A rotary detonation engine device and aircraft

Abstract

The application discloses a rotary detonation engine device and an aircraft. The rotary detonation engine device comprises a rotary detonation engine body and a solid fuel supply device. The rotary detonation engine body is provided with a combustion chamber. The solid fuel supply device comprises a solid fuel supply module and a fluidization module. The solid fuel supply module is connected with the fluidization module and is arranged to supply solid fuel to the fluidization module. The fluidization module is communicated with the combustion chamber and is arranged to fluidize the solid fuel into solid powder and deliver the solid powder to the combustion chamber. The rotary detonation engine device provided by the application has the characteristics of simplifying the structure and process of the rotary detonation engine device and shortening the launch period of the aircraft under the condition of obtaining higher thrust.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of engines, and more particularly, to a rotating detonation engine device and an aircraft. BACKGROUND

[0002] There are two combustion modes in nature, deflagration combustion and detonation combustion. The flame propagation rate of deflagration combustion is relatively low, and the combustion mode in power devices such as internal combustion engines, aeroengines and gas turbines is deflagration combustion. The detonation combustion is characterized by a shock structure upstream of the combustion zone, and the shock and the combustion zone are coupled together and propagate. The flame propagation speed of detonation combustion is much higher than that of deflagration combustion, and usually reaches thousands of meters per second. Rotating detonation engine is a kind of engine type created by using detonation combustion. The detonation wave propagates along the circular axis of the engine, continuously igniting the fuel injected into the combustion chamber.

[0003] With the increasing competition in the field of aerospace, along with the continuous deepening of the research on hypersonic aircraft and single-stage orbiting power systems, new rotating detonation engine technology has developed rapidly. Rotating detonation engine is fundamentally different from traditional aeroengines, rocket engines and the like. Rotating detonation engine can produce larger thrust at low pressure ratio, and the combustion chamber is designed to be smaller, so that higher thrust-to-weight ratio is obtained. Studies have shown that the propulsion technology based on detonation combustion can greatly reduce fuel consumption and greatly improve the specific impulse characteristics of power devices, which has important significance for widening the working envelope of air-breathing aircraft and improving the economic efficiency and combat performance of existing weapon equipment.

[0004] According to its working mode, the detonation engine can be roughly divided into the following three types: pulse detonation engine, continuous rotating detonation engine (RDE) and oblique detonation engine. According to its application mode, the detonation engine can be divided into rocket-type detonation engine, ramjet-type detonation engine and combined-type detonation engine.

[0005] Due to the strong flowability and easy to push control characteristics of gaseous fuel and liquid fuel, rotating detonation engine generally uses gaseous fuel or liquid fuel for detonation combustion. Rotating detonation engine using gaseous or liquid fuel faces the following problems: a special gaseous fuel or liquid fuel storage and supply device needs to be set, and an oxidizer storage and supply device also needs to be set, which occupies a large space of the engine; and the gaseous or liquid fuel storage device must have good structural sealing; the transportation and filling of gaseous or liquid fuel to the engine occupies a lot of manpower and working hours, and prolongs the launch period of the aircraft. SUMMARY

[0006] Compared with gaseous and liquid fuels, solid fuels have their unique advantages: on the one hand, some solid fuels have higher energy density, better stability, stronger environmental adaptability, are convenient to store and transport, and have a wide range of raw materials and low prices; on the other hand, solid fuel engines also have their unique advantages, including better reliability and simpler structure. In addition, the solid fuel engine does not need a complex and time-consuming fuel loading process before ignition, so the launch cycle is shorter and the response is faster.

[0007] Rotary detonation combustion generally uses gaseous or liquid fuel, and rarely uses solid powder fuel, especially in the field of continuous rotary detonation ramjet engines of solid fuel, there is currently no related patent and engineering practice. The main reason why rotary detonation combustion rarely uses solid powder fuel is that detonation combustion requires particularly harsh combustion conditions, such as good mixing method, ignition condition, engine geometry, etc.

[0008] The main purpose of the embodiment of the present application is to provide a rotary detonation engine device, which delivers the solid fuel powder that has been fluidized by the fluidization module of the solid fuel supply device to the rotary detonation engine body, and organizes combustion through continuous rotary detonation waves. The rotary detonation engine device of the present application can make the structure design of the rotary detonation engine device smaller, obtain higher thrust-to-weight ratio, and obtain higher thermal efficiency of the solid fuel, and simplify the device structure and process of the fuel supply part.

[0009] The embodiment of the present application provides a rotary detonation engine device, which comprises:

[0010] The rotary detonation engine body is provided with a combustion chamber; and

[0011] The solid fuel supply device comprises a solid fuel supply module and a fluidization module, the solid fuel supply module is connected with the fluidization module and is arranged to supply solid fuel to the fluidization module; the fluidization module is in communication with the combustion chamber and is arranged to fluidize the solid fuel into solid powder and deliver the solid powder to the combustion chamber.

[0012] The embodiment of the present application provides an aircraft comprising the rotary detonation engine device according to any one of the above exemplary embodiments.

[0013] The rotary detonation engine device of the embodiment of the present application delivers the solid powder that has been fluidized by the fluidization module of the solid fuel supply device to the rotary detonation engine body, and generates thrust through organized combustion by continuous rotary detonation waves. Since the detonation wave of the rotary detonation engine has the characteristics of self-pressurization, the pressure and thermal efficiency of the combustion chamber can be greatly improved, and the advantages of the rotary detonation engine are obtained, that is, a larger thrust can be generated at a low pressure ratio, the combustion chamber can be designed to be relatively smaller, and the thrust-to-weight ratio is higher.

[0014] And, the rotary detonation engine device of the application adopts the fluidization module of the solid fuel supply device to provide solid fuel for the rotary detonation engine device. The solid fuel has the advantages of higher energy density, better stability, stronger environmental adaptability, convenient storage and transportation, and low price of raw materials. Therefore, the rotary detonation engine device of the application can use high-speed airflow to blow up the solid powder to form a more easily combustible solid powder similar to a fluid state. In this way, it is not necessary to specially design an oxidant supply device and a complex gas and liquid fuel supply device. Therefore, compared with the rotary detonation engine device supplied with gas and liquid fuel, the rotary detonation engine device of the application can simplify the structural design of the engine device, improve the thermal efficiency of the fuel, shorten the launch cycle of the engine, simplify the fuel loading process, and reduce the manufacturing cost of the engine.

[0015] And, the solid powder fuel has good stream following property and is convenient to adjust, so that the engine can be started multiple times and the thrust can be adjusted. At the same time, the continuous detonation engine based on solid powder is a revolutionary technology, which can be applied to land-based and sea-based hypersonic strategic missiles to achieve global precision strike.

[0016] Other features and advantages of the rotary detonation engine device of the embodiments of the application will be described in the subsequent description. BRIEF DESCRIPTION OF DRAWINGS

[0017] The accompanying drawings are included to provide a further understanding of the technical solutions of the application, and constitute a part of the specification, and are used to explain the technical solutions of the application together with the embodiments of the application, and do not constitute a limitation to the technical solutions of the application.

[0018] Figure 1 FIG. 1 is a structural schematic diagram of the rotary detonation engine device of the application;

[0019] Figure 2 FIG. 2 is a cross-sectional structural schematic diagram of the rotary detonation engine device of the application; Figure 1

[0020] Figure 3 FIG. 3 is a cross-sectional structural schematic diagram of the rotary detonation engine device of the application along the A-A direction. Figure 2

[0021] Reference signs:

[0022] ​​1 - rotary engine body, 11 - combustion chamber, 12 - intake port, 13 - intake port inner cone, 131 - cavity, 14 - intake port outer shell, 15 - tail jet module, 16 - ignition module, 2 - solid fuel supply device, 21 - solid fuel supply module, 211 - solid fuel storage cavity, 212 - drive module, 2121 - piston, 22 - fluidization module, 221 - airflow channel, 222 - fluidization cavity, 2221 - first air inlet channel, 23 - mixing module, 231 - mixing cavity, 232 - premixing module, 233 - secondary mixing module, 2321 - first mixing cavity, 2331 - second mixing cavity, 2332 - second air inlet channel, 234 - compensation channel. DETAILED DESCRIPTION

[0023] To make the objectives, technical solutions and advantages of the present application clearer, below the embodiments of the present application will be described in detail with reference to the drawings. Obviously, the described embodiments are only a part of the embodiments of the present application, but not all the embodiments. Based on the embodiments in the present application, all the other embodiments obtained by those skilled in the art without creative work belong to the scope of protection of the present application.

[0024] At present, the existing rotary detonation combustion generally uses gaseous fuel or liquid fuel combustion. The main reason why rotary detonation combustion does not use solid powder fuel is that detonation combustion method requires particularly harsh combustion conditions, such as good mixing method, ignition condition, engine geometry, etc.

[0025] Compared with gaseous and liquid fuels, solid fuel has its unique advantages: on the one hand, the energy density of some solid fuels is higher, the stability is better, the environmental adaptability is stronger, the storage and transportation are convenient, and the raw materials are widely available and low in price. On the other hand, solid fuel engine also has its unique advantages, including better reliability and simpler structure. In addition, the solid fuel engine does not need a complex and time-consuming fuel loading process before ignition, so its launch cycle is shorter and its response is faster.

[0026] The embodiments of the present application fluidize and inject solid fuel powder, ensure the structural strength of the combustion chamber and the detonation wave initiation condition, and combine the new advanced detonation combustion with the traditional solid fuel powder fluidization treatment technology in the rotary detonation engine device of the embodiments of the present application.

[0027] Please refer to the drawings of the specification Figures 1 to 3The embodiment of the present application provides a rotary detonation engine device, which comprises a rotary detonation engine body 1 and a solid fuel supply device 2, wherein the rotary detonation engine body 1 is provided with a combustion chamber 11; the solid fuel supply device 2 comprises a solid fuel supply module 21 and a fluidization module 22; the solid fuel supply module 21 is connected with the fluidization module 22 and is arranged to supply solid fuel to the fluidization module 22; the fluidization module 22 is communicated with the combustion chamber 11 and is arranged to fluidize the solid fuel into solid powder and deliver the solid powder to the combustion chamber 11.

[0028] Specifically, as shown in the figure, Figures 1 to 2 the rotary detonation engine device of the present application not only comprises the rotary detonation engine body 1, but also comprises the solid fuel supply device 2; the rotary detonation engine body 1 comprises the combustion chamber 11, an air inlet 12 and an air inlet device (not shown in the figure), a tail jet module 15 and an ignition module 16. The air inlet device can be a special oxidant air inlet device, or the air inlet device can be directly communicated with the outside atmosphere.

[0029] It is worth noting that the fluidization module 22 is communicated with the combustion chamber 11 and is arranged to fluidize the solid fuel into solid powder and deliver the solid powder to the combustion chamber 11. The fluidization module 22 can be a device for blowing the solid powder by using high-pressure gas to form a state similar to fluid, and the solid powder similar to fluid is easier to burn. Of course, it is not necessarily to mix the solid powder and the high-pressure gas to form the fluidized solid powder, for example, the large-particle solid state can be crushed and then mixed and fluidized, which is not limited herein.

[0030] The rotary detonation engine device provided by the embodiment of the present application delivers the fluidized solid powder to the rotary detonation engine body through the fluidization module of the solid fuel supply device, and generates thrust through continuous rotary detonation wave organization combustion. Since the detonation wave of the rotary detonation engine has the self-pressurization characteristic, the rotary detonation engine of the present application can greatly improve the pressure and thermal efficiency of the combustion chamber compared with the conventional internal combustion engine, aero-engine and gas turbine power device, and has the advantages of the rotary detonation engine, that is, a larger thrust can be generated under a low pressure ratio, the combustion chamber can be designed to be relatively smaller, and the thrust-to-weight ratio is higher.

[0031] Existing rotary detonation engines all use gaseous or liquid fuel to supply the combustion chamber. The rotary detonation engine device of this application uses a solid fuel supply device to provide solid fuel to the rotary detonation engine device. Some solid fuels have advantages over liquid and gaseous fuels, such as higher energy density, better stability, stronger environmental adaptability, easier storage and transportation, and wider availability and lower cost of raw materials. Furthermore, the rotary detonation engine device of this application can utilize high-speed airflow to agitate the solid powder, forming a fluid-like solid powder that is easier to combust. This eliminates the need for a specially designed oxidizer supply device and a complex gas / liquid fuel supply device. Therefore, compared to rotary detonation engine devices supplied with gas or liquid fuel, the rotary detonation engine device of this application, while achieving higher thrust, simplifies the engine device's structural design, improves fuel thermal efficiency, shortens the engine's launch cycle, simplifies the fuel loading process, and reduces the engine's manufacturing cost.

[0032] Furthermore, solid powder fuel exhibits good flow characteristics, making it easy to adjust and enabling multiple engine starts and adjustable thrust. Meanwhile, the continuous rotating detonation engine based on solid fluidized powder is a revolutionary technology that can be applied to land-based and sea-based hypersonic strategic missiles, achieving global precision strikes.

[0033] In one exemplary embodiment, such as Figure 2 As shown, the fluidization module 22 is provided with an airflow channel 221 and a fluidization cavity 222. The cavity wall of the fluidization cavity 222 is provided with a first air inlet channel 2221 that connects the airflow channel 221 and the fluidization cavity 222.

[0034] The solid fuel supply module 21 is provided with a solid fuel storage chamber 211 and a drive module 212. The solid fuel storage chamber 211 is connected to the fluidization chamber 222. The drive module 212 is configured to drive the solid fuel powder in the solid fuel storage chamber 211 into the fluidization chamber 222 so that the solid fuel powder is fluidized under the action of the airflow conveyed by the airflow channel 221.

[0035] Specifically, such as Figure 2 As shown, the first air inlet channel 2221 can be provided with multiple layers of air inlet channels along the axial direction of the cavity wall of the fluidizing cavity 222, and each layer of air inlet channels has multiple air inlets evenly distributed at intervals along the circumferential direction of the cavity wall of the fluidizing cavity 222.

[0036] In an exemplary embodiment, the rotating detonation engine body 1 is provided with an air intake 12, which is configured to deliver a gaseous oxidant, and the output end of the air intake 12 is connected to the input end of the airflow channel 221.

[0037] Specifically, an air intake duct 12 is provided to transport gaseous oxidant, and the output end of the air intake duct 12 is connected to the input end of the airflow channel 221. Thus, the airflow used to fluidize the solid powder originates from the air intake duct 12 that transports the gaseous oxidant. Of course, the airflow channel 221 and the airflow used to fluidize the solid powder can also originate from other gaseous fuel devices, utilizing gaseous fuel to fluidize solid fuel powder and achieving mixed combustion of multiple fuels in the combustion chamber. Connecting the output end of the air intake duct 12 to the input end of the airflow channel 221 simplifies the structural design and manufacturing process of the rotary detonation engine device of this application.

[0038] In an exemplary embodiment, the inlet of the intake duct 12 is connected to the outside atmosphere, and the airflow passage 221 surrounds the outside of the solid fuel storage chamber 211 and the fluidization chamber 222.

[0039] Specifically, the input end of the intake duct 12 is connected to the outside atmosphere, and the intake air passage 221 is connected to the intake duct 12. This utilizes the atmosphere as the intake source, with atmospheric oxygen acting as the oxidant. The oxygen reacts with the solid fuel (i.e., the reducing agent) provided by the fluidization module 22 of the solid fuel supply device 2 in the rotary detonation engine, forming a high-temperature, high-pressure gas. This gas is then discharged through the nozzle module 15, generating thrust. Thus, the rotary detonation engine device of this application becomes a rotary detonation ramjet engine device. This design simplifies the structural design and manufacturing process of the rotary detonation engine, eliminating the need for a dedicated oxidant supply device.

[0040] In an exemplary embodiment, the solid fuel storage chamber 211 and the fluidization chamber 222 are connected to form an integrated structure, which simplifies the structural design and space occupation of the solid fuel supply device 2 and helps to reduce costs.

[0041] In one exemplary embodiment, the cross-sectional area of ​​the fluidization chamber 222 gradually decreases along the direction close to the combustion chamber 11.

[0042] In an exemplary embodiment, the solid fuel storage chamber 211 and the fluidization chamber 222 are connected to form an integral structure, and the cross-sectional area of ​​the fluidization chamber 222 gradually decreases along the direction close to the combustion chamber 11.

[0043] Specifically, such as Figure 2 As shown, a first air inlet channel 2221 is provided in the cavity wall region where the cross-sectional area of ​​the fluidization cavity 222 gradually decreases. This structure allows the airflow through the airflow channel 221 and the first air inlet channel 2221 to converge more effectively and fully contact the solid fuel powder to achieve the fluidization process.

[0044] In an exemplary embodiment, the driving module 212 comprises a piston 2121 arranged inside the solid fuel storage cavity 211, and a driving member (not shown in the figure) connected to the piston 2121. The fluidization cavity 222 is in communication with the end of the solid fuel storage cavity 211 away from the piston 2121.

[0045] The driving member (not shown in the figure) is arranged to drive the piston 2121 to move, so as to push the solid fuel powder to the fluidization cavity 222.

[0046] In an exemplary embodiment, as shown in Figure 2 The rotary detonation engine body 1 further comprises an air inlet inner cone 13 and an air inlet shell 14, the air inlet shell 14 being sleeved outside the air inlet inner cone 13 and surrounding the air inlet inner cone 13 to form the air inlet 12. The air inlet inner cone 13 is provided with a cavity 131 connected with the solid fuel storage cavity 211, for accommodating the driving member (not shown in the figure). In this way, the space inside the air inlet is reasonably utilized to accommodate the driving member, without the need to additionally arrange other space to accommodate the driving member, which is conducive to reducing the volume and weight of the engine.

[0047] In an exemplary embodiment, the driving member (not shown in the figure) is an electric motor or a cylinder; when the driving member (not shown in the figure) is a cylinder, the air inlet inner cone 13 is provided with a through hole in communication with the air inlet 12 and the cavity 131.

[0048] Specifically, since the powder particles in the solid fuel storage cavity 211 are in a discrete solid state, they have no flowability, and therefore need a corresponding flow carrier to realize fluidization and powder delivery. In order to keep the solid fuel in the solid fuel storage cavity 211 have the same density in the spatial distribution in the cavity, a common method is to add a piston 2121 in the solid fuel storage cavity 211, and apply the piston 2121 to push the solid fuel forward to fill the gap left by the output powder. According to the driving mode of the piston 2121, the driving module 212 can be divided into a pneumatic driving piston and an electric motor driving piston, i.e. the driving member (not shown in the figure) is an electric motor or a cylinder.

[0049] Among them, the pneumatic driving piston has a more compact fluidization powder feeding structure, and the negative mass of the driving module 212 is smaller. In order to prevent the solid fuel from accumulating in the converging part, a one-way gas path is generally added in the converging structure. The fluidization powder feeding structure of the pneumatic driving piston can flexibly adjust the powder flow rate.

[0050] The fluidized powder feeding structure driven by the motor drives the piston, and the driving cavity and the fluidized cavity are connected with the pipeline powder feeding to keep the pressure difference of the piston relatively stable. The powder feeding is realized by the motor driving the piston movement, the system pipeline is relatively simple, the operation difficulty of the thrust adjustment is relatively small, however, the negative mass of the motor driving the piston is large, the requirement of the engine system integration is high, the motor speed can be adjusted to control the movement rate of the piston, and the stable movement of the piston is realized.

[0051] In an exemplary embodiment, as shown in Figure 2 The solid fuel supply device 2 further comprises at least one mixing module 23 between the fluidization module 22 and the combustion chamber 11, and the mixing module 23 is provided with a mixing cavity 231. The rotary detonation engine body 1 is provided with an air inlet 12 arranged to transport gaseous oxidant, and the air inlet 12 is in communication with the mixing cavity 231.

[0052] The mixing module 23 is arranged to mix the solid fuel powder fluidized and output by the fluidization module 22 with the gaseous oxidant transported by the air inlet 12.

[0053] Specifically, at least one mixing module 23 is arranged between the fluidization module 22 and the combustion chamber 11, so as to more fully fluidize and mix the solid powder fluidized by the fluidization module 22; at the same time, the solid fuel powder fluidized and output by the fluidization module 22 is mixed with the gaseous oxidant transported by the air inlet 12, so as to realize the mixing of the fuel and the oxidant and facilitate the adjustment of the air-fuel ratio of the rotary detonation engine.

[0054] In an exemplary embodiment, as shown in Figure 2 The number of mixing modules 23 is two, and the two mixing modules 23 are respectively a premixing module 232 and a secondary mixing module 233. The mixing cavities 231 of the premixing module 232 and the secondary mixing module 233 are respectively denoted as a first mixing cavity 2321 and a second mixing cavity 2331, and an electric control valve (not shown in the figure) is arranged between the first mixing cavity 2321 and the second mixing cavity 2331. The fluidization module 22, the premixing module 232, the electric control valve (not shown in the figure), the secondary mixing module 233 and the combustion chamber 11 are sequentially connected.

[0055] The premixing module 232 is arranged to premix the solid fuel powder and the gaseous oxidant under the action of the airflow transported by the air inlet 12; and the secondary mixing module 233 is arranged to perform secondary mixing of the solid fuel powder and the gaseous oxidant under the action of the compensation airflow 234 transported by the air inlet 12. The main purpose of the secondary mixing is to avoid the accumulation of the solid fuel powder in the conveying process, and it is also beneficial to optimize the air-fuel ratio.

[0056] It should be noted that the number of mixing modules 23 is not limited to two, but can be one, three or more, so that the mixed solid powder is better, and the air-fuel ratio between the solid powder and the gaseous oxidant is better.

[0057] The first mixing chamber 2321 and the second mixing chamber 2331 are provided with an electrically controlled valve, which adjusts the air-fuel ratio between the solid powder and the gaseous oxidant by opening and closing the electromagnetic valve in combination with the second mixing chamber 2331.

[0058] In an exemplary embodiment, as shown in Figure 2 The fluidization module 22 is provided with a fluidization chamber 222, the first mixing chamber 2321 is in communication with the fluidization chamber 222, the input end of the air inlet channel 12 is in communication with the outside atmosphere, and the output end of the air inlet channel 12 is in communication with the fluidization chamber 222 through the airflow passage 221.

[0059] The airflow passage 221 is connected with a compensation flow channel 234, the two ends of the compensation flow channel 234 are in communication with the airflow passage 221 and the second mixing chamber 2331 respectively, and the air inlet channel 12 is indirectly connected with the second mixing chamber 2331 through the airflow passage 221 and the compensation flow channel 234.

[0060] In this way, the same air inlet channel can provide airflow to the fluidization chamber 222, the first mixing chamber 2321 and the second mixing chamber 2331, greatly simplifying the air supply structure of the engine.

[0061] In an exemplary embodiment, the airflow passage 221 surrounds the outside of the fluidization chamber 222, and the number of compensation flow channels 234 is multiple, and the multiple compensation flow channels 234 are arranged in a circumferential direction of the airflow passage 221.

[0062] Specifically, as shown in Figure 3 The compensation flow channels 234 are arranged in a circumferential direction of the airflow passage 221, and the number of compensation flow channels 234 is six, of course, the number of compensation flow channels 234 is not limited to six.

[0063] In an exemplary embodiment, as shown in Figures 2-3 The second mixing chamber 2331 is provided with multiple second air inlet channels 2332 at one end close to the combustion chamber 11, and the second air inlet channels 2332 are used for the mixed solid fuel powder and gaseous oxidant to enter the combustion chamber 11.

[0064] Specifically, Figure 3 The cross-sectional structure diagram of the rotary detonation engine device of the embodiment shown in the figure, the second air inlet channel 2332 is a 3-circle air inlet channel, of course, the second air inlet channel 2332 of the rotary detonation engine device of the present application is not limited to 3 circles.

[0065] In an exemplary embodiment, the solid fuel powder includes at least one of boron powder and magnesium powder.

[0066] Specifically, using high-energy metal or / and metalloid powder such as boron powder or magnesium powder as fuel, stable continuous detonation can be achieved, and the propulsion performance of the rotary detonation engine device is greatly improved, and the specific impulse and range of the aircraft are greatly improved.

[0067] In an exemplary embodiment, as shown in Figure 1 and Figure 3 The rotary detonation engine body 1 further comprises an ignition module 16, which can be a pre-detonation tube, an electric detonator. Of course, the ignition module 16 is not limited to a pre-detonation tube, an electric detonator.

[0068] In an exemplary embodiment, as shown in Figure 1 and Figure 2 The rotary detonation engine body 1 further comprises a tail jet module 15, and a tail jet channel is formed between the tail jet module 15 and the combustion chamber 11, which is used to discharge the tail jet flow to generate thrust.

[0069] The embodiment of the present application provides a kind of aircraft, comprising the rotary detonation engine device as described in any one of the above exemplary embodiments.

[0070] The aircraft provided by the embodiment of the present application comprises the rotary detonation engine device as described in any one of the above exemplary embodiments, and therefore has the technical features and advantages of the rotary detonation engine device as described in any one of the above exemplary embodiments, which will not be repeated here.

[0071] Unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connecting", "fixing" and the like should be understood in a broad sense, for example, it can be fixedly connected, or it can be detachably connected, or it can be integrated; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the internal communication of two elements or the interaction relationship between two elements, unless otherwise explicitly limited. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0072] In the description of the specification, the description of the terms "one embodiment", "some embodiments", "an example", "a specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are contained in at least one embodiment or example of the present application. In the specification, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any suitable manner in any one or more embodiments or examples. In addition, the person skilled in the art can combine and combine the different embodiments or examples described in the specification and the features of the different embodiments or examples without contradiction.

[0073] Although the embodiments of the present application have been shown and described above, it is understood that the above-described embodiments are exemplary and are not to be construed as limiting the present application, and those skilled in the art can make changes, modifications, replacements and variations to the above-described embodiments within the scope of the present application.

Claims

1. A rotary detonation engine apparatus, characterized by, The rotary detonation engine device comprises: a rotary detonation engine body (1) provided with a combustion chamber (11); and a solid fuel supply device (2) comprising a solid fuel supply module (21) and a fluidization module (22), the solid fuel supply module (21) is connected with the fluidization module (22) and is arranged to supply solid fuel to the fluidization module (22); the fluidization module (22) is communicated with the combustion chamber (11) and is arranged to fluidize the solid fuel into solid powder and deliver the solid powder to the combustion chamber (11); the fluidization module (22) is provided with an airflow flow channel (221) and a fluidization cavity (222), the cavity wall of the fluidization cavity (222) is provided with a first air inlet channel (2221) communicated with the airflow flow channel (221) and the fluidization cavity (222); the rotary detonation engine body (1) is provided with an air inlet channel (12), the air inlet channel (12) is arranged to deliver gaseous oxidant, and the output end of the air inlet channel (12) is communicated with the input end of the airflow flow channel (221). the solid fuel supply module (21) is provided with a solid fuel storage cavity (211) and a driving module (212), the solid fuel storage cavity (211) is communicated with the fluidization cavity (222), and the driving module (212) is arranged to drive the solid powder in the solid fuel storage cavity (211) into the fluidization cavity (222) so that the solid powder is fluidized under the action of the airflow delivered by the airflow flow channel (221).

2. The rotary detonation engine apparatus of claim 1, wherein, the input end of the air inlet channel (12) is communicated with the outside atmosphere, and the airflow flow channel (221) is arranged outside the solid fuel storage cavity (211) and the fluidization cavity (222).

3. The rotary detonation engine device of claim 2, wherein, 4. The rotary detonation engine device according to claim 2, wherein the solid fuel storage cavity (211) and the fluidization cavity (222) are integrated; and / or the cross-sectional area of the fluidization cavity (222) gradually decreases along the direction close to the combustion chamber (11). the driving module (212) comprises a piston (2121) arranged inside the solid fuel storage cavity (211) and a driving member connected with the piston (2121), and the fluidization cavity (222) is communicated with the end of the solid fuel storage cavity (211) away from the piston (2121); 5. The rotary detonation engine apparatus of any one of claims 2-4, wherein, the driving member is arranged to drive the piston (2121) to move so as to push the solid powder into the fluidization cavity (222). the rotary detonation engine body (1) further comprises an air inlet channel inner cone (13) and an air inlet channel shell (14), the air inlet channel shell (14) is arranged outside the air inlet channel inner cone (13) and cooperates with the air inlet channel inner cone (13) to form the air inlet channel (12), and the air inlet channel inner cone (13) is provided with a cavity (131) connected with the solid fuel storage cavity (211) and used for accommodating the driving member.

6. The rotary detonation engine device of claim 5, wherein, the driving member is an electric motor or an air cylinder, and when the driving member is an air cylinder, the air inlet channel inner cone (13) is provided with a through hole communicated with the air inlet channel (12) and the cavity (131).

7. The rotary detonation engine device of claim 6, wherein, ​ 8. The rotary detonation engine apparatus of any one of claims 1-4, wherein, The solid fuel supply device (2) further comprises at least one mixing module (23) between the fluidization module (22) and the combustion chamber (11), and the mixing module (23) is provided with a mixing cavity (231); the rotary detonation engine body (1) is provided with an air inlet channel (12) configured to deliver gaseous oxidants, and the air inlet channel (12) is in communication with the mixing cavity (231). The mixing module (23) is configured to mix the solid powder fluidized and output by the fluidization module (22) with the gaseous oxidants delivered by the air inlet channel (12).

9. The rotary detonation engine device of claim 8, wherein, The number of the mixing modules (23) is two, and the two mixing modules (23) are respectively a premixing module (232) and a secondary mixing module (233), the mixing cavities (231) of the premixing module (232) and the secondary mixing module (233) are respectively denoted as a first mixing cavity (2321) and a second mixing cavity (2331), and an electric control valve is arranged between the first mixing cavity (2321) and the second mixing cavity (2331); the fluidization module (22), the premixing module (232), the electric control valve, the secondary mixing module (233), and the combustion chamber (11) are sequentially connected. The premixing module (232) is configured to premix the solid fuel powder and the gaseous oxidants under the action of the airflow delivered by the air inlet channel (12); and the secondary mixing module (233) is configured to secondarily mix the solid fuel powder and the gaseous oxidants under the action of a compensation airflow delivered by the air inlet channel (12).

10. The rotary detonation engine device of claim 9, wherein, The fluidization module (22) is provided with a fluidization cavity (222), the first mixing cavity (2321) is in communication with the fluidization cavity (222), an input end of the air inlet channel (12) is in communication with the external atmosphere, and an output end of the air inlet channel (12) is in communication with the fluidization cavity (222) through an airflow flow channel (221). The airflow flow channel (221) is connected with a compensation flow channel (234), two ends of the compensation flow channel (234) are respectively in communication with the airflow flow channel (221) and the second mixing cavity (2331), and the air inlet channel (12) is indirectly connected with the second mixing cavity (2331) through the airflow flow channel (221) and the compensation flow channel (234).

11. The rotary detonation engine device of claim 10, wherein, The airflow flow channel (221) surrounds the outside of the fluidization cavity (222), and the number of the compensation flow channels (234) is multiple, and the multiple compensation flow channels (234) are arranged along the circumference of the airflow flow channel (221).

12. The rotary detonation engine device of claim 9, wherein, The second mixing cavity (2331) is provided with multiple second air inlet channels (2332) near one end of the combustion chamber (11), and the second air inlet channels (2332) are configured to allow the mixed solid powder and gaseous oxidants to enter the combustion chamber (11).

13. The rotary detonation engine device of any one of claims 1-4, wherein, The solid powder comprises at least one of boron powder and magnesium powder.

14. An aircraft, characterized in that The rotary detonation engine device comprises the rotary detonation engine device according to any one of claims 1 to 13.

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