Powder fuel ramjet rotary detonation engine with double combustion chambers
By configuring a dual combustion chamber structure with a pre-combustion chamber and a detonation main combustion chamber, the problems of low reaction rate and long ignition delay time of solid powder fuels are solved, achieving stable and efficient detonation combustion of pure powder fuels and improving engine performance.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- BEIHANG UNIV
- Filing Date
- 2025-12-01
- Publication Date
- 2026-05-19
AI Technical Summary
In existing rotary detonation engines, the reaction rate of solid powder fuel is low and the ignition delay time is long, making it difficult to achieve efficient and stable pure powder combustion.
It adopts a dual combustion chamber structure, including a pre-combustion chamber and a detonation main combustion chamber. The pre-combustion chamber increases the temperature and activity of powdered fuel and shortens the ignition delay time. The detonation main combustion chamber organizes rotational detonation combustion, eliminating the dependence on highly active gaseous or liquid assisted combustion fuels.
It achieves stable and efficient detonation combustion of pure powder fuel, improves engine performance, simplifies the fuel supply system, and maximizes the high calorific value characteristics of powder fuel.
Smart Images
Figure CN122062277A_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of aerospace technology, and in particular to a powder-fueled ramjet rotary detonation engine with dual combustion chambers. Background Technology
[0002] The power unit of an aerospace engine converts chemical energy into thermal energy by burning fuel, and then converts it into power through components such as nozzles. This power is thrust.
[0003] Combustion can be categorized into slow combustion and detonation. Slow combustion can be considered isobaric combustion, with a propagation speed on the order of m / s; while detonation combustion is a combustion wave with strong coupling between shock waves and combustion waves, representing shock wave-dominated isochoric combustion with a propagation speed on the order of km / s. Slow combustion is commonly found in liquid rocket engines, scramjet engines, and other propagation devices. However, due to the limitations of the thermodynamic cycle, significantly improving the performance of these propulsion devices becomes extremely difficult. In comparison, detonation engines, which use detonation combustion as their energy release method, offer advantages such as high thermodynamic efficiency, rapid and intense energy release, and a compact structure. Rotary detonation engines have become a focus of attention due to their broad application prospects.
[0004] Currently, rotating detonation engines primarily use gaseous fuels (hydrogen, ethylene) and liquid fuels (kerosene). Compared to these, solid powder fuels (magnesium powder, aluminum powder, boron powder, carbon powder) have the advantage of high volumetric calorific value. Furthermore, solid powder fuels do not require atomization and have adjustable thrust, offering significant fuel advantages. Therefore, their efficient application in rotating detonation engines is expected to greatly improve engine performance. The combustion process of solid powder fuels mainly occurs on or around their surface, i.e., surface reaction or evaporative diffusion combustion. The unique combustion behavior of these powder fuels results in a low reaction rate, long ignition delay time, and difficulty in initiating detonation in engines. Currently, rotating detonation combustion of solid powder fuels mainly relies on the addition of highly reactive gaseous or liquid fuels as auxiliary agents to achieve initiation and stable combustion of the powder fuel.
[0005] However, no efficient detonation combustion scheme using solid powder as a single fuel has been proposed to date. Summary of the Invention
[0006] The purpose of this application is to provide a powder fuel ramjet rotary detonation engine with dual combustion chambers, so as to get rid of the dependence on highly active gaseous or liquid oxidizing fuels in the existing powder fuel rotary detonation combustion organization mode, and achieve stable and efficient detonation combustion of pure powder fuel.
[0007] This application discloses a powder-fueled ramjet rotary detonation engine with dual combustion chambers, comprising: The central cone shaft includes a flow-diverting section and a storage section connected sequentially along a first direction; the flow-diverting section has a pointed cone structure in a direction opposite to the first direction, which can divide the incoming flow into an annular flow; the storage section is used to store combustion powder. The pre-combustion chamber has one end near the storage section that surrounds the storage section and forms a first air intake between it and the storage section; the other end of the pre-combustion chamber away from the storage section is surrounded by a pre-combustion cavity that communicates with the first air intake and the storage section for burning the combustion powder. The detonation main combustion chamber includes a main body and a guide section; the guide section is disposed on the side of the pre-combustion chamber opposite to the central cone axis; the main body is sleeved on the outside of the pre-combustion chamber and the guide section, forming a second air intake passage between the main body and the pre-combustion chamber to guide the incoming flow, forming a main combustion chamber with the front part of the guide section and an injection chamber with the rear part of the guide section; an injection hole is formed between the guide section and the pre-combustion chamber to guide the products generated in the pre-combustion chamber to the main combustion chamber.
[0008] In the above technical solution, the pre-combustion chamber further includes an enclosing section and a pre-combustion section connected to the enclosing section; The encircling section encircles the storage unit, and a first air intake is formed between the encircling section and the storage unit; The pre-combustion section surrounds the pre-combustion chamber, which communicates with the storage section and the first air intake. The pre-combustion chamber has a gradually expanding structure along the first direction.
[0009] In the above technical solution, the inner wall of the circumferential section is further described as having a spherical structure, making the first air intake channel have an annular structure. The first air intake includes a first air intake section and a first isolation section that are sequentially connected along the first direction.
[0010] In the above technical solution, the end of the circumferential section that is away from the pre-combustion section is further described as having a pointed structure; The tip structure is capable of dividing the annular fluid into a first annular flow that is directed to the first air intake and a second annular flow that is directed to the second air intake.
[0011] In the above technical solution, the pre-combustion chamber further includes a first outer side wall and a second outer side wall; One end of the first outer sidewall is tangent to one end of the circumferential section away from the pre-combustion section, and the other end is connected to the second outer sidewall at a first preset obtuse angle.
[0012] In the above technical solution, the pre-combustion chamber and the guide section are further integrally formed; The injection hole is located at the connection between the pre-combustion chamber and the guide section, and the injection hole is opened at a first preset angle with the axial direction of the guide section, so that the product is injected into the main combustion chamber at the first preset angle.
[0013] In the above technical solution, the injection holes are further provided in multiple spaced intervals along the circumferential direction of the pre-combustion chamber; The diameter of the injection hole is set between 1mm and 1.4mm.
[0014] In the above technical solution, the guide portion is further convex towards the pre-combustion chamber.
[0015] In the above technical solution, the detonation main combustion chamber further has a third inner wall and a fourth inner wall connected at a second preset obtuse angle; The second air intake includes a second air intake section and a second isolation section that are sequentially connected along the first direction; The third inner sidewall and the second outer sidewall form a second preset angle, the third inner sidewall and the first outer sidewall form a second air intake section, and the third inner sidewall and the second outer sidewall form a second isolation section. The main combustion chamber is formed between the fourth inner sidewall and the guide portion and at the end near the pre-combustion chamber, and the injection chamber is formed between the fourth inner sidewall and the guide portion and at the end away from the pre-combustion chamber.
[0016] In the above technical solution, the guide portion further has a tapered structure along the first direction within the injection chamber.
[0017] Compared with the prior art, this application has the following beneficial effects: This application discloses a powder-fueled ramjet rotary detonation engine with dual combustion chambers, comprising: The central cone shaft includes a flow-diverting section and a storage section connected sequentially along a first direction; the flow-diverting section has a pointed cone structure in a direction opposite to the first direction, which can divide the incoming flow into an annular flow; the storage section is used to store combustion powder. The pre-combustion chamber has one end near the storage section that surrounds the storage section and forms a first air intake between it and the storage section; the other end of the pre-combustion chamber away from the storage section is surrounded by a pre-combustion cavity that communicates with the first air intake and the storage section for burning the combustion powder. The detonation main combustion chamber includes a main body and a guide section; the guide section is disposed on the side of the pre-combustion chamber opposite to the central cone axis; the main body is sleeved on the outside of the pre-combustion chamber and the guide section, forming a second air intake passage between the main body and the pre-combustion chamber to guide the incoming flow, forming a main combustion chamber with the front part of the guide section and an injection chamber with the rear part of the guide section; an injection hole is formed between the guide section and the pre-combustion chamber to guide the products generated in the pre-combustion chamber to the main combustion chamber.
[0018] In summary, this application is equipped with two combustion chambers, namely a pre-combustion chamber and a detonation main combustion chamber. The pre-combustion chamber pre-combusts the powder to increase the temperature of the powder fuel, reduce the thickness of the oxide layer, and shorten the ignition delay time, thereby improving the activity of the powder fuel. The detonation main combustion chamber is used to organize the rotational detonation combustion of the powder fuel after the activity has been improved.
[0019] Specifically, this method improves the reactivity of low-activity powdered fuel by pre-combustion, increases its temperature, reduces oxide layer thickness, and shortens ignition delay time. This overcomes the difficulty of directly organizing rotary detonation combustion caused by the low reaction rate and long ignition delay time of powdered fuel. Compared to existing methods that add highly reactive gaseous or liquid oxidizers, leading to complex engine and fuel supply systems, this application uses powdered fuel as a single fuel, eliminating the need for other fuels, maximizing the usable equivalence ratio of powdered fuel, and maximizing its high calorific value characteristics. Attached Figure Description
[0020] To more clearly illustrate the technical solutions in the specific embodiments of this application or the prior art, the 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 this application. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.
[0021] Figure 1 This is a schematic diagram of the structure of the powder fuel ramjet rotary detonation engine with dual combustion chambers provided in this application.
[0022] Figure 2 for Figure 1 Enlarged view of point A in the image.
[0023] Reference numerals: 1-Central cone shaft; 101-First direction; 102-Diverter section; 103-Storage section; 104-Piston; 105-High-pressure gas source; 106-Powdered fuel storage chamber; 2-Pre-combustion chamber; 201-First air intake duct; 203-Annular section; 204-Pre-combustion section; 205-First air intake section; 206-First isolation section; 207-First outer wall; 208-Second outer wall; 209-Pre-combustion cavity; 3-Knock main combustion chamber; 301-Main body; 302-Flow guide; 303-Second air intake; 304-Main combustion chamber; 305-Injection chamber; 306-Injection hole; 307-Raised shape; 308-Third inner wall; 309-Fourth inner wall; 310-Second air intake section; 311-Second isolation section; 312-Gradual narrowing structure; 4-Ignition device. Detailed Implementation
[0024] The following detailed embodiments are provided to aid the reader in gaining a comprehensive understanding of the methods, apparatus, and / or systems described herein. However, various changes, modifications, and equivalents of the methods, apparatus, and / or systems described herein will be apparent upon understanding the disclosure of this application. For example, the order of operations described herein is merely illustrative and is not limited to the order presented herein; rather, changes that will be apparent upon understanding the disclosure of this application are possible, except for operations that must occur in a specific order. Furthermore, descriptions of features known in the art may be omitted for clarity and brevity. The features described herein may be implemented in different forms and should not be construed as limited to the examples described herein. Rather, the examples described herein are provided only to illustrate some of the many possible ways of implementing the methods, apparatus, and / or systems described herein that will be apparent upon understanding the disclosure of this application. Throughout this specification, when an element (such as a layer, region, or substrate) is described as being "on" another element, "connected to" another element, "bonded to" another element, "on" another element, or "covering" another element, it may be directly "on" another element, "connected to" another element, "bonded to" another element, "on" another element, or "covering" another element, or there may be one or more other elements in between. Conversely, when an element is described as being "directly on" another element, "directly connected to" another element, "directly bonded to" another element, "directly on" another element, or "directly covering" another element, there may be no other elements in between. As used herein, the term "and / or" includes any one of the relevant items listed and any combination of any two or more of them. Although terms such as "first," "second," and "third" may be used herein to describe individual components, assemblies, regions, layers, or portions, these components, assemblies, regions, layers, or portions are not limited by these terms. More precisely, these terms are used only to distinguish one component, assembly, region, layer, or part from another. Therefore, without departing from the teachings of the examples described herein, the first component, assembly, region, layer, or part referred to as such in the examples may also be referred to as the second component, assembly, region, layer, or part. For ease of description, spatial relational terms such as “above,” “upper,” “below,” and “lower” may be used herein to describe the relationship between one element and another, as shown in the accompanying drawings. Such spatial relational terms are intended to include not only the orientation depicted in the drawings but also the different orientations of the device in use or operation. For example, if the device in the drawings is flipped, an element described as being “above” or “upper” relative to another element will subsequently be “below” or “lower” relative to that other element.Therefore, the term "above" includes both "above" and "below" depending on the spatial orientation of the device. The device may also be positioned in other ways (e.g., oscillating 90 degrees or in other orientations), and the spatial relational terms used herein will be interpreted accordingly. The terminology used herein is for describing various examples only and is not intended to limit this disclosure. Unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. The terms "comprising," "including," and "having" enumerate the stated features, quantities, operations, components, elements, and / or combinations thereof, but do not exclude the presence or addition of one or more other features, quantities, operations, components, elements, and / or combinations thereof. Variations in the shapes shown in the figures may occur due to manufacturing techniques and / or tolerances. Therefore, the examples described herein are not limited to the specific shapes shown in the figures but include changes in shape that occur during manufacturing. The features of the examples described herein may be combined in various ways that will be apparent upon understanding the disclosure of this application. Furthermore, although the examples described herein have a wide variety of constructions, other constructions are possible as will be apparent upon understanding the disclosure of this application.
[0025] To address the technical problems raised in the prior art, this application provides a powder fuel ramjet rotary detonation engine with dual combustion chambers, which is described below in conjunction with... Figure 1 and Figure 2 The structure is described in detail.
[0026] Combination Figure 1 As shown, the powder-fueled ramjet rotary detonation engine with dual combustion chambers includes a central cone shaft 1. The central cone shaft 1 includes a flow divider 102 and a storage section 103 connected sequentially along a first direction 101. Regarding the first direction 101, according to... Figure 1 Taking the direction shown in the figure as an example, the first direction 101 is the right direction, which means that the central vertebral axis is formed with the diversion section 102 and the storage section 103 in sequence along the right direction.
[0027] The diverting section 102 has a pointed cone structure in the direction opposite to the first direction 101. Optionally, the pointed cone structure is a triangular pyramid, a square pyramid, a hexagonal prism, a cone, etc.; preferably, it is a cone. The conical diverting section 102 diverts the incoming flow. Specifically, the incoming flow passes through the surface of the diverting section 102 and is then diverted into an annular flow.
[0028] The storage section 103 is used to store combustion powder. Specifically, a chamber is formed within the storage section 103, which is divided by the piston 104 into a high-pressure gas source chamber 105 and a powdered fuel storage chamber 106. Furthermore, the powdered fuel storage chamber 106 is located away from the diversion section 102. The high-pressure gas source chamber 105 is used to store high-pressure gas, and the powdered fuel storage chamber 106 is used to store fuel powder, which can be high-energy solid powdered fuels such as magnesium powder, aluminum powder, carbon powder, and boron powder.
[0029] It should be noted that the above-mentioned diversion section 102 and storage section 103 form a drip-shaped structure, which can ensure that the incoming flow enters at a relatively fast speed and is diverted at a relatively slow speed.
[0030] Still combined Figure 1 As shown, the powder fuel ramjet rotary detonation engine with dual combustion chambers also includes a pre-combustion chamber 2. The pre-combustion chamber 2 surrounds the storage section 103 at one end near the storage section 103, and a first air intake duct 201 is formed between the pre-combustion chamber 2 and the storage section 103. The first air intake duct 201 guides at least a portion of the aforementioned annular flow. This portion of the annular flow is compressed within the first air intake duct 201, resulting in higher temperature and pressure of the gas entering the subsequent pre-combustion chamber 209, and a reduced flow velocity.
[0031] The pre-combustion chamber 2, located away from the storage section 103, is surrounded by a pre-combustion cavity 209. The pre-combustion cavity 209 is connected to the first air intake duct 201, meaning that gas flowing through the first intake duct can be guided to the pre-combustion cavity 209. Furthermore, the pre-combustion cavity 209 is also connected to the storage section 103. Specifically, a through-channel is provided on the storage section 103, which partially connects the powdered fuel storage chamber 106 and the pre-combustion cavity 209. In use, firstly, the high-pressure gas source 105 pushes the piston 104 and acts on the fuel powder, injecting the fuel powder through the through-channel into the pre-combustion cavity 209. Then, slow combustion, i.e., pre-combustion, is organized within the pre-combustion cavity 209.
[0032] Continue to combine Figure 1 As shown, the powder fuel ramjet rotary detonation engine with dual combustion chambers also includes a detonation main combustion chamber 3, which includes a main body 301 and a flow guide 302.
[0033] The guide section 302 is located on the side of the pre-combustion chamber 2 away from the central cone axis 1 and extends along the first direction 101.
[0034] The main body 301 is fitted outside the pre-combustion chamber 2 and the guide section 302, forming a second intake duct 303 between the main body 301 and the pre-combustion chamber 2 to guide the remaining annular flow. Specifically, firstly, the flow divider 102 divides the incoming flow into annular flow. Then, the sidewall of the pre-combustion chamber 2 can further divide this annular flow into two paths: one enters the pre-combustion chamber 209, and the other proceeds to the main combustion chamber 304 described below. The second intake duct 303 can further compress the annular flow, resulting in higher temperature and pressure for the gas entering the main combustion chamber.
[0035] The main combustion chamber 304, as described above, is formed at the front of the main body 301 and the guide section 302, while an injection chamber 305 is formed at the rear of the guide section 302. Furthermore, an injection hole 306 is formed between the guide section 302 and the pre-combustion chamber 2 to guide the products generated in the pre-combustion chamber 209 to the main combustion chamber 304. That is, the pre-combustion chamber 2 is used to pre-combust the low-activity powder fuel. The pre-combustion process increases the temperature of the powder fuel, reduces the oxide layer thickness, and shortens the ignition delay time, thereby enhancing the activity of the powder fuel entering the main combustion chamber 304 through the injection hole 306. This promotes stable ignition and operation of the pure powder fuel, eliminating dependence on highly active gaseous or liquid oxidizing fuels. Finally, rotational detonation combustion is organized within the main combustion chamber 304, where the internal energy of the high-temperature combustion gas is converted into kinetic energy to generate axial thrust. It is worth noting that in the above-described distribution of the annular flow, the flow rate of the pre-combustion chamber accounts for 20%, and the flow rate of the detonation main combustion chamber 3 accounts for 80%.
[0036] In summary, this application is equipped with two combustion chambers, namely a pre-combustion chamber 2 and a detonation main combustion chamber 3. The pre-combustion chamber pre-combusts the powder to increase the temperature of the powder fuel, reduce the thickness of the oxide layer, and shorten the ignition delay time, thereby improving the activity of the powder fuel. The detonation main combustion chamber 3 is used to organize the rotational detonation combustion of the powder fuel after the activity has been improved.
[0037] Specifically, this method improves the reactivity of low-activity powdered fuel by pre-combustion, increases its temperature, reduces oxide layer thickness, and shortens ignition delay time. This overcomes the difficulty of directly organizing rotary detonation combustion caused by the low reaction rate and long ignition delay time of powdered fuel. Compared to existing methods that add highly reactive gaseous or liquid oxidizers, leading to complex engine and fuel supply systems, this application uses powdered fuel as a single fuel, eliminating the need for other fuels, maximizing the usable equivalence ratio of powdered fuel, and maximizing its high calorific value characteristics.
[0038] In this embodiment, the pre-combustion chamber 2 further includes an enclosing section 203 and a pre-combustion section 204 communicating with the enclosing section 203. The enclosing section 203 encloses the storage section 103 and forms a first intake passage 201 for compressing the annular flow between the enclosing section 203 and the storage section 103.
[0039] Specifically, the pre-combustion section 204 is surrounded by a pre-combustion chamber 209 that communicates with the storage section 103 and the first air intake 201. The pre-combustion chamber 209 has a gradually expanding structure along the first direction 101.
[0040] Furthermore, combined Figure 1 As shown, the inner wall of the circumferential section 203 has a spherical structure. Optionally, the inner wall of the circumferential section 203 is ellipsoidal. Since the outer wall of the storage section 103 is also ellipsoidal, the first air intake duct 201 formed by the circumferential section 203 and the storage section 103 has an annular structure. This annular structure of the first air intake duct 201 includes a first air intake section 205 and a first isolation section 206 connected sequentially along the first direction 101. The first isolation section 206 isolates the first air intake section 205 from the pre-combustion chamber 209 through shock wave action.
[0041] Furthermore, combined Figure 1 As shown, the end of the circumferential section 203 away from the pre-combustion section 204 has a pointed structure; the pointed structure can divide the above-mentioned annular fluid into a first annular flow that is guided to the first air intake 201 and a second annular flow that is guided to the second air intake 303.
[0042] Furthermore, combining Figure 1 As shown, the pre-combustion chamber 2 includes a first outer side wall 207 and a second outer side wall 208; wherein, one end of the first outer side wall 207 is tangent to the inner side wall of the circumferential section 203 away from the pre-combustion section 204, such that the end of the circumferential section 203 away from the pre-combustion section 204 has the aforementioned pointed structure. The other end of the first outer side wall 207 is connected to the second outer side wall 208 at a first predetermined obtuse angle, thus combining... Figure 1 As shown, the outer wall of the pre-combustion chamber 2 first expands gradually along the first direction 101, and then gradually contracts.
[0043] In this embodiment, the pre-combustion chamber 2 and the guide section 302 are preferably integrally formed. The injection hole 306 is opened at the connection position between the pre-combustion chamber 2 and the guide section 302, and the injection hole 306 is opened at a first preset angle with the axial direction of the guide section 302, so that the product of the pre-combustion chamber 2 is injected into the main combustion chamber 304 at the first preset angle.
[0044] Furthermore, multiple injection holes 306 are spaced apart along the circumferential direction of the pre-combustion chamber 2; preferably, 60 injection holes 306 are provided, and the 60 injection holes 306 are spaced apart along the circumferential direction of the pre-combustion chamber 2.
[0045] Furthermore, the diameter of the injection hole 306 is set between 1 mm and 1.4 mm, preferably 1.2 mm.
[0046] Furthermore, the first preset angle is 45°.
[0047] In this embodiment, the detonation main combustion chamber 3 further includes a third inner wall 308 and a fourth inner wall 309 connected at a second preset obtuse angle; wherein, the second air intake duct 303 includes a second air intake section 310 and a second isolation section 311 connected sequentially along the first direction 101; the second isolation section 311 isolates the second air intake duct 303 from the downstream main combustion chamber through shock wave action.
[0048] The third inner wall 308 and the second outer wall 208 are at a second preset angle, a second air intake section 310 is formed between the third inner wall 308 and the first outer wall 207, and a second isolation section 311 is formed between the side walls of the third inner wall 308 and the second outer wall 208.
[0049] A main combustion chamber 304 is formed between the fourth inner wall 309 and the guide portion 302 and at the end near the pre-combustion chamber 2, and an injection chamber 305 is formed between the fourth inner wall 309 and the guide portion 302 and at the end away from the pre-combustion chamber 2.
[0050] Furthermore, the guide section 302 has a tapered structure 312 within the injection chamber 305 along the first direction 101. Optionally, the main body and tail of the guide section 302 are connected by a frustum, that is, the guide section 302 extends along the first direction 101 first, then expands, and finally contracts.
[0051] Furthermore, the guide section 302 is raised 307 towards the pre-combustion chamber 209. The products of combustion in the pre-combustion chamber 2 will be ejected along the raised surface and from the injection hole 306.
[0052] In practical implementation: the aircraft is designed to cruise at Mach 5, using a central cone axisymmetric air intake method, which splits the incoming airflow through the central cone. The main stream after splitting is further split into two paths by the outer wall of the pre-combustion chamber, one path entering the pre-combustion chamber and the other path entering the detonation main combustion chamber 3.
[0053] Of the total airflow, 20% enters the pre-combustion chamber. The high-enthalpy incoming airflow is first compressed by several oblique shock waves in the pre-combustion chamber inlet, reducing its velocity from Mach 5 to Mach 0.8 at the inlet outlet. It then passes through the first isolation section 206 into the pre-combustion chamber. The powdered fuel storage chamber 106 contains pre-filled powdered fuel, and the high-pressure air source 105 pushes the piston 104 to supply the powdered fuel to the pre-combustion chamber. The air entering the pre-combustion chamber mixes with the powdered fuel and undergoes slow combustion. Because the incoming flow is subsonic and the static pressure is relatively high, this increases the combustion rate of the powdered fuel.
[0054] After pre-combustion, the temperature of the rich combustion gas reaches 1200K~2000K (the gas temperature varies when using different powdered fuels). Under the action of the turbulence cone of the guide section 302, the gas is injected radially into the detonation main combustion chamber 3 at an injection angle of 45°. The injection holes 306 have a diameter of 1.2mm, and a total of 60 holes are evenly distributed in the circumferential direction.
[0055] The high-enthalpy incoming air about to enter the detonation main combustion chamber 3 is compressed by an oblique shock wave in the second intake duct 303 of the detonation main combustion chamber 3. At the outlet of the second intake duct 303, the airflow velocity is reduced from Mach 5 to Mach 2, and then it enters the detonation main combustion chamber 3 through the second isolation section 311. The high-speed incoming airflow is further mixed with the injected pre-combustion gas to organize rotational detonation combustion. The detonation main combustion chamber 3 is an annular combustion chamber with a length of 500 mm and a width of 50 mm, which is sufficient to meet the detonation requirements of the pre-combustion powder fuel. The mixed pre-combustion powder fuel and air are ignited by a forced ignition device 4, which contains a detonation tube arranged tangentially in the detonation main combustion chamber 3. The detonation tube uses the same powder fuel as the engine, and oxygen is selected as the oxidizer. The two form the initial powder fuel positive detonation wave, which enters the detonation main combustion chamber 3 tangentially to complete the ignition process. After detonation combustion, the gas temperature will reach 2000K~3500K (the gas temperature varies when different powder fuels are used). The high-temperature gas expands and does work through the tail nozzle, thereby propelling the aircraft into flight.
[0056] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this application.
Claims
1. A powder-fueled ramjet rotary detonation engine with dual combustion chambers, characterized in that, include: The central cone shaft includes a flow-diverting section and a storage section connected sequentially along a first direction; the flow-diverting section has a pointed cone structure in a direction opposite to the first direction, which can divide the incoming flow into an annular flow; the storage section is used to store combustion powder. The pre-combustion chamber has one end near the storage section that surrounds the storage section and forms a first air intake between it and the storage section; the other end of the pre-combustion chamber away from the storage section is surrounded by a pre-combustion cavity that communicates with the first air intake and the storage section for burning the combustion powder. The detonation main combustion chamber includes a main body and a guide section; the guide section is disposed on the side of the pre-combustion chamber opposite to the central cone axis; the main body is sleeved on the outside of the pre-combustion chamber and the guide section, forming a second air intake passage between the main body and the pre-combustion chamber that can guide the incoming flow, forming a main combustion chamber with the front part of the guide section, and forming an injection chamber with the rear part of the guide section; An injection hole is formed between the guide section and the pre-combustion chamber to guide the products generated in the pre-combustion chamber to the main combustion chamber.
2. The powder-fueled ramjet rotary detonation engine with dual combustion chambers according to claim 1, characterized in that, The pre-combustion chamber includes an enclosing section and a pre-combustion section connected to the enclosing section; The encircling section encircles the storage unit, and a first air intake is formed between the encircling section and the storage unit; The pre-combustion section surrounds the pre-combustion chamber, which communicates with the storage section and the first air intake. The pre-combustion chamber has a gradually expanding structure along the first direction.
3. The powder fuel ramjet rotary detonation engine with dual combustion chambers according to claim 2, characterized in that, The inner wall of the circumferential section has a spherical structure, which makes the first air intake channel have a ring structure. The first air intake includes a first air intake section and a first isolation section that are sequentially connected along the first direction.
4. The powder fuel ramjet rotary detonation engine with dual combustion chambers according to claim 2, characterized in that, The end of the circumferential section opposite to the pre-combustion section has a pointed structure; The tip structure can divide the annular flow into a first annular flow that is directed to the first air intake and a second annular flow that is directed to the second air intake.
5. The powder-fueled ramjet rotary detonation engine with dual combustion chambers according to claim 4, characterized in that, The pre-combustion chamber includes a first outer side wall and a second outer side wall; One end of the first outer sidewall is tangent to one end of the circumferential section away from the pre-combustion section, and the other end is connected to the second outer sidewall at a first preset obtuse angle.
6. The powder fuel ramjet rotary detonation engine with dual combustion chambers according to claim 1, characterized in that, The pre-combustion chamber and the flow guide are integrally formed; The injection hole is located at the connection between the pre-combustion chamber and the guide section, and the injection hole is opened at a first preset angle with the axial direction of the guide section, so that the product is injected into the main combustion chamber at the first preset angle.
7. The powder-fueled ramjet rotary detonation engine with dual combustion chambers according to claim 6, characterized in that, The injection holes are spaced apart along the circumferential direction of the pre-combustion chamber; The diameter of the injection hole is set between 1mm and 1.4mm.
8. The powder-fueled ramjet rotary detonation engine with dual combustion chambers according to claim 6, characterized in that, The flow guide is raised towards the pre-combustion chamber.
9. The powder-fueled ramjet rotary detonation engine with dual combustion chambers according to claim 5, characterized in that, The detonation main combustion chamber has a third inner wall and a fourth inner wall connected at a second preset obtuse angle; The second air intake includes a second air intake section and a second isolation section that are sequentially connected along the first direction; The third inner sidewall and the second outer sidewall form a second preset angle, the third inner sidewall and the first outer sidewall form a second air intake section, and the third inner sidewall and the second outer sidewall form a second isolation section. The main combustion chamber is formed between the fourth inner sidewall and the guide portion and at the end near the pre-combustion chamber, and the injection chamber is formed between the fourth inner sidewall and the guide portion and at the end away from the pre-combustion chamber.
10. The powder-fueled ramjet rotary detonation engine with dual combustion chambers according to claim 8, characterized in that, The guide section has a tapering structure along the first direction within the injection chamber.