A compound device applied to a combustion chamber and a ramjet

Abstract

The application discloses a composite device applied to a combustion chamber and a ramjet engine, and relates to the technical field of ramjet engines, to solve the problem of how to improve the mixing efficiency of fuel and air. The composite device applied to the combustion chamber comprises a support plate injector, a cover plate provided with a first through hole, and a pipeline, and the cover plate covers one open end of the pipeline. Two sides of one support plate injector are respectively provided with one evaporation type flame stabilizer, the evaporation type flame stabilizer is in a blocking state in the composite device applied to the combustion chamber. The evaporation type flame stabilizer comprises a first pipeline in communication with the pipeline, a second pipeline connected with the side wall of the pipeline, and the first pipeline is located in the second pipeline. The first pipeline is provided with a second through hole for transmitting a first fluid in the first pipeline to the second pipeline, the second pipeline comprises a first connecting plate provided with an air bleeding port for transmitting a second fluid to the second pipeline, and a second connecting plate provided with a third through hole.

Description

Technical Field

[0001] This invention relates to the field of engine technology, and more particularly to a composite device for use in a combustion chamber and a ramjet engine. Background Technology

[0002] Ramjet engines utilize atmospheric oxygen as an oxidizer, thus possessing a high specific impulse, making them ideal power sources for hypersonic cruise missiles and spaceplanes. As the operating speed range of ramjet engines widens, the requirements for fuel injectors and flame stabilizers become increasingly stringent in order to achieve efficient and stable operation of the ramjet combustion chamber. A prerequisite for efficient and stable combustion in the combustion chamber is good mixing of the fuel with the mainstream (such as air).

[0003] Therefore, how to improve the mixing efficiency of fuel and air is a technical problem that the industry urgently needs to solve. Summary of the Invention

[0004] The purpose of this invention is to provide a compounding device and a ramjet engine for use in a combustion chamber to improve the mixing efficiency of fuel and air.

[0005] To achieve the above objectives, in a first aspect, the present invention provides a composite device for use in a combustion chamber. This composite device for use in a combustion chamber includes: at least one support injector and at least two evaporative flame stabilizers. The support injector includes a cover plate and a pipe; along the length of the pipe, the pipe has a first channel penetrating the pipe; the cover plate covers one open end of the pipe; both the side wall of the pipe and the cover plate have first through holes. An evaporative flame stabilizer is respectively disposed on both sides of one support injector, the evaporative flame stabilizer having a first end and a second end opposite to each other, the first end of the evaporative flame stabilizer being connected to the side wall of the pipe; in the composite device for use in a combustion chamber, when the second end of the evaporative flame stabilizer is a free end, the free end is in a blocked state. The evaporative flame stabilizer includes a first pipe and a second pipe, the first pipe being located within the second pipe; the second pipe has a third end and a fourth end opposite to each other, the third end of the second pipe being connected to the side wall of the pipe, the first pipe being in communication with the pipe; when the fourth end of the second pipe is a free end, the free end is in a blocked state. A second through hole is provided on the side wall of the first pipe, which is used to transfer the first fluid in the first pipe to the second pipe. The second pipe includes a first connecting plate and a second connecting plate arranged opposite to each other. An air inlet is provided on the first connecting plate, and a third through hole is provided on the second connecting plate. The air inlet is used to transfer the second fluid to the second pipe. The first fluid and the second fluid mix in the second pipe and are ejected through the third through hole.

[0006] Compared with the prior art, the beneficial effects of this application are as follows: In the composite device for combustion chambers provided by this invention, since the second end of the evaporative flame stabilizer is a free end and is in a blocked state, the fluid entering the support injector through the other open end of the pipeline will not be ejected from the free end of the evaporative flame stabilizer. It should be noted that the "free end of the evaporative flame stabilizer" here refers to the end of the evaporative flame stabilizer that is not connected to the side wall of the pipeline. Furthermore, since the pipeline has a first channel running through it along its length, it has two relatively distributed open ends along its length. In this application, a cover plate covers one of the open ends. In actual use, the first fluid enters the support injector through the other open end of the pipeline. At this time, a portion of the first fluid is directly injected into the combustion chamber through the first through-hole, and the remaining first fluid enters the first pipe connected to the pipeline. Then, the remaining first fluid enters the second pipe through a second through-hole opened on the side wall of the first pipe. Furthermore, since the vent is used to transfer the second fluid into the second pipe, the remaining first fluid and the second fluid mix in the second pipe. In practical use, the second fluid can be air, and the first fluid can be fuel. In this case, the air and fuel are mixed within the second pipe, and the fuel is atomized and broken up into droplets. The mixed air and fuel are then ejected through the third through-hole. It should be noted that the mixed air and fuel are in a highly fuel-rich state and will not burn within the second pipe.

[0007] As described above, the composite device for combustion chambers provided in this application significantly reduces fuel evaporation and atomization distance at low Mach numbers, thereby improving air-fuel mixing efficiency. At high Mach numbers, fuel injected directly from the first through-hole of the spur injector has higher momentum, resulting in greater penetration depth and thus better mixing efficiency. Furthermore, compared to evaporative flame stabilizers, spur injectors exhibit lower aerodynamic drag, enabling the combustion chamber to achieve higher performance at high Mach numbers.

[0008] In one implementation, the evaporative flame stabilizer further includes: A third connecting plate and a fourth connecting plate are arranged opposite to each other; along the width direction of the third connecting plate, the third connecting plate includes a first part and a second part; along the width direction of the fourth connecting plate, the fourth connecting plate includes a third part and a fourth part; the first connecting plate, the second connecting plate, the first part of the third connecting plate and the third part of the fourth connecting plate enclose a second pipe; along the length direction of the second pipe, the second pipe has a second channel penetrating the second pipe; A fifth connecting plate; at least a portion of the first part of the fifth connecting plate and the third connecting plate enclose a first pipe; along the length direction of the first pipe, the first pipe has a third channel penetrating the first pipe; along the length direction of the first pipe, the fifth connecting plate is provided with a plurality of spaced second through holes.

[0009] In one implementation, the opening area of ​​a single air vent is larger than the opening area of ​​a single second through hole; The direction perpendicular to the air inlet is the first direction; the direction perpendicular to the second through hole is the second direction; the intersection of the first direction and the second direction is located within the second channel.

[0010] In one implementation, the first direction is perpendicular to the second direction.

[0011] In one implementation, the spacing between the third and fourth connecting plates increases along a direction away from the first connecting plate.

[0012] In one implementation, the composite device applied to the combustion chamber includes a plurality of the said support injectors and a plurality of the said evaporative flame stabilizers; Multiple vapor flame stabilizers are arranged in a ring, and a support plate injector is provided between two adjacent vapor flame stabilizers; Multiple cover plates are located near the central region of the annularly arranged vapor flame stabilizer, and the multiple cover plates are spaced apart.

[0013] In one implementation, the support plate injector and the vapor flame stabilizer are integrally formed; The shape of the plurality of said evaporative flame stabilizers is the same as the cross-sectional shape of the combustion chamber at the combustion chamber installation location.

[0014] In one implementation, along the length of the pipeline, the pipeline includes a first pipeline and a second pipeline; the first pipeline is located inside the annularly arranged vapor flame stabilizer, and the length of the second pipeline is greater than the length of the first pipeline.

[0015] In one implementation, the ratio of the fluid content ejected through the support plate injector to the content of the first fluid entering the evaporative flame stabilizer is equal to the ratio of the total opening area of ​​the first through hole to the total opening area of ​​the second through hole.

[0016] Secondly, the present invention also provides a ramjet engine, including a combustion chamber and the composite device applied to the combustion chamber as described in the above-mentioned technical solution. The combustion chamber includes a combustion chamber body, and the other open end of a pipeline is connected to the combustion chamber body.

[0017] The beneficial effects of the ramjet engine provided by this invention are the same as those of the composite device applied to the combustion chamber described in the above technical solution, and will not be repeated here. Attached Figure Description

[0018] The accompanying drawings, which are included to provide a further understanding of the invention and form part of this invention, illustrate exemplary embodiments of the invention and are used to explain the invention, but do not constitute an undue limitation of the invention. In the drawings: Figure 1 This is a front view of the composite device applied to the combustion chamber in an embodiment of the present invention; Figure 2 As described in the embodiments of the present invention Figure 1 Enlarged schematic diagram of part of the structure Figure 1 ; Figure 3 As described in the embodiments of the present invention Figure 2 The center section view; Figure 4 As described in the embodiments of the present invention Figure 2 Enlarged schematic diagram of part of the structure; Figure 5 As described in the embodiments of the present invention Figure 1 Enlarged schematic diagram of part of the structure Figure 2 .

[0019] Figure label: 1-Support plate injector, 10-Cover plate, 11-Pipeline, 12-First through hole, 13-First pipeline, 14-Second pipeline, 15-Second opening end; 2-Evaporative flame stabilizer, 20-First pipe, 200-Second through hole, 201-Third channel; 21-Second pipe, 210-First connecting plate, 211-Second connecting plate, 212-Air vent, 213-Third through hole, 214-Third connecting plate, 215-Fourth connecting plate, 216-Fifth connecting plate; 3-Low speed zone. Detailed Implementation

[0020] To facilitate a clear description of the technical solutions in the embodiments of the present invention, the terms "first" and "second" are used to distinguish identical or similar items with essentially the same function and effect. For example, the first threshold and the second threshold are merely used to distinguish different thresholds and do not limit their order. Those skilled in the art will understand that the terms "first" and "second" do not limit the quantity or execution order, and that the terms "first" and "second" are not necessarily different.

[0021] It should be noted that in this invention, the terms "exemplary" or "for example" are used to indicate examples, illustrations, or descriptions. Any embodiment or design described as "exemplary" or "for example" in this invention should not be construed as being more preferred or advantageous than other embodiments or designs. Specifically, the use of terms such as "exemplary" or "for example" is intended to present the relevant concepts in a concrete manner.

[0022] In this invention, "at least one" refers to one or more, and "more than one" refers to two or more. "And / or" describes the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A alone, A and B simultaneously, or B alone, where A and B can be singular or plural. The character " / " generally indicates that the preceding and following related objects are in an "or" relationship. "At least one of the following" or similar expressions refer to any combination of these items, including any combination of single or plural items. For example, at least one of a, b, or c can represent: a, b, c, a combination of a and b, a combination of a and c, a combination of b and c, or a, b, and c, where a, b, and c can be single or multiple.

[0023] Ramjet engines utilize atmospheric oxygen as an oxidizer, thus possessing a high specific impulse, making them ideal power sources for hypersonic cruise missiles and spaceplanes. As the operating speed range of ramjet engines widens, the requirements for fuel injectors and flame stabilizers become increasingly stringent in order to achieve efficient and stable operation of the ramjet combustion chamber. A prerequisite for efficient and stable combustion in the combustion chamber is good mixing of the fuel with the mainstream (such as air).

[0024] For example, the factors influencing efficient blending of fuel and mainstream differ under low and high Mach number conditions. At low Mach numbers, the incoming flow temperature is lower, and the breakup and atomization of fuel (e.g., kerosene) droplets require a longer distance. In this case, accelerating the breakup and atomization of kerosene droplets can increase the blending efficiency between kerosene and the mainstream. However, as the incoming flow velocity increases, the incoming flow temperature gradually increases, allowing kerosene droplets to break up and atomize within a shorter time and distance. At this point, due to the higher mainstream velocity, the main factor affecting fuel blending becomes the fuel penetration depth.

[0025] To address the aforementioned technical problems, in a first aspect, the present invention provides a composite device applied to a combustion chamber. (See also...) Figures 1 to 5The composite device applied to the combustion chamber includes: at least one support injector 1 and at least two evaporative flame stabilizers 2. The support injector 1 includes a cover plate 10 and a pipe 11. Along the length L1 of the pipe 11, the pipe 11 has a first channel penetrating the pipe 11. The cover plate 10 covers one open end of the pipe 11, and both the side wall of the pipe 11 and the cover plate 10 have first through holes 12. An evaporative flame stabilizer 2 is respectively disposed on both sides of each support injector 1. The evaporative flame stabilizer 2 has a first end and a second end opposite to each other, and the first end of the evaporative flame stabilizer 2 is connected to the side wall of the pipe 11. In the composite device applied to the combustion chamber, when the second end of the evaporative flame stabilizer 2 is a free end, the free end is in a blocked state. The evaporative flame stabilizer 2 includes a first pipe 20 and a second pipe 21, with the first pipe 20 located within the second pipe 21. The second pipe 21 has a third end and a fourth end. The third end of the second pipe 21 is connected to the side wall of the pipe 11, and the first pipe 20 is connected to the first channel of the pipe 11. When the fourth end of the second pipe 21 is a free end, the free end is in a blocked state. A second through hole 200 is provided on the side wall of the first pipe 20, which is used to transfer the first fluid in the first pipe 20 to the second pipe 21. The second pipe 21 includes a first connecting plate 210 and a second connecting plate 211 arranged opposite to each other. An air inlet 212 is provided on the first connecting plate 210, and a third through hole 213 is provided on the second connecting plate 211. The air inlet 212 is used to transfer the second fluid to the second pipe 21, and the first fluid and the second fluid mix in the second pipe 21 and are ejected through the third through hole 213.

[0026] See Figures 1 to 5 Compared with the prior art, the beneficial effects of this application are as follows: In the composite device applied to the combustion chamber provided by this invention, since the second end of the evaporative flame stabilizer 2 is a free end, the free end is in a blocked state. Therefore, the fluid entering the support injector 1 through the other open end of the pipe 11 (defined as the second open end 15 for ease of labeling) will not be ejected from the free end of the evaporative flame stabilizer 2. It should be noted that the "free end of the evaporative flame stabilizer 2" here refers to the end of the evaporative flame stabilizer 2 that is not connected to the side wall of the pipe 11. For example... Figure 2In this design, an evaporative flame stabilizer 2 is installed on each side of a support plate injector 1. Each evaporative flame stabilizer 2 has a free end not connected to the pipe 11. This free end is sealed; the sealing method is not specifically limited, as long as it does not affect the normal operation of the composite device applied to the combustion chamber. Furthermore, since the pipe 11 has a first channel running through it along its length, it has two relatively distributed open ends along its length. In this application, a cover plate 10 covers one of these open ends. In actual use, the first fluid enters the support plate injector 1 through the other open end of the pipe 11. At this time, a portion of the first fluid is directly injected into the combustion chamber through the first through-hole 12, and the remaining first fluid enters the first pipe 20 connected to the pipe 11. Then, the remaining first fluid enters the second pipe 21 through the second through-hole 200 opened on the side wall of the first pipe 20. Furthermore, since the air inlet 212 is used to transfer the second fluid into the second pipe 21, the remaining first fluid and the second fluid mix within the second pipe 21. In actual use, the second fluid can be air, and the first fluid can be fuel. At this point, the air and fuel are mixed within the second pipe 21, and the fuel undergoes droplet breakup and atomization within the second pipe 21. The mixed air and fuel are then ejected through the third through-hole 213. It should be noted that the mixed air and fuel are in an absolutely fuel-rich state and will not burn within the second pipe 21.

[0027] As described above, by employing the composite device for combustion chambers provided in this application, the evaporative flame stabilizer 2 can significantly reduce fuel evaporation and atomization distance under low Mach number conditions, thereby improving the air-fuel mixing efficiency. Under high Mach number conditions, the fuel directly injected from the first through-hole 12 of the support injector 1 has higher momentum. High-momentum fuel has a higher penetration depth, increasing the fuel penetration depth and thus achieving better mixing efficiency. Furthermore, compared to the evaporative flame stabilizer 2, the support injector 1 has lower aerodynamic drag, enabling the combustion chamber to achieve higher performance under high Mach number conditions.

[0028] As one possible implementation, see Figures 1 to 5 A first through hole 12 penetrates the pipe 11 along its thickness direction. Multiple first through holes 12 are spaced apart along the length L1 of the pipe 11. Whether the pipe 11 has single-sided or double-sided openings can be determined based on actual conditions and is not specifically limited here.

[0029] In some embodiments, the above-mentioned pipeline can be a support plate in the art. The specific structure of the support plate is not specifically limited here, as long as it can meet the actual needs.

[0030] The cover plate 10 has two first through holes 12.

[0031] The aforementioned first through hole 12 can be understood as a spray hole.

[0032] The air intake 212 is located on the windward side, and the third through hole 213 is located on the leeward side.

[0033] As one possible implementation, see Figures 1 to 5 The evaporative flame stabilizer 2 also includes a fifth connecting plate 216 and a third connecting plate 214 and a fourth connecting plate 215 disposed opposite to each other.

[0034] Along the width direction L2 of the third connecting plate 214, the third connecting plate 214 includes a first part and a second part. Along the width direction L3 of the fourth connecting plate 215, the fourth connecting plate 215 includes a third part and a fourth part. The first connecting plate 210, the second connecting plate 211, the first part of the third connecting plate 214, and the third part of the fourth connecting plate 215 enclose and form a second conduit 21. Along the length direction of the second conduit 21, the second conduit 21 has a second channel penetrating through the second conduit 21.

[0035] At least a portion of the first portion of the fifth connecting plate 216 and the third connecting plate 214 enclose a first conduit 20. Along the length of the first conduit 20, the first conduit 20 has a third channel 201 extending through it. Along the length of the first conduit 20, the fifth connecting plate 216 has a plurality of spaced-apart second through holes 200.

[0036] In some embodiments, both the first connecting plate 210 and the fifth connecting plate 216 are arc-shaped connecting plates.

[0037] The second connecting plate 211, the second part of the third connecting plate 214, and the fourth part of the fourth connecting plate 215 form a region, which is the low-speed region 3. The third through hole 213 is located between the second part of the third connecting plate 214 and the fourth part of the fourth connecting plate 215. At this time, it can be ensured that the mixture of the first fluid and the second fluid injected through the third through hole 213 is injected into the low-speed region 3. Furthermore, the evaporative flame stabilizer 2 provides the low-speed region 3 downstream to achieve efficient and stable combustion in the combustion chamber and stabilize the flame. Specifically, the mixed fuel and air are injected into the low-speed region 3 of the combustion chamber and further mixed with the mainstream (e.g., air) to achieve stable combustion.

[0038] In one alternative approach, see Figure 4 and Figure 5 Along the direction away from the first connecting plate 210, the distance between the third connecting plate 214 and the fourth connecting plate 215 increases.

[0039] With the above technical solution, a large low-speed region 3 is formed downstream of the evaporative flame stabilizer 2, which can better stabilize the flame.

[0040] For example, see Figure 4 and Figure 5 Along the direction away from the second connecting plate 211, the distance between the third connecting plate 214 and the fourth connecting plate 215 increases.

[0041] In one alternative approach, see Figure 4 The opening area of ​​a single air vent 212 is larger than the opening area of ​​a single second through hole 200.

[0042] The direction perpendicular to the air inlet 212 is the first direction, and the direction perpendicular to the second through hole 200 is the second direction. The intersection of the first and second directions is located within the second channel. This prevents the first fluid from being ejected through the air inlet 212 and ensures that the air captured by the air inlet 212 directly impacts the first fluid injected through the second through hole 200, thereby enhancing mixing efficiency. The angle between the first and second directions is greater than 0° and less than 360°.

[0043] In some embodiments, the first direction is perpendicular to the second direction. This ensures better mixing of the first and second fluids, enabling efficient and stable combustion of the flame within the combustion chamber.

[0044] As one possible implementation, see Figures 1 to 5 The composite device applied to the combustion chamber includes multiple support injectors 1 and multiple evaporative flame stabilizers 2. The multiple evaporative flame stabilizers 2 are arranged in a ring, with a support injector 1 positioned between every two adjacent evaporative flame stabilizers 2. Multiple cover plates are located near the central area of ​​the ring-arranged evaporative flame stabilizers 2, and the cover plates are spaced apart. It should be noted that because the multiple evaporative flame stabilizers 2 are arranged in a ring, there are no free ends to the evaporative flame stabilizers 2, eliminating the need for additional sealing operations. Furthermore, the multiple support injectors 1 and the multiple evaporative flame stabilizers 2 are circumferentially connected via pipe 11 and a first pipe 20.

[0045] With the above technical solution, since multiple evaporative flame stabilizers 2 are arranged in a ring, circumferential flame communication can be achieved, further improving the stability of the flame in the combustion chamber.

[0046] For example, the aforementioned ring can be a circular ring, a quasi-circular ring, a square ring, a quasi-square ring, an elliptical ring, or a quasi-elliptical ring, etc. For example, Figure 1 Multiple evaporative flame stabilizers 2 are arranged in a circular pattern.

[0047] In some embodiments, the shape enclosed by the plurality of evaporative flame stabilizers 2 is the same as or similar to the cross-sectional shape of the combustion chamber at the combustion chamber mounting location.

[0048] In one alternative approach, see Figure 1 The composite device applied to the combustion chamber includes five support plate injectors 1 and five vapor flame stabilizers 2.

[0049] In one alternative configuration, the support plate injector 1 and the vapor flame stabilizer 2 are integrally formed.

[0050] In one alternative approach, see Figure 1 Along the length direction L1 of the pipe 11, the pipe 11 includes a first pipe 13 and a second pipe 14. The first pipe 13 is located inside the annularly arranged vapor-type flame stabilizer 2, and the length of the second pipe 14 is greater than the length of the first pipe 13.

[0051] As one possible implementation, see Figures 1 to 5 The ratio of the fluid content ejected through the support plate injector 1 to the content of the first fluid entering the evaporative flame stabilizer 2 is equal to the ratio of the total opening area of ​​the first through hole 12 to the total opening area of ​​the second through hole 200.

[0052] The composite device for combustion chamber provided in this application uses an internal connection of the fuel supply line to transport the fuel supplied by the support plate injector 1 to the evaporative flame stabilizer 2. The fuel distribution is controlled by the ratio of the total opening area of ​​the first through hole 12 to the total opening area of ​​the second through hole 200, thereby reducing the complexity of the fuel system.

[0053] As one possible implementation, the composite device applied to the combustion chamber in this application needs to operate within the mainstream for extended periods; therefore, the composite device applied to the combustion chamber needs to be able to withstand high temperatures and high pressures. Based on this, the composite device applied to the combustion chamber is made of high-temperature resistant composite materials or high-temperature alloys. The specific temperature and pressure ranges that the high-temperature resistant composite materials or high-temperature alloys can withstand are not limited here; appropriate materials can be selected according to actual needs.

[0054] In summary, at low Mach numbers, the total temperature is relatively low. On the one hand, auxiliary measures are needed to reduce the time for fuel (e.g., kerosene) droplet breakup and atomization; on the other hand, a large low-speed zone needs to be created within the combustion chamber to achieve flame stability. In this application, an evaporative flame stabilizer 2 is used to achieve stable combustion at low Mach numbers. Specifically, air and fuel are mixed within the second pipe 21, reducing the time for fuel droplet breakup and atomization. Furthermore, the second connecting plate 211, the second portion of the third connecting plate 214, and the fourth portion of the fourth connecting plate 215 form a region, which is a low-speed region 3. At this point, the evaporative flame stabilizer 2 provides a low-speed region 3 downstream, achieving efficient and stable combustion in the combustion chamber and stabilizing the flame.

[0055] At higher Mach numbers, the total temperature of the incoming flow is higher. At this point, the kerosene droplet breakup and atomization distance is shorter, and the ignition delay time is lower. The requirements for accelerating droplet breakup and atomization, as well as the low-speed zone, are reduced. However, the high Mach number of the incoming flow reduces the fuel penetration depth. Therefore, it is necessary to increase the fuel momentum to increase the fuel penetration depth, obtain higher mixing efficiency, and thus improve combustion efficiency. The fuel penetration depth injected by the evaporative flame stabilizer 2 is relatively low, and its large frontal area causes significant resistance, reducing combustion chamber performance. Therefore, at higher Mach numbers, the support plate injector 1 directly injects fuel into the main flow of the combustion chamber through the first through-hole 12 to increase the fuel penetration depth. Furthermore, the smaller low-speed zone 3 formed by the second part of the second connecting plate 211, the second part of the third connecting plate 214, and the fourth part of the fourth connecting plate 215 can meet the combustion requirements for the low-speed zone.

[0056] In summary, the composite device for combustion chambers provided in this application meets the requirements of wide-range combustion organization for fuel injection and flame stability, achieving efficient and stable combustion within a wide range. In other words, the composite device for combustion chambers provided in this application can adapt to the needs of wide-range combustion, creating a suitable environment for flame stability. It should be noted that the aforementioned wide range includes both low-speed and high-speed ranges. For example, the low Mach number range is 2.5 to 5, and the high Mach number range is 5 to 7.

[0057] Secondly, embodiments of the present invention also provide a ramjet engine, including a combustion chamber and the composite device applied to the combustion chamber as described in the above-mentioned technical solution. The combustion chamber includes a combustion chamber body, and the other open end of a pipe is connected to the combustion chamber body. It should be noted that the other open end of the pipe can be integrally 3D printed with the combustion chamber body or through the design of a corresponding mechanical connection structure.

[0058] The beneficial effects of the ramjet engine provided in this embodiment of the invention are the same as those of the composite device applied to the combustion chamber described in the above technical solution, and will not be repeated here.

[0059] Although the invention has been described in conjunction with specific features and embodiments, it is obvious that various modifications and combinations can be made therein without departing from the spirit and scope of the invention. Accordingly, this specification and drawings are merely exemplary descriptions of the invention as defined by the appended claims, and are considered to cover any and all modifications, variations, combinations, or equivalents within the scope of the invention. Clearly, those skilled in the art can make various alterations and modifications to the invention without departing from its spirit and scope. Thus, if such modifications and modifications of the invention fall within the scope of the claims and their equivalents, the invention is also intended to include such modifications and modifications.

Claims

1. A composite device applied in a combustion chamber, characterized in that, include: At least one support plate injector and at least two vapor flame stabilizers; The support plate injector includes a cover plate and a pipeline; along the length of the pipeline, the pipeline has a first channel penetrating the pipeline; the cover plate covers one open end of the pipeline; a first through hole is provided on both the side wall of the pipeline and the cover plate; An evaporative flame stabilizer is provided on each side of one of the support plate injectors; the evaporative flame stabilizer has a first end and a second end opposite to each other, and the first end of the evaporative flame stabilizer is connected to the side wall of the pipeline; in the composite device applied to the combustion chamber, when the second end of the evaporative flame stabilizer is a free end, the free end is in a blocked state; The evaporative flame stabilizer includes a first pipe and a second pipe, with the first pipe located inside the second pipe. The second pipe has a third end and a fourth end opposite to each other. The third end of the second pipe is connected to the side wall of the pipeline, and the first pipe is in communication with the pipeline. When the fourth end of the second pipe is a free end, the free end is in a blocked state. A second through hole is provided on the side wall of the first pipe, which is used to transfer a first fluid in the first pipe to the second pipe. The second pipe includes a first connecting plate and a second connecting plate disposed opposite to each other. The first connecting plate has an air inlet that penetrates through the first connecting plate, and the second connecting plate has a third through hole that penetrates through the second connecting plate. The air inlet is used to transmit a second fluid into the second pipe. The first fluid and the second fluid mix in the second pipe and are ejected through the third through hole.

2. The composite device applied to a combustion chamber according to claim 1, characterized in that, The evaporative flame stabilizer also includes: A third connecting plate and a fourth connecting plate are arranged opposite to each other; along the width direction of the third connecting plate, the third connecting plate includes a first part and a second part; along the width direction of the fourth connecting plate, the fourth connecting plate includes a third part and a fourth part; the first connecting plate, the second connecting plate, the first part of the third connecting plate and the third part of the fourth connecting plate enclose a second pipe; along the length direction of the second pipe, the second pipe has a second channel penetrating the second pipe; A fifth connecting plate; at least a portion of the first part of the fifth connecting plate and the third connecting plate enclose a first pipe; along the length direction of the first pipe, the first pipe has a third channel penetrating the first pipe; along the length direction of the first pipe, the fifth connecting plate is provided with a plurality of spaced second through holes.

3. The composite device applied to the combustion chamber according to claim 2, characterized in that, The opening area of ​​a single air inlet is larger than the opening area of ​​a single second through hole; The direction perpendicular to the air inlet is the first direction; the direction perpendicular to the second through hole is the second direction; the intersection of the first direction and the second direction is located within the second channel.

4. The composite device applied to the combustion chamber according to claim 3, characterized in that, The first direction is perpendicular to the second direction.

5. The composite device applied to a combustion chamber according to claim 2, characterized in that, The distance between the third and fourth connecting plates increases in the direction away from the first connecting plate.

6. The composite device applied to a combustion chamber according to claim 1, characterized in that, The composite device applied to the combustion chamber includes multiple of the aforementioned support plate injectors and multiple of the aforementioned evaporative flame stabilizers; Multiple vapor flame stabilizers are arranged in a ring, and a support plate injector is provided between two adjacent vapor flame stabilizers; Multiple cover plates are located near the central region of the annularly arranged vapor flame stabilizer, and the multiple cover plates are spaced apart.

7. The composite device applied to a combustion chamber according to claim 6, characterized in that, The support plate injector and the evaporative flame stabilizer are integrally molded; The shape of the plurality of said evaporative flame stabilizers is the same as the cross-sectional shape of the combustion chamber at the combustion chamber installation location.

8. The composite device applied to a combustion chamber according to claim 6, characterized in that, Along the length of the pipeline, the pipeline includes a first pipeline and a second pipeline; the first pipeline is located inside the annularly arranged vapor flame stabilizer, and the length of the second pipeline is greater than the length of the first pipeline.

9. The composite device applied to a combustion chamber according to claim 1, characterized in that, The ratio of the fluid content ejected through the support plate injector to the content of the first fluid entering the evaporative flame stabilizer is equal to the ratio of the total opening area of ​​the first through hole to the total opening area of ​​the second through hole.

10. A ramjet engine, characterized in that, include: Combustion chamber, the combustion chamber including a combustion chamber body; The composite device applied to a combustion chamber according to any one of claims 1 to 9; The other open end of the pipeline is connected to the combustion chamber body.

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