A nozzle and injection system for a rotary detonation engine

Abstract

This application provides a nozzle and injection system for a rotating detonation engine, relating to the field of aerospace propulsion system engine technology. The nozzle for a rotating detonation engine includes: a nozzle body having an axially aligned inlet end and an outlet end, with a through-flow Tesla valve flow channel formed between the inlet and outlet ends; and a partition plate disposed within the nozzle body and radially connected to it, dividing the Tesla valve flow channel into a first flow path and a second flow path; wherein the first and second flow paths are configured to allow fluid to flow from the inlet end to the outlet end and to prevent fluid from flowing back from the outlet end to the inlet end. The nozzle provided in this application, used in a rotating detonation engine, achieves high-frequency adaptive backflow prevention without moving parts, while also providing advantages such as thermal protection, atomization mixing, and system lightweighting, thus facilitating high-performance and high-reliability operation of the rotating detonation engine.

Description

Technical Field

[0001] This invention relates to the field of aerospace propulsion system engine technology, and in particular to a nozzle and injection system for a rotating detonation engine. Background Technology

[0002] Rotating Detonation Engine (RDE) utilizes detonation waves propagating circumferentially along the annular combustion chamber to achieve combustion pressurization. It has advantages such as high thermal cycle efficiency and compact structure, and has important application prospects in the field of aerospace propulsion.

[0003] As the core component of the rotary detonation engine injection system, the nozzle can inject liquid propellant into the combustion chamber to participate in the detonation reaction. During its operation, when the detonation wave repeatedly sweeps across the nozzle, it will generate high temperature and high pressure impact, which can easily cause the gas to flow back into the propellant supply channel, causing pressure oscillations in the supply system or even backfire and explosion.

[0004] To combat gas backflow, existing technologies primarily employ the following injection schemes: One type uses high-pressure drop direct current / centrifugal nozzles, which generate a high injection pressure drop through extremely small injection orifice diameters or complex centrifugal channels, utilizing "pneumatic blocking" or "critical flow" effects to resist detonation pressure peaks. However, this scheme requires a supply pressure significantly higher than the detonation peak, resulting in a bulky booster system and a reduced thrust-to-weight ratio. Furthermore, when backflow occurs, high-temperature gas easily penetrates deep into the nozzle orifice, and due to the small heat exchange area and low heat exchange efficiency of the nozzle, the end face and flow channel are easily eroded. Another type uses impact injectors, which utilize the impact of multiple fluid streams to form a liquid fan, relying on momentum balance to block backflow. However, impact injectors are sensitive to pressure fluctuations; when the detonation wave manifests as a high-pressure pulse, the fluid momentum barrier is easily breached, leading to gas backflow causing pressure oscillations or even backfire explosions. Moreover, the difference between forward and reverse flow resistance is small, lacking the ideal control characteristics of "low resistance in the forward direction and high resistance in the reverse direction," resulting in significant flow loss during the filling stage and weak resistance to backflow. In addition, there are solutions that install moving parts such as mechanical check valves in the fluid supply pipeline. However, the moving parts have a large mass inertia, resulting in a lag in dynamic response during injection. They cannot adapt to high-frequency oscillations of several kilohertz and are prone to fatigue failure at high temperatures.

[0005] In view of the above, this application is hereby submitted. Summary of the Invention

[0006] This application provides a nozzle and injection system for a rotary detonation engine, aiming to solve at least one of the defects existing in the prior art.

[0007] This application provides a nozzle for a rotary detonation engine, comprising: a nozzle body having an axially opposite inlet end and an outlet end, with a through Tesla valve flow channel formed between the inlet end and the outlet end; and a partition plate disposed within the nozzle body and radially connected to the nozzle body to divide the Tesla valve flow channel into a first flow path and a second flow path that are independent of each other; wherein the first flow path and the second flow path are configured to allow fluid to flow from the inlet end to the outlet end and to prevent fluid from flowing back from the outlet end to the inlet end.

[0008] By optimizing the nozzle structure, a through Tesla valve flow channel is set in the nozzle body, and a partition plate is used to divide it into an independent first flow path and a second flow path. Each flow path has the fluid diode characteristics of "low resistance in the forward direction and high resistance in the reverse direction", so as to realize the high-frequency adaptive anti-backflow function without moving parts.

[0009] In some embodiments, the outlets of the first flow path and the second flow path converge toward the central axis of the nozzle body towards the outlet end of the nozzle body, so that the fluids ejected from the first flow path and the second flow path collide with each other.

[0010] In some embodiments, the nozzle body includes a nozzle housing, a nozzle core, and multiple flow guiding units; the nozzle core is disposed inside the nozzle housing and is radially spaced from the nozzle housing; a partition plate is radially connected between the nozzle housing and the nozzle core; multiple flow guiding units are sequentially arranged axially between the nozzle housing and the nozzle core and are connected to the partition plate, so as to form a Tesla valve flow channel together with the inner wall of the nozzle housing and the outer wall of the nozzle core.

[0011] In some embodiments, each flow guiding unit includes an inner flow guiding island and an outer flow guiding island; an inner flow channel is formed between the inner flow guiding island and the outer wall of the nozzle core, and an outer flow channel is formed between the outer flow guiding island and the inner wall of the nozzle housing, and a main flow path is formed between the inner flow guiding island and the outer flow guiding island; both ends of the inner flow channel and the outer flow channel are connected to the main flow path, and the inner flow guiding islands and outer flow guiding islands of adjacent flow guiding units are staggered in the axial direction, so as to force the fluid to divert into the inner flow channel and / or the outer flow channel to generate a turning countercurrent when the fluid flows back from the outlet end to the inlet end.

[0012] In some implementations, both the inner and outer guide islands have axially cross-sections with a rounded end toward the inlet and a tapered end toward the outlet.

[0013] Another aspect of this application provides an injection system for a rotary detonation engine, including a plurality of nozzles as described above, and further comprising: a mounting assembly having a plurality of nozzle mounting holes axially spaced around the mounting assembly, each nozzle mounting hole housing one nozzle, and the mounting assembly having an oxidizer distribution channel; an outer casing of the combustion chamber, fitted onto the mounting assembly and forming a combustion chamber together with the mounting assembly, the nozzle outlet end located within the combustion chamber; and an oxidizer rectifier headplate connected to one axial end of the mounting assembly, the oxidizer rectifier headplate having an oxidizer injection port, the oxidizer injection port being connected to the oxidizer distribution channel. The system includes: a liquid distribution channel; a dual-channel liquid collection ring fitted onto the mounting base assembly and positioned axially between the mounting base assembly and the oxidizer rectifier head plate; a fuel distribution ring fitted onto the dual-channel liquid collection ring and positioned axially between the combustion chamber outer shell and the oxidizer rectifier head plate, with a fuel injection port on the fuel distribution ring; wherein, a first liquid collection chamber is formed between the dual-channel liquid collection ring and the mounting base assembly, the first liquid collection chamber being connected to the oxidizer distribution channel and to the first flow path of each nozzle; a second liquid collection chamber is formed between the dual-channel liquid collection ring and the fuel distribution ring, the second liquid collection chamber being connected to the fuel injection port and to the second flow path of each nozzle.

[0014] In some embodiments, the dual-channel liquid collecting ring includes an injection section, an annular groove section, and a connecting section connected sequentially along the axial direction. The injection section is located axially between the annular groove section and the nozzle mounting hole, and is fitted together with the annular groove section on the mounting base assembly. The outer circumferential surface of the annular groove section has an outer annular groove extending circumferentially, and the inner circumferential surface has an inner annular groove extending circumferentially. A second liquid collecting cavity is formed between the outer annular groove and the inner wall of the fuel distribution ring, and a first liquid collecting cavity is formed between the inner annular groove and the outer wall of the mounting base assembly. The connecting section is located axially between the annular groove section and the oxidizer rectifier head plate, and is connected to the mounting base assembly, the fuel distribution ring, and the oxidizer rectifier head plate, respectively. The injection section has multiple pairs of circumferentially spaced first injection holes and second injection holes. The first injection holes penetrate the injection section and communicate with the first liquid collecting cavity, and the second injection holes penetrate the injection section and communicate with the second liquid collecting cavity. Each first injection hole communicates with the first flow path of the corresponding nozzle, and each second injection hole communicates with the second flow path of the corresponding nozzle.

[0015] In some embodiments, the mounting assembly includes a central cone, a nozzle mounting portion, and an oxidizer distribution portion; the central cone portion is disposed inside the outer casing of the combustion chamber and is radially spaced from the outer casing of the combustion chamber to form a combustion chamber; the nozzle mounting portion protrudes radially from the circumference of the central cone and is located axially at one end of the combustion chamber, and a plurality of nozzle mounting holes are circumferentially spaced on the nozzle mounting portion; the oxidizer distribution portion is disposed at one end of the central cone, and the end opposite to the central cone is connected to the oxidizer rectifier head plate; a dual-channel liquid collecting ring is sleeved on the oxidizer distribution portion and is located between the nozzle mounting portion and the oxidizer distribution portion; a first liquid collecting chamber is formed between the dual-channel liquid collecting ring and the oxidizer distribution portion, and an oxidizer distribution channel is disposed inside the oxidizer distribution portion and is respectively connected to the oxidizer injection port and the first liquid collecting chamber.

[0016] In some embodiments, the oxidant diversion channel includes a first diversion channel and a second diversion channel; the first diversion channel extends radially and is disposed through the oxidant diversion section, and both ends of the first diversion channel are connected to the first liquid collection chamber; the second diversion channel extends axially, and one end of the second diversion channel is connected to the first diversion channel and the other end is connected to the oxidant injection port.

[0017] In some embodiments, the outer diameter of the end of the central cone away from the oxidant diversion section gradually decreases in the direction away from the combustion chamber, and the outer peripheral surface of the central cone near the combustion chamber outlet is provided with an annular flange that protrudes radially outward, forming a narrowed annular channel cross section between the annular flange and the inner wall of the outer casing of the combustion chamber.

[0018] The nozzle and injection system for a rotary detonation engine provided in this application have at least the following advantages compared to the prior art: First, it achieves passive adaptive check valve operation, solving the high-frequency response problem. This application utilizes the geometric characteristics of the Tesla valve's flow channel to force the backflowing high-temperature, high-pressure gas to change direction, generating high flow resistance and effectively preventing gas backflow. This process does not rely on any moving parts, avoiding the problem of traditional mechanical check valves being unable to respond to high-frequency oscillations of several kilohertz due to their large mass inertia. It also avoids the risk of moving parts fatigue failure, ablation, and jamming under high-temperature environments, significantly improving the reliability and service life of the nozzle.

[0019] Second, it reduces the pressure requirements and improves the system's thrust-to-weight ratio. This application relies on the reverse high flow resistance characteristics of the Tesla valve flow channel itself to resist backflow, eliminating the need for extremely high injection pressure drop as required by high-pressure drop nozzles. This significantly reduces the requirements for fluid supply pressure, allowing the turbocharger system to be lightweight and thus improving the overall thrust-to-weight ratio of the engine.

[0020] Third, it enhances system stability and eliminates the risk of backfire and explosion. Compared to the shortcomings of impact injectors, which rely on momentum balance to resist backflow and are sensitive to pressure fluctuations, this application utilizes the geometric flow resistance generated inside the Tesla valve flow channel to make the reverse flow resistance much greater than the forward flow resistance. Even if abnormal peak pressure occurs in the combustion chamber, the nozzle can strongly cut off backflow like a "diode," preventing pressure coupling oscillations in the supply collection chamber and fundamentally eliminating the risk of backfire and explosion.

[0021] Fourth, it enhances thermal protection capabilities and extends structural lifespan. The complex geometry inside the Tesla valve flow channel increases the contact area between the fluid and the nozzle body, while the partition plate not only acts as a flow path separator but also serves as a highly efficient heat exchange framework. Together, they rapidly transfer heat that is difficult to dissipate from the nozzle center to the high-speed flowing cryogenic propellant through the vast surface area, achieving active regenerative cooling across the entire structure. This effectively solves the ablation problem at the nozzle throat and end face of rotating detonation engines, significantly improving engine operational safety.

[0022] In summary, the nozzle provided in this application achieves high-frequency adaptive backflow prevention function through the organic combination of Tesla valve flow channel and partition plate without moving parts. It also takes into account multiple advantages such as lightweight, system stability and thermal protection, providing an innovative solution for the high-performance and high-reliability operation of rotary detonation engine.

[0023] Additional aspects and advantages of this application will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of this application. Attached Figure Description

[0024] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the accompanying drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without any creative effort.

[0025] Figure 1 This is a schematic diagram of the overall structure of the nozzle from one perspective according to an embodiment of this application; Figure 2 This is a schematic diagram of the overall structure of the nozzle provided according to an embodiment of this application from another perspective; Figure 3 This is a schematic cross-sectional view of the nozzle along the axial direction according to an embodiment of this application; Figure 4 This is a schematic diagram of the overall structure of the injection system provided according to an embodiment of this application from one perspective; Figure 5This is a schematic diagram of the overall structure of the injection system provided according to an embodiment of this application from another perspective; Figure 6 This is a schematic cross-sectional view along the axial direction of the injection system provided according to an embodiment of this application; Figure 7 An exploded view of the injection system provided according to an embodiment of this application; Figure 8 This is a schematic diagram of the mounting bracket assembly provided according to an embodiment of this application; Figure 9 This is a schematic diagram of the structure of the dual-channel liquid collection ring provided according to an embodiment of this application from one perspective; Figure 10 This is a schematic diagram of the dual-channel liquid collection ring provided according to an embodiment of this application from another perspective; Figure 11 This is a schematic diagram of the structure of the fuel distribution ring provided according to an embodiment of this application from one perspective; Figure 12 This is a schematic diagram of the fuel distribution ring provided according to an embodiment of this application from another perspective; Figure 13 This is a schematic diagram of the oxidant rectifier headstock provided according to an embodiment of this application, viewed from one angle. Figure 14 This is a schematic diagram of the oxidant rectifier headstock provided according to an embodiment of this application from another perspective; Figure 15 This is a schematic diagram of the structure of the outer casing of the combustion chamber according to an embodiment of this application; Figure 16 This is an assembly diagram of the injection system provided according to an embodiment of this application.

[0026] The attached figures are labeled as follows: 10. Injection system; 100. Nozzle; 110. Nozzle body; 111. Nozzle housing; 112. Nozzle core; 113. Flow guiding unit; 1131. Inner flow guiding island; 1132. Outer flow guiding island; 120. Partition plate; R1. First flow path; R2. Second flow path; 200, Mounting base assembly; 201, Nozzle mounting hole; 202, Oxidant diversion channel; 202A, First diversion channel; 202B, Second diversion channel; 210, Central cone; 211, Annular flange; 220, Nozzle mounting part; 230, Oxidant diversion part; V1, First mounting hole; W1, Second mounting hole; 300. Combustion chamber outer shell; 301. Radial extension section; 302. Axial extension section; X1. Eleventh mounting hole; 400, Oxidant rectifier head plate; 410, Oxidant injection port; 420, Mounting ring groove; V2, Seventh mounting hole; W3, Eighth mounting hole; X3, Ninth mounting hole; Y3, Tenth mounting hole; 500, Dual-channel liquid collection ring; 510, Injection section; 511, First injection hole; 512, Second injection hole; 520, Ring groove section; 521, Outer ring groove; 522, Inner ring groove; 530, Connecting section; Y1, Third mounting hole; W2, Fourth mounting hole; 600, Fuel distribution ring; 610, Fuel injection port; X2, Fifth mounting hole; Y2, Sixth mounting hole; S, combustion chamber; T1, first liquid collection chamber; T2, second liquid collection chamber. Detailed Implementation

[0027] In the description of this invention, it should be understood that, unless otherwise specified, terms such as “center,” “inner,” “outer,” “axial,” “radial,” and “circumferential” indicating orientation or positional relationship are used only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention.

[0028] Furthermore, features specified with "first" or "second" for descriptive purposes only should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Features specified with "first" or "second" may explicitly or implicitly include at least one of the specified features. The description of "multiple" generally means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0029] It should be noted that the Tesla valve flow channel R in this embodiment is a fixed geometric structure fluid channel designed based on the Tesla valve principle. It has no moving parts and relies entirely on its special flow channel geometry to achieve unidirectional fluid flow. The core structure can consist of multiple asymmetric flow guiding units arranged sequentially along the flow direction. Its working principle is based on the inertial effect and flow separation characteristics in fluid mechanics: when the fluid flows in the forward direction (designed flow direction), the flow channel is relatively smooth, and the fluid mainly flows along the main flow path, resulting in low flow resistance; when the fluid flows in the reverse direction (return flow direction), the flow channel structure forces the fluid to divert into the bypass channel, generating turning, countercurrent, and vortex, forming significant energy dissipation, thus generating flow resistance much higher than in the forward direction. That is, it exhibits low flow resistance conduction in one direction and high flow resistance cutoff in the opposite direction.

[0030] As mentioned above, existing rotary detonation engine injection systems suffer from technical defects in backfire prevention, such as high fuel supply pressure requirements, slow dynamic response, insufficient thermal protection, and lack of "low resistance in the forward direction and high resistance in the reverse direction" flow resistance control characteristics. The inventive concept of this application is to provide a nozzle 100 for a rotary detonation engine and an injection system 10 including the nozzle 100. By combining the Tesla valve flow channel R with the partition plate 120 in the nozzle body 110, two independent flow paths with unidirectional conduction characteristics are formed within the nozzle body 110. The geometric structure of the Tesla valve flow channel R itself realizes the fluid diode effect of low resistance in the forward direction and high resistance in the reverse direction, thereby achieving high-frequency adaptive backflow prevention function without moving parts, while taking into account multiple advantages such as thermal protection, compact structure, and system stability.

[0031] Based on the above concept, and referring to Figures 1-3 As shown, this application embodiment provides a nozzle 100 for a rotary detonation engine, including: a nozzle body 110 having an axially opposite inlet end and an outlet end, and a through Tesla valve flow channel R formed between the inlet end and the outlet end; a partition plate 120 disposed within the nozzle body 110 and radially connected to the nozzle body 110 to divide the Tesla valve flow channel R into a first flow path R1 and a second flow path R2 that are independent of each other; wherein the first flow path R1 and the second flow path R2 are configured to allow fluid to flow from the inlet end to the outlet end and to prevent fluid from flowing back from the outlet end to the inlet end.

[0032] It is understood that by combining the Tesla valve flow channel R with the partition plate 120, two independent flow paths R1 and R2 with fluid diode characteristics are formed within a single nozzle body 110. The first flow path R1 can be used to inject oxidant, and the second flow path R2 can be used to inject fuel. Since the Tesla valve flow channel R itself has the geometric characteristics of low resistance in the forward direction and high resistance in the reverse direction, and the partition plate 120 divides it into the first flow path R1 and the second flow path R2, each flow path retains the complete Tesla valve characteristics. Thus, when the nozzle 100 is used for a rotary detonation engine, the first flow path R1 and the second flow path R2 can be used to deliver oxidant and fuel respectively. Both exhibit low resistance conduction during the flow to the combustion chamber (from the inlet end to the outlet end). However, when encountering the high-pressure impact of the detonation wave and the high-temperature and high-pressure gas attempting to flow back (from the outlet end to the inlet end), each flow path can generate high flow resistance by relying on its own Tesla valve flow channel R structure, effectively preventing gas backflow.

[0033] Furthermore, the Tesla valve flow channel R has a complex internal geometry, significantly increasing the contact area between the fluid and the nozzle body 110. Simultaneously, the partition plate 120 not only isolates the flow paths but also acts as a highly efficient heat exchange framework, rapidly transferring heat that is difficult to dissipate from the nozzle center to the cryogenic propellant (oxidizer and fuel) flowing through the first flow path R1 and the second flow path R2 via its large surface area. This fully-structured active regenerative cooling effect effectively solves the ablation problem of the nozzle throat and end face in rotating detonation engines, significantly improving the nozzle's service life and the engine's operational safety.

[0034] It should be noted that the radial connection between the partition plate 120 and the nozzle body 110 can take various forms, such as integral molding, welding, threaded connection, or interference fit, as long as it can separate the Tesla valve flow channel R into two independent and sealed flow paths. Furthermore, the function of "being configured to allow fluid to flow from the inlet end to the outlet end and prevent fluid from flowing back from the outlet end to the inlet end," i.e., the flow resistance from the inlet end to the outlet end is less than the flow resistance from the outlet end to the inlet end, is achieved through the geometry of the Tesla valve flow channel R itself. It does not rely on any moving parts or external control to achieve passive adaptive check flow, avoiding the response hysteresis problem under high-frequency knocking caused by the presence of moving parts, and also avoiding the risk of fatigue failure and jamming of moving parts under high-temperature environments.

[0035] To improve the rapid refilling and atomization efficiency of propellant during the detonation interval, refer to Figure 3 In some embodiments, the outlets of the first flow path R1 and the second flow path R2 converge toward the central axis of the nozzle body 110 toward the outlet end of the nozzle body 110, so that the fluids ejected from the first flow path R1 and the second flow path R2 collide with each other.

[0036] By converging the outlets of the first flow path R1 and the second flow path R2 towards the central axis, the outlet axes of the first flow path R1 and the second flow path R2 have a converging angle, causing the two independent propellant jets to collide with each other at a radial velocity component the instant they leave the nozzle body 110 outlet end. The shearing effect generated by this impact can break the liquid column or liquid film into finer droplets, significantly improving the atomization quality. At the same time, since the propellant has already generated high turbulence when flowing through the Tesla valve flow channel R, the fluid already has strong turbulent energy before the outlet impact, further enhancing the impact atomization effect. This dual atomization mechanism of "pre-turbulence + post-impact" can effectively reduce the average droplet diameter and increase the specific surface area of ​​the propellant, thereby achieving rapid mixing during the detonation interval and providing favorable conditions for the stable establishment of the next detonation cycle. Compared with ordinary straight-hole or impact injectors, it can greatly improve the detonation combustion efficiency.

[0037] Optionally, the exit convergence angles of the first flow path R1 and the second flow path R2 can be optimized based on operating parameters such as propellant type, flow rate, and combustion chamber pressure. For example, they can be set to an angle between 30° and 60° to achieve optimal atomization and penetration depth. It should be noted that the exit convergence structure can be achieved by machining the geometry of the nozzle body 110's exit end. For example, the inner or outer wall of the exit end can be machined into an inclined or curved surface tilted towards the axis, so that the exit axes of the first flow path R1 and the second flow path R2 intersect at a point downstream of the nozzle. Furthermore, this exit convergence structure works synergistically with the anti-backflow function of the aforementioned Tesla valve flow channel R: in the forward flow phase, the convergence structure promotes atomization mixing; in the reverse impact phase, the Tesla valve flow channel R acts as a check valve, and together they ensure the stable operation of the rotary detonation engine under high-frequency operating conditions.

[0038] Continue to refer to Figure 3 In some embodiments, the nozzle body 110 includes a nozzle housing 111, a nozzle core 112, and a plurality of flow guiding units 113; the nozzle core 112 is disposed inside the nozzle housing 111 and is radially spaced from the nozzle housing 111; a partition plate 120 is radially connected between the nozzle housing 111 and the nozzle core 112; the plurality of flow guiding units 113 are arranged axially between the nozzle housing 111 and the nozzle core 112 and are connected to the partition plate 120, so as to form a Tesla valve flow channel R together with the inner wall of the nozzle housing 111 and the outer wall of the nozzle core 112.

[0039] In this embodiment, the nozzle body 110 can be cylindrical in shape. The nozzle housing 111 and the nozzle core 112 are coaxially arranged, and the annular gap between them constitutes the basic space of the Tesla valve flow channel R. The partition plate 120 is radially connected between the nozzle housing 111 and the nozzle core 112, dividing the annular gap into two independent semi-cylindrical flow paths, namely the first flow path R1 and the second flow path R2. Multiple flow guiding units 113, as the core functional units of the Tesla valve, are arranged sequentially in the annular gap along the axial direction and are fixedly connected to the partition plate 120, thereby forming a complex flow guiding structure inside each flow path. When the flow guiding unit 113 is fixedly connected to the partition plate 120, a specific gap is formed between its outer edge and the inner wall of the nozzle housing 111, and between its inner edge and the outer wall of the nozzle core 112. These gaps, in conjunction with the geometry of the multiple flow guiding units 113, together constitute the Tesla valve flow channel R with unidirectional conduction characteristics.

[0040] Furthermore, each flow guiding unit 113 includes an inner flow guiding island 1131 and an outer flow guiding island 1132; an inner flow channel is formed between the inner flow guiding island 1131 and the outer wall of the nozzle core 112, and an outer flow channel is formed between the outer flow guiding island 1132 and the inner wall of the nozzle housing 111, and a main flow path is formed between the inner flow guiding island 1131 and the outer flow guiding island 1132; both ends of the inner flow channel and the outer flow channel are connected to the main flow path, and the inner flow guiding island 1131 and the outer flow guiding island 1132 of adjacent flow guiding units 113 are staggered in the axial direction, so that when the fluid flows back from the outlet end to the inlet end, the fluid is forced to divert into the inner flow channel and / or the outer flow channel to generate a turning countercurrent.

[0041] like Figure 3 As shown, a typical Tesla valve flow channel structure is constructed through the coordinated arrangement of the inner guide island 1131 and the outer guide island 1132. Specifically, three parallel flow paths are formed within each guide unit 113: the main flow path in the middle, and the inner and outer bypass channels located radially on both sides of the main flow path. Because the inner guide island 1131 and the outer guide island 1132 of adjacent guide units 113 are staggered axially, these flow paths form an asymmetrical connection between the guide units 113. When the fluid flows from the inlet to the outlet, the fluid mainly flows smoothly along the main flow path, with only a small amount diverted into the bypass channels. Due to the short and smooth flow of the main flow path, the overall flow resistance is low, exhibiting a "low-resistance conduction" characteristic. This allows the propellant to quickly fill the injector during the detonation interval, meeting the refilling speed requirements of high-frequency operation. When high-temperature, high-pressure combustion gas attempts to flow back, the staggered arrangement of the inner guide island 1131 and the outer guide island 1132 forces the backflowing fluid to be diverted into the inner and / or outer bypass channels. Within these bypass channels, the fluid is forced to turn and circumvent, colliding with fluids from other paths at the channel outlet, creating strong vortices and energy dissipation. This results in flow resistance far exceeding that of the forward flow, exhibiting a "high-resistance cutoff" characteristic. This geometric flow resistance effect allows the nozzle to effectively block combustion gas backflow without any moving parts, protecting the upstream supply system.

[0042] It is worth noting that the arrangement of the inner guide island 1131 and the outer guide island 1132 also significantly increases the contact area between the fluid and the nozzle body 110, so as to improve the heat exchange efficiency and avoid the ablation of the nozzle 100 end face and internal flow channel.

[0043] The geometry, number, and degree of overlap of the inner guide island 1131 and the outer guide island 1132 can be optimized according to specific operating conditions. In some embodiments, the cross-sections of both the inner guide island 1131 and the outer guide island 1132 along the axial direction have a smooth end towards the inlet and a tapered end towards the outlet, meaning the inner guide island 1131 and the outer guide island 1132 can be teardrop-shaped. Figure 3 As shown, when the fluid flows forward from the inlet to the outlet, it encounters the smooth end of the inner guide island 1131. The streamlined profile of the smooth end guides the flow, reducing flow separation and eddy losses, and guiding the fluid smoothly into the main flow path. When the fluid flows backward from the outlet to the inlet, it first encounters the tapered end of the outer guide island 1132, forcing the fluid to enter the outer bypass channel on one side of the outer guide island 1132. After being forced to turn and bypass within the outer bypass channel, the fluid finally leaves from the smooth end of the outer guide island 1132, where it collides with fluids from other paths. In adjacent guide units 113, the tapered and smooth ends of the inner guide island 1131 and the outer guide island 1132 are axially misaligned, causing the gas to change direction at each guide unit 113 during recirculation, forming a maze-like flow path, thus generating flow resistance several times greater than that of the injection flow on a macroscopic scale.

[0044] In some embodiments, the first flow path R1 and the second flow path R2 are symmetrically arranged along the radial partition plate 120. This symmetrical structure makes the two flow paths have exactly the same geometric features and flow characteristics, which is beneficial for the symmetrical injection and uniform mixing of oxidant and fuel.

[0045] In some embodiments, the Tesla valve flow path R can be composed of... Figure 3 The two-dimensional Tesla valve flow channel shown is generated by rotating around the central axis of the nozzle 100. That is, by rotating the two-dimensional Tesla valve flow channel around the central axis of the nozzle 100, the features originally in the plane, such as the inner guide island 1131 and outer guide island 1132, the main flow path, the inner bypass channel, and the outer bypass channel, are mapped to corresponding structures in a three-dimensional annular space. Although the Tesla valve flow channel R in this embodiment can be generated by rotation, the specific structures of the first flow path R1 and the second flow path R2 are not limited to complete symmetry. In some alternatives, the number, shape, or bypass channel size of the two flow paths can be differentiated according to the different physical properties (such as density, viscosity, flow rate, etc.) of the oxidant and fuel to obtain their respective optimal flow characteristics. Such differentiated design also falls within the scope of protection of this application.

[0046] refer to Figures 4-16As shown, another embodiment of this application provides an injection system 10 for a rotary detonation engine, including a plurality of nozzles 100 as described above, and further including: a mounting base assembly 200, having a plurality of nozzle mounting holes 201 axially arranged, the plurality of nozzle mounting holes 201 being spaced apart and arranged circumferentially around the mounting base assembly 200, each nozzle mounting hole 201 housing a nozzle 100, and an oxidizer diversion channel 202 provided within the mounting base assembly 200; an outer casing 300 of the combustion chamber, sleeved on the mounting base assembly 200 and together with the mounting base assembly 200 forming a combustion chamber S, the outlet end of the nozzle 100 being located within the combustion chamber S; and an oxidizer rectifier head plate 400 connected to one axial end of the mounting base assembly 200, the oxidizer rectifier head plate 400 having an oxidizer injection port 410, the oxidizer injection port 410 being diverted from the oxidizer. Channel 202 is connected; a dual-channel liquid collecting ring 500 is sleeved on the mounting base assembly 200 and is located axially between the mounting base assembly 200 and the oxidant rectifier head plate 400; a fuel distribution ring 600 is sleeved on the dual-channel liquid collecting ring 500 and is located axially between the combustion chamber outer shell 300 and the oxidant rectifier head plate 400, and a fuel injection port 610 is provided on the fuel distribution ring 600; wherein, a first liquid collecting chamber T1 is formed between the dual-channel liquid collecting ring 500 and the mounting base assembly 200, the first liquid collecting chamber T1 is connected to the oxidant diversion channel 202 and is connected to the first flow path R1 of each nozzle 100; a second liquid collecting chamber T2 is formed between the dual-channel liquid collecting ring 500 and the fuel distribution ring 600, the second liquid collecting chamber T2 is connected to the fuel injection port 610 and is connected to the second flow path R2 of each nozzle 100.

[0047] The injection system 10 in this embodiment adopts a split coaxial assembly structure, which can realize the isolated delivery and aligned injection of bicomponent propellant in an extremely compact space. Specifically, the injection system 10 consists of several nozzles 100, a mounting base assembly 200, an outer combustion chamber 300, an oxidizer rectifier head 400, a dual-channel liquid collection ring 500, and a fuel distribution ring 600. The mounting base assembly 200 is located at the center of the system. The mounting base assembly 200 can be designed with six nozzle mounting holes 201, so that six nozzles 100 are fixedly installed in their respective nozzle mounting holes 201 to form a ring-shaped injection array. The outer combustion chamber 300 is fitted onto the mounting base assembly 200. The inner wall of the outer combustion chamber 300 and the outer wall of the mounting base assembly 200 together form an annular combustion chamber S. The outlet end of each nozzle 100 is located at one axial end of the combustion chamber S. The mounting bracket assembly 200 is fixedly connected to the oxidizer rectifying head plate 400 at the end opposite to the combustion chamber S, so that the oxidizer injection port 410 is connected to the oxidizer distribution channel 202. A dual-channel liquid collecting ring 500 is sleeved on the mounting bracket assembly 200 and clamped between the mounting bracket assembly 200 and the oxidizer rectifying head plate 400, forming a first liquid collecting chamber T1 with the mounting bracket assembly 200. A fuel distribution ring 600 is sleeved around the dual-channel liquid collecting ring 500 and clamped between the combustion chamber outer shell 300 and the oxidizer rectifying head plate 400, forming a second liquid collecting chamber T2 with the dual-channel liquid collecting ring 500. This nested assembly method makes the system structure highly compact and minimizes the radial dimensions, which is beneficial for arranging multiple nozzles 100 in a limited space to meet high thrust requirements.

[0048] During the operation of the injection system 10 in this embodiment, when the rotary detonation engine is ignited and started, high-pressure liquid oxidizer is injected through the oxidizer injection port 410 on the oxidizer rectifier head plate 400 and flows into the first liquid collection chamber T1 through the oxidizer diversion channel 202 in the mounting base assembly 200; simultaneously, liquid fuel is injected through the fuel injection port 610 on the fuel distribution ring 600 and flows directly into the second liquid collection chamber T2. Under pressure, the oxidizer and fuel enter the first flow path R1 and the second flow path R2 from the first liquid collection chamber T1 and the second liquid collection chamber T2, respectively. Due to the characteristic of low forward flow resistance in the Tesla valve flow channel R, the two propellants are smoothly accelerated in their respective flow paths, and finally at the outlet of the nozzle 100, they are constrained by the outlet convergence structure of the first flow path R1 and the second flow path R2 and converge towards the central axis at a specific angle. The high-speed flowing oxidizer jet and fuel jet collide violently immediately downstream of the nozzle outlet, forming a fan-shaped or cone-shaped liquid film that is rapidly broken and atomized, completing the initial mixing. It is then ignited by the ignition source, establishing detonation combustion in the combustion chamber S.

[0049] After ignition, a rotating detonation wave propagates at high speed circumferentially within the combustion chamber S. When the peak of the detonation wave sweeps across the outlet end of a nozzle 100, the pressure at the nozzle 100 outlet surges instantaneously. The high-temperature, high-pressure combustion gas attempts to flow backward into the nozzle 100. At this moment, the Tesla valve flow channel R inside the nozzle 100 acts as a "fluid diode," preventing the combustion gas from flowing back from the outlet end to the inlet end. After the detonation wave passes, the outlet pressure of the nozzle 100 drops sharply, and the flow resistance within the nozzle 100 quickly returns to a low-resistance state. The oxidizer and fuel are then smoothly ejected again, achieving rapid refilling and preparing for the next detonation cycle. Throughout the process, the nozzle 100 relies on the geometric characteristics of the Tesla valve flow channel R itself to achieve an adaptive anti-backflow response, requiring no external control or moving parts, perfectly matching the high-frequency detonation working environment of several kilohertz.

[0050] In one specific embodiment, when the gas flows back from the outlet to the inlet, it first encounters the staggered inner guide island 1131 and outer guide island 1132 in the guide unit 113. Because the guide islands of adjacent guide units 113 are staggered axially, the reverse-flowing gas cannot flow directly along the main flow path and is forced to divert into the inner bypass channel and / or the outer bypass channel. Within the bypass channel, the gas is forced to turn and bypass, and at the channel outlet, it collides with fluids from other paths, forming strong eddies and energy dissipation, thus generating a geometric flow resistance much higher than that of the forward flow. This high flow resistance effect, without any moving parts, instantly cuts off or significantly attenuates the return flow of gas to the first liquid collecting chamber T1 and the second liquid collecting chamber T2, protecting the upstream supply system.

[0051] refer to Figure 6 , Figure 9 and Figure 10As shown, in some embodiments, the dual-channel liquid collection ring 500 includes an injection section 510, an annular groove section 520, and a connecting section 530 connected sequentially along the axial direction; the injection section 510 is located axially between the annular groove section 520 and the nozzle mounting hole 201, and is sleeved on the mounting base assembly 200 together with the annular groove section 520; the outer peripheral surface of the annular groove section 520 has an outer annular groove 521 extending circumferentially, and the inner peripheral surface has an inner annular groove 522 extending circumferentially; the outer annular groove 521 and the inner wall of the fuel distribution ring 600 form a second liquid collection chamber T2, and the inner annular groove 522 and the outer wall of the mounting base assembly 200 form a first liquid collection chamber T1; the connecting section 530 is located axially between the annular groove section 520 and the oxidant assembly 200. The flow head plate 400 is connected to the mounting base assembly 200, the fuel distribution ring 600, and the oxidant rectifier head plate 400 respectively. The injection section 510 has multiple pairs of first injection holes 511 and second injection holes 512 that are circumferentially spaced. The first injection hole 511 passes through the injection section 510 and communicates with the first liquid collection chamber T1. The second injection hole 512 passes through the injection section 510 and communicates with the second liquid collection chamber T2. Each first injection hole 511 is connected to the first flow path R1 of the corresponding nozzle 100 to supply oxidant to the corresponding first flow path R1. Each second injection hole 512 is connected to the second flow path R2 of the corresponding nozzle 100 to supply fuel to the corresponding second flow path R2.

[0052] In this embodiment, the injection section 510 is responsible for accurately distributing the propellant in the two collection chambers to each nozzle 100. Each pair of first injection holes 511 and second injection holes 512 on the section correspond to the nozzle mounting holes 201, ensuring that the first flow path R1 and the second flow path R2 of each nozzle 100 can obtain independent oxidizer and fuel supply respectively. The annular groove section 520 cooperates with adjacent components (mounting seat assembly 200 and fuel distribution ring 600) through the inner annular groove 522 and the outer annular groove 521 to form independent and large-volume first collection chamber T1 and second collection chamber T2, which play the role of stabilizing pressure and equalizing flow. The connecting section 530 serves as a structural connector, forming a reliable fixed connection with the mounting seat assembly 200, the fuel distribution ring 600 and the oxidizer rectifier head plate 400, ensuring the structural integrity of the entire injection system 10.

[0053] Furthermore, the first liquid collecting chamber T1 is formed by the inner annular groove 522 and the outer wall of the mounting base assembly 200, while the second liquid collecting chamber T2 is formed by the outer annular groove 521 and the inner wall of the fuel distribution ring 600. This "annular groove + mating surface" cavity formation method eliminates the need to process complex closed cavities within a single component, reducing processing difficulty and cost. On the other hand, by adjusting the depth, width, and axial length of the inner and outer annular grooves, the volumes of the first liquid collecting chamber T1 and the second liquid collecting chamber T2 can be flexibly changed to adapt to different flow rate and pressure conditions. Simultaneously, the continuous circumferential extension of the inner and outer annular grooves makes the fluid pressure distribution within the two liquid collecting chambers more uniform, which is beneficial for each nozzle 100 to obtain a consistent supply pressure. In this embodiment, the injection section 510, the ring groove section 520, and the connecting section 530 of the dual-channel liquid collection ring 500 can be an integrally formed structure, or they can be combined by welding, threaded connection, or flange connection. The integrally formed structure has better sealing performance and structural strength, and is suitable for high-pressure conditions; the split combination structure is easier to process and debug. Those skilled in the art can choose the appropriate molding method according to actual needs.

[0054] refer to Figure 6 , Figure 13 and Figure 14 In this embodiment, the oxidant injection port 410 on the oxidant rectifier head plate 400 can be axially opened at the axis of the oxidant rectifier head plate 400. The end face of the oxidant rectifier head plate 400 facing the dual-channel liquid collecting ring 500 is formed with a mounting ring groove 420. The mounting ring groove 420 is adapted to the shape of the connecting section 530 so as to accommodate the connecting section 530 in the mounting ring groove 420, so that the dual-channel liquid collecting ring 500 can be axially pressed by the oxidant rectifier head plate 400, ensuring a tight fit between the injection section 510 and the nozzle mounting hole 201, and avoiding propellant leakage.

[0055] refer to Figure 6 , Figure 7 and Figure 8As shown, in some embodiments, the mounting base assembly 200 includes a central cone 210, a nozzle mounting portion 220, and an oxidant distribution portion 230; the central cone 210 is partially disposed within the outer casing 300 of the combustion chamber and is radially spaced from the outer casing 300 to form the combustion chamber S; the nozzle mounting portion 220 protrudes radially from the circumference of the central cone 210 and is axially located at one end of the combustion chamber S; a plurality of nozzle mounting holes 201 are circumferentially spaced on the nozzle mounting portion 220; the oxidant distribution portion... The flow section 230 is located at one end of the central cone 210, and the end opposite to the central cone 210 is connected to the oxidant rectifier head plate 400; the dual-channel liquid collecting ring 500 is sleeved on the oxidant diversion section 230 and is located between the nozzle mounting section 220 and the oxidant diversion section 230; the dual-channel liquid collecting ring 500 and the oxidant diversion section 230 form a first liquid collecting chamber T1, and the oxidant diversion channel 202 is located in the oxidant diversion section 230 and is connected to the oxidant injection port 410 and the first liquid collecting chamber T1 respectively.

[0056] In this embodiment, the central cone 210, the nozzle mounting portion 220, and the oxidant diversion portion 230 can be integrally formed. The central cone 210 serves as the inner wall surface of the combustion chamber S, and together with the outer shell 300 of the combustion chamber, it forms the flow channel boundary of the annular combustion chamber S. The nozzle mounting portion 220 serves as the supporting structure for the nozzle 100, protruding radially from the circumference of the central cone 210 and located axially at one end of the combustion chamber S. The nozzle mounting holes 201 evenly arranged circumferentially in the nozzle mounting portion 220 ensure the precise positioning and circumferential distribution of multiple nozzles 100, so as to form an annular injection array at one end of the combustion chamber S. The nozzle mounting holes 201 can be threaded holes, thereby screwing the nozzles 100 into the nozzle mounting holes 201. The oxidant diversion portion 230, as the core component for oxidant flow path conversion, is responsible for evenly distributing the oxidant introduced by the oxidant rectifier head 400 to the first liquid collection chamber T1. This modular design makes each component functionally singular and structurally clear, reducing manufacturing difficulty and facilitating independent optimization of each module according to different working conditions.

[0057] Furthermore, the dual-channel liquid collecting ring 500 is integrally sleeved on the oxidant diversion section 230 and located between the nozzle mounting section 220 and the oxidant diversion section 230. The injection section 510 of the dual-channel liquid collecting ring 500 is adjacent to the nozzle mounting section 220. The inner ring groove 522 of the dual-channel liquid collecting ring 500 and the oxidant diversion section 230 form a first liquid collecting chamber T1, so that each pair of injection holes on the injection section 510 can be precisely aligned with the flow path in the corresponding nozzle 100. The oxidant diversion channel 202 is disposed within the oxidant diversion section 230 and is connected to the oxidant injection port 410 and the first liquid collection chamber T1 respectively. This design can convert the axial introduction of the oxidant into a circumferentially distributed one. On the one hand, it avoids the need to process complex three-dimensional flow channels inside the mounting base assembly 200. On the other hand, the oxidant diversion channel 202 can be designed as multiple radial branches as needed to ensure that the oxidant can flow evenly into the first liquid collection chamber T1 that extends continuously in the circumferential direction, thereby enabling each nozzle 100 to obtain a consistent oxidant supply pressure.

[0058] Specifically, in some embodiments, the oxidant diversion channel 202 can have a "T"-shaped cross-section along the axial direction. The oxidant diversion channel 202 includes a first diversion channel 202A and a second diversion channel 202B. The first diversion channel 202A extends radially and is disposed through the oxidant diversion section 230, with both ends of the first diversion channel 202A connected to the first liquid collection chamber T1. The second diversion channel 202B extends axially, with one end connected to the first diversion channel 202A and the other end connected to the oxidant injection port 410. After the oxidant enters from the oxidant injection port 410 of the oxidant rectifier head plate 400, it first flows along the axially extending second diversion channel 202B, and then enters the radially through first diversion channel 202A. Since the first diversion channel 202A penetrates the oxidant diversion section 230 radially and both ends are connected to the first liquid collection chamber T1, the oxidant can flow into the first liquid collection chamber T1 simultaneously from both radial sides. This bidirectional diversion method effectively avoids the problem of uneven circumferential pressure that may be caused by unilateral injection, ensuring that the oxidant pressure at each position along the circumference in the first liquid collection chamber T1 is basically the same.

[0059] It should be understood that the number of first diversion channels 202A can be adjusted as needed. In some preferred embodiments, multiple first diversion channels 202A can be provided circumferentially at intervals around the oxidant diversion section 230, each first diversion channel 202A communicating with a second diversion channel 202B, thereby further enhancing the circumferential uniformity of oxidant distribution. In other embodiments, the first diversion channel 202A can also be configured as a blind hole, communicating with the first liquid collection chamber T1 at only one end, but the through-type design (both ends are connected) has a better bidirectional diversion effect.

[0060] refer to Figure 6 , Figure 11 and Figure 12 In some embodiments, the fuel injection port 610 of the fuel distribution ring 600 is radially disposed between the inner wall and the outer wall of the fuel distribution ring 600. The inner wall of the fuel distribution ring 600 and the outer ring groove 521 of the dual-channel liquid collection ring 500 form a second liquid collection cavity T2, and the fuel injection port 610 allows fuel to be radially injected into the second liquid collection cavity T2.

[0061] Continue to refer to Figures 4-6 In some embodiments, the end of the central cone 210 away from the oxidizer diversion section 230 is located outside the combustion chamber S, and its outer diameter gradually decreases in the direction away from the combustion chamber S, which plays a role in guiding the airflow to facilitate the smooth expansion and exhaust of combustion products, reduce flow losses, and improve thrust efficiency. The outer peripheral surface of the central cone 210 near the outlet of the combustion chamber S is provided with an annular flange 211 that protrudes radially outward. The annular flange 211 and the inner wall of the outer shell 300 of the combustion chamber form a narrowed annular channel cross section to help maintain the required pressure level in the combustion chamber S and provide favorable back pressure conditions for the stable propagation of the detonation wave. Furthermore, since the annular flange 211 is located near the outlet of the combustion chamber S, its direct interference with the detonation wave is small, so as to avoid affecting the circumferential propagation of the detonation wave in the main section of the combustion chamber S.

[0062] Continue to refer to Figure 6 and Figure 15 In some embodiments, the outer casing 300 of the combustion chamber includes a radially extending section 301 and an axially extending section 302. The axially extending section 302 is sleeved on the nozzle mounting portion 220 of the mounting base assembly 200 and is radially spaced from the central cone 210 to jointly form the combustion chamber S. The radially extending section 301 is located at one end of the axially extending section 302 near the fuel distribution ring 600 and extends radially outward, connecting with the fuel distribution ring 600. The axially extending section 302, as the main body of the outer casing 300 of the combustion chamber, is axially sleeved on the mounting base assembly 200 and, together with the central cone 210, forms the outer and inner walls of the annular combustion chamber S. Its main function is to form the pressure-bearing boundary and flow channel space of the combustion chamber. The radially extending section 301, as a connecting structure, extends radially outward and connects with the fuel distribution ring 600. Its main function is to achieve a fixed connection and seal between the outer casing 300 of the combustion chamber and the fuel distribution ring 600.

[0063] To facilitate precise assembly and reliable connection between components, refer to Figures 8-16 As shown, in some embodiments, the mounting base assembly 200, the dual-channel liquid collecting ring 500, the fuel distribution ring 600, the oxidizer rectifier head plate 400, and the combustion chamber outer shell 300 are respectively provided with corresponding mounting holes, which allow corresponding connectors to pass through to achieve connection between corresponding components.

[0064] Specifically, the oxidizer distribution section 230 of the mounting base assembly 200 has multiple first mounting holes V1 (e.g., 6 M10 threaded holes) and multiple second mounting holes W1 (e.g., 12 M3 threaded holes) spaced apart circumferentially on its end face opposite to the central cone 210. The first mounting holes V1 and the second mounting holes W1 are radially spaced apart and located radially inside the second mounting holes W1. The dual-channel liquid collecting ring 500 has multiple third mounting holes Y1 (e.g., 12 φ3 through holes) and multiple fourth mounting holes W2 (e.g., 12 φ3 through holes) on its axial end face. The third mounting holes Y1 are located radially outside the fourth mounting holes W2. The fuel distribution ring 600 has a fifth mounting hole X2 (e.g., 12 φ10 through holes) and a sixth mounting hole Y2 (e.g., 12 M3 threaded holes) on its axial end face. The fifth mounting hole X2 is located radially outside the sixth mounting hole Y2. The oxidizer rectifier head plate 400 has multiple seventh mounting holes V2 (e.g., 6 φ10 through holes), multiple eighth mounting holes W3 (e.g., 12 φ3 through holes), multiple ninth mounting holes X3 (e.g., 12 φ10 through holes), and multiple tenth mounting holes Y3 (e.g., 12 φ3 through holes) on its axial end face. The seventh mounting holes V2, eighth mounting holes W3, tenth mounting holes Y3, and ninth mounting holes X3 are arranged radially outwards in sequence. The radial extension section 301 of the combustion chamber outer shell 300 has an eleventh mounting hole X1 (e.g., 12 φ10 through holes) on its axial end face. Each first mounting hole V1 is axially aligned with its corresponding seventh mounting hole V2; each second mounting hole W1 and each fourth mounting hole W2 is axially aligned with its corresponding eighth mounting hole W3; each eleventh mounting hole X1 and each fifth mounting hole X2 is axially aligned with its corresponding ninth mounting hole X3; and each third mounting hole Y1 and each sixth mounting hole Y2 is axially aligned with its corresponding tenth mounting hole Y3.

[0065] During the assembly of the injection system 10, the first connector (such as a bolt) passes through the seventh mounting hole V2 and is screwed into the corresponding first mounting hole V1, securing the oxidant rectifier head plate 400 to the end face of the mounting base assembly 200, while simultaneously clamping the dual-channel liquid collecting ring 500 between the two, thus sealing the first liquid collecting chamber T1; the second connector (such as a screw) passes axially through the eighth mounting hole W3 and the fourth mounting hole W2 in sequence and is screwed into the second mounting hole W1, thus connecting the oxidant rectifier head plate 400, the dual-channel liquid collecting ring 500, and the mounting base assembly 200; the third The connecting parts (such as long bolts) pass through the ninth mounting hole X3, the fifth mounting hole X2, and the eleventh mounting hole X1 in sequence along the axial direction and are then tightened with the mating parts (such as nuts) to achieve the fastening of the oxidizer rectifier head plate 400, the fuel distribution ring 600 and the outer casing 300 of the combustion chamber, thus completing the assembly of the outer wall system; the fourth connecting part (such as screws) passes through the tenth mounting hole Y3 and the third mounting hole Y1 in sequence along the axial direction and is then screwed into the sixth mounting hole Y2 to further fix the outer side of the dual-channel liquid collecting ring 500 to the fuel distribution ring 600 and the oxidizer rectifier head plate 400.

[0066] In summary, the nozzle 100 and injection system 10 provided in this application achieve high-frequency adaptive backflow prevention function through the synergistic effect of the Tesla valve flow channel R and the partition plate 120 without moving parts. At the same time, it takes into account multiple advantages such as lightweight, system stability and thermal protection, and provides an innovative solution for the high-performance and high-reliability operation of rotary detonation engines.

[0067] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A nozzle (100) for a rotary detonation engine, characterized in that, include: The nozzle body (110) has an opposing inlet end and an outlet end along the axial direction, and a through Tesla valve flow channel (R) is formed between the inlet end and the outlet end. A partition plate (120) is disposed within the nozzle body (110) and radially connected to the nozzle body (110) to divide the Tesla valve flow channel (R) into a first flow path (R1) and a second flow path (R2) that are independent of each other. The first flow path (R1) and the second flow path (R2) are configured to allow fluid to flow from the inlet end to the outlet end and to prevent fluid from flowing back from the outlet end to the inlet end.

2. The nozzle (100) for a rotary detonation engine according to claim 1, characterized in that, Towards the outlet end of the nozzle body (110), the outlets of the first flow path (R1) and the second flow path (R2) converge toward the central axis of the nozzle body (110) so that the fluids ejected from the first flow path (R1) and the second flow path (R2) collide with each other.

3. The nozzle (100) for a rotary detonation engine according to claim 1 or 2, characterized in that, The nozzle body (110) includes a nozzle housing (111), a nozzle core (112), and multiple flow guiding units (113). The nozzle core (112) is disposed inside the nozzle housing (111) and is radially spaced from the nozzle housing (111); The partition plate (120) is radially connected between the nozzle housing (111) and the nozzle core (112); Multiple flow guiding units (113) are arranged sequentially along the axial direction between the nozzle housing (111) and the nozzle core (112), and are connected to the partition plate (120) to form a Tesla valve flow channel (R) together with the inner wall of the nozzle housing (111) and the outer wall of the nozzle core (112).

4. The nozzle (100) for a rotary detonation engine according to claim 3, characterized in that, Each of the flow guiding units (113) includes an inner flow guiding island (1131) and an outer flow guiding island (1132). An inner flow channel is formed between the inner guide island (1131) and the outer wall of the nozzle core (112), and an outer flow channel is formed between the outer guide island (1132) and the inner wall of the nozzle shell (111). A main flow path is formed between the inner guide island (1131) and the outer guide island (1132). Both ends of the inner and outer bypass channels are connected to the main flow path, and the inner guide island (1131) and the outer guide island (1132) of the adjacent guide unit (113) are staggered in the axial direction so that when the fluid flows back from the outlet end to the inlet end, the fluid is forced to divert into the inner bypass channel and / or the outer bypass channel to generate a turning countercurrent.

5. The nozzle (100) for a rotary detonation engine according to claim 4, characterized in that, Both the inner guide island (1131) and the outer guide island (1132) have a smooth end facing the inlet end and a tapered end facing the outlet end along the axial direction.

6. An injection system (10) for a rotary detonation engine, characterized in that, Including a plurality of nozzles (100) as described in any one of claims 1-5, further comprising: The mounting base assembly (200) has a plurality of nozzle mounting holes (201) along the axial direction. The plurality of nozzle mounting holes (201) are spaced apart and arranged in a ring around the circumference of the mounting base assembly (200). Each nozzle mounting hole (201) has a nozzle (100) installed in it. The mounting base assembly (200) has an oxidant diversion channel (202). The outer casing (300) of the combustion chamber is sleeved on the mounting base assembly (200) and together with the mounting base assembly (200) forms a combustion chamber (S), and the outlet end of the nozzle (100) is located inside the combustion chamber (S); An oxidant rectifier head plate (400) is connected to one axial end of the mounting base assembly (200). The oxidant rectifier head plate (400) is provided with an oxidant injection port (410), which is connected to the oxidant diversion channel (202). A dual-channel liquid collection ring (500) is sleeved on the mounting base assembly (200) and is located axially between the mounting base assembly (200) and the oxidant rectifier head plate (400); A fuel distribution ring (600) is sleeved on the dual-channel liquid collection ring (500) and is located axially between the combustion chamber outer shell (300) and the oxidant rectifier head plate (400). A fuel injection port (610) is provided on the fuel distribution ring (600). The dual-channel liquid collecting ring (500) and the mounting base assembly (200) form a first liquid collecting chamber (T1), which is connected to the oxidant diversion channel (202) and to the first flow path (R1) of each nozzle (100). A second liquid collection chamber (T2) is formed between the dual-channel liquid collection ring (500) and the fuel distribution ring (600). The second liquid collection chamber (T2) is connected to the fuel injection port (610) and to the second flow path (R2) of each nozzle (100).

7. The injection system (10) for a rotary detonation engine according to claim 6, characterized in that, The dual-channel liquid collection ring (500) includes a spray section (510), a ring groove section (520) and a connecting section (530) connected sequentially along the axial direction. The injection section (510) is located axially between the annular groove section (520) and the nozzle mounting hole (201), and together with the annular groove section (520), it is sleeved on the mounting base assembly (200); The outer circumferential surface of the annular groove section (520) is provided with an outer annular groove (521) extending in the circumferential direction, and the inner circumferential surface is provided with an inner annular groove (522) extending in the circumferential direction. The second liquid collection chamber (T2) is formed between the outer annular groove (521) and the inner wall of the fuel distribution ring (600), and the first liquid collection chamber (T1) is formed between the inner annular groove (522) and the outer wall of the mounting base assembly (200). The connecting section (530) is located axially between the annular groove section (520) and the oxidant rectifier head plate (400), and is connected to the mounting base assembly (200), the fuel distribution ring (600) and the oxidant rectifier head plate (400) respectively; The injection section (510) has multiple pairs of first injection holes (511) and second injection holes (512) spaced apart along the circumference. The first injection hole (511) passes through the injection section (510) and communicates with the first liquid collection chamber (T1). The second injection hole (512) passes through the injection section (510) and communicates with the second liquid collection chamber (T2). Each first injection hole (511) is connected to the first flow path (R1) of the corresponding nozzle (100), and each second injection hole (512) is connected to the second flow path (R2) of the corresponding nozzle (100).

8. The injection system (10) for a rotary detonation engine according to claim 6 or 7, characterized in that, The mounting base assembly (200) includes a central cone (210), a nozzle mounting portion (220), and an oxidant distribution portion (230). The central cone (210) is partially disposed inside the outer casing (300) of the combustion chamber and is radially spaced from the outer casing (300) of the combustion chamber, together forming the combustion chamber (S). The nozzle mounting portion (220) is radially protruding on the circumference of the central cone (210) and axially located at one end of the combustion chamber (S). A plurality of nozzle mounting holes (201) are circumferentially spaced on the nozzle mounting portion (220). The oxidant diversion section (230) is disposed at one end of the central cone (210), and the end opposite to the central cone (210) is connected to the oxidant rectifier head plate (400); The dual-channel liquid collecting ring (500) is sleeved on the oxidant diversion section (230) and located between the nozzle mounting section (220) and the oxidant diversion section (230); the dual-channel liquid collecting ring (500) and the oxidant diversion section (230) form a first liquid collecting chamber (T1); the oxidant diversion channel (202) is disposed in the oxidant diversion section (230) and is connected to the oxidant injection port (410) and the first liquid collecting chamber (T1) respectively.

9. The injection system (10) for a rotary detonation engine according to claim 8, characterized in that, The oxidant diversion channel (202) includes a first diversion channel (202A) and a second diversion channel (202B); The first diversion channel (202A) extends radially and is disposed through the oxidant diversion section (230), and both ends of the first diversion channel (202A) are connected to the first liquid collection chamber (T1); The second diversion channel (202B) extends axially, with one end connected to the first diversion channel (202A) and the other end connected to the oxidant injection port (410).

10. The injection system (10) for a rotary detonation engine according to claim 8, characterized in that, The outer diameter of the end of the central cone (210) away from the oxidant diversion section (230) gradually decreases in the direction away from the combustion chamber (S), and the outer peripheral surface of the central cone (210) near the outlet of the combustion chamber (S) is provided with an annular flange (211) that protrudes radially outward, and the annular flange (211) and the inner wall of the outer shell (300) of the combustion chamber form a narrowed annular channel cross section.

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