Continuous rotating detonation ramjet engine and aircraft based on solid-liquid mixed fuel

Abstract

The present invention relates to a continuous rotating detonation ramjet engine and an aircraft based on solid-liquid mixed fuel, wherein the continuous rotating detonation ramjet engine comprises: a hollow outer shell, a hollow center body arranged in the outer shell, and a gas generating device at least partially installed in the center body; the gas generating device comprises: a gas generator, a mixed cracker connected to the gas generator, a fuel storage tank connected to the mixed cracker, and a gas injector connected to the mixed cracker; a reflux channel is arranged on the side wall of the center body, and the reflux channel is respectively connected to the mixed cracker and the fuel storage tank; the gas generator is filled with oxygen-poor propellant solid to generate primary fuel-rich gas; the fuel storage tank is filled with liquid fuel and compressed gas, so that the liquid fuel is driven by the compressed gas to be injected into the mixed cracker along the reflux channel.

Description

Technical Field

[0001] The present invention relates to the field of aerospace, and in particular to a continuous rotating detonation ramjet engine and an aircraft based on solid-liquid mixed fuel. Background Art

[0002] The solid rocket continuous rotating detonation ramjet engine based on detonation combustion is a new type of continuous rotating detonation engine. It produces a primary fuel-rich gas by self-sustaining combustion after ignition of the oxygen-poor solid propellant in the gas generator. The primary fuel-rich gas is mixed with the air flow through the gas injection device and completes the detonation combustion, which effectively improves the specific impulse and cycle efficiency of the traditional deflagration combustion ramjet engine, and greatly reduces the engine structure mass. It has the advantages of high volume specific impulse, stable and easy flow adjustment, fast response, and long storage time. It is suitable as a power propulsion device for aircraft with limited volume. In the current conventional configuration, the primary fuel-rich gas generated by the gas generator has a high temperature and a high content of large-particle condensed phase components. Since the primary fuel-rich gas itself has a high temperature, generally around 1500℃, if it is directly sprayed into the annular combustion chamber without treatment and mixed with the incoming flow, it will quickly cause deflagration combustion to consume the premixed gas, resulting in a large amount of fuel consumed to maintain the continuous propagation of the rotating detonation wave, making the detonation wave intensity unstable or even extinguished, thereby reducing the overall efficiency of the primary fuel-rich gas combustion.

[0003] In addition, the traditional kerosene pre-combustion rotating detonation ramjet engine uses kerosene as a regenerative coolant, which is passed into the pre-combustion chamber after absorbing heat, and is premixed with a portion of oxygen or air to generate more active rich fuel gas. Since an oxygen supply system or an air boost supply system needs to be added as the input source of oxidizing gas in the pre-combustion chamber, the system has more parts and components, and its maintenance and operation are more complicated than the solid fuel rotating detonation ramjet engine using a gas generator. Moreover, kerosene itself has poor chemical activity and requires atomization and evaporation, making it difficult to organize efficient combustion.

[0004] In addition, detonation combustion requires the engine combustion chamber and the inner wall of the tail nozzle to withstand extremely high temperatures, and the thermal protection pressure is high. Simply relying on passive protection of thermal protection materials will bring more dead weight, reducing the range and payload of the aircraft. If active thermal protection measures such as liquid CO2 are used, a complex supply system will also be required, which makes it difficult to achieve long-range operation. Summary of the invention

[0005] The object of the present invention is to provide a continuous rotating detonation ramjet engine and an aircraft based on solid-liquid mixed fuel, so as to solve the problem of low overall efficiency of primary rich fuel gas combustion in a traditional continuous rotating detonation engine.

[0006] Another object of the present invention is to provide a continuous rotating detonation ramjet engine and aircraft based on solid-liquid mixed fuel, which is used to solve the problem that traditional continuous rotating detonation engines rely solely on passive protection, which will bring more dead weight and reduce the range and load of the aircraft.

[0007] To achieve the above-mentioned purpose, the present invention provides a continuous rotating detonation ramjet engine based on solid-liquid mixed fuel, comprising: a hollow outer shell, a hollow center body, and a gas generating device at least partially installed in the center body;

[0008] The gas generating device comprises: a gas generator, a mixed cracker connected to the gas generator, a fuel storage tank and a gas injector connected to the mixed cracker;

[0009] A reflux channel for connecting the hybrid cracker and the fuel tank is provided on the side wall of the center body; wherein the reflux channels converge and communicate at the tip of the conical tail nozzle of the center body, and the convergence part of the reflux channels is communicated with the fuel tank;

[0010] The gas generator is filled with oxygen-depleted propellant solid;

[0011] The fuel tank is filled with liquid fuel and compressed gas, and the compressed gas drives the liquid fuel to flow along the reflux channel to cool the center body and heat it to become fuel vapor, and then inject it into the hybrid cracker;

[0012] The hybrid cracker comprises: a mixing cavity, and a channel connector arranged outside the mixing cavity;

[0013] The channel connector has a transition channel,

[0014] The mixing chamber has a side wall connecting channel; wherein the side wall connecting channel, the transition channel and the reflux channel are connected;

[0015] The gas injector comprises: a connecting pipe, and an injection distributor connected to the connecting pipe;

[0016] A plurality of injection ports are arranged at equal intervals in the circumferential direction of the injection distributor;

[0017] The side wall of the central body is provided with a plurality of injection ports connected to the injection ports;

[0018] The injection port and the reflux channel are arranged in a staggered manner.

[0019] According to one aspect of the present invention, the mixing chamber is in a hollow cylindrical structure as a whole;

[0020] Along the axial direction of the mixing cavity, the channel connector is arranged at the middle position of the mixing cavity;

[0021] The cross-sectional size of the side wall connecting channel is smaller than the cross-sectional size of the transition channel.

[0022] According to one aspect of the present invention, at least one side wall connecting channel connected to each of the transition channels is provided on the mixing chamber; wherein, if the number of the side wall connecting channels connected to each of the transition channels is more than one, the opening spacing of adjacent side wall connecting channels on the inner wall of the mixing chamber is greater than the opening spacing on the outer wall of the mixing chamber.

[0023] According to one aspect of the present invention, the connecting pipe is coaxially arranged with the injection distributor;

[0024] The injection distributor has a hollow gas containing chamber;

[0025] The injection port is arranged to communicate with the gas containing chamber;

[0026] The hollow portion of the connecting pipe is in communication with the gas containing chamber;

[0027] The space of the gas containing chamber is larger than the space of the hollow part of the connecting pipe, and the ratio of the space of the gas containing chamber to the space of the hollow part of the connecting pipe satisfies: greater than 1 and less than or equal to 2;

[0028] The gas containing cavity is a funnel-shaped annular cavity;

[0029] Along the direction from the connecting pipe to the injection distributor, the cross-sectional area of ​​the gas containing chamber is gradually reduced along the axial direction.

[0030] According to one aspect of the present invention, a partition is provided in the reflux channel, and the partition is located between adjacent injection ports, and a connecting through hole is provided on the partition;

[0031] The connecting through hole is used to maintain the connectivity of the reflux channel;

[0032] The diameter of the connecting through hole is smaller than the cross-sectional size of the reflux channel.

[0033] According to one aspect of the present invention, the outer shell and the center body are spaced apart to form an isolation section, an annular detonation combustion chamber and an ejection section that are sequentially connected between the outer shell and the center body;

[0034] The injection port is communicated with the annular detonation combustion chamber, and the injection port is located at one end of the annular detonation combustion chamber connected to the isolation section.

[0035] According to one aspect of the present invention, the central body further comprises: a hollow cylinder;

[0036] Along the direction from the isolation section to the ejection section, the barrel and the conical tail nozzle are connected in sequence.

[0037] According to one aspect of the present invention, the center body is provided with a pre-detonation tube;

[0038] The pre-detonation tube is arranged adjacent to the gas injector;

[0039] Along the direction from the isolation section to the ejection section, the gas injector and the pre-detonation tube are arranged in sequence along the central body.

[0040] According to one aspect of the present invention, a gas flow regulating device is provided between the gas generator and the mixed cracker;

[0041] A fuel flow regulating device is provided at the connection position between the fuel tank and the reflux channel;

[0042] The thickness of the wall of the conical tail nozzle opposite to the converging part of the return channel is greater than or equal to 3 mm;

[0043] The outlet position of the pre-detonation tube is spaced 10 mm to 50 mm from the center of the injection port.

[0044] To achieve the above-mentioned purpose, the present invention provides an aircraft using the above-mentioned continuous rotating detonation ramjet engine, comprising: an aircraft body and a continuous rotating detonation ramjet engine installed in the aircraft body;

[0045] The continuous rotating detonation ramjet engine comprises: a hollow outer casing, a hollow center body, and a gas generating device at least partially installed in the center body;

[0046] The gas generating device comprises: a gas generator, a mixed cracker connected to the gas generator, a fuel storage tank and a gas injector connected to the mixed cracker;

[0047] A reflux channel for connecting the hybrid cracker and the fuel tank is provided on the side wall of the center body; wherein the reflux channels converge and communicate at the tip of the conical tail nozzle of the center body, and the convergence part of the reflux channels is communicated with the fuel tank;

[0048] The gas generator is filled with oxygen-depleted propellant solid;

[0049] The fuel tank is filled with liquid fuel and compressed gas, and the compressed gas drives the liquid fuel to flow along the reflux channel to cool the center body and inject it into the hybrid cracker after thermal cracking;

[0050] The hybrid cracker comprises: a mixing cavity, and a channel connector arranged outside the mixing cavity;

[0051] The channel connector has a transition channel,

[0052] The mixing chamber has a side wall connecting channel; wherein the side wall connecting channel, the transition channel and the reflux channel are connected;

[0053] The gas injector comprises: a connecting pipe, and an injection distributor connected to the connecting pipe;

[0054] A plurality of injection ports are arranged at equal intervals in the circumferential direction of the injection distributor;

[0055] The side wall of the central body is provided with a plurality of injection ports connected to the injection ports;

[0056] The injection port and the reflux channel are arranged in a staggered manner.

[0057] The present invention has the following beneficial effects:

[0058] According to one solution of the present invention, the present invention combines the advantages of the simple structure of the solid engine and the ability of liquid fuel to be used for regenerative cooling, thereby achieving the generation of low-temperature and high-activity secondary fuel-rich combustion gas.

[0059] According to one solution of the present invention, the fuel storage tank is provided with liquid hydrocarbon fuel, and the liquid hydrocarbon fuel firstly absorbs heat through the reflux channel on the wall of the center body and becomes gaseous fuel, and then further absorbs heat and cracks into low molecular hydrocarbons through premixing with the primary fuel-rich gas, thereby reducing the temperature of the primary fuel-rich gas. At the same time, the small molecular hydrocarbons generated after the liquid hydrocarbon fuel absorbs heat and cracks can enhance the explosiveness of the primary fuel-rich gas.

[0060] According to one solution of the present invention, since the introduced coolant is a liquid hydrocarbon fuel, it has a strong cracking heat absorption capacity, can effectively reduce the primary gas temperature and achieve wall cooling, which is beneficial to the long-term operation of the combustion chamber.

[0061] According to one scheme of the present invention, the present invention adopts a liquid hydrocarbon fuel regenerative cooling method to absorb heat through phase change in the reflux channel of the wall, thereby cooling the wall surface inside the engine, which is helpful for long-term operation of the engine; in addition, the gas generator has a simple structure and can be used as a duty flame to generate a high-temperature primary fuel-rich gas to mix and react with the gaseous hydrocarbon fuel after the phase change, thereby promoting the endothermic cracking of the low-temperature hydrocarbon fuel, which not only reduces the temperature of the primary fuel-rich gas, but also generates a large amount of small molecular hydrocarbon products, and further, based on the low molecular hydrocarbon compounds and the primary fuel-rich gas, a low-temperature and high-activity secondary fuel-rich gas is formed.

[0062] According to one solution of the present invention, a one-way valve is installed at the connection between the end of the reflux channel and the mixed cracker, so that only the gaseous hydrocarbon fuel in the reflux channel is allowed to spray outward into the mixed cracker, thereby preventing the high-temperature and high-pressure primary rich fuel gas in the cracking chamber at the initial stage of the engine from entering the reflux channel and causing blockage.

[0063] According to one solution of the present invention, the gas containing chamber is set as a funnel-shaped annular chamber, which can effectively avoid the disadvantage that the secondary rich fuel gas contains a large amount of condensed phase components and causes clogging of the gas injector, thereby achieving smooth diversion of the rich fuel gas.

[0064] According to one solution of the present invention, the present invention simultaneously adopts oxygen-deficient solid propellant and liquid hydrocarbon fuel which are respectively installed in the gas generator and the fuel tank, so that the two fuels complement each other, improve the engine specific impulse, and increase the aircraft's load capacity and range.

[0065] According to one scheme of the present invention, the present invention can flexibly arrange the positions of the gas generator and the fuel tank. For example, the gas generator and the fuel tank can be set inside the center body or outside the center body. The internal configuration of the present invention can be flexibly adjusted according to different integration requirements, so that the present invention has better flexibility of use.

[0066] According to one scheme of the present invention, when the flight conditions of the engine of the present invention change, the primary rich fuel gas flow and the liquid fuel flow can be adjusted by controlling the gas flow regulating device and the fuel flow regulating device respectively, thereby realizing the generation of secondary rich fuel gas with different parameters to achieve optimal combustion efficiency.

[0067] According to one solution of the present invention, the present invention has a simple structure and high reliability, and combines the advantages and disadvantages of solid fuel and liquid hydrocarbon fuel in the application of continuous rotating detonation ramjet engines to make it have higher performance and reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0068] Figure 1 is a structural diagram schematically showing a continuous rotating detonation ramjet engine according to an embodiment of the present invention;

[0069] Figure 2is a schematic diagram showing a connection structure of a hybrid cracker and a fuel gas injector according to an embodiment of the present invention;

[0070] Figure 3 is a schematic structural diagram of a hybrid cracker according to an embodiment of the present invention;

[0071] Figure 4 is a partial structural diagram schematically showing a hybrid cracker according to an embodiment of the present invention;

[0072] Figure 5 is a structural diagram schematically showing a gas injector according to an embodiment of the present invention;

[0073] Figure 6 FIG. 4 is a cross-sectional view schematically showing the position of a pre-detonation tube in a continuous rotating detonation ramjet engine according to an embodiment of the present invention.

[0074] Description of Reference Numerals

[0075] 1. Outer shell; 2. Center body; 3. Gas generating device; 31. Gas generator; 32. Mixed cracker; 33. Fuel storage tank; 34. Gas injector; 311. Oxygen-poor propellant solid; 331. Liquid fuel; 332. Compressed gas; 31a. Gas flow regulating device; 33a. Fuel flow regulating device; 321. Mixing cavity; 322. Channel connector; 322a. Transition channel; 321a. Side wall connecting channel; 341. Connecting pipe; 342. Injection distributor; 342a. Gas containing cavity; 342b. Injection port; 3421. Distributor upper wall; 3422. Distributor lower wall; 3423. Annular connecting wall; 211. Partition; 1a. Isolation section; 1b. Annular detonation combustion chamber; 1c. Ejection section; 2a. Cylinder; 2b. Conical tail nozzle; 2c. Pre-detonation tube. DETAILED DESCRIPTION

[0076] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0077] When describing the embodiments of the present invention, the orientation or positional relationship expressed by the terms "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" are based on the orientation or positional relationship shown in the relevant drawings and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, be constructed and operate in a specific orientation. Therefore, the above terms should not be understood as limiting the present invention.

[0078] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments. The embodiments cannot be described one by one here, but the embodiments of the present invention are not therefore limited to the following embodiments.

[0079] Combination Figure 1 and Figure 2 As shown, according to one embodiment of the present invention, a continuous rotating detonation ramjet engine based on solid-liquid mixed fuel provided by the present invention comprises: a hollow outer shell 1, a hollow center body 2 arranged in the outer shell 1, and a gas generator 3 installed in the center body 2; in this embodiment, the gas generator 3 comprises: a gas generator 31, a mixed cracker 32 connected to the gas generator 31, a fuel storage tank 33 connected to the mixed cracker 32, and a gas injector 34 connected to the mixed cracker 32; wherein, a reflux channel 21 is arranged on the side wall of the center body 2, and the reflux channel 21 is connected to the mixed cracker 32 and the fuel storage tank 33 respectively. In this embodiment, the gas generator 31 is filled with oxygen-poor propellant solid 311 to generate a primary fuel-rich gas; the fuel storage tank 33 is filled with liquid fuel 331 and compressed gas 332, so that the liquid fuel 331 is driven to be injected into the mixed cracker 32 along the reflux channel 21 based on the compressed gas 332. In this embodiment, the liquid fuel 331 may be liquid hydrocarbon fuel, such as kerosene, gasoline, etc.

[0080] In this embodiment, at least one of the central body 2, the gas generator 31, the hybrid cracker 32, the fuel tank 33 and the hybrid cracker 32 can be manufactured by 3D printing.

[0081] In this embodiment, the liquid fuel 331 can effectively reduce the temperature of the center body 2 through heat exchange in the reflux channel 21, so that the temperature of the liquid fuel 331 increases and the phase changes into fuel vapor. Further, when the fuel vapor is injected into the mixed cracker 32, low molecular hydrocarbon compounds are generated through endothermic cracking promoted by the primary rich fuel gas. At the same time, the temperature of the primary rich fuel gas is reduced, and the two are mixed to generate a secondary rich fuel gas with a lower temperature and higher activity. Furthermore, the generated secondary rich fuel gas can be transported to the gas injector 34.

[0082] like Figure 1 As shown, according to one embodiment of the present invention, a gas flow regulating device 31a is provided between the gas generator 31 and the mixed cracker 32; in this embodiment, the gas flow regulating device 31a can adopt a sliding disc valve structure driven by a motor to adjust the pressure in the gas generator 31 by controlling the cross-sectional area of ​​the throat connecting the gas generator 31 and the mixed cracker 32, thereby adjusting the flow of the primary fuel-rich gas.

[0083] like Figure 1 As shown, according to one embodiment of the present invention, a fuel flow regulating device 33a is provided at the connection position between the fuel tank 33 and the return channel 21. The speed of the liquid fuel 331 being sprayed out can be conveniently achieved by the provided fuel flow regulating device 33a.

[0084] Combination Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, according to an embodiment of the present invention, the hybrid cracker 32 includes: a mixing chamber 321, and a channel connector 322 arranged outside the mixing chamber 321; in this embodiment, the mixing chamber 321 is a hollow cylindrical structure as a whole; its opposite ends are arranged as flat plate structures, and connecting pipes are respectively arranged at the center positions of the flat plate structures at the opposite ends to facilitate the connection with the gas generator 31 and the gas injector 34. Further, along the axial direction of the mixing chamber 321, the channel connector 322 is arranged at the middle position of the mixing chamber 321, thereby, it can be realized that the position of the input fuel is distributed with a gap between the two axial ends, so as to conveniently utilize the space between the opposite ends of the mixing chamber 321 to form a large area of ​​reflux area, and promote the full mixing of the primary rich fuel gas and the liquid fuel.

[0085] In this embodiment, the channel connector 322 is provided with a transition channel 322a for connecting the return channel 21; wherein the channel connector 322 can be set as a tube body or an annular plate body. In this embodiment, if the channel connector 322 is set as a tube body, then in the circumferential direction of the mixing cavity 321, the channel connectors 322 are independent of each other, and the channel connectors 322 are set one by one with the return channel 21 on the central body 2; wherein, along the direction close to the mixing cavity 321, the cross-sectional size of the transition channel 322a is constant or gradually decreases; wherein, the cross-sectional size of the transition channel 322a can be set as a rectangle, a circle, etc. If the channel connector 322 is set as an annular plate body, the transition channels 322a are set at equal intervals along the axial direction of the channel connector 322, wherein, since the outer diameter of the annular plate body is greater than the inner diameter, the cross-sectional size of the transition channel 322a along the direction from the radial outer side to the radial inner side of the annular plate body is gradually reduced; wherein, the cross-sectional size of the transition channel 322a can be set as a rectangle, a circle, etc.

[0086] In the present embodiment, a side wall connecting channel 321a for connecting the transition channel 322a is provided on the side wall of the mixing cavity 321; wherein the cross-sectional dimension of the side wall connecting channel 321a is smaller than the cross-sectional dimension of the transition channel 322a. In the present embodiment, at least one side wall connecting channel 321a connected to each transition channel 322a is provided on the mixing cavity 321; wherein, if the number of side wall connecting channels 321a connected to each transition channel 322a is more than one, the opening spacing of adjacent side wall connecting channels 321a on the inner wall of the mixing cavity 321 is greater than the opening spacing on the outer wall of the mixing cavity 321; for example, if the number of side wall connecting channels 321a connected to each transition channel 322a is set to three, then the three side wall connecting channels 321a are connected along the mixing cavity. The side wall connecting channel 321a in the middle position can be arranged coaxially with the transition channel 322a, and the side wall connecting channels 321a arranged on both sides are arranged obliquely with the side wall connecting channel 321a in the middle position, so that on the inner wall of the mixing cavity 321, the opening spacing of adjacent side wall connecting channels 321a on the inner wall of the mixing cavity 321 is greater than the opening spacing on the outer wall of the mixing cavity 321, so that the fuel passing through the narrow transition channel 322a can be distributed in a wide range in the mixing cavity 321. Of course, the number of side wall connecting channels 321a connected to each transition channel 322a can also be set to two, four, five, etc., which can be arranged in the form of linear distribution, annular distribution, rectangular distribution, etc., wherein some side wall connecting channels 321a are arranged in an oblique manner to further distribute the fuel in a wider range.

[0087] Through the above arrangement, it is effectively ensured that the primary fuel-rich gas and the liquid fuel are fully mixed, the mixing efficiency is effectively ensured, and the working performance of the present invention is improved.

[0088] Combination Figure 1 , Figure 2 and Figure 5 As shown, according to one embodiment of the present invention, the gas injector 34 includes: a connecting pipe 341, and an injection distributor 342 connected to the connecting pipe 341; wherein the connecting pipe 341 and the injection distributor 342 are coaxially arranged. In this embodiment, the injection distributor 342 has a hollow gas containing chamber 342a, and a plurality of injection ports 342b are arranged at equal intervals in the circumferential direction of the injection distributor 342; wherein the injection ports 342b are connected to the gas containing chamber 342a. In this embodiment, the hollow portion of the connecting pipe 341 is connected to the gas containing chamber 342a; wherein the hollow portion of the connecting pipe 341 and the gas containing chamber 342a are also coaxially arranged.

[0089] Combination Figure 1 , Figure 2 and Figure 5 As shown, according to one embodiment of the present invention, the space of the gas accommodating chamber 342a is larger than the space of the hollow portion of the connecting pipe 341, and the ratio of the space of the gas accommodating chamber 342a to the space of the hollow portion of the connecting pipe 341 satisfies: greater than 1 and less than or equal to 2; through the above-mentioned arrangement, it is effectively ensured that the gas accommodating chamber 342a has sufficient space to fully accommodate the secondary fuel-rich gas formed after mixing, so as to ensure sufficient gas output and avoid the retention of the secondary fuel-rich gas in the mixed cracker 32.

[0090] Further, the gas containing chamber 342a is a funnel-shaped annular chamber; in this embodiment, the injection distributor 342 includes: a distributor upper wall 3421, a distributor lower wall 3422 and an annular connecting wall 3423; wherein the distributor upper wall 3421 and the distributor lower wall 3422 are coaxially arranged with a spacing from each other. In this embodiment, the distributor upper wall 3421 is a truncated cone structure as a whole, and the distributor lower wall 3422 is a conical structure as a whole; wherein the distributor upper wall 3421 and the distributor lower wall 3422 are respectively arranged at two ends of the annular connecting wall 3423 in the axial direction, wherein the small diameter end of the distributor upper wall 3421 is coaxially connected to the connecting pipe 341, and its large diameter end is connected to one end of the annular connecting wall 3423 in the axial direction; the large diameter end of the distributor lower wall 3422 is connected to the other end of the annular connecting wall 3423 in the axial direction, and the tip of the distributor lower wall 3422 is opposite to the small diameter end of the distributor upper wall 3421. In this embodiment, the injection port 342b is on the annular connecting wall 3423 and is arranged at equal intervals along the circumference of the annular connecting wall 3423; wherein the axial direction of the injection port 342b is consistent with the extension direction of the gas containing cavity 342a, so that the entire injection port 342b can better discharge the internal high-temperature gas.

[0091] Through the above arrangement, the injection distributor 342 of the present invention has a simple structure and light weight, which is beneficial to improving the propulsion efficiency of the present invention.

[0092] In this embodiment, the cross-sectional area of ​​the gas accommodating cavity 342a is gradually reduced along the axial direction along the direction from the connecting pipe 341 to the injection distributor 342. Through the above arrangement, based on the cavity with a gradually reduced cross-sectional area, it is easier to guide the secondary fuel-rich gas to the injection port 342b, and it is easier for the secondary fuel-rich gas to pass through the injection port 342b with a smaller size, so as to facilitate output.

[0093] Combination Figure 1 , Figure 2 and Figure 5As shown, according to one embodiment of the present invention, a plurality of injection ports 22 are arranged on the side wall of the central body 2; in this embodiment, the plurality of injection ports 22 are arranged at equal intervals along the circumference of the central body 2; wherein the injection ports 22 penetrate the side wall of the central body 2 and are connected, so that the injection ports 22 and the injection ports 342b can be connected in a one-to-one corresponding manner; in this embodiment, the injection ports 22 and the reflow channel 21 are staggered, so that the injection ports 22 and the reflow channel 21 are isolated from each other to ensure the independence of the reflow channel 21 and the gas injection.

[0094] In this embodiment, a partition 211 is provided in the reflux channel 21, and the partition 211 is located between adjacent injection ports 22, and a connecting through hole 211a is provided on the partition 211, and the connection of the reflux channel 21 is conveniently realized through the provided connecting through hole 211a, so that the reflux channel 21 is divided into two parts before and after the partition 211. Further, the diameter of the connecting through hole 211a is smaller than the cross-sectional size of the reflux channel 21, thereby, the flow of liquid fuel can be controlled by the provided partition 211, for example, the channel portion of the reflux channel 21 from the partition 211 to the conical tail nozzle 2b can more easily restrict the flow of liquid fuel, so as to facilitate the heat exchange cooling of the center body 2, and the channel portion of the reflux channel 21 between the mixed cracker 32 and the partition 211 can make the liquid fuel passing through the connecting through hole 211a flow more quickly, so as to facilitate the input to the mixed cracker 32.

[0095] In this embodiment, the injection port 22 and the injection port 342b are coaxially arranged, wherein the axial inclination angle of the injection port 22 and the injection port 342b can be set to 60°, thereby achieving the injection of secondary rich fuel gas into the rear structure (such as the annular detonation combustion chamber 1b), effectively ensuring the balance between the penetration depth of the secondary rich fuel gas jet and the internal flow resistance generated by the secondary rich fuel gas jet.

[0096] like Figure 1 As shown, according to one embodiment of the present invention, the outer shell 1 and the center body 2 are spaced apart to form an isolation section 1a, an annular detonation combustion chamber 1b and an ejection section 1c that are connected in sequence between the outer shell 1 and the center body 2; in this embodiment, the injection port 22 is connected to the annular detonation combustion chamber 1b, and the injection port 22 is located at one end where the annular detonation combustion chamber 1b is connected to the isolation section 1a.

[0097] In the present embodiment, the injection port 22 provided on the side wall of the center body 2 is positioned at the entrance of the expansion portion of the annular detonation combustion chamber 1b, so as to effectively utilize the high pressure generated inside the gas generator 31 when it is working, which is generally above 1 MPa. This pressure effectively provides a reliable driving force for the output jet of the secondary fuel-rich gas, thereby promoting the stable output of the secondary fuel-rich gas and its full mixing with the incoming air, which is further beneficial to improving the working performance of the present invention.

[0098] like Figure 1 As shown, according to an embodiment of the present invention, the central body 2 includes: a hollow cylinder 2a and a hollow conical tail nozzle 2b; in this embodiment, along the direction from the isolation section 1a to the ejection section 1c, the cylinder 2a and the conical tail nozzle 2b are sequentially connected, specifically, the hollow part of the cylinder 2a and the hollow part of the conical tail nozzle 2b are connected to each other, so as to realize the installation of at least part of the structure in the gas generator 3, so as to facilitate the integration of the central body 2 and the structure in the gas generator 3, and effectively improve the structural integration of the present invention. In this embodiment, the return channel 21 is connected at the tip of the conical tail nozzle 2b, and the return channel 21 is connected to the fuel tank 33 at the converging part of the tip of the conical tail nozzle 2b; wherein, the fuel tank 33 is connected to the converging part of the return channel 21 by a connecting pipe, and the connecting pipe can be coaxially arranged with the conical tail nozzle 2b to achieve structural symmetry and ensure uniform mass distribution of the entire structure.

[0099] Through the above arrangement, the return channel 21 can be evenly distributed around the central body 2 by converging the return channel 21 at the tip of the conical tail nozzle 2b, which can effectively reduce the complexity of the arrangement of the return channel 21 on the one hand, and can more advantageously achieve a unified connection with the fuel storage tank 33 and help ensure the uniform distribution of liquid fuel, improve the uniformity of heat exchange for liquid fuel, and then achieve uniform distribution of fuel in all directions of the mixed cracker 32, effectively ensuring full mixing with the primary high-energy fuel gas. In addition, the number of fuel flow regulating devices 33a can be effectively reduced to achieve reliable and stable system operation.

[0100] In this embodiment, the thickness of the wall surface of the tapered tail nozzle 2b opposite to the converging portion of the reflow channel 21 is greater than or equal to 3 mm.

[0101] Through the above arrangement, the wall strength of the conical tail nozzle 2b is effectively guaranteed, so that the liquid fuel in the fuel storage tank 33 forms a strong stagnation pressure at the injection position, effectively ensuring the uniformity and reliability of the reverse distribution.

[0102] Combination Figure 1 and Figure 6As shown, according to an embodiment of the present invention, the central body 2 is provided with a pre-detonation tube 2c; wherein the pre-detonation tube 2c is arranged adjacent to the gas injector 34. In this embodiment, along the direction from the isolation section 1a to the ejection section 1c, the gas injector 34 and the pre-detonation tube 2c are arranged in sequence along the central body 2. In this embodiment, the pre-detonation tube 2c is used to output a hot jet, wherein the hot jet is a strong detonation jet formed by the deflagration-to-detonation (DDT) process after the hydrogen and oxygen mixture is ignited, and acts as the secondary rich fuel gas output by the initiation gas generating device 3.

[0103] In the present embodiment, the outlet position of the pre-detonation tube 2 c is spaced 10 mm to 50 mm from the center of the injection port 22 .

[0104] In this embodiment, along the circumferential direction of the center body 2, the outlet of the pre-detonation tube 2c should be tangent to the inner cylindrical surface of the annular detonation combustion chamber 1b.

[0105] Through the above arrangement, the stability and reliability of its detonation are effectively guaranteed.

[0106] Combination Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 5 As shown, according to one embodiment of the present invention, a one-way valve is provided at one end of the reflux channel 21 connected to the transition channel 322a of the mixed cracker 32; wherein, the one-way valve is provided so that the fuel vapor in the reflux channel 21 can only be sprayed into the mixed cracker 32, so as to avoid the high-temperature and high-pressure primary rich fuel gas in the mixed cracker 32 at the initial stage of the engine operation from entering the reflux channel 21 and causing blockage, thereby making the operation of the present invention more stable and reliable.

[0107] According to one embodiment of the present invention, the present invention provides an aircraft using the aforementioned continuous rotating detonation ramjet engine, comprising: an aircraft body and a continuous rotating detonation ramjet engine installed in the aircraft body; in this embodiment, the continuous rotating detonation ramjet engine comprises: a hollow outer shell 1, a hollow center body 2 arranged in the outer shell 1, and a gas generating device 3 installed in the center body 2; in this embodiment, the gas generating device 3 comprises: a gas generator 31, a mixed cracker 32 connected to the gas generator 31, a fuel storage tank 33 connected to the mixed cracker 32, and a gas injector 34 connected to the mixed cracker 32; wherein a reflux channel 21 is provided on the side wall of the center body 2, and the reflux channel 21 is respectively connected to the mixed cracker 32 and the fuel storage tank 33. In this embodiment, the gas generator 31 is filled with oxygen-depleted propellant solid 311 to generate primary fuel-rich gas; the fuel storage tank 33 is filled with liquid fuel 331 and compressed gas 332 to drive the liquid fuel 331 to be injected into the mixed cracker 32 along the reflux channel 21 based on the compressed gas 332.

[0108] In order to further illustrate the present solution, the working principle of the series variable parameter rich fuel gas generating device of the present invention is further described.

[0109] Ignite the oxygen-poor propellant solid 311 in the gas generator 31 to generate a primary fuel-rich gas in the gas generator 31;

[0110] Controlling the opening of the gas flow regulating device 31a to achieve the injection of the primary fuel-rich gas into the mixing chamber 321 of the hybrid cracker 32;

[0111] Control the opening of the fuel flow regulating device 33a, so as to allow the liquid fuel 331 to enter the transition channel 322a of the channel connector 322 of the hybrid cracker 32 along each reflux channel 21 based on the compressed gas 332 in the fuel storage tank 33; wherein, since a partition 211 is provided in the reflux channel 21, and the aperture of the connecting through hole 211a on the partition 211 is smaller than the cross-sectional size of the reflux channel 21, the liquid fuel 331 can stay in the reflux channel 21 between the partition 211 and the fuel storage tank 33 for a certain period of time to achieve a longer heat exchange time with the central body 2, and the liquid fuel 331 passing through the connecting through hole 211a is further transported to the transition channel 322a based on the reflux channel 21;

[0112] The liquid fuel 331 passing through the reflux channel 21 is injected into the mixing chamber 321 through the side wall connecting channel 321a to achieve mixed combustion with the primary fuel-rich gas to generate secondary fuel-rich gas;

[0113] The secondary rich fuel gas is ejected into the combustion chamber through the injection port 342b on the fuel gas injector 34 and the injection port 22 on the center body 2 to continue to be mixed with the incoming air for combustion.

[0114] The above contents are merely examples of specific solutions of the present invention. For devices and structures not described in detail therein, it should be understood that they can be implemented by adopting general devices and general methods available in the art.

[0115] The above is only one solution of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A continuous rotating detonation ramjet engine based on solid-liquid mixed fuel, characterized in that: include: A hollow outer shell (1), a hollow central body (2), and a gas generating device (3) at least partially mounted in the central body (2); The gas generating device (3) comprises: a gas generator (31), a mixed cracker (32) connected to the gas generator (31), a fuel storage tank (33) and a gas injector (34) connected to the mixed cracker (32); A reflux channel (21) for connecting the mixed cracker (32) and the fuel tank (33) is provided on the side wall of the center body (2); wherein the reflux channels (21) converge and communicate at the tip of the conical tail nozzle (2b) of the center body (2), and the convergent portion of the reflux channels (21) is in communication with the fuel tank (33); The gas generator (31) is filled with oxygen-deficient propellant solid (311); The fuel storage tank (33) is filled with liquid fuel (331) and compressed gas (332), and the compressed gas (332) drives the liquid fuel (331) to flow along the reflux channel (21) to cool the center body (2) and heat it to become fuel vapor before being injected into the hybrid cracker (32); The mixed cracker (32) comprises: a mixing chamber (321), and a channel connector (322) arranged outside the mixing chamber (321); The channel connector (322) has a transition channel (322a), The mixing chamber (321) has a side wall connecting channel (321a); ​​wherein the side wall connecting channel (321a), the transition channel (322a) and the reflux channel (21) are connected; The fuel gas injector (34) comprises: a connecting pipe (341), and an injection distributor (342) connected to the connecting pipe (341); A plurality of injection ports (342b) are arranged at equal intervals in the circumferential direction of the injection distributor (342); A plurality of injection ports (22) connected to the injection ports (342b) are provided on the side wall of the central body (2); The injection port (22) and the reflux channel (21) are arranged in a staggered manner.

2. The continuous rotating detonation ramjet engine based on solid-liquid mixed fuel according to claim 1, characterized in that: The mixing cavity (321) is in the shape of a hollow column as a whole; Along the axial direction of the mixing cavity (321), the channel connecting piece (322) is arranged at a middle position of the mixing cavity (321); The cross-sectional dimension of the side wall connecting channel (321a) is smaller than the cross-sectional dimension of the transition channel (322a).

3. The continuous rotating detonation ramjet engine based on solid-liquid mixed fuel according to claim 2, characterized in that: At least one side wall connecting channel (321a) is provided on the mixing cavity (321) and is connected to each of the transition channels (322a); wherein, if the number of the side wall connecting channels (321a) connected to each of the transition channels (322a) is more than one, the opening spacing between adjacent side wall connecting channels (321a) on the inner wall of the mixing cavity (321) is greater than the opening spacing on the outer wall of the mixing cavity (321).

4. The continuous rotating detonation ramjet engine based on solid-liquid mixed fuel according to claim 3, characterized in that: The connecting pipe (341) and the injection distributor (342) are coaxially arranged; The injection distributor (342) has a hollow fuel gas containing chamber (342a); The injection port (342b) is arranged to communicate with the gas containing chamber (342a); The hollow portion of the connecting pipe (341) is connected to the gas containing chamber (342a); The space of the gas containing cavity (342a) is larger than the space of the hollow portion of the connecting pipe (341), and the ratio of the space of the gas containing cavity (342a) to the space of the hollow portion of the connecting pipe (341) satisfies: greater than 1 and less than or equal to 2; The gas containing cavity (342a) is a funnel-shaped annular cavity; Along the direction from the connecting pipe (341) to the injection distributor (342), the cross-sectional area of ​​the gas containing chamber (342a) is gradually reduced along the axial direction.

5. The continuous rotating detonation ramjet engine based on solid-liquid mixed fuel according to claim 4, characterized in that: A partition (211) is provided in the reflux channel (21), the partition (211) is located between adjacent injection ports (22), and a connecting through hole (211a) is provided on the partition (211); The connecting through hole (211a) is used to maintain the connectivity of the reflux channel (21); The caliber of the connecting through hole (211a) is smaller than the cross-sectional size of the reflux channel (21).

6. The continuous rotating detonation ramjet engine based on solid-liquid mixed fuel according to claim 5, characterized in that: The outer shell (1) and the center body (2) are arranged at a distance so as to form an isolation section (1a), an annular detonation combustion chamber (1b) and an ejection section (1c) which are connected in sequence between the outer shell (1) and the center body (2); The injection port (22) is arranged to communicate with the annular detonation combustion chamber (1b), and the injection port (22) is located at one end of the annular detonation combustion chamber (1b) connected to the isolation section (1a).

7. The continuous rotating detonation ramjet engine based on solid-liquid mixed fuel according to claim 6, characterized in that: The central body (2) further comprises: a hollow cylinder (2a); Along the direction from the isolation section (1a) to the ejection section (1c), the barrel (2a) and the conical tail nozzle (2b) are arranged to be connected in sequence.

8. The continuous rotating detonation ramjet engine based on solid-liquid mixed fuel according to claim 7, characterized in that: The central body (2) is provided with a pre-detonation tube (2c); The pre-detonation tube (2c) is arranged adjacent to the fuel gas injector (34); Along the direction from the isolation section (1a) to the ejection section (1c), the gas injector (34) and the pre-detonation tube (2c) are arranged in sequence along the center body (2).

9. The continuous rotating detonation ramjet engine based on solid-liquid mixed fuel according to claim 8, characterized in that: A gas flow regulating device (31a) is provided between the gas generator (31) and the mixed cracker (32); A fuel flow regulating device (33a) is provided at the connection position between the fuel storage tank (33) and the return channel (21); The thickness of the wall surface of the conical tail nozzle (2b) opposite to the converging portion of the reflow channel (21) is greater than or equal to 3 mm; The outlet position of the pre-detonation tube (2c) is spaced 10 mm to 50 mm from the center of the injection port (22).

10. An aircraft using a continuous rotating detonation ramjet engine based on a solid-liquid mixed fuel as claimed in any one of claims 1 to 9, characterized in that: include: An aircraft body and a continuously rotating detonation ramjet engine installed in the aircraft body; The continuous rotating detonation ramjet engine comprises: a hollow outer casing (1), a hollow center body (2), and a gas generating device (3) at least partially installed in the center body (2); The gas generating device (3) comprises: a gas generator (31), a mixed cracker (32) connected to the gas generator (31), a fuel storage tank (33) and a gas injector (34) connected to the mixed cracker (32); A reflux channel (21) for connecting the mixed cracker (32) and the fuel tank (33) is provided on the side wall of the center body (2); wherein the reflux channels (21) converge and communicate at the tip of the conical tail nozzle (2b) of the center body (2), and the convergent portion of the reflux channels (21) is in communication with the fuel tank (33); The gas generator (31) is filled with oxygen-deficient propellant solid (311); The fuel storage tank (33) is filled with liquid fuel (331) and compressed gas (332), and the compressed gas (332) drives the liquid fuel (331) to flow along the reflux channel (21) to cool the center body (2) and to inject the liquid fuel (331) into the hybrid cracker (32) after thermal cracking. The mixed cracker (32) comprises: a mixing chamber (321), and a channel connector (322) arranged outside the mixing chamber (321); The channel connector (322) has a transition channel (322a), The mixing chamber (321) has a side wall connecting channel (321a); ​​wherein the side wall connecting channel (321a), the transition channel (322a) and the reflux channel (21) are connected; The fuel gas injector (34) comprises: a connecting pipe (341), and an injection distributor (342) connected to the connecting pipe (341); A plurality of injection ports (342b) are arranged at equal intervals in the circumferential direction of the injection distributor (342); A plurality of injection ports (22) connected to the injection ports (342b) are provided on the side wall of the central body (2); The injection port (22) and the reflux channel (21) are arranged in a staggered manner.

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