Cross-medium scramjet engine

Abstract

The cross-medium scramjet engine comprises an engine body, flow deflectors are fixedly installed on the outer side of the circumference of an injection opening in the tail end of the engine body, an air inlet channel is formed in the end, away from the flow deflectors, of the engine body, and a butt joint base is fixedly arranged on the outer side of the air inlet channel at the end of the engine body; an air inlet cylinder is fixedly arranged at the end of the butt joint seat, air inlet holes are formed in the circumferential outer wall of the air inlet cylinder, and flow penetrating pieces are fixedly arranged on the circumferential outer side of the air inlet cylinder. A turbine is arranged at the position, close to the injection opening, in the engine body, and a gas compressor is arranged at the position, close to the gas channel, in the engine body. A combustion assembly is installed between the gas compressor and the turbine. According to the cross-medium scramjet engine, the mixing uniformity of fuel and air in the combustion chamber is improved, more stable and efficient combustion is achieved, the problems of local overheating or insufficient combustion and the like are reduced, and the reliability and thrust output stability of the engine are improved.

Description

Technical Field

[0001] The present invention relates to the field of engines, and in particular to a cross-medium scramjet engine. Background Art

[0002] The cross-medium aircraft is a new concept aircraft that can fly in the air and dive underwater. It has both the speed of an aircraft and the stealth of a submarine. It can maneuver underwater and launch attacks from underwater or above the water. It can also fly close to the sea and carry out covert precision strikes. It can effectively use the blind spots of radar and various detection equipment to launch surprise attacks on enemy aircraft carriers, warships and submarines. It has efficient penetration strike and multi-task capabilities. As early as the 1920s and 1930s, some people proposed the idea of ​​a diving aircraft or a flying submarine, but due to the limited technical level, it has not been successfully transformed into an engineering model.

[0003] Regarding the patent of cross-medium scramjet engine, after searching, the publication number is CN109098891A, which discloses a cross-medium ramjet engine based on solid propulsion. The article includes that the flow channel is evenly arranged on the outer circumference of the gas generator, and the flow channel and the gas generator are integrated into a design, which not only ensures the normal operation of the engine, but also ensures the streamlined shape of the gas generator;

[0004] Although the above-mentioned device realizes dual-mode conversion of the propulsion system and works across media, fully combining the advantages of aerial flight and underwater diving, when the ramjet engine is used as a propeller in the air, when the ramjet engine is taking in air, the airflow entering the inlet duct has uneven distribution of parameters such as velocity and pressure on the cross section, which will make the combustion process in the combustion chamber unstable, reduce combustion efficiency, and affect the engine performance and thrust output. Summary of the invention

[0005] The object of the present invention is to provide a cross-medium scramjet engine to solve the defects mentioned in the above background technology.

[0006] To achieve the above-mentioned purpose, a cross-medium scramjet engine is provided, comprising an engine body, a guide vane is fixedly installed on the circumferential outer side of the jet port at the tail end of the engine body, an air inlet duct is provided inside the end of the engine body away from the guide vane, a docking seat is fixedly provided on the outer side of the air inlet duct at the end of the engine body, an air inlet cylinder is fixedly provided at the end of the docking seat, an air inlet hole is provided on the circumferential outer wall of the air inlet cylinder, and a flow-through vane is fixedly provided on the circumferential outer side of the air inlet cylinder; a turbine is provided at a place inside the engine body close to the jet port, a compressor is provided at a place inside the engine body close to the air duct; a combustion assembly is installed between the compressor and the turbine.

[0007] As a preferred embodiment, the guide vanes are evenly arranged in four groups along the outer side of the circumference of the tail end injection port of the engine body, the cross-section of the guide vanes is trapezoidal, the outer surface of the engine body is streamlined, and the engine body as a whole is spherical.

[0008] As a preferred embodiment, the engine body includes a docking seat, a turbine, a worm wheel blade, a combustion assembly and a compressor. A combustion chamber is arranged inside the combustion assembly. The combustion assembly is evenly arranged in six groups between the turbine and the compressor. Cooling jackets are provided on both sides of the inner wall of the engine body; multiple groups of worm wheel blades are evenly arranged on the circumferential outer side of the turbine.

[0009] As a preferred embodiment, the air intake cylinder includes an air intake hole, a flow-through piece, a flow-piercing portion, a connecting piece, a retarder and a guide cover. The air intake cylinder is bullet-shaped, and a flow-piercing portion is provided at one end of the air intake cylinder away from the engine body. The external airflow passes through the air intake hole, impacts the retarder and decelerates, and then enters the engine air duct after being filtered through the guide cover.

[0010] As a preferred embodiment, four groups of flow-through plates are evenly arranged on the outer side of the circumference of the air inlet cylinder. The flow-through plates are arranged in a fan shape, and the outer surface of the flow-through plates is arranged in a streamlined shape; one end of the air inlet cylinder away from the piercing part is screwed and fixed to the docking seat.

[0011] As a preferred embodiment, a retarder cylinder is arranged inside the air intake cylinder, and the retarder cylinder is bullet-shaped. A plurality of connecting plates are evenly arranged on the outside of the retarder cylinder, and one end of the connecting plate away from the retarder cylinder is fixed on the inner wall of the air intake cylinder; a plurality of air intake holes are evenly arranged on the circumferential outer wall of the air intake cylinder, and the air intake holes are strip-shaped; the axial section of the air intake cylinder and the retarder cylinder inside it is a concentric circle structure.

[0012] As a preferred embodiment, a deflector is threadedly installed on the lower side of the inner part of the air intake cylinder, and the deflector covers the air passage of the engine body. The deflector includes a fixing seat, an air intake outer cover and an air intake inner cover.

[0013] As a preferred embodiment, a fixing seat is fixedly installed on the top of the air deflector, an air intake outer cover is fixedly connected to the bottom of the fixing seat, and an air intake inner cover is fixedly installed on the bottom of the air intake outer cover; the axial section of the fixing seat, the air intake outer cover and the air intake inner cover is a concentric circle structure.

[0014] As a preferred implementation, the cross-sections of the air intake outer cover and the air intake inner cover are both isosceles trapezoidal, the air intake inner cover covers the outside of the compressor, and a plurality of groups of guide holes are evenly arranged on the guide cover.

[0015] As a preferred embodiment, the bottom of the air intake cylinder is evenly provided with multiple groups of oblique through holes and screw holes, the circumferential inner wall of the fixing seat is evenly provided with multiple groups of connecting holes, the surface of the docking seat is evenly provided with multiple groups of oblique screw holes, the oblique screw holes and the oblique through holes are arranged opposite to each other, the first fixing bolt passes through the oblique through hole and is screwed into the inside of the oblique screw hole, and the second fixing bolt passes through the connecting hole and is screwed into the inside of the screw hole.

[0016] Compared with the prior art, the present invention has the following beneficial effects:

[0017] 1. The present invention can evenly distribute the airflow entering the air inlet through the arrangement of the deflector; it can split and rectify the airflow about to enter the air inlet, reduce the degree of turbulence of the airflow, and make the velocity and pressure distribution of the airflow entering the engine on the cross section more uniform; it helps to improve the mixing uniformity of fuel and air in the combustion chamber, achieve more stable and efficient combustion, reduce problems such as local overheating or incomplete combustion, and improve the reliability and thrust output stability of the engine;

[0018] 2. The present invention can decelerate the gas that is about to enter the intake duct when the airflow passes through the intake hole and impacts the outer side of the circumference of the retarder. According to the principle of ramjet engines, during the gas deceleration process, kinetic energy is converted into pressure energy, which increases the static pressure of the gas. This provides a suitable pressure environment for subsequent combustion, allowing the fuel and air to be mixed and burned more fully and efficiently, thereby improving the thermal efficiency and thrust output of the engine. The combustion chamber of the scramjet engine requires air at a specific pressure to ensure stable and efficient combustion of the fuel. The gas deceleration and pressurization before intake can ensure that the air pressure entering the combustion chamber meets the combustion requirements and maintain a stable combustion process. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The accompanying drawings, which are incorporated herein and constitute a part of the specification, illustrate embodiments of the invention and, together with the description, further serve to explain the principles of the invention and to enable those skilled in the relevant art to make and use the invention.

[0020] Figure 1 It is a front view schematic diagram of the structure of the present invention;

[0021] Figure 2 It is a rear view of the structure of the present invention;

[0022] Figure 3 It is a front view of the structure of the present invention;

[0023] Figure 4 for Figure 1 A cross-sectional view of

[0024] Figure 5 for Figure 4 Front view of

[0025] Figure 6 for Figure 4 Rear view of

[0026] Figure 7 for Figure 4 A top view of

[0027] Figure 8 for Figure 7 A is an enlarged structural diagram;

[0028] Fig. 9 It is a schematic diagram of the air intake cylinder;

[0029] Fig.10 for Fig. 9 Rear view of

[0030] Fig.11 for Fig. 9 Top view of the .

[0031] [reference numerals]

[0032] 1. Engine body; 10. Docking seat; 11. Turbine; 12. Turbine blades; 13. Combustion assembly; 14. Compressor; 2. Guide vane; 3. Intake cylinder; 31. Intake hole; 32. Flow-through vane; 33. Flow-piercing part; 34. Connecting piece; 35. Retarder; 36. Guide cover; 361. Fixing seat; 362. Intake outer cover; 363. Intake inner cover; 100. Oblique screw hole; 200. Oblique through hole; 300. Screw hole; 400. Connecting hole. DETAILED DESCRIPTION

[0033] The present invention is described in detail below in conjunction with the accompanying drawings and specific embodiments. At the same time, it is explained here that in order to make the embodiments more detailed, the following embodiments are the best and preferred embodiments, and those skilled in the art may also adopt other alternatives to implement some known technologies; and the accompanying drawings are only for more specific description of the embodiments, and are not intended to specifically limit the present invention.

[0034] It should be noted that the references to "one embodiment", "an embodiment", "an exemplary embodiment", "some embodiments" and the like in the specification indicate that the embodiments described may include specific features, structures or characteristics, but not every embodiment may include the specific features, structures or characteristics. In addition, when a specific feature, structure or characteristic is described in conjunction with an embodiment, it should be within the knowledge of a person skilled in the art to implement such feature, structure or characteristic in conjunction with other embodiments (whether or not explicitly described).

[0035] In general, a term can be understood, at least in part, from its use in context. For example, depending, at least in part, on the context, the term "one or more" as used herein can be used to describe any feature, structure, or characteristic in the singular sense, or can be used to describe a combination of features, structures, or characteristics in the plural sense. Additionally, the term "based on" can be understood as not necessarily intended to convey an exclusive set of factors, but can instead, depending, at least in part, on the context, allow for the presence of other factors that are not necessarily explicitly described.

[0036] It will be understood that the meanings of “on,” “over,” and “above” in the present invention should be interpreted in the broadest manner, so that “on” not only means “directly on” something, but also includes the meaning of being “on” something with intervening features or layers therebetween, and “on” or “over” not only means “on” or “above” something, but also includes the meaning of being “on” or “above” something with no intervening features or layers therebetween.

[0037] Additionally, spatially relative terms such as "under," "beneath," "lower," "above," "upper," and the like may be used herein for descriptive convenience to describe the relationship of one element or feature to another element or features, as shown in the accompanying drawings. Spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the accompanying drawings. The device may be oriented in other ways, and the spatially relative descriptors used herein may be similarly interpreted accordingly.

[0038] Specific implementation method 1: Please refer to Figure 1-4 The present invention provides a technical solution: a cross-medium scramjet engine, comprising an engine body 1, a guide vane 2 is fixedly installed on the circumferential outer side of the jet port at the tail end of the engine body 1, an air inlet duct is provided inside the end of the engine body 1 away from the guide vane 2, a docking seat 10 is fixedly provided on the outer side of the air inlet duct at the end of the engine body 1, an air inlet cylinder 3 is fixedly provided at the end of the docking seat 10, an air inlet hole 31 is provided on the circumferential outer wall of the air inlet cylinder 3, and a flow-through vane 32 is fixedly provided on the circumferential outer side of the air inlet cylinder 3; a turbine 11 is provided at a place near the jet port inside the engine body 1, a compressor 14 is provided at a place near the air duct inside the engine body 1; a combustion assembly 13 is installed between the compressor 14 and the turbine 11.

[0039] like Figure 1 , Figure 2 and Figure 3As shown, specific embodiment 2: This embodiment is a further limitation of specific embodiment 1, and four groups of guide vanes 2 are evenly arranged along the outer side of the circumference of the tail end injection port of the engine body 1, the cross-section of the guide vanes 2 is trapezoidal, the outer surface of the engine body 1 is streamlined, and the engine body 1 as a whole is spherical.

[0040] like Figure 1 , Figure 3 and Figure 4 As shown, specific embodiment three: This embodiment is a further limitation of specific embodiment one, the engine body 1 includes a docking seat 10, a turbine 11, worm blades 12, a combustion assembly 13 and a compressor 14, a combustion chamber is arranged inside the combustion assembly 13, the combustion assembly 13 is evenly arranged into six groups between the turbine 11 and the compressor 14, and cooling jackets are provided on both sides of the inner wall of the engine body 1; a plurality of groups of worm blades 12 are evenly arranged on the circumferential outer side of the turbine 11.

[0041] like Figure 1 , Figure 4 and Figure 5 As shown, specific implementation mode four: This implementation mode is a further limitation of specific implementation mode one, the air intake cylinder 3 includes an air intake hole 31, a flow-through piece 32, a flow-piercing portion 33, a connecting piece 34, a retarder 35 and a guide cover 36, the air intake cylinder 3 is bullet-shaped, and a retarder 33 is provided at one end of the air intake cylinder 3 away from the engine body 1; the external airflow passes through the air intake hole 31, impacts the retarder 35 and is decelerated, and then is filtered through the guide cover 36 and enters the engine airway.

[0042] like Figure 1 , Figure 2 , Figure 5 , Figure 6 and Figure 7 As shown, specific implementation mode five: This implementation mode is a further limitation of specific implementation mode four, and four groups of flow-through plates 32 are evenly arranged on the circumferential outer side of the air inlet cylinder 3, the flow-through plates 32 are arranged in a fan shape, and the outer surface of the flow-through plates 32 is arranged in a streamlined shape; one end of the air inlet cylinder 3 away from the piercing portion 33 is screwed and fixed to the docking seat 10.

[0043] like Figure 5 , Figure 6 and Figure 7 As shown, specific implementation method six: this implementation method is a further limitation of specific implementation method four, a retarder cylinder 35 is arranged inside the air intake cylinder 3, the retarder cylinder 35 is arranged in a bullet shape, a plurality of groups of connecting plates 34 are evenly arranged on the outside of the retarder cylinder 35, and one end of the connecting plate 34 away from the retarder cylinder 35 is fixed on the inner wall of the air intake cylinder 3; a plurality of groups of air intake holes 31 are evenly arranged on the circumferential outer wall of the air intake cylinder 3, and the air intake holes 31 are arranged in a strip shape; the axial section of the air intake cylinder 3 and the retarder cylinder 35 inside it is a concentric circle structure.

[0044] like Fig. 9 , Fig.10 and Fig.11 As shown, specific embodiment seven: This embodiment is a further limitation of specific embodiment one, a guide cover 36 is screwedly installed on the lower side of the inner part of the intake cylinder 3, and the guide cover 36 covers the air passage of the engine body 1. The guide cover 36 includes a fixing seat 361, an intake outer cover 362 and an intake inner cover 363.

[0045] like Fig. 9 , Fig.10 and Fig.11 As shown, specific embodiment eight: This embodiment is a further limitation of specific embodiment seven, the top of the air deflector 36 is fixedly installed with a fixing seat 361, the bottom of the fixing seat 361 is fixedly connected with an air intake outer cover 362, and the bottom of the air intake outer cover 362 is fixedly installed with an air intake inner cover 363; the axial section of the fixing seat 361, the air intake outer cover 362 and the air intake inner cover 363 is a concentric circle structure.

[0046] Working principle: When the aircraft flies at hypersonic speed, the outside air enters the air inlet at the end of the engine body 1 at an extremely high speed; the air inlet adopts shock wave compression to make the high-speed airflow produce a series of shock waves. When the airflow passes through the shock wave, the speed decreases, the pressure and temperature increase, and the initial compression of the air is achieved; the combustion component 13 includes a combustion chamber, which is the place where the fuel and air are mixed and burned; after the compressed and stabilized subsonic air enters the combustion chamber, the fuel is sprayed into the combustion chamber in a suitable manner through a special nozzle; the fuel is quickly mixed with the air in the subsonic airflow and is ignited under the action of the ignition source. Due to the compression effect of the shock wave on the incoming gas, the combustion process is carried out in a low-speed and high-pressure airflow. This combustion The method can increase the static pressure of the gas, improve the combustion efficiency, and produce high-temperature and high-pressure combustion gas; the high-temperature and high-pressure combustion gas produced by the combustion enters the tail nozzle; the shape and structural design of the tail nozzle allow the combustion gas to expand and accelerate therein, and according to the law of conservation of momentum, the combustion gas is ejected backward at high speed, generating a forward reaction force, i.e. thrust, to push the aircraft forward; when the air intake duct at the engine body 1 is intake, since an air intake cylinder 3 is arranged in front of the air intake duct, the air intake cylinder 3 is bullet-shaped, and a plurality of groups of air intake holes 31 are evenly arranged on the outer side of the circumference, the external airflow can enter the interior of the air intake duct from the air intake holes 31, so as to prevent flying birds from entering the interior of the air intake duct; the bullet-shaped air intake cylinder 3 can make the oncoming airflow converge to the air intake duct more smoothly, thereby increasing the efficiency of the aircraft. The large intake volume capture coefficient provides the engine with sufficient air for combustion; the intake holes 31 on the circumferential outer wall can guide part of the airflow, so that the airflow enters the intake duct more evenly, improves the intake efficiency, and ensures that the engine can stably obtain the required amount of air under different flight postures and working conditions; the bullet-shaped intake cylinder 3 will generate shock waves in the high-speed airflow, preliminarily compress the incoming air, increase the air pressure and temperature, and facilitate the subsequent combustion process; the presence of the slots can further fine-tune the intensity and position of the shock wave, making the pre-compression effect more ideal, so that the air state entering the combustion chamber is more in line with the combustion requirements, and improving the overall performance of the engine; at the same time, when the airflow passes through the intake hole 31 and impacts the outer side of the retarder 35, It can decelerate the gas that is about to enter the air intake duct. According to the principle of ramjet engines, during the deceleration of gas, kinetic energy is converted into pressure energy, which increases the static pressure of the gas. This provides a suitable pressure environment for subsequent combustion, allowing the fuel and air to mix and burn more fully and efficiently, thereby improving the thermal efficiency and thrust output of the engine. The combustion chamber of the scramjet engine requires air at a specific pressure to ensure stable and efficient combustion of the fuel. The deceleration and pressurization of the gas before the intake can ensure that the air pressure entering the combustion chamber meets the combustion requirements, maintain a stable combustion process, and prevent problems such as unstable combustion and flameout. After the gas is decelerated, the flow rate in the engine is relatively reduced, which prolongs the residence time of the fuel and air in the combustion chamber.This is conducive to more complete mixing and chemical reaction between fuel and air, improving combustion efficiency, allowing the chemical energy of the fuel to be more fully converted into heat energy, thereby improving engine performance; the decelerated airflow impacts the deflector 36;

[0047] The air guide 36 covers the air passage of the engine body 1, and the air guide 36 includes a fixing seat 361, an air intake outer cover 362 and an air intake inner cover 363; the air intake inner cover 363 covers the outer side of the compressor 14, and a plurality of air guide holes are evenly arranged on the air guide 36; the arrangement of the air guide 36 can make the airflow entering the inside of the air intake duct be evenly distributed; it can divert and rectify the airflow about to enter the inside of the air intake duct, reduce the degree of turbulence of the airflow, and make the velocity and pressure distribution of the airflow entering the engine on the cross section more uniform; it helps to improve the mixing uniformity of fuel and air in the combustion chamber, achieve more stable and efficient combustion, reduce local overheating or incomplete combustion and other problems, and improve the reliability and thrust output stability of the engine; the airflow forms a specific flow pattern after entering the air intake duct, which is conducive to more complete mixing of fuel and air before entering the combustion chamber; a more uniform fuel-air mixture ratio can make the combustion closer to the ideal state, improve the combustion efficiency, release more energy, and thus increase the thrust of the engine; The airflow entering the combustion chamber is more stable and orderly, providing a more stable environment for combustion; it helps to maintain the stability of combustion, prevent the flame from being extinguished or unstable combustion phenomena such as oscillating combustion, and ensure that the engine can work reliably under various flight conditions, especially under high Mach number flight or complex airflow conditions; the guide vanes 2 are evenly arranged in four groups along the outer side of the circumference of the tail end injection port of the engine body 1, which can make the high-speed airflow ejected from the tail end injection port more stable and orderly; prevent the airflow from being turbulent and fluctuating, ensure that the engine can maintain a stable thrust output under different flight conditions and working conditions, and help improve the stability and controllability of the aircraft flight; the guide vanes 2 can optimize and shape the airflow of the tail nozzle so that the airflow is ejected in a more ideal state; reduce the energy loss and turbulence of the airflow, increase the axial momentum of the airflow, thereby improving the thrust efficiency of the engine to a certain extent, so that the engine can generate greater thrust under the same fuel consumption, which helps to improve the flight speed and range of the aircraft.

[0048] like Fig.10 and Fig.11 As shown, specific embodiment nine: This embodiment is a further limitation of specific embodiment eight, the cross-sections of the air intake outer cover 362 and the air intake inner cover 363 are both isosceles trapezoidal, the air intake inner cover 363 covers the outside of the compressor 14, and a plurality of groups of guide holes are evenly arranged on the guide cover 36.

[0049] like Figure 4 , Figure 5 , Figure 6 , Figure 7 and Figure 8 As shown, specific embodiment ten: This embodiment is a further limitation of specific embodiment four or eight, a plurality of groups of oblique through holes 200 and screw holes 300 are evenly arranged on the bottom of the air intake cylinder 3, a plurality of groups of connecting holes 400 are evenly arranged on the circumferential inner wall of the fixing seat 361, a plurality of groups of oblique screw holes 100 are evenly arranged on the surface of the docking seat 10, the oblique screw holes 100 and the oblique through holes 200 are arranged opposite to each other, a first fixing bolt passes through the oblique through hole 200 and is screwed in the oblique screw hole 100, and a second fixing bolt passes through the connecting hole 400 and is screwed in the screw hole 300.

[0050] The present invention covers any substitution, modification, equivalent method and scheme made on the essence and scope of the present invention. In order to make the public have a thorough understanding of the present invention, specific details are described in detail in the following preferred embodiments of the present invention, but those skilled in the art can fully understand the present invention without the description of these details. In addition, in order to avoid unnecessary confusion about the essence of the present invention, well-known methods, processes, procedures, components and circuits are not described in detail.

[0051] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principle of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A cross-medium scramjet engine, comprising an engine body (1), characterized in that: A guide vane (2) is fixedly mounted on the circumferential outer side of the jet outlet at the tail end of the engine body (1); an air inlet duct is provided inside the end of the engine body (1) away from the guide vane (2); a docking seat (10) is fixedly mounted on the outer side of the air inlet duct at the end of the engine body (1); an air inlet cylinder (3) is fixedly mounted on the end of the docking seat (10); an air inlet hole (31) is provided on the circumferential outer wall of the air inlet cylinder (3); a flow-through vane (32) is fixedly mounted on the circumferential outer side of the air inlet cylinder (3); a turbine (11) is provided at a location inside the engine body (1) close to the jet outlet; a compressor (14) is provided at a location inside the engine body (1) close to the air duct; and a combustion assembly (13) is mounted between the compressor (14) and the turbine (11).

2. A cross-medium scramjet engine according to claim 1, characterized in that: The guide vanes (2) are evenly arranged in four groups along the outer side of the circumference of the tail end injection port of the engine body (1); the cross section of the guide vanes (2) is arranged in a trapezoidal shape, the outer surface of the engine body (1) is arranged in a streamlined shape, and the engine body (1) as a whole is arranged in a spherical shape.

3. A cross-medium scramjet engine according to claim 1, characterized in that: The engine body (1) comprises a docking seat (10), a turbine (11), worm wheel blades (12), a combustion assembly (13) and a compressor (14); a combustion chamber is arranged inside the combustion assembly (13); the combustion assembly (13) is evenly arranged in six groups between the turbine (11) and the compressor (14); cooling jackets are provided on both sides of the inner wall of the engine body (1); and a plurality of worm wheel blades (12) are evenly arranged on the outer circumference of the turbine (11).

4. A cross-medium scramjet engine according to claim 1, characterized in that: The air intake cylinder (3) comprises an air intake hole (31), a flow-through sheet (32), a flow-piercing portion (33), a connecting sheet (34), a retarder (35) and a flow guide cover (36); the air intake cylinder (3) is arranged in a bullet shape, and the retarder (33) is arranged at one end of the air intake cylinder (3) away from the engine body (1); the external airflow passes through the air intake hole (31), impacts the retarder (35), decelerates, passes through the flow guide cover (36), and then enters the engine airway after being filtered.

5. A cross-medium scramjet engine according to claim 4, characterized in that: Four groups of flow-through sheets (32) are evenly arranged on the outer side of the circumference of the air inlet cylinder (3), the flow-through sheets (32) are arranged in a fan shape, and the outer surface of the flow-through sheets (32) is arranged in a streamline shape; one end of the air inlet cylinder (3) away from the piercing portion (33) is screwed and fixed to the docking seat (10).

6. A cross-medium scramjet engine according to claim 4, characterized in that: The air intake cylinder (3) is provided with a retarder cylinder (35) in a bullet shape. A plurality of connecting plates (34) are evenly arranged on the outer side of the retarder cylinder (35). One end of the connecting plate (34) away from the retarder cylinder (35) is fixedly arranged on the inner wall of the air intake cylinder (3). A plurality of air intake holes (31) are evenly arranged on the circumferential outer wall of the air intake cylinder (3). The air intake holes (31) are arranged in a strip shape. The axial section of the air intake cylinder (3) and the retarder cylinder (35) inside it is a concentric circle structure.

7. The cross-medium scramjet engine according to claim 1, characterized in that: A deflector (36) is threadedly mounted on the lower side of the air intake cylinder (3). The deflector (36) covers the air passage of the engine body (1). The deflector (36) comprises a fixing seat (361), an air intake outer cover (362) and an air intake inner cover (363).

8. A cross-medium scramjet engine according to claim 7, characterized in that: A fixing seat (361) is fixedly mounted on the top of the air guide cover (36), an air intake outer cover (362) is fixedly connected to the bottom of the fixing seat (361), and an air intake inner cover (363) is fixedly mounted on the bottom of the air intake outer cover (362); an axial section of the fixing seat (361), the air intake outer cover (362) and the air intake inner cover (363) is a concentric circle structure.

9. A cross-medium scramjet engine according to claim 8, characterized in that: The cross-sections of the air intake outer cover (362) and the air intake inner cover (363) are both isosceles trapezoidal. The air intake inner cover (363) covers the outer side of the compressor (14). The guide cover (36) is evenly provided with a plurality of groups of guide holes.

10. A cross-medium scramjet engine according to any one of claims 4 or 8, characterized in that: The bottom of the air intake cylinder (3) is evenly provided with a plurality of groups of oblique through holes (200) and screw holes (300), the circumferential inner wall of the fixing seat (361) is evenly provided with a plurality of groups of connecting holes (400), the surface of the docking seat (10) is evenly provided with a plurality of groups of oblique screw holes (100), the oblique screw holes (100) and the oblique through holes (200) are arranged opposite to each other, the first fixing bolt passes through the oblique through hole (200) and is screwed into the inside of the oblique screw hole (100), and the second fixing bolt passes through the connecting hole (400) and is screwed into the inside of the screw hole (300).

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