1 near the inner wall of the flow channel. This not only enables the two stops 2 to move synchronously, allowing the fuel-rich gas channels on both sides of the support plate 1 to open and close synchronously, but also ensures that the translational slider 3 is located on the outermost side of the flow channel to avoid generating resistance to the incoming flow.

[0036] As shown in the figure Figure 3 The diagram shows a linear displacement mechanism. Preferably, the linear displacement mechanism includes: a screw 31, which passes through and is threadedly connected to the translational slider 3. The screw 31 and the translational slider 3 are parallel to each other. A rotary power unit 32 is connected to the support plate 1. The output end of the rotary power unit 32 is connected to the screw 31 to drive the screw 31 to rotate.

[0037] The linear displacement mechanism disclosed in this embodiment can not only drive the stop block to move to open and close the fuel-rich gas passage, but also automatically open the fuel-rich gas passage under low-speed and low total temperature conditions to improve the mixed combustion efficiency, and automatically close the fuel-rich gas passage under high-speed and high total temperature conditions to improve the engine's specific impulse performance. Moreover, it can achieve stability in opening and closing, so that the engine can work stably.

[0038] In this embodiment, the translational slider 3 has a threaded hole 33, and the screw 31 passes through the threaded hole 33 and is threadedly connected to it.

[0039] During use, the flame stabilizer of the present invention requires the baffle 2 to move back and forth during the low and high temperature stages of the engine, so it is necessary to reduce the resistance to the movement of the baffle 2 and the resistance to the incoming airflow.

[0040] Based on this, the support plate is improved in this embodiment, such as... Figure 5 The figure shown is a cross-sectional view of the support plate in this embodiment. Figure 6 The figure shows a longitudinal sectional view of the flame stabilizer of this embodiment. Preferably, the inner walls of the support plate 1 near the rich gas passage 11 are provided with sliding grooves 12. The sliding grooves 12 are connected to the rich gas passage 11. The stop block 2 is embedded in the sliding groove 12 and slidably connected to it. The side of the sliding groove 12 near the translational slider 3 passes through the support plate 1, as shown in the figure. Figure 7This is a schematic diagram of the stop block in this embodiment. The stop block 2 is connected to a stop block connecting section 21, which extends out of the sliding groove 12 and connects to the translational slider 3.

[0041] In this embodiment, the sliding groove 12 opened in the inner wall of the support plate 1 is used to realize the back and forth movement of the stop block 2 in the sliding groove 12, thereby effectively reducing the resistance to the movement of the stop block 2 and the resistance to the incoming airflow, and improving the specific impulse performance of the engine.

[0042] As a further optimization scheme, as shown in the figure, Figure 8 This is a longitudinal cross-sectional view of the flame stabilizer along the track in this embodiment. Preferably, the sliding groove 12 is located on the upper and lower sides of the rich gas passage 11 and is horizontally connected to the track 13, and the stop block 2 moves along the track 13.

[0043] In this embodiment, the track 13 is used to improve the stability of the stop 2 moving in the sliding groove 12, thereby further improving the stability of the combined power engine.

[0044] The flame stabilizer of the present invention needs to be connected to the inner wall of the flow channel, and the driving mechanism is located on the side of the support plate 1 close to the inner wall of the flow channel, so it is necessary to improve the stability of the connection between the flame stabilizer and the inner wall of the flow channel.

[0045] Preferably, the support plate 1 is horizontally connected to the mounting plate 4 on the side near the inner wall of the flow channel, and the drive mechanism is connected to the mounting plate 4.

[0046] In this embodiment, the mounting plate 4 not only facilitates the stable connection between the support plate flame stabilizer and the inner wall of the flow channel, but also facilitates the installation of the drive mechanism.

[0047] As shown in the figure Figure 4 This is a schematic diagram of the sliding groove on the support plate in this embodiment. Figure 9 This is a schematic diagram of the translational slider 3 in this embodiment. In this embodiment, the sliding groove 12 continues to penetrate the mounting plate 4 upwards. The end of the stop block connecting section 21 away from the stop block 2 is a stud 22. The translational slider 3 is provided with a through hole 34 directly above the sliding groove 12. The stop block connecting section 21 passes through the mounting plate 4 and the translational slider 3 in one go. The stud 22 extends out of the through hole 34 and is detachably fixed to the nut 35. The through hole 33 is a square hole.

[0048] As a further optimization, preferably, multiple fuel injection holes 14 are equally spaced on both sides of the support plate 1 along the radial direction of the flow channel. The fuel injection holes 14 are located on the side of the fuel-rich gas passage 11 away from the combustion chamber, and the fuel injection holes 14 are connected to the fuel tank through pipes.

[0049] In this embodiment, a fuel injection hole 14 is provided in front of the fuel-rich gas passage 11 on the support plate 1. The fuel injected by the fuel injection hole 14 is first mixed with air, and then the fuel-air mixture is mixed with the fuel-rich gas. The reaction between the fuel-rich gas and air releases heat, which not only increases the temperature of the engine, but also heats the fuel-air mixture, thereby improving the combustion performance of the engine.

[0050] As a further optimization, preferably, the support plate 1 is provided with a fuel passage 15 inside, and multiple fuel injection holes 14 are respectively connected to the fuel passage 15. The fuel passage 15 is connected to the fuel tank through a pipe.

[0051] In this embodiment, the fuel passage 15 is used to make the fuel sprayed out synchronously from the fuel passage 15, which improves the mixing effect with air and further improves the combustion performance of the engine.

[0052] As a further optimization, preferably, the support plate 1 is connected to the vortex generator 16 between the fuel injection hole 14 and the fuel passage 15.

[0053] In this embodiment, the vortex generator can induce the incoming airflow to generate transverse and longitudinal vortices, thereby enhancing the mixing efficiency of air, fuel oil, and fuel-rich gas.

[0054] As a further optimization, preferably, the thickness of the support plate 1 on the side away from the combustion chamber gradually decreases from the end closest to the vortex generator 16 to the other end.

[0055] In this embodiment, the front end of the support plate 1 is set in a conical shape, which can further reduce the resistance to the incoming airflow.

[0056] The working principle of the flame stabilizer of this invention is as follows: When the engine is operating at low speed, the combustion chamber is in a low-temperature environment. At this time, it is necessary to open the fuel-rich gas passage 11. The rotary power unit 32 drives the screw 31 to rotate counterclockwise, which interacts with the thread on the threaded hole 33 on the translational slider 3, causing the translational slider 3 to slide backward. This causes the stop block 2 to move backward along the track 13. When the stop block 2 moves to the rightmost position, the fuel-rich gas passage 22 is opened. Figure 1 The diagram shown is a schematic of the opening of the fuel-rich gas passage.

[0057] When the engine operates at high speed, the combustion chamber is in a high total temperature environment. To improve the engine's specific impulse performance, the fuel-rich combustion passage 11 needs to be closed. This is achieved by rotating the screw 31 clockwise via the power unit 32. The screw interacts with the threaded hole 33 on the translational slider 3, causing the translational slider 3 to move forward. This moves the stop block 2 forward along the track 13. When the stop block 2 reaches its leftmost position, the fuel-rich combustion passage 11 is closed. Figure 2The diagram shows the closure of the fuel-rich gas passage. At the same time, kerosene enters from the fuel oil passage 15 and is vertically sprayed out from multiple fuel oil injection holes 14 on both sides of the support plate, mixing with the incoming air.

[0058] The above-disclosed embodiments are merely preferred embodiments of the present invention. However, the embodiments of the present invention are not limited thereto, and any variations that can be conceived by those skilled in the art should fall within the protection scope of the present invention.

Claims

1. A multi-channel fuel-rich gas support flame stabilizer suitable for wide-speed-range combined power systems, comprising: A support plate (1) connected to the combustion chamber flow channel, through which air flows, is characterized in that it further includes: a mixing assembly disposed on the support plate (1), the mixing assembly comprising: A fuel-rich gas passage (11) is provided on both sides of the support plate (1). The support plate (1) is hollow inside and connected to the fuel-rich gas passage (11). The interior of the support plate (1) is connected to the output port of the rocket engine. The fuel-rich gas is ejected from the fuel-rich gas passage (11) and mixed with the air flowing on both sides of the support plate (1). Two blocks (2) are respectively set on both sides of the support plate (1), and the blocks (2) abut against the support plate (1); A drive mechanism is provided on the support plate (1). The output end of the drive mechanism is connected to the stop block (2) and is used to drive the stop block (2) to move towards or away from the rich gas passage (11). The stop block (2) is used to close or open the rich gas passage (11). The driving mechanism includes: a translational slider (3), which is horizontally disposed on the side of the support plate (1) near the inner wall of the flow channel. The translational slider (3) is slidably connected to the support plate (1) along its length direction. Two stops (2) are respectively connected to the translational slider (3). A linear displacement mechanism is connected to the support plate (1), and the output end of the linear displacement mechanism is connected to the translational slider (3). The support plate (1) has sliding grooves (12) on both sides of the inner wall near the rich gas channel (11). The sliding grooves (12) are connected to the rich gas channel (11). The stop block (2) is embedded in the sliding groove (12) and slidably connected to it. The sliding groove (12) passes through the support plate (1) on the side near the translation slider (3). The stop block (2) is connected to a stop block connecting section (21). The stop block connecting section (21) extends out of the sliding groove (12) and is connected to the translation slider (3). The sliding groove (12) is located on the upper and lower sides of the fuel-rich gas channel (11) and is horizontally connected to the track (13). The stop block (2) moves along the track (13).

2. The multi-channel fuel-rich gas support plate flame stabilizer suitable for wide-speed-range combined power as described in claim 1, characterized in that, The linear displacement mechanism includes: a screw (31), which passes through the translational slider (3) and is threadedly connected to it. The screw (31) and the translational slider (3) are parallel to each other. A rotary power unit (32) is connected to the support plate (1). The output end of the rotary power unit (32) is connected to the screw (31) to drive the screw (31) to rotate.

3. The multi-channel fuel-rich gas support plate flame stabilizer suitable for wide-speed-range combined power as described in claim 2, characterized in that, The support plate (1) is horizontally connected to the mounting plate (4) on the side near the inner wall of the flow channel, and the drive mechanism is connected to the mounting plate (4).

4. The multi-channel fuel-rich gas support plate flame stabilizer suitable for wide-speed-range combined power as described in claim 1, characterized in that, Multiple fuel injection holes (14) are equally spaced on both sides of the support plate (1) along the radial direction of the flow channel. The fuel injection holes (14) are located on the side of the fuel-rich gas passage (11) away from the combustion chamber. The fuel injection holes (14) are connected to the fuel tank through a pipe.

5. The multi-channel fuel-rich gas support plate flame stabilizer suitable for wide-speed-range combined power as described in claim 4, characterized in that, The support plate (1) is provided with a fuel channel (15) inside, and a plurality of fuel injection holes (14) are respectively connected to the fuel channel (15). The fuel channel (15) is connected to the fuel tank through a pipe.

6. The multi-channel fuel-rich gas support plate flame stabilizer suitable for wide-speed-range combined power as described in claim 5, characterized in that, The support plate (1) is located between the fuel injection hole (14) and the fuel passage (15) and is connected to a vortex generator (16).

7. The multi-channel fuel-rich gas support plate flame stabilizer suitable for wide-speed-range combined power as described in claim 6, characterized in that, The thickness of the support plate (1) on the side away from the combustion chamber gradually decreases from one end near the vortex generator (16) to the other end.

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