Medium channel, rotary detonation engine outer wall and rotary detonation engine

Abstract

The invention discloses a medium channel, a rotary detonation engine outer wall and a rotary detonation engine, and relates to the technical field of rotary detonation engine active thermal protection, the medium channel comprises a first spiral section and a second spiral section which are integrated, and the space curve axis of the first spiral section and the space curve axis of the second spiral section are spiral lines; the screw pitch of the first spiral section is larger than that of the second spiral section, and the section of the first spiral section and the section of the second spiral section are rectangular and consistent in size, and the first spiral section and the second spiral section are consistent in rotating direction. The medium channel is arranged in the outer wall of the rotary detonation engine, and the outer wall of the rotary detonation engine is used for forming the rotary detonation engine. The technical prejudice in the prior art is overcome, the curve-shaped medium channel is applied to the outer wall of the rotary detonation engine, the problem that the straight channel type heat exchange effect is poor can be solved, and the problems that a dead zone is more likely to be formed by curve modeling, wall face cracking is likely to be caused, and sealing failure is likely to be caused can be solved.

Description

Technical Field

[0001] This invention relates to the field of active thermal protection technology for rotary detonation engines, and in particular to the medium channel, the outer wall of a rotary detonation engine, and the rotary detonation engine itself. Background Technology

[0002] Rotating detonation engines utilize supersonic detonation for pressurized combustion, offering advantages such as simple structure, high specific impulse and efficiency, and a wide operating range. The annular combustion chamber is formed by the spaced combustion chamber and central body. Rotating detonation occurs within the annular combustion chamber, which is connected to the exhaust nozzle. High-temperature combustion products expand and are ejected within the exhaust nozzle, providing thrust. The combustion chamber and exhaust nozzle together form the engine's outer wall. Therefore, the high-frequency propagation of the detonation wave leads to severe periodic fluctuations in temperature and pressure across the entire engine's outer wall, resulting in extremely high localized heat load peaks on the engine surface. This poses a significant challenge to the thermal protection of rotating detonation engines.

[0003] Existing technology employs a medium channel within the engine's outer wall, through which a flowing, low-temperature heat exchange medium is introduced to achieve continuous heat absorption and reduce the engine's outer wall temperature. Conventional medium channels are straight-channel type, meaning the channel's axis is completely parallel to the engine's outer wall axis. In this straight-channel structure, the heat exchange medium can only exhibit a single, linear flow pattern, resulting in limited heat exchange efficiency and an inability to quickly balance the localized overheating caused by detonation waves. Furthermore, the engine casing's outer wall is not a uniformly shaped columnar structure; it is often composed of combustion chambers, exhaust nozzles, and other structures of varying diameters. Dead zones in the heat exchange medium's flow are prone to appear at these transition points, reducing heat exchange efficiency and further weakening the medium channel's cooling capacity. While curved channels can increase the flow path length and create turbulence within the coolant to further reduce flow velocity, they are more prone to creating dead zones. Moreover, curved shapes are susceptible to non-uniform deformation and stress concentration at high temperatures, easily leading to wall cracking and seal failure. Clearly, curved channels have more severe negative effects; therefore, despite the defects of the straight-channel type, it remains the preferred design for the medium channel on the outer wall of rotating detonation engines. Summary of the Invention

[0004] The purpose of this invention is to provide a medium channel, the outer wall of a rotary detonation engine, and the rotary detonation engine itself, overcoming the technical biases of existing technologies. The first helical section with a large pitch is located in the combustion chamber section, where the heat load is relatively gentle. This results in relatively low flow resistance and a relatively high coolant velocity, achieving sufficient heat exchange in a short time while balancing flow efficiency and heat exchange effect. The second helical section with a small pitch is located in the tailpipe section, where the heat load is higher. This results in relatively greater flow resistance and a relatively lower coolant velocity, significantly improving the heat transfer coefficient to match the high heat load requirements. Simultaneously, the reduced coolant velocity increases the liquid pressure at the speed-changing section, overcoming the problem of dead zones. The rectangular cross-section structure allows the thermoelastic deformation of the channel to match the thermal deformation of the engine wall, avoiding structural failure caused by stress concentration.

[0005] To achieve the above objectives, the present invention provides the following solution: This invention provides a medium channel disposed within a plate or shell for circulating a heat exchange medium. It includes an integral first helical segment and a second helical segment. Both the spatial curve axes of the first and second helical segments are helices, and the pitch of the spatial curve axis of the first helical segment is greater than the pitch of the spatial curve axis of the second helical segment. A cross-section perpendicular to the spatial curve axis of the first helical segment is a first cross-section, and all dimensions of the first cross-section are identical. A cross-section perpendicular to the spatial curve axis of the second helical segment is a second cross-section, and all dimensions of the second cross-section are identical. Both the first and second cross-sections are rectangular. The helical directions of the first and second helical segments are consistent.

[0006] The present invention also provides an outer wall of a rotating detonation engine, comprising a combustion chamber section, a tailpipe section, and the aforementioned medium channel. The combustion chamber section and the tailpipe section are coaxially arranged, and the combustion chamber outlet is sealed to the tailpipe inlet. The combustion chamber outlet and the tailpipe inlet have the same shape and size. The medium channel is equidistantly arranged circumferentially around the axes of the combustion chamber section and the tailpipe section within the combustion chamber section and the tailpipe section. A first helical section is located within the wall of the combustion chamber section, and the inlet of the first helical section is located in the plane where the combustion chamber inlet is located. A second helical section is located within the wall of the tailpipe section, and the outlet of the second helical section is located in the plane where the tailpipe outlet is located. The thickness of the wall on the combustion chamber section located outside the first cross-section is greater than the thickness of the wall located inside the first cross-section, and the thickness of the wall on the tailpipe section located outside the second cross-section is greater than the thickness of the wall located inside the second cross-section.

[0007] In one embodiment, the combustion chamber section is a circular tubular structure, and the dimensions and shapes of each radial section of the combustion chamber section are consistent. The tail nozzle section is a Laval nozzle, and the size of the tail nozzle inlet is smaller than the size of the tail nozzle outlet.

[0008] In one embodiment, the combined length of the combustion chamber section and the tailpipe section along the axial direction is 650 mm to 720 mm; the inner diameter of the combustion chamber section is 160 mm to 175 mm; the wall thickness of the combustion chamber section is 5 mm to 7 mm; the wall thickness of the tailpipe section is 5 mm to 7 mm; the length of the first cross-section is 2 mm to 4 mm; the width of the first cross-section is 2 mm to 4 mm; the height of the first cross-section is 1 mm to 3 mm; the thickness of the wall on the outer side of the first cross-section of the combustion chamber section is 0.5 mm to 0.7 mm greater than the thickness of the wall on the inner side of the first cross-section; the thickness of the wall on the outer side of the second cross-section of the tailpipe section is 0.5 mm to 0.7 mm greater than the thickness of the wall on the second cross-section; the number of medium channels is 100 to 140; the pitch of the first helical section is 1200 mm to 1800 mm; and the pitch of the second helical section is 600 mm to 900 mm.

[0009] In one embodiment, the pitch of the first helical segment is twice the pitch of the second helical segment.

[0010] In one embodiment, the number of medium channels is linearly proportional to the pitch of the first helical segment.

[0011] In one embodiment, the first helical segment 1 rotates in a clockwise or counterclockwise direction.

[0012] In one embodiment, the system further includes a collector and a return pipe. The collector is disposed on the wall of the tailpipe outlet. The collector is sealed to the tailpipe section, and the outlet of the second spiral section communicates with the cavity inside the collector. The inlet of the return pipe communicates with the cavity inside the collector, and the pipe body of the return pipe is fixed to the outside of the combustion chamber section and the tailpipe section.

[0013] In one embodiment, the radial cross-section of the cavity within the collector is a third cross-section, the third cross-section being rectangular, the length of the third cross-section being 12 mm to 18 mm, the width of the third cross-section being 12 mm to 18 mm, and the height of the third cross-section being 10 mm to 14 mm; the return pipes are arranged equidistantly along the axial direction of the collector, the number of the return pipes being 4 to 8, and the inner diameter of the return pipes being 10 mm to 14 mm.

[0014] The present invention also provides a rotating detonation engine, including a propellant injection system, an initiation device, a coolant circulation device, and the aforementioned rotating detonation engine outer wall. The initiation device is disposed within the combustion chamber section. The propellant injection system is used to provide a combustible mixture to the initiation device. The coolant circulation device is used to drive the coolant circulating within the rotating detonation engine outer wall.

[0015] The present invention achieves the following technical effects compared to the prior art: This invention provides a medium channel, the outer wall of a rotary detonation engine, and a rotary detonation engine, overcoming the technical biases of existing technologies by using an integrated medium channel comprising two helical flow channels. The first helical section with a large pitch is located in the combustion chamber section where the heat load is relatively gentle, resulting in relatively low flow resistance and relatively high coolant velocity, achieving sufficient heat exchange in a short time while balancing flow efficiency and heat exchange effect. The second helical section with a small pitch is located in the tailpipe section where the heat load is higher, resulting in relatively greater flow resistance and relatively lower coolant velocity, significantly improving the heat transfer coefficient to match the high heat load requirements. Simultaneously, the reduced coolant velocity increases the liquid pressure at the speed-changing section, overcoming the problem of dead zones. The rectangular cross-section structure allows the thermoelastic deformation of the channel to match the thermal deformation of the engine wall, avoiding structural failure caused by stress concentration. The coolant within the helical flow channel easily forms turbulence, and the smaller the pitch, the more pronounced the turbulence effect. Turbulence hinders coolant flow, increases the coolant's heat absorption time, and improves the heat exchange effect. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the external mechanism of the outer wall of a rotary detonation engine according to an embodiment of the present invention; Figure 2 This is a schematic diagram of the first side structure of the outer wall of a rotating detonation engine, which shows the medium channel through a perspective effect, according to an embodiment of the present invention. Figure 3 This is a schematic diagram of a first lateral structure with an independently displayed medium channel in an embodiment of the present invention; Figure 4 This is a schematic diagram of the second lateral structure of the outer wall of a rotating detonation engine, which displays the medium channel through a perspective effect, according to an embodiment of the present invention. Figure 5This is a schematic diagram of a second lateral structure in which the medium channel is independently displayed in an embodiment of the present invention; Figure 6 This is a front view schematic diagram of a combustion chamber inlet direction according to an embodiment of the present invention; Figure 7 This is a front view schematic diagram of a combustion chamber inlet direction with the medium channel independently displayed in an embodiment of the present invention; Figure 8 This is a front view schematic diagram of the tail nozzle outlet direction in an embodiment of the present invention; Figure 9 This is a front view schematic diagram of the tail nozzle outlet direction, which is independently displayed in an embodiment of the present invention.

[0018] Among them, 1. First spiral section; 2. Second spiral section; 3. Combustion chamber section; 4. Tail nozzle section; 5. Combustion chamber outlet; 6. Combustion chamber inlet; 7. Tail nozzle outlet; 8. Collector; 9. Return pipe. Detailed Implementation

[0019] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0020] It should be understood that the structures, proportions, sizes, etc., depicted in the accompanying drawings of this specification are merely for illustrative purposes to aid those skilled in the art and are not intended to limit the implementation conditions of the invention. Therefore, they have no substantial technical significance. Any modifications to the structure, changes in proportions, or adjustments to size, without affecting the effectiveness and purpose of the invention, should still fall within the scope of the technical content disclosed in this invention. In the description of this invention, it should be understood that the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings. They are merely for the convenience of describing the invention 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 the invention. Furthermore, the terms "first," "second," and "third," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Thus, features defined with "first," "second," etc., may explicitly or implicitly include one or more of those features. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0021] It should also be noted that in the embodiments of this application, the same reference numerals are used to denote the same component or the same part.

[0022] The purpose of this invention is to provide a medium channel, a rotating detonation engine outer wall, and a rotating detonation engine, overcoming the technical biases of existing technologies. It utilizes an integrated medium channel comprising two helical flow paths. The first helical section with a large pitch is located in the combustion chamber section where the heat load is relatively gentle, resulting in relatively low flow resistance and relatively high coolant velocity, achieving sufficient heat exchange in a short time while balancing flow efficiency and heat exchange effect. The second helical section with a small pitch is located in the tailpipe section where the heat load is higher, resulting in relatively greater flow resistance and relatively lower coolant velocity, significantly improving the heat transfer coefficient to match the high heat load requirements. Simultaneously, the reduced coolant velocity increases the liquid pressure at the speed-changing section, overcoming the problem of dead zones. The rectangular cross-section structure allows the thermoelastic deformation of the channel to match the thermal deformation of the engine wall, avoiding structural failure caused by stress concentration.

[0023] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0024] Example 1 like Figures 1 to 9As shown, the present invention provides a medium channel disposed within a plate or shell for the flow of a heat exchange medium. It includes an integral first helical segment 1 and a second helical segment 2. Both the spatial curve axis of the first helical segment 1 and the spatial curve axis of the second helical segment 2 are helices. The pitch of the spatial curve axis of the first helical segment 1 is greater than the pitch of the spatial curve axis of the second helical segment 2. A cross-section perpendicular to the spatial curve axis of the first helical segment 1 is a first cross-section, and all dimensions of the first cross-section are identical. A cross-section perpendicular to the spatial curve axis of the second helical segment 2 is a second cross-section, and all dimensions of the second cross-section are identical. Both the first and second cross-sections are rectangular. The rotation directions of the first helical segment 1 and the second helical segment 2 are the same.

[0025] The medium channel provided in this application can be used to introduce gaseous, liquid, and other flowable heat exchange media. When used for cooling, the temperature of the heat exchange medium should be lower than the target temperature; when used for heating, the temperature of the heat exchange medium should be higher than the target temperature. The curved channel allows the heat exchange medium to exhibit a curved trajectory, thus easily generating turbulence to slow its flow and increase heat exchange time. The intensity and quantity of turbulence are related to the pitch at its location; the smaller the pitch, the more pronounced the turbulence. The shape and size of the cross-section at all locations within the medium channel are completely consistent, preventing sudden changes in the area of ​​the heat exchange medium and eliminating other uncertainties affecting flow. The first helical section 1 and the second helical section 2 rotate in the same direction, avoiding the loss of power during reversal and ensuring the flow of the heat exchange medium. At the variable pitch cross-section, the impact force of the heat exchange medium is enhanced, further ensuring its flow, avoiding dead zones, and maintaining a balance between the turbulence slowing effect and the flow.

[0026] It should be noted that "integrated" means that the media channel is set in a whole plate or shell, and the media channel is not spliced.

[0027] It should be noted that the axis of the spatial curve is the geometric center baseline of the medium channel.

[0028] It should be noted that, in Figures 2 to 5 The intersecting medium channels are not actually adjacent medium channels intersecting, but rather an illusion created by the projection of the cylindrical three-dimensional structure onto the horizontal plane under perspective.

[0029] Example 2 like Figures 1 to 9As shown, the present invention also provides an outer wall of a rotating detonation engine, including a combustion chamber section 3, a tailpipe section 4, and the aforementioned medium channel. The combustion chamber section 3 and the tailpipe section 4 are coaxially arranged, and the combustion chamber outlet 5 is sealed to the tailpipe inlet. The combustion chamber outlet 5 and the tailpipe inlet have the same shape and size. The medium channel is equidistantly arranged circumferentially around the axes of the combustion chamber section 3 and the tailpipe section 4. A first helical section 1 is located within the wall of the combustion chamber section 3, and the inlet of the first helical section 1 is located in the plane where the combustion chamber inlet 6 is located. A second helical section 2 is located within the wall of the tailpipe section 4, and the outlet of the second helical section 2 is located in the plane where the tailpipe outlet 7 is located. The thickness of the wall on the combustion chamber section 3 located outside the first cross-section is greater than the thickness of the wall located inside the first cross-section. The thickness of the wall on the tailpipe section 4 located outside the second cross-section is greater than the thickness of the wall located inside the second cross-section.

[0030] Working principle: The inlet and outlet of the medium channel are located on the plane of the combustion chamber inlet 6 and the plane of the tail nozzle outlet 7, respectively. The heat exchange medium flows from the front to the rear, passing over the outer wall of the rotating detonation engine to achieve complete coverage and eliminate heat absorption dead zones. The large pitch design of the first helical section 1 makes the helical channel approach a straight channel while retaining the helical curvature. Due to the constraint of the channel's spatial curve, the heat exchange medium generates a large-scale circulation around the channel axis. At the same time, the high-speed flow brought about by low flow resistance provides kinetic energy for turbulence generation. In addition, the large-pitch helical channel still has continuous helical guiding characteristics. When the coolant flows along the channel axis, it will be affected by the helical tangential force of the channel wall, deviating from the straight flow trajectory and forming a regular large-scale circulation along the channel cross-section. This circulation will break the laminar boundary layer of the coolant in the channel, allowing the high-temperature coolant in the center of the channel to fully mix with the low-temperature coolant on the channel wall, creating conditions for the generation of small-scale turbulence. The first helical section 1 features a small-pitch design. The helix angle of this small-pitch channel is much larger than that of the first helical section 1. The flow trajectory of the heat exchange medium needs to make more rapid turns along with the channel. The originally stable large-scale circulation is repeatedly cut and compressed by the channel wall, breaking into numerous irregular small-scale turbulent vortices. The generation, development, and dissipation of these vortices are significantly accelerated. This intense turbulence completely destroys the laminar boundary layer between the coolant and the channel wall, forming an extremely thin turbulent boundary layer, which greatly improves the convective heat transfer efficiency between the heat exchange medium and the channel wall. The outer wall of a rotating detonation engine deforms and experiences stress concentration after being heated and impacted. The rectangular cross-section structure allows the thermoelastic deformation of the channel to match the thermal deformation of the engine wall, preventing structural failure caused by stress concentration. The deformed medium channel applies pressure to the heat exchange medium, promoting its flow. However, it also creates irregular structures, increasing the probability and effectiveness of turbulence generation, and hindering its flow. The combined effect of these promoting and hindering forces maintain the flow velocity of the heat exchange medium within a suitable range, allowing it to effectively absorb heat and carry it away, achieving a good cooling effect. To achieve expansion injection, the tail nozzle section 4 is often a multi-conical tube combination structure with constricted ends. Abrupt geometric changes occur at the junction of the combustion chamber section 3 and the tail nozzle section 4, easily leading to flow dead zones. In this invention, the pitch of the first helical section 1 is greater than that of the second helical section 2. The heat exchange medium experiences a deceleration effect as it enters the second helical section 2 from the first helical section 1, and the increased force through the interface between the first and second helical sections 1 and 2 prevents the formation of dead zones. The shape and size of the combustion chamber outlet 5 and the tail nozzle inlet, eliminating other irregular structures at the interface between the first and second helical sections 1 and 2, also effectively prevent the formation of dead zones.

[0031] It should be noted that, due to a technical bias in the art that curved media channels are unsuitable for the outer walls of rotating detonation engines, people tend to disregard the possibility of a specific curved shape being applicable. This invention overcomes this technical bias by employing a technique that was abandoned due to this bias, thereby solving the technical problem. Furthermore, this invention overcomes the technical bias not only by simply using a curved media channel not used in the prior art, but also because this curved media channel effectively matches the combustion effects of the combustion chamber section 3 and the tailpipe section 4, eliminates dead zones in the heat exchange medium flow, effectively matches the thermal deformation of the engine wall, and balances the compression acceleration and turbulence resistance of the heat exchange medium during deformation.

[0032] In one embodiment, the combustion chamber section 3 is a circular tubular structure, with all radial cross-sections of the combustion chamber section 3 having the same size and shape. The tail nozzle section 4 is a Laval nozzle, with the inlet size smaller than the outlet size. Since this invention is based on the principle of rotary detonation, the circular tubular structure of the combustion chamber section 3 can form a uniformly spaced annular combustion chamber, providing stable and uniform power, and the heat and impact generated by rotary detonation are relatively uniform. The undeformed circular tubular structure does not have any obvious locations where heat concentration occurs, and even if deformed, the heat concentration effect is weaker than other structures, making it more suitable for rotary detonation engines. The Laval nozzle includes a converging section, a throat, and a diverging section connected sequentially. The converging section extends from the inlet to the throat, characterized by a gradually decreasing radial cross-sectional area. The throat is the point where the radial cross-sectional area of ​​the entire nozzle is the smallest, resulting in congested flow. The diverging section extends from the throat to the outlet, characterized by a gradually increasing radial cross-sectional area. The Laval nozzle operates on the principle of utilizing the flow characteristics of compressible gases. Through a convergent-divergent cross-sectional area change, the internal and pressure energy of the gas is converted into kinetic energy, achieving continuous acceleration from subsonic to supersonic speeds. In this invention, the high-temperature combustion products are first compressed and then expanded before being ejected into the tailpipe section 4, thereby generating sufficient thrust. The inlet of the converging section of tailpipe section 4 is the tailpipe inlet.

[0033] In one embodiment, the combined length of the combustion chamber section 3 and the tail nozzle section 4 along the axial direction is 650 mm to 720 mm, the inner diameter of the combustion chamber section 3 is 160 mm to 175 mm, the wall thickness of the combustion chamber section 3 is 5 mm to 7 mm, the wall thickness of the tail nozzle section 4 is 5 mm to 7 mm, the length of the first cross section is 2 mm to 4 mm, the width of the first cross section is 2 mm to 4 mm, the height of the first cross section is 1 mm to 3 mm, the thickness of the wall on the outer side of the first cross section of the combustion chamber section 3 is 0.5 mm to 0.7 mm more than the thickness of the wall on the inner side of the first cross section, the thickness of the wall on the outer side of the second cross section of the tail nozzle section 4 is 0.5 mm to 0.7 mm more than the thickness of the wall on the second cross section, the number of medium channels is 100 to 140, the pitch of the first helical section 1 is 1200 mm to 1800 mm, and the pitch of the second helical section 2 is 600 mm to 900 mm.

[0034] Simulation verification parameters and results: The heat exchange medium is low-temperature kerosene. The inlet temperature of the medium channel is 300 Kelvin, and the inlet flow rate is 0.8 kg / s. The pitch of the first spiral section 1 in combustion chamber section 3 is 1500 mm, and the maximum flow velocity of the heat exchange medium is 13.2 m / s. The pitch of the second spiral section 2 in tail nozzle section 4 is 750 mm, and the maximum flow velocity of the heat exchange medium is 9.8 m / s. Compared with the equal pitch design, the flow velocity of the heat exchange medium in the first spiral section 1 increases by 3.1% while the flow resistance only increases by 3.2%, and the heat transfer coefficient increases by 5.1%. The wall temperature at combustion chamber outlet 5 is controlled at 712 Kelvin, which is 13 Kelvin lower than the equal pitch design. The flow velocity of the heat exchange medium in the second spiral section 2 decreases by 23.4%, the liquid pressure increases by 34.7%, the heat transfer coefficient increases by 49.3%, and the wall temperature at tail nozzle outlet 7 is controlled at 735 Kelvin, which is 93 Kelvin lower than the equal pitch design. The maximum thermal stress decreases by 27.9%. It is evident that, after applying the medium channel proposed in this invention, the heat exchange efficiency of the outer wall of the rotating detonation engine is significantly improved, overcoming the problem of flow dead zones appearing at the deformation locations of the wall.

[0035] In one embodiment, the pitch of the first helical segment 1 is preferably twice the pitch of the second helical segment 2.

[0036] In one embodiment, the number of medium channels is preferably linearly proportional to the pitch of the first helical segment 1. The larger the pitch, the closer it is to a straight channel, and the more medium channels can be accommodated. While retaining the preference for curved channels, the heat exchange efficiency is directly improved by increasing the total amount of heat exchange medium.

[0037] In one embodiment, the first helical segment 1 rotates in a clockwise or counterclockwise direction.

[0038] In one embodiment, the system further includes a collector 8 and a return pipe 9. The collector 8 is disposed on the wall of the tail nozzle outlet 7, and is sealed to the tail nozzle section 4. The outlet of the second spiral section 2 communicates with the cavity inside the collector 8. The inlet of the return pipe 9 communicates with the cavity inside the collector 8, and the pipe body of the return pipe 9 is fixed to the outside of the combustion chamber section 3 and the tail nozzle section 4. The collector 8 and the return pipe 9 can recover the heat exchange medium, realizing the recycling of the heat exchange medium. Although the collector 8 is also affected by high temperatures, the heat exchange medium inside it can absorb heat, ensuring the structural reliability of the collector 8.

[0039] In one embodiment, the radial section of the cavity inside the collector 8 is a third section, which is rectangular, with a length of 12 mm to 18 mm, a width of 12 mm to 18 mm, and a height of 10 mm to 14 mm. The return pipes 9 are arranged equidistantly along the axial direction of the collector 8, with a number of 4 to 8, and an inner diameter of 10 mm to 14 mm.

[0040] In one embodiment, the maximum diameter of the tailpipe section 4 is located at the tailpipe outlet 7, and the maximum diameter of the tailpipe 4 is greater than the maximum diameter of the combustion chamber section 3. Therefore, in Figure 6 and Figure 7 The combustion chamber inlet 6, the manifold 8, and the return pipe 9 can be seen simultaneously. Figure 7 The first helical segment 1 and the second helical segment 2 can be seen simultaneously. It should also be noted that... Figure 7 In the diagram, the first helical segment 1 and the second helical segment 2 have opposite bending directions, but this does not mean that the first helical segment 1 and the second helical segment 2 have opposite rotation directions. The first helical segment 1 and the second helical segment 2 are a single helical structure. As the axis of the spatial curve deflects continuously, the bending direction changes.

[0041] Example 3 like Figures 1 to 9 As shown, the present invention provides a rotary detonation engine, including a propellant injection system, an initiation device, a coolant circulation device, and the aforementioned rotary detonation engine outer wall. The initiation device is disposed in the combustion chamber section 3. The propellant injection system is used to provide a combustible mixture to the initiation device, and the coolant circulation device is used to drive the coolant circulating within the rotary detonation engine outer wall.

[0042] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0043] If this invention discloses or relates to components or structural parts that are fixedly connected to each other, then, unless otherwise stated, a fixed connection can be understood as: a fixed connection that can be detached (e.g., using bolts or screws), or a fixed connection that cannot be detached (e.g., riveting, welding). Of course, a fixed connection can also be replaced by an integral structure (e.g., manufactured in one piece using a casting process) (except where it is obviously impossible to use an integral molding process).

[0044] In addition, unless otherwise stated, the terms used in any of the technical solutions disclosed in this invention to indicate positional relationships or shapes include states or shapes that are similar to, close to, or approximate with those states or shapes.

[0045] Any component provided by this invention can be assembled from multiple individual components or can be a single component manufactured by a one-piece molding process.

[0046] Any adaptive changes made according to actual needs are within the scope of protection of this invention.

[0047] It should be noted that, for those skilled in the art, it is obvious that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0048] Specific examples have been used to illustrate the principles and implementation methods of this invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of this invention. Furthermore, those skilled in the art will recognize that, based on the ideas of this invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of this invention.

Claims

1. A medium channel, disposed within a plate or shell, for circulating a heat exchange medium, characterized in that: It includes an integral first helical segment (1) and a second helical segment (2), the spatial curve axis of the first helical segment (1) and the spatial curve axis of the second helical segment (2) are both helices, and the pitch of the spatial curve axis of the first helical segment (1) is greater than the pitch of the spatial curve axis of the second helical segment (2). The cross section perpendicular to the spatial curve axis of the first helical segment (1) is the first cross section, and the dimensions of any first cross section are completely identical. The cross section perpendicular to the spatial curve axis of the second helical segment (2) is the second cross section, and the dimensions of any second cross section are completely identical. Both the first cross section and the second cross section are rectangular. The first helical segment (1) and the second helical segment (2) have the same direction of rotation.

2. An outer wall of a rotating detonation engine, characterized in that: It includes a combustion chamber section (3), a tail nozzle section (4) and the medium channel as described in claim 1. The combustion chamber section (3) and the tail nozzle section (4) are coaxially arranged. The combustion chamber outlet (5) is sealed to the tail nozzle inlet. The combustion chamber outlet (5) and the tail nozzle inlet have the same shape and size. The medium channel is equidistantly arranged around the axis of the combustion chamber section (3) and the tail nozzle section (4) within the combustion chamber section (3) and the tail nozzle section (4). The first spiral section (1) is located in the wall of the combustion chamber section (3), and the inlet of the first spiral section (1) is located in the plane of the combustion chamber inlet (6). The second spiral section (2) is located in the wall of the tail nozzle section (4), and the outlet of the second spiral section (2) is located in the plane of the tail nozzle outlet (7). The thickness of the wall on the combustion chamber section (3) located outside the first cross section is greater than the thickness of the wall located inside the first cross section, and the thickness of the wall on the tail nozzle section (4) located outside the second cross section is greater than the thickness of the wall located inside the second cross section.

3. The outer wall of the rotating detonation engine according to claim 2, characterized in that: The combustion chamber section (3) is a circular tube structure. The dimensions and shapes of each radial section of the combustion chamber section (3) are consistent. The tail nozzle section (4) is a Laval nozzle. The size of the tail nozzle inlet is smaller than the size of the tail nozzle outlet (7).

4. The outer wall of the rotating detonation engine according to claim 3, characterized in that: The combined length of the combustion chamber section (3) and the tail nozzle section (4) along the axial direction is 650 mm to 720 mm. The inner diameter of the combustion chamber section (3) is 160 mm to 175 mm. The wall thickness of the combustion chamber section (3) is 5 mm to 7 mm. The wall thickness of the tail nozzle section (4) is 5 mm to 7 mm. The length of the first cross section is 2 mm to 4 mm. The width of the first cross section is 2 mm to 4 mm. The height of the first cross section is 1 mm to 3 mm. The wall thickness of the combustion chamber section (3) located outside the first cross section is 0.5 mm to 0.7 mm thicker than the wall thickness of the combustion chamber section (3) located inside the first cross section. The wall thickness of the tail nozzle section (4) located outside the second cross section is 0.5 mm to 0.7 mm thicker than the wall thickness of the combustion chamber section (3) located inside the second cross section. The number of media channels is 100 to 140, the pitch of the first helical segment (1) is 1200 mm to 1800 mm, and the pitch of the second helical segment (2) is 600 mm to 900 mm.

5. The outer wall of the rotating detonation engine according to claim 4, characterized in that: The pitch of the first helical segment (1) is twice the pitch of the second helical segment (2).

6. The outer wall of the rotating detonation engine according to claim 5, characterized in that: The number of media channels is linearly proportional to the pitch of the first helical segment (1).

7. The outer wall of the rotating detonation engine according to claim 2, characterized in that: The first spiral segment (1) rotates in either a clockwise or counterclockwise direction.

8. The outer wall of the rotating detonation engine according to claim 2, characterized in that: It also includes a collector (8) and a return pipe (9). The collector (8) is disposed on the wall of the tail nozzle outlet (7). The collector (8) is sealed to the tail nozzle section (4) and the outlet of the second spiral section (2) is connected to the cavity inside the collector (8). The inlet of the return pipe (9) is connected to the cavity inside the collector (8). The pipe body of the return pipe (9) is fixed to the outside of the combustion chamber section (3) and the tail nozzle section (4).

9. The outer wall of the rotating detonation engine according to claim 8, characterized in that: The radial section of the cavity inside the collector (8) is a third section, the third section is rectangular, the length of the third section is 12 mm to 18 mm, the width of the third section is 12 mm to 18 mm, and the height of the third section is 10 mm to 14 mm; The return pipes (9) are arranged equidistantly along the axial direction of the collector (8), and the number of return pipes (9) is 4 to 8, with an inner diameter of 10 mm to 14 mm.

10. A rotary detonation engine, characterized in that: It includes a propellant injection system, an initiation device, a coolant circulation device, and the outer wall of the rotating detonation engine as described in claims 2-9. The initiation device is disposed in the combustion chamber section (3). The propellant injection system is used to provide a combustible mixture to the initiation device. The coolant circulation device is used to drive the coolant circulating within the outer wall of the rotating detonation engine.

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