Solid rocket ramjet engine arc discharge plasma combustion aid

Abstract

This invention discloses an arc discharge plasma combustion-enhancing device for solid rocket ramjet engines, belonging to the field of solid rocket ramjet engine combustion enhancement. It includes a cathode, an anode, and a casing. The anode has an anode connector and an anode channel inside. The casing has a flexible hose fastening bolt and internally has a first connection hole, a second connection hole, and a third connection hole. A cyclone separator is located between the first connection hole and the anode channel. The cyclone separator has a through hole in its center, surrounded by several vent holes. The cathode passes through the through hole, with one end fixed to the second connection hole and extending into the third connection hole, while the other end extends into the anode channel. This invention utilizes the high temperature, chemical reactivity, and aerodynamic characteristics of the plasma jet to enhance the combustion process under wide-range conditions. This combustion-enhancing device design features high reliability, low complexity, and a significant improvement in combustion efficiency, providing a new technical path for the application of solid rocket ramjet engines.

Description

Technical Field

[0001] This invention relates to a combustion-supporting device, and more particularly to a solid rocket ramjet engine arc discharge plasma combustion-supporting device. Background Technology

[0002] Hypersonic vehicles are considered key to next-generation aerospace technology, typically reaching speeds of Mach 5 and above, significantly enhancing the rapid response capabilities and penetration efficiency of weaponry. Solid-propellant ramjet engines, due to their simple structure, reliable operation, ease of use, and high maneuverability, have become an indispensable core propulsion system for hypersonic flight. Compared to traditional solid-propellant rocket engines, solid-propellant ramjet engines utilize ambient air as an oxidizer, reducing the need for oxidizer in the propellant and thus improving parameters such as specific impulse. Furthermore, their design eliminates the need for complex fuel injection and cooling systems, simplifying the overall structure. The long-term storage performance and ease of operation of solid fuels make them more reliable and practical in tactical applications, eliminating the volatilization, leakage, and cryogenic storage problems associated with liquid fuels. Especially in the hypersonic range, solid-propellant ramjet engines exhibit superior performance, making them a crucial technology for achieving efficient propulsion and excellent combat capabilities in hypersonic vehicles.

[0003] The afterburner chamber, as the primary site for fuel combustion and energy release in solid rocket ramjet engines, plays a decisive role in the overall performance of these engines due to its combustion efficiency. However, under wide-range, high-speed airflow conditions, the gas flow and mixing characteristics within the afterburner chamber are complex, making the effective improvement of combustion efficiency a significant challenge in current technological development. Traditional combustion methods exhibit problems such as low combustion efficiency, poor fuel utilization, and limited combustion organization capabilities. Currently, domestic and international research primarily focuses on enhancing combustion through passive and active combustion organization methods. Passive combustion organization methods include ramps, supports, and cavities. However, because the effectiveness of passive combustion organization methods is highly dependent on their geometric structure, flow control is limited and imprecise, and the geometric structure intruding into the flow field can lead to significant total pressure losses.

[0004] Traditional active combustion organization methods include transverse jets, pulsed jets, and dielectric barrier discharge (DBD), which offer advantages such as precise control, significant effects, and overcoming energy losses inherent in passive methods. However, they also have some drawbacks. Transverse and pulsed jets primarily rely on mechanical devices or pneumatic systems, resulting in long response times and difficulty adapting to rapidly changing flow field requirements. Furthermore, their operating parameters are typically limited to specific regions, hindering comprehensive control of complex flow fields. DBD discharge may experience significant energy losses during energy transfer, leading to low overall energy utilization efficiency. In contrast, arc plasma jets, driven by an electric field, can respond in an extremely short time, adapting to rapidly changing flow field requirements. Their high temperature and high energy density characteristics enable them to provide powerful thermodynamic effects, effectively exciting the gas-fuel mixture in the flow field and promoting rapid combustion initiation. They directly convert electrical energy into kinetic and thermal energy, reducing energy losses in intermediate stages and improving energy utilization efficiency. By adjusting discharge parameters, arc plasma jets can achieve effective control of flow fields of different scales and complexities, offering greater flexibility. The high-speed jet and pulsating characteristics of plasma jets can disturb the surrounding flow field, increase turbulence, and thus enhance fuel-air mixing. Furthermore, arc plasma jets can generate a large number of high-energy electrons, ions, and free radicals, further enhancing the combustion reaction process, while also broadening the fuel's flammability limit and improving combustion efficiency and flame stability. In summary, arc plasma jets significantly outperform traditional active combustion methods in terms of high temperature and high energy density, response speed, energy utilization efficiency, control range, enhanced mixing, and active particle generation. Summary of the Invention

[0005] To address the problem of low combustion efficiency of solid rocket ramjet engines under wide-range high-speed airflow conditions in the prior art, this invention provides an arc discharge plasma combustion-supporting device for solid rocket ramjet engines, comprising a cathode, an anode, and a casing. The anode is provided with an anode connector, and an anode channel is provided inside the anode. The casing is provided with a flexible hose fastening bolt, and its interior is provided with a first connection hole, a second connection hole, and a third connection hole. A cyclone separator is provided between the first connection hole and the anode channel. A through hole is provided in the middle of the cyclone separator, and several ventilation holes are provided around the through hole. After the cathode passes through the through hole, one end is fixed to the second connection hole and continues to extend into the third connection hole, while the other end extends into the anode channel.

[0006] Furthermore, the anode is provided with sealing threads, and the anode connector is fixed to the anode through the sealing threads; the anode is provided with an anode channel inside.

[0007] Furthermore, the housing is provided with sealing threads, and the hose fastening plug is fixed to the housing through the sealing threads; after the hose fastening plug is fixed to the housing, its connecting end is connected to the first connecting hole.

[0008] Furthermore, the vent is either a straight or oblique hole.

[0009] Furthermore, the hydrocyclone is made of ceramic material.

[0010] Furthermore, the anode channel is 5mm long and 4mm in diameter, and the anode adopts a 45° compression angle design.

[0011] Furthermore, the cathode is made of high-temperature erosion-resistant tungsten material with a diameter of 2mm.

[0012] Furthermore, the casing is made of polytetrafluoroethylene (PTFE) material.

[0013] Furthermore, the hose fastening plug is made of high-strength heat-resistant material.

[0014] Furthermore, the hydrocyclone has a step and an external thread on its surface; the anode channel and the first connecting hole have an internal thread that matches the external thread at one end opening, and the anode channel and the first connecting hole are connected together by the hydrocyclone thread, thereby realizing a detachable connection between the anode and the shell.

[0015] The beneficial effects of this invention are as follows:

[0016] This invention proposes a plasma combustion-enhancing device for solid rocket ramjet engines based on quasi-DC arc plasma. Utilizing the high temperature, chemical reactivity, and aerodynamic characteristics of the plasma jet, it enhances the combustion organization process under wide-range conditions. This combustion-enhancing device design features high reliability, low complexity, and a significant improvement in combustion efficiency, providing a new technical path for the application of solid rocket ramjet engines.

[0017] To address the problems of incomplete combustion, complex structure, slow response, and difficulty in adapting to various operating conditions in existing combustion organization methods, this invention proposes a combustion-aiding method with a simple structure, high integration, and rapid response, which can significantly improve combustion efficiency under various inflow conditions. Through an innovatively designed combustion-aiding device structure, the high temperature, chemical, and aerodynamic effects of the plasma jet are efficiently utilized to enhance the fuel combustion process, providing a new technical solution for achieving high-efficiency combustion under wide operating conditions. 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:

[0019] Figure 1 A three-dimensional schematic diagram of an arc discharge plasma combustion-supporting device for a solid rocket ramjet engine.

[0020] Figure 2 Cross-sectional view of the arc discharge plasma combustion-supporting device for a solid rocket ramjet engine;

[0021] Figure 3 This is a three-dimensional schematic diagram of a hydrocyclone.

[0022] Figure 4 This is a schematic diagram of the hydrocyclone outlet structure.

[0023] Figure 5 This is a cross-sectional view of a straight-hole hydrocyclone.

[0024] Figure 6 This is a cross-sectional view of an inclined-hole hydrocyclone.

[0025] The above figures include the following reference numerals:

[0026] 1. Anode connector; 2. Anode; 21. Anode channel; 3. Hydrocyclone; 31. Through hole; 32. Vent hole; 4. Cathode; 5. Hose fastener; 6. Shell; 61. First connection hole; 62. Second connection hole; 63. Third connection hole. Detailed Implementation

[0027] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0028] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments of the present invention. As used herein, the singular form may also include the plural form unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0029] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the invention. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following figures denote similar items; therefore, once an item is defined in one figure, it need not be further discussed in subsequent figures.

[0030] See Figures 1 to 6 As shown, this invention provides a plasma combustion-supporting device for arc discharge in a solid rocket ramjet engine, comprising a cathode 4, an anode 2, and a casing 6. The outer surface of the anode 2 is provided with sealing threads, and the interior is provided with an anode channel 21. The outer surface of the casing 6 is provided with sealing threads, and the interior is provided with a first connecting hole 61, a second connecting hole 62, and a third connecting hole 63. A cyclone separator 3 is provided between the first connecting hole 61 and the anode channel 21. A through hole 31 is provided in the middle of the cyclone separator 3, and several ventilation holes 32 are provided around the through hole 31. After the cathode 4 passes through the through hole 31, one end is fixed on the second connecting hole 62 and continues to extend into the third connecting hole 63. After the cathode is fixed, the end of the cathode 4 (the protruding end of the cathode 4 in the third connecting hole 63) is connected to the power supply cathode. The other end of the cathode 4 extends from the position of the through hole 31 into the anode channel 21. In addition, the anode connector 1 is fixed to the anode 2 by a sealing thread provided on the anode 2. After the anode connector 1 is fixed, it is connected to the power supply anode through a circuit, thereby providing a stable positive voltage for this device. The hose fastener 5 is fixed to the housing 6 by a sealing thread provided on the housing 6, and the hose fastener 5 penetrates the wall of the housing 6 to connect to the first connection hole 61. In addition, the joint portions of the anode connector 1 and the hose fastener 5 have precisely machined external threads, which are used to achieve a sealed connection with the anode 2 and the housing 6, respectively, to ensure the structural stability of the device.

[0031] In practical use, the housing 6 protects and supports the overall structure of the device, ensuring the sealing of the gas flow path and the arc discharge space. The hose fastener 5 secures the hose, while the other end of the hose connects to an air compressor or gas tank, providing high-pressure, high-speed airflow into the device to maintain the operating conditions required for arc discharge. The cathode 4 provides an electron emission source, forming an arc discharge with the anode 2 to generate high-temperature plasma.

[0032] The cyclone separator 3, positioned between the first connecting hole 61 and the anode channel 21, serves to rectify high-speed airflow and isolate the electrodes. The specific working process is as follows:

[0033] High-speed airflow rectification: The high-speed airflow entering the device from the hose is rectified by the cyclone separator 3 to make the airflow direction consistent with the electrode, ensuring stable interaction between the airflow and the electric arc.

[0034] Electrode isolation: The structure of the cyclone separator 3 can effectively isolate the cathode 4 and the anode 2, preventing the gas flow working fluid from interfering with the arc discharge process and providing electrical insulation protection.

[0035] In addition, it is also possible to install a current probe and a voltage probe at the anode connector 1 and the cathode 4 end (the cathode 4 protruding end located in the third connection hole 63) respectively, to monitor the current and voltage signals provided by the power supply in real time, analyze the electrical characteristics of the arc discharge process, and ensure the stable operation of the device.

[0036] In other words, a high-speed airflow (working fluid) supplied by an air compressor or gas tank enters the device through the hose fastening bolt 5; the cyclone separator 3 rectifies the side-entering airflow to align with the electrode direction, while simultaneously isolating the cathode 4 from the anode 2, ensuring stable airflow and good device insulation; the anode connector 1 is connected to the power supply anode via a circuit, and the end of the cathode 4 (the protruding end of the cathode 4 located in the third connection hole 63) is connected to the power supply cathode via a circuit. Applying a high voltage ionizes the gas, forming an electric arc and generating a high-temperature plasma jet; the plasma jet generated by the arc discharge is ejected at high speed through the anode channel 21. This plasma jet possesses high temperature and high energy characteristics, enabling combustion chamber combustion assistance or solid propellant ignition. Current and voltage probes monitor the current and voltage supplied by the power supply in real time, acquiring arc discharge characteristic data to ensure the controllable and stable operation of the device.

[0037] To simplify the gas and electrical circuitry, the solid rocket ramjet engine arc discharge plasma combustion-enhancing device presented in this paper adopts a side-intake approach. This avoids the complex structure of traditional front-intake devices where the electrical circuitry and gas flow are in the same direction, thus improving the overall compactness of the device. This compact structure allows for application in solid rocket ramjet engines. Previously, plasma jet devices were rarely used in solid engines, primarily in liquid engines or other fields. This device can not only be used for combustion enhancement in engine combustion chambers, but its high-temperature, high-energy characteristics also make it suitable for igniting solid fuels.

[0038] As a preferred option, the number of holes in the hydrocyclone 3 can be varied. The vent holes 32 on the hydrocyclone 3 can be straight or oblique holes, and the inclination angle of the oblique holes can be changed. Based on the different types of holes, the hydrocyclone 3 is divided into straight-hole hydrocyclones 3 and oblique-hole hydrocyclones 3. In practical use, the straight-hole hydrocyclone 3: rectifies the high-speed airflow entering the device into a flow direction consistent with the electrode direction, which is beneficial for stabilizing jet formation and achieving faster excitation. The oblique-hole hydrocyclone 3: introduces a certain radial airflow component to cope with more complex flow fields. Through the design of the holes in the hydrocyclone 3, the adaptability of the plasma combustion device to different operating conditions can be improved.

[0039] As a preferred option, the hydrocyclone 3 is made of ceramic material, which effectively improves the stability and insulation performance of the device in high-temperature environments.

[0040] As a preferred embodiment, the anode channel 21 is 5 mm long and 4 mm in diameter, while the anode 2 adopts a 45° compression angle design, which helps to maintain the stability of the arc discharge and guide the output of the plasma jet.

[0041] As a preferred option, cathode 4 is made of high-temperature erosion-resistant tungsten material with a diameter of about 2mm. Tungsten material has the characteristics of high heat resistance and low ablation rate, which can effectively extend the working life of cathode 4, thereby achieving long-term stable operation.

[0042] As a preferred option, the housing 6 is made of polytetrafluoroethylene (PTFE), which has excellent insulation and high-temperature resistance. In actual use, the internal structure of the housing 6 remains insulated from the electrode portion to prevent arc leakage.

[0043] As a preferred option, the hose fastener 5 is made of high-strength heat-resistant material.

[0044] As a preferred embodiment, the hydrocyclone 3 has a step, and its surface is provided with external threads; that is, the hydrocyclone 3 has both small-diameter and large-diameter threads, while the anode channel 21 and the first connecting hole 61 have internal threads at one end that match the small-diameter and large-diameter threads, respectively, thereby achieving the purpose of detachably connecting the anode 2 and the housing 6 together. In actual use, after disassembling the anode 2 and the housing 6, the internal components of the combustion-supporting device can be easily maintained.

[0045] For ease of description, spatial relative terms such as "above," "on top of," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation beyond the orientation of the device as described in the figures. For example, if the device in the figures were inverted, a device described as "above" or "on top of" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein will be interpreted accordingly.

[0046] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore should not be construed as limiting the scope of protection of this invention.

[0047] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A solid rocket ramjet engine arc discharge plasma combustion-supporting device, characterized in that, The device includes a cathode (4), an anode (2), and a housing (6). The anode (2) has an anode connector (1) at its top and an anode channel (21) inside. The housing (6) has a hose fastening plug (5) on its top and a first connecting hole (61), a second connecting hole (62), and a third connecting hole (63) inside. A hydrocyclone (3) is provided between the first connecting hole (61) and the anode channel (21). A through hole (31) is provided in the middle of the hydrocyclone (3), and several ventilation holes (32) are provided around the through hole (31). After the cathode (4) passes through the through hole (31), one end is fixed to the second connecting hole (62) and continues to extend into the third connecting hole (63), while the other end extends into the anode channel (21). The hydrocyclone (3) has a step and an external thread on its surface; the anode channel (21) and the first connecting hole (61) have an internal thread that matches the external thread at one end opening. The anode channel (21) and the first connecting hole (61) are connected together by the hydrocyclone (3) thread, thereby realizing the detachable connection between the anode (2) and the shell (6).

2. The solid rocket ramjet engine arc discharge plasma combustion aid device according to claim 1, characterized in that, The anode (2) is provided with a sealing thread, and the anode connector (1) is fixed to the anode (2) by the sealing thread.

3. The solid rocket ramjet engine arc discharge plasma combustion aid device according to claim 1, characterized in that, The housing (6) is provided with a sealing thread, and the hose fastener (5) is fixed on the housing (6) by the sealing thread; after the hose fastener (5) is fixed on the housing (6), its connecting end is connected to the first connecting hole (61).

4. The solid rocket ramjet engine arc discharge plasma combustion aid device according to claim 1, characterized in that, The vent (32) is a straight hole or an oblique hole.

5. The solid rocket ramjet engine arc discharge plasma combustion aid device according to claim 1, characterized in that, The hydrocyclone (3) is made of ceramic material.

6. The solid rocket ramjet engine arc discharge plasma combustion aid device according to claim 1, characterized in that, The anode channel (21) is 5 mm long and 4 mm in diameter, and the anode (2) is designed with a 45° compression angle.

7. The solid rocket ramjet engine arc discharge plasma combustion aid device according to claim 1, characterized in that, The cathode (4) is made of high-temperature erosion resistant tungsten material and has a diameter of 2 mm.

8. The solid rocket ramjet engine arc discharge plasma combustion aid device according to claim 1, characterized in that, The shell (6) is made of polytetrafluoroethylene (PTFE) material.

9. The solid rocket ramjet engine arc discharge plasma combustion aid device according to claim 1, characterized in that, The hose fastener (5) is made of high-strength heat-resistant material.

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