Double-ring continuous rotary detonation ramjet engine

Abstract

This invention discloses a dual-ring continuous rotary detonation ramjet engine, comprising: an inner cylinder; a first outer cylinder sleeved outside the inner cylinder, the first outer cylinder and the inner cylinder forming an inner combustion chamber; a second outer cylinder sleeved outside the first outer cylinder, the second outer cylinder and the first outer cylinder forming an outer combustion chamber; an air intake assembly, the air outlet of the air intake assembly being connected to the air inlets of the inner combustion chamber and the outer combustion chamber respectively; a tail nozzle, the air inlet of the tail nozzle being connected to the air outlet of the inner combustion chamber and the outer combustion chamber respectively; and a fuel injection assembly, the fuel injection assembly including a first fuel injector disposed on the inner cylinder and a second fuel injector disposed on the second outer cylinder. Since the inner and outer combustion chambers are independent of each other, they can operate individually or simultaneously, meeting the different thrust requirements of the ramjet engine. By using a sleeved arrangement to simultaneously house the inner and outer combustion chambers within one engine, the problem of poor space utilization caused by using multiple engines in combination is avoided, thus improving space utilization.

Description

Technical Field

[0001] This invention relates to the field of aerospace equipment technology, and in particular to a dual-ring type continuous rotating detonation ramjet engine. Background Technology

[0002] Continuous rotary detonation ramjet engines have been increasingly widely used because they can fully utilize the performance advantages brought by detonation combustion.

[0003] The continuous rotary detonation ramjet engine utilizes the self-pressurization advantage of detonation combustion, which not only effectively improves the performance of the ramjet engine, but also simplifies the structure of the entire ramjet engine system.

[0004] However, current continuous rotary detonation ramjet engines typically employ an annular combustion chamber. When the thrust of the ramjet engine is insufficient, multiple ramjet engines are usually required to be used in combination. However, multiple ramjet engines result in poor space utilization. Summary of the Invention

[0005] In view of this, the purpose of the present invention is to provide a dual-ring continuous rotary detonation ramjet engine, which aims to improve the space utilization of the engine.

[0006] To achieve the above objectives, the present invention provides the following solution:

[0007] A dual-ring type continuous rotating detonation ramjet engine, comprising:

[0008] Inner cylinder;

[0009] A first outer cylinder is fitted outside the inner cylinder, and the first outer cylinder and the inner cylinder enclose an inner combustion chamber;

[0010] A second outer cylinder is fitted outside the first outer cylinder, and the second outer cylinder and the first outer cylinder together form an outer combustion chamber;

[0011] An air intake assembly, wherein the air outlet of the air intake assembly is connected to the air inlets of the inner combustion chamber and the outer combustion chamber, respectively;

[0012] The tail nozzle has an air inlet that is connected to the air outlet of the inner combustion chamber and the outer combustion chamber, respectively.

[0013] The oil injection assembly includes a first oil injection element disposed on the inner cylinder and a second oil injection element disposed on the second outer cylinder.

[0014] In one specific implementation, the air intake assembly includes a first air intake channel and a second air intake channel;

[0015] The outlet of the first air intake passage is connected to the inner combustion chamber, and the outlet of the second air intake passage is connected to the outer combustion chamber.

[0016] In another specific implementation, the second air intake channel is sleeved outside the first air intake channel, and both the first air intake channel and the second air intake channel are annular channels and are coaxially arranged;

[0017] The inner ring wall of the second air intake channel is shared with the outer ring wall of the first air intake channel;

[0018] The inner ring wall of the first air intake channel is connected to the inner cylinder and is coaxially arranged; the outer ring wall of the first air intake channel is connected to the first outer cylinder and is coaxially arranged; the outer ring wall of the second air intake channel is connected to the second outer cylinder and is coaxially arranged.

[0019] In another specific embodiment, the dual-ring continuous rotary detonation ramjet engine further includes a first transition section, a second transition section, and a third transition section;

[0020] The inner ring wall of the first air intake channel is smoothly connected to the inner cylinder through the first transition part, and the outer diameter and inner diameter of the first transition part gradually decrease along the direction close to the inner cylinder;

[0021] The outer ring wall of the first air intake channel is smoothly connected to the first outer cylinder through the second transition section, and the outer diameter and inner diameter of the second transition section gradually decrease along the direction close to the first outer cylinder;

[0022] The outer ring wall of the second air intake channel is smoothly connected to the second outer cylinder through the third transition section, and the outer diameter and inner diameter of the third transition section gradually decrease along the direction close to the second outer cylinder.

[0023] In another specific implementation, a partition plate is provided at the end of the inner cylinder facing the first transition portion to block the inner cylinder, and the inner ring wall of the first airflow channel and the partition plate form a first fuel supply chamber.

[0024] The first fuel injector is a first fuel ring formed on the partition plate and connected to the first fuel supply chamber and the first airflow passage;

[0025] The outer ring wall of the second outer cylinder is provided with a cavity that surrounds the second fuel supply chamber, and the second fuel injector is a second fuel ring that is opened on the third transition part and connects the second fuel supply chamber with the outer combustion chamber.

[0026] In another specific embodiment, the first fuel ring is inclined in a direction away from the axis of the first partition along a direction away from the first fuel supply chamber, and the outlet of the first fuel ring is located at the inlet of the internal combustion chamber.

[0027] The air inlet of the second fuel ring is located at the position of the first transition section near the second outer cylinder, and along the direction away from the outer combustion chamber, the second fuel ring is inclined towards the axis line of the third transition section.

[0028] In another specific embodiment, the dual-ring continuous rotary detonation ramjet engine further includes a support bracket;

[0029] The bracket includes a first connector and a second connector. One end of the first connector is connected to the inner ring wall of the first air intake channel, and one end of the second connector is connected to the outer ring wall of the second air intake channel. The other end of the first connector is connected to the other end of the second connector. Along the direction of the air outlet near the air intake assembly, the first connector and the second connector are both inclined towards each other.

[0030] The first connector and the second connector are provided with a snap-fit ​​groove at the connection point to snap onto the outer ring wall of the first air intake channel, and the snap-fit ​​groove is provided at the end of the first connector and the second connector facing the air outlet of the air intake assembly.

[0031] In another specific embodiment, the dual-ring continuous rotary detonation ramjet engine further includes an intake rectifier cone;

[0032] The larger end of the intake rectifier cone is connected to the end of the inner ring wall of the first intake channel that is away from the inner combustion chamber.

[0033] The second outer cylinder is provided with a first guide at the end away from the outer combustion chamber, and the first guide is inclined towards the intake rectifier cone along the direction away from the second outer cylinder.

[0034] In another specific embodiment, the dual-ring continuous rotary detonation ramjet engine further includes an exhaust rectifier cone;

[0035] The larger end of the exhaust rectifier cone is connected to the end of the inner cylinder that is furthest from the intake assembly.

[0036] In another specific implementation, one end of the tail nozzle is connected to the end of the second outer cylinder away from the air intake assembly, and the tail nozzle is inclined toward the exhaust rectifier cone along the direction away from the air intake assembly.

[0037] The first outer cylinder is provided with a second guide at the end away from the air intake assembly. Along the direction away from the air intake assembly, the second guide is inclined toward the direction of the exhaust rectifier cone, and the end of the second guide away from the first outer cylinder is accommodated in the space enclosed by the tail nozzle and the outer wall of the exhaust rectifier cone.

[0038] The various embodiments of the present invention can be combined arbitrarily as needed, and the resulting embodiments are also within the scope of the present invention and are part of the specific implementation of the present invention.

[0039] The dual-ring continuous rotary detonation ramjet engine provided by this invention features an inner combustion chamber formed by the first outer cylinder and inner cylinder, and an outer combustion chamber formed by the second outer cylinder and first outer cylinder. The inner and outer combustion chambers are independent of each other and can operate individually or simultaneously, thus meeting the different thrust requirements of ramjet engines. By using a nested arrangement to simultaneously house the inner and outer combustion chambers within a single engine, the space utilization problem associated with using multiple engines in combination is avoided, thereby improving the engine's space utilization rate. Attached Figure Description

[0040] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art 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.

[0041] Figure 1 This is a cross-sectional structural schematic diagram of the double-ring continuous rotating detonation ramjet engine provided by the present invention.

[0042] in, Figure 1 middle:

[0043] A dual-ring continuous rotary detonation ramjet engine 100 includes an inner cylinder 101, a first outer cylinder 102, an inner combustion chamber 103, a second outer cylinder 104, an outer combustion chamber 105, an intake duct assembly 106, a tail nozzle 107, a fuel injection assembly 108, a first fuel injector 108a, a second fuel injector 108b, a first intake passage 106a, a second intake passage 106b, a first transition section 109, a second transition section 110, a third transition section 111, a partition plate 112, a first fuel supply chamber 113, a second fuel supply chamber 114, a bracket 115, a first connector 115a, a second connector 115b, an intake rectifier cone 116, a first guide vane 117, an exhaust rectifier cone 118, and a second guide vane 119. Detailed Implementation

[0044] The following will refer to the appendices in the embodiments of the present invention. Figure 1 The technical solutions in the embodiments of the present invention are clearly and completely described herein. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0045] In the description of this invention, it should be understood that the terms "upper," "lower," "top surface," "bottom surface," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the indicated position or element must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations of the invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0046] Combination Figure 1 As shown, the present invention provides a dual-ring continuous rotary detonation ramjet engine 100 to improve the space utilization of the engine.

[0047] The dual-ring continuous rotary detonation ramjet engine 100 includes an inner cylinder 101, a first outer cylinder 102, a second outer cylinder 104, an air intake assembly 106, a tail nozzle 107, and a fuel injection assembly 108.

[0048] The first outer cylinder 102 is sleeved outside the inner cylinder 101, and the first outer cylinder 102 and the inner cylinder 101 enclose the inner combustion chamber 103. Specifically, the first outer cylinder 102 and the inner cylinder 101 are both cylinders, and they are coaxially arranged to achieve uniform combustion in the inner combustion chamber 103.

[0049] The second outer cylinder 104 is sleeved outside the first outer cylinder 102, and the second outer cylinder 104 and the first outer cylinder 102 enclose the outer combustion chamber 105. Specifically, the second outer cylinder 104 is a cylinder, and the second outer cylinder 104 and the first outer cylinder 102 are coaxially arranged to achieve uniform combustion in the outer combustion chamber 105.

[0050] The air outlet of the intake duct assembly 106 is connected to the air inlets of the inner combustion chamber 103 and the outer combustion chamber 105 respectively. The intake duct assembly 106 provides oxidant to the inner combustion chamber 103 and the outer combustion chamber 105 respectively. The specific oxidant is air or the like.

[0051] The air inlet of the tail nozzle 107 is connected to the air outlet of the inner combustion chamber 103 and the outer combustion chamber 105 respectively, and is used to discharge the exhaust gas from the combustion in the inner combustion chamber 103 and the outer combustion chamber 105.

[0052] The fuel injection assembly 108 includes a first fuel injector 108a disposed on the inner cylinder 101 and a second fuel injector 108b disposed on the second outer cylinder 104. The first fuel injector 108a and the second fuel injector 108b are respectively used to supply fuel to the inner combustion chamber 103 and the outer combustion chamber 105.

[0053] In this invention, the first outer cylinder 102 and the inner cylinder 101 enclose the inner combustion chamber 103, and the second outer cylinder 104 and the first outer cylinder 102 enclose the outer combustion chamber 105. The inner combustion chamber 103 and the outer combustion chamber 105 are independent of each other and can work individually or simultaneously, thus meeting the different thrust requirements of the ramjet engine. Because the inner combustion chamber 103 and the outer combustion chamber 105 are simultaneously housed within a single engine using a nested configuration, the problem of poor space utilization caused by using multiple engines in combination is avoided, thereby improving the engine's space utilization rate.

[0054] In some embodiments, the intake duct assembly 106 includes a first intake passage 106a and a second intake passage 106b. The outlet of the first intake passage 106a is connected to the inner combustion chamber 103, and the outlet of the second intake passage 106b is connected to the outer combustion chamber 105. That is, the first intake passage 106a and the second intake passage 106b provide oxidant to the inner combustion chamber 103 and the outer combustion chamber 105, respectively.

[0055] Furthermore, this invention discloses a second intake passage 106b fitted outside the first intake passage 106a. Both the first intake passage 106a and the second intake passage 106b are annular channels and are coaxially arranged, achieving uniform air intake between the first intake passage 106a and the second intake passage 106b. Simultaneously, the way the second intake passage 106b and the first intake passage 106a are fitted together further improves the space utilization of the engine.

[0056] The inner ring wall of the second intake passage 106b is shared with the outer ring wall of the first intake passage 106a. In other words, the inner ring wall surrounding the second intake passage 106b and the outer ring wall surrounding the first intake passage 106a are the same wall, which further improves the space utilization of the engine and saves materials.

[0057] The inner ring wall of the first air intake channel 106a is connected to the inner cylinder 101 and is coaxially arranged. The outer ring wall of the first air intake channel 106a is connected to the first outer cylinder 102 and is coaxially arranged. The outer ring wall of the second air intake channel 106b is connected to the second outer cylinder 104 and is coaxially arranged.

[0058] Furthermore, the present invention discloses a dual-ring continuous rotary detonation ramjet engine 100, which further includes a first transition portion 109, a second transition portion 110, and a third transition portion 111. The inner ring wall of the first intake passage 106a and the inner cylinder 101 are smoothly connected via the first transition portion 109, and the outer and inner diameters of the first transition portion 109 gradually decrease along the direction close to the inner cylinder 101. It should be noted that the inner ring wall of the first intake passage 106a, the first transition portion 109, and the inner cylinder 101 all have the same wall thickness and are integrally formed. Specifically, they can be integrally formed by additive manufacturing, which facilitates processing and manufacturing. It can be understood that the smooth transition connection between the inner ring wall of the first intake passage 106a and the inner cylinder 101 via the first transition portion 109 means that the connection between the first transition portion 109 and the inner ring wall of the first intake passage 106a and the inner cylinder 101 is achieved through rounded corners to avoid sharp corners that may affect fluid flow.

[0059] The outer ring wall of the first air intake channel 106a is smoothly connected to the first outer cylinder 102 through the second transition portion 110, and the outer diameter and inner diameter of the second transition portion 110 gradually decrease along the direction close to the first outer cylinder 102.

[0060] It should be noted that the outer ring wall of the first air intake channel 106a, the second transition part 110 and the first outer cylinder 102 have the same wall thickness and are integrally formed and connected. Specifically, they can be integrally formed and connected by additive manufacturing, which is convenient for processing and manufacturing.

[0061] Understandably, the smooth transition connection between the outer ring wall of the first air intake channel 106a and the first outer cylinder 102 via the second transition portion 110 means that the connection between the second transition portion 110 and the outer ring wall of the first air intake channel 106a and the first outer cylinder 102 is achieved through rounded corners to avoid sharp corners that could affect fluid flow.

[0062] The outer ring wall of the second air intake passage 106b and the second outer cylinder 104 are smoothly connected by a third transition portion 111, and the outer diameter and inner diameter of the third transition portion 111 gradually decrease along the direction close to the second outer cylinder 104.

[0063] It should be noted that the outer ring wall of the second air intake channel 106b, the third transition part 111 and the second outer cylinder 104 have the same wall thickness and are integrally formed and connected. Specifically, they can be integrally formed and connected by additive manufacturing, which is convenient for processing and manufacturing.

[0064] Understandably, the smooth transition connection between the outer ring wall of the second air intake channel 106b and the second outer cylinder 104 via the third transition part 111 means that the connection between the third transition part 111 and the outer ring wall of the second air intake channel 106b and the second outer cylinder 104 is achieved through rounded corners to avoid sharp corners that could affect fluid flow.

[0065] In some embodiments, a partition plate 112 is provided at the end of the inner cylinder 101 facing the first transition portion 109 to block the inner cylinder 101. The partition plate 112 separates the inner cavity enclosed by the first transition portion 109 and the inner cavity enclosed by the inner cylinder 101. The inner ring wall of the first airflow channel and the partition plate 112 enclose a first fuel supply cavity 113 to facilitate fuel supply.

[0066] The first fuel injector 108a is a first fuel ring that is opened on the partition plate 112 and connects the first fuel supply chamber 113 and the first airflow passage. The first fuel ring provides atomized fuel to the inner combustion chamber 103.

[0067] The outer ring wall of the second outer cylinder 104 is provided with a cavity that surrounds the second fuel supply chamber 114. The second fuel injector 108b is a second fuel ring that is opened on the third transition part 111 and connects the second fuel supply chamber 114 with the outer combustion chamber 105. The second fuel ring is used to provide atomized fuel to the outer combustion chamber 105.

[0068] It should be noted that the first fuel ring and the second fuel ring are not limited to continuous annular holes, but can also be formed by multiple holes arranged intermittently.

[0069] like Figure 1 As shown, the cavity surrounding the second fuel supply chamber 114 is an annular cavity connected to the second outer cylinder 104. Furthermore, this invention discloses that the annular cavity and the second outer cylinder 104 are integrally formed, improving connection stability. Specifically, the annular cavity and the second outer cylinder 104 are integrally formed through additive manufacturing.

[0070] Furthermore, the present invention discloses that the first fuel ring is inclined in a direction away from the first fuel supply chamber 113 and away from the axis of the first partition, and the outlet of the first fuel ring is located at the entrance of the inner combustion chamber 103, which facilitates the injection of fuel into the inner combustion chamber 103. When the oxidant provided by the first air supply channel enters the inner combustion chamber 103 through the transition channel enclosed by the first transition section 109 and the second transition section 110, the oxidant fluid can be decomposed into a first oxidant component that enters the inner combustion chamber 103 axially along the transition channel and a second oxidant component that moves radially towards the axis of the transition channel. The fuel injected by the first fuel ring can be decomposed into a first fuel component that enters the inner combustion chamber 103 axially along the transition channel and a second fuel component that moves radially away from the axis of the transition channel. The second oxidant component and the second fuel component interact, so that the fuel and oxidant can be fully atomized and mixed.

[0071] The air inlet of the second fuel ring is located at the position of the first transition section 109 near the second outer cylinder 104, and along the direction away from the outer combustion chamber 105, the second fuel ring is inclined towards the axis of the third transition section 111. That is, a portion of the fuel injected by the second fuel ring faces the flow direction of the oxidant in the second air supply channel, which further improves the mixing uniformity of the fuel and the oxidant in the second air supply channel.

[0072] In some embodiments, the dual-ring continuous rotary detonation ramjet engine 100 further includes a bracket 115 for mounting an intake duct assembly 106.

[0073] Specifically, the number of brackets 115 can be arbitrary, and they are evenly distributed in a ring along the axis of the intake duct assembly 106.

[0074] The bracket 115 includes a first connector 115a and a second connector 115b. One end of the first connector 115a is connected to the inner ring wall of the first air intake channel 106a, and one end of the second connector 115b is connected to the outer ring wall of the second air intake channel 106b. The other end of the first connector 115a is connected to the other end of the second connector 115b. Along the direction of the air outlet near the air intake assembly 106, both the first connector 115a and the second connector 115b are inclined towards each other. To improve the connection strength between the first connector 115a and the second connector 115b, this invention discloses that the first connector 115a is integrally connected to the inner ring wall of the first air intake channel 106a by additive manufacturing, and the second connector 115b is integrally connected to the inner ring wall of the second air intake channel 106b by additive manufacturing. It is understood that the connection method disclosed above is only one specific embodiment of the present invention. In practical applications, other connection methods such as welding can also be used.

[0075] A snap-fit ​​groove is provided at the connection between the first connector 115a and the second connector 115b to snap onto the outer ring wall of the first air intake channel 106a, and the snap-fit ​​groove is provided at the end of the first connector 115a and the second connector 115b facing the air outlet of the air intake assembly 106.

[0076] In order to achieve stable connection between the outer ring wall of the first air intake channel 106a and the snap-fit ​​groove, the present invention discloses that the outer ring wall of the first air intake channel 106a and the snap-fit ​​groove are integrally formed by additive manufacturing.

[0077] In some embodiments, the dual-ring continuous rotary detonation ramjet engine 100 further includes an intake rectifier cone 116, the larger end of which is connected to the end of the inner ring wall of the first intake passage 106a that is away from the inner combustion chamber 103.

[0078] Specifically, the intake rectifier cone 116 is a hollow structure, which reduces the overall weight of the dual-ring continuous rotating detonation ramjet engine 100.

[0079] The inner wall of the intake rectifier cone 116, together with the inner wall surface of the inner ring wall of the first intake passage 106a and the baffle, forms the first fuel supply chamber.

[0080] The second outer cylinder 104 is provided with a first guide 117 at the end away from the outer combustion chamber 105. Along the direction away from the second outer cylinder 104, the first guide 117 is inclined towards the intake rectifier cone 116, so that the oxidant gas flow can enter the first intake channel 106a and / or the second intake channel 106b along the channel surrounded by the first guide cylinder and the intake rectifier cone 116.

[0081] Understandably, adjustable gates or valves can be installed at the air inlets of the first air inlet channel 106a and the second air inlet channel 106b respectively, so as to adjust the oxidation dose of the first air inlet channel 106a and the second air inlet channel 106b.

[0082] In some embodiments, the dual-ring continuous rotary detonation ramjet engine 100 further includes an exhaust rectifier cone 118, the larger end of which is connected to the end of the inner cylinder 101 away from the intake duct assembly 106 to facilitate exhaust gas discharge.

[0083] Furthermore, the present invention discloses that one end of the tail nozzle 107 is connected to the end of the second outer cylinder 104 away from the intake duct assembly 106, and along the direction away from the intake duct assembly 106, the tail nozzle 107 is inclined towards the exhaust rectifier cone 118 to facilitate the rapid discharge of exhaust gas.

[0084] The first outer cylinder 102 is provided with a second guide 119 at the end away from the intake duct assembly 106. Along the direction away from the intake duct assembly 106, the second guide 119 is inclined toward the exhaust rectifier cone 118 to prevent the exhaust gas after combustion in the inner combustion chamber 103 from flowing into the outer combustion chamber 105.

[0085] The end of the second guide 119 that is away from the first outer cylinder 102 is housed in the space enclosed by the outer wall of the tail nozzle 107 and the exhaust flow cone 118. On the one hand, this saves materials, and on the other hand, it facilitates the merging and discharge of the exhaust gases generated after combustion in the inner combustion chamber 103 and the outer combustion chamber 105.

[0086] The present invention has the following advantages:

[0087] (1) The air intake channel is divided into two channels: the first air intake channel 106a and the second air intake channel 106b. This enables precise control and allows the selection of the working combustion chamber and its number based on the flight platform's requirements for engine thrust performance.

[0088] (2) It has extremely high space utilization. It is used in a ring-within-a-ring manner, which effectively improves the space utilization of the combustion chamber.

[0089] (3) The inner combustion chamber 103 and the outer combustion chamber 105 can work independently or work together.

[0090] The engine can be used more flexibly.

[0091] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0092] The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and inventive features disclosed herein.

[0093] In the description of this specification, references to terms such as "an embodiment," "example," "specific example," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0094] The preferred embodiments of the present invention disclosed above are merely illustrative of the invention. These preferred embodiments do not exhaustively describe all details, nor do they limit the invention to any specific implementation. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of the invention, thereby enabling those skilled in the art to better understand and utilize the invention. The invention is limited only by the claims and their full scope and equivalents.

Claims

1. A dual-ring type continuous rotary detonation ramjet engine, characterized in that, include: Inner cylinder; A first outer cylinder is fitted outside the inner cylinder, and the first outer cylinder and the inner cylinder together form an inner combustion chamber; A second outer cylinder is fitted outside the first outer cylinder, and the second outer cylinder and the first outer cylinder together form an outer combustion chamber; The intake duct assembly has its outlet connected to the intake ports of the inner combustion chamber and the outer combustion chamber, respectively. The tail nozzle has an air inlet that is connected to the air outlets of the inner combustion chamber and the outer combustion chamber, respectively. The oil injection assembly includes a first oil injection element disposed on the inner cylinder and a second oil injection element disposed on the second outer cylinder; The air intake assembly includes a first air intake passage and a second air intake passage; The outlet of the first intake passage is connected to the inner combustion chamber, and the outlet of the second intake passage is connected to the outer combustion chamber. The second air intake channel is fitted outside the first air intake channel. Both the first and second air intake channels are annular channels and are coaxially arranged. The inner ring wall of the second air intake passage is shared with the outer ring wall of the first air intake passage. The inner ring wall of the first air intake channel is connected to the inner cylinder and is coaxially arranged; the outer ring wall of the first air intake channel is connected to the first outer cylinder and is coaxially arranged; the outer ring wall of the second air intake channel is connected to the second outer cylinder and is coaxially arranged. It also includes a bracket for mounting the intake duct assembly. The bracket is evenly distributed in a ring around the intake duct assembly. The bracket includes a first connector and a second connector. One end of the first connector is connected to the inner ring wall of the first intake channel, and one end of the second connector is connected to the outer ring wall of the second intake channel. The other end of the first connector is connected to the other end of the second connector. Along the direction of the air outlet near the intake duct assembly, the first connector and the second connector are both inclined towards each other.

2. The dual-ring continuous rotary detonation ramjet engine according to claim 1, characterized in that, It also includes a first transition section, a second transition section, and a third transition section; The inner ring wall of the first air intake passage is smoothly connected to the inner cylinder through the first transition section, and the outer diameter and inner diameter of the first transition section gradually decrease along the direction close to the inner cylinder; The outer ring wall of the first air intake passage is smoothly connected to the first outer cylinder through the second transition section, and the outer diameter and inner diameter of the second transition section gradually decrease along the direction close to the first outer cylinder; The outer ring wall of the second air intake passage and the second outer cylinder are smoothly connected by a third transition section, and the outer diameter and inner diameter of the third transition section gradually decrease along the direction close to the second outer cylinder.

3. The dual-ring continuous rotary detonation ramjet engine according to claim 2, characterized in that, A partition plate is provided at the end of the inner cylinder facing the first transition section to block the inner cylinder, and the inner ring wall of the first air intake passage and the partition plate form the first fuel supply chamber. The first fuel injector is a first fuel ring that is disposed on the partition plate and connects the first fuel supply chamber and the first air intake passage. The outer ring wall of the second outer cylinder is provided with a cavity that encloses the second fuel supply chamber, and the second fuel injector is a second fuel ring that is opened on the third transition part and connects the second fuel supply chamber and the outer combustion chamber.

4. The dual-ring type continuous rotary detonation ramjet engine according to claim 3, characterized in that, The first fuel ring is inclined in a direction away from the axis of the first partition along a direction away from the first fuel supply chamber, and the outlet of the first fuel ring is located at the inlet of the internal combustion chamber. The air inlet of the second fuel ring is located in the third transition section near the second outer cylinder, and along the direction away from the outer combustion chamber, the second fuel ring is inclined towards the axis of the third transition section.

5. The dual-ring continuous rotary detonation ramjet engine according to claim 1, characterized in that, The first connector and the second connector are connected by a snap-fit ​​groove that snaps into the outer ring wall of the first air intake channel, and the snap-fit ​​groove is located at the end of the first connector and the second connector facing the air outlet of the air intake assembly.

6. The dual-ring continuous rotary detonation ramjet engine according to claim 1, characterized in that, It also includes the intake rectifier cone; The larger end of the intake rectifier cone is connected to the end of the inner ring wall of the first intake passage that is away from the inner combustion chamber. The second outer cylinder is provided with a first guide at the end away from the outer combustion chamber, and the first guide is inclined towards the intake rectifier cone along the direction away from the second outer cylinder.

7. The double-ring type continuous rotary detonation ramjet engine according to any one of claims 1-6, characterized in that, It also includes the exhaust rectifier cone; The larger end of the exhaust rectifier cone is connected to the end of the inner cylinder furthest from the intake assembly.

8. The dual-ring continuous rotary detonation ramjet engine according to claim 7, characterized in that, One end of the tail nozzle is connected to the end of the second outer cylinder away from the air intake assembly, and along the direction away from the air intake assembly, the tail nozzle is inclined toward the direction of the exhaust rectifier cone. The second guide is provided at the end of the first outer cylinder away from the air intake assembly. Along the direction away from the air intake assembly, the second guide is inclined towards the direction of the exhaust rectifier cone. The end of the second guide away from the first outer cylinder is accommodated in the space enclosed by the outer wall of the tail nozzle and the exhaust rectifier cone.

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