A cross-media scramjet engine

Abstract

The application discloses a cross-medium scramjet engine and relates to the field of engines.The cross-medium scramjet engine comprises an engine body, a guide vane is fixedly installed on the circumferential outer side of a tail-end injection port of the engine body, an air inlet channel is formed in the inner side of the end of the engine body away from the guide vane, a butt joint seat is fixedly arranged on the outer side of the end air inlet channel 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 a flow-through vane is fixedly arranged on the circumferential outer side of the air inlet cylinder; a turbine is arranged at a position close to the injection port in the inner side of the engine body; and a combustion assembly is arranged between the turbine and the air inlet channel.The cross-medium scramjet engine is helpful to improve the mixing uniformity of fuel and air in the combustion chamber, realize more stable and efficient combustion, reduce problems such as local overheating or insufficient combustion, and improve the reliability and thrust output stability of the engine.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of engine, in particular to a cross-medium scramjet engine. BACKGROUND

[0002] The cross-medium aircraft is a new concept aircraft that can fly in the air and dive underwater, which has the speed of aircraft and the concealment of underwater vehicle, can maneuver underwater, launch attacks from underwater and water surface, fly close to the sea and implement concealed precision strikes, can effectively use the blind area of radar and various detection equipment to launch attacks on enemy aircraft carriers, warships and submarines, and has high efficient penetration strike and multi-task capability.

[0003] As for the cross-medium scramjet engine, through retrieval, the cross-medium scramjet engine based on solid propelling is disclosed in the patent with the publication number CN109098891A, which includes flow channels uniformly arranged on the outer circumference of the gas generator, and the flow channels are designed in an integrated manner with the gas generator, which not only ensures the normal operation of the engine, but also ensures the streamline shape of the gas generator.

[0004] Although the above-mentioned device realizes the double-mode conversion of the propelling system and the cross-medium operation, and fully combines the advantages of air flight and underwater diving, when the scramjet engine is used as a propeller in the air, the air flow entering the inlet duct is not uniformly distributed in terms of velocity, pressure and other parameters on the cross section during the air intake of the scramjet engine, which will make the combustion process in the combustion chamber unstable, reduce the combustion efficiency, and affect the performance and thrust output of the engine. SUMMARY

[0005] The present application aims to provide a cross-medium scramjet engine to solve the defects mentioned in the background.

[0006] To achieve the above-mentioned purpose, a cross-medium scramjet engine is provided, which comprises an engine body, a guide vane is fixedly installed on the outer side of the circumference of the tail end injection port of the engine body, an inlet duct is formed in the inner side of the end of the engine body away from the guide vane, a butt joint seat is fixedly arranged on the outer side of the end inlet duct 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 outer wall of the circumference of the air inlet cylinder, and a flow-through vane is fixedly arranged on the outer side of the circumference of the air inlet cylinder; a turbine is arranged at a place close to the injection port in the inner side of the engine body, a compressor is arranged at a place close to the air duct in the inner side of the engine body, and a combustion assembly is installed between the compressor and the turbine.

[0007] As a preferred implementation, the guide vane is evenly arranged in four groups along the outer side of the tail end of the engine body, the cross section of the guide vane is arranged in a trapezoidal shape, the outer surface of the engine body is arranged in a streamline shape, and the engine body is arranged in a spherical shape as a whole.

[0008] As a preferred implementation, the engine body includes a docking seat, a turbine, turbine blades, a combustion assembly, and a compressor, the combustion assembly is internally provided with a combustion chamber, the combustion assembly is evenly arranged in six groups between the turbine and the compressor, and the inner wall of the engine body is provided with a cooling jacket on both sides; the turbine is evenly provided with a plurality of turbine blades on the outer side of the circumference.

[0009] As a preferred implementation, the intake cylinder includes an intake hole, a flow-through vane, a flow-striking part, a connecting piece, a speed-reducing cylinder, and a flow guide cover, the intake cylinder is arranged in a bullet shape, and the end of the intake cylinder away from the engine body is provided with a flow-striking part; external airflow impacts on the speed-reducing cylinder through the intake hole and enters the engine air passage after being filtered by the flow guide cover.

[0010] As a preferred implementation, the intake cylinder is evenly provided with four groups of flow-through vanes on the outer side of the circumference, the flow-through vanes are arranged in a fan shape, and the outer surface of the flow-through vanes is arranged in a streamline shape; the end of the intake cylinder away from the flow-striking part is screw-fixed with the docking seat.

[0011] As a preferred implementation, the intake cylinder is internally provided with a speed-reducing cylinder, the speed-reducing cylinder is arranged in a bullet shape, the outer side of the speed-reducing cylinder is evenly provided with a plurality of connecting pieces, and the end of the connecting piece away from the speed-reducing cylinder is fixedly arranged on the inner wall of the intake cylinder; a plurality of intake holes are evenly arranged on the outer wall of the circumference of the intake cylinder, and the intake holes are arranged in a strip shape; the axial cross section of the intake cylinder and the speed-reducing cylinder inside the intake cylinder is a concentric circle structure.

[0012] As a preferred implementation, the flow guide cover is screw-mounted on the inside of the intake cylinder, the flow guide cover covers the air passage of the engine body, and the flow guide cover includes a fixed seat, an intake outer cover, and an intake inner cover.

[0013] As a preferred implementation, the fixed seat is fixedly installed on the top of the flow guide cover, the intake outer cover is fixedly connected to the bottom of the fixed seat, and the intake inner cover is fixedly installed on the bottom of the intake outer cover; the axial cross section of the fixed seat, the intake outer cover, and the intake inner cover is a concentric circle structure.

[0014] As a preferred implementation, the cross section of the intake outer cover and the intake inner cover is arranged in an isosceles trapezoidal shape, the intake inner cover covers the outer side of the compressor, and a plurality of flow guide holes are evenly arranged on the flow guide cover.

[0015] As a preferable implementation, the bottom of the air inlet cylinder is uniformly provided with multiple groups of inclined through holes and screw holes, the circumferential inner wall of the fixing seat is uniformly provided with multiple groups of connecting holes, and the surface of the abutting seat is uniformly provided with multiple groups of inclined screw holes.

[0016] Compared with the prior art, the present application has the following advantages:

[0017] 1. The air flow entering the air inlet channel can be uniformly distributed by the fairing, the air flow entering the air inlet channel can be divided and rectified, the degree of turbulence of the air flow is reduced, the velocity and pressure distribution of the air flow entering the engine on the cross section are more uniform, the mixing uniformity of fuel and air in the combustion chamber is improved, more stable and efficient combustion is realized, problems such as local overheating or insufficient combustion are reduced, and the reliability and thrust output stability of the engine are improved.

[0018] 2. The air flow entering the air inlet channel can be slowed down when the air flow passes through the air inlet hole and impacts the circumferential outer side of the speed reduction cylinder, according to the ramjet principle, during the air flow slowing down process, kinetic energy is converted into pressure energy, so that the static pressure of the air flow is increased, which provides a suitable pressure environment for the subsequent combustion, so that the fuel and air can be more fully and efficiently mixed and burned, thereby improving the thermal efficiency and thrust output of the engine, the combustion chamber of the scramjet engine needs air with a specific pressure to ensure stable and efficient combustion of the fuel, and the air pressure entering the combustion chamber can meet the combustion requirements and maintain a stable combustion process. BRIEF DESCRIPTION OF DRAWINGS

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

[0020] Figure 1 is a front view of the structure of the present application;

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

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

[0023] Figure 4 is a sectional view of Figure 1 ;

[0024] Figure 5 is a front view of Figure 4 ;

[0025] Figure 6 is a rear view of Figure 4

[0026] Figure 7 is a top view of Figure 4

[0027] Figure 8 is an enlarged structural schematic view of A in Figure 7

[0028] Figure 9 is a schematic view of an air intake cylinder

[0029] Figure 10 is a rear view of Figure 9

[0030] Figure 11 is a top view of Figure 9

[0031] [Reference Signs]

[0032] 1, engine body; 10, abutment; 11, turbine; 12, turbine blade; 13, combustion assembly; 14, compressor; 2, deflector; 3, air intake cylinder; 31, air intake hole; 32, through-flow piece; 33, impingement portion; 34, connecting piece; 35, retardation cylinder; 36, deflector cover; 361, fixing seat; 362, air intake outer cover; 363, air intake inner cover; 100, inclined screw hole; 200, inclined through hole; 300, screw hole; 400, connecting hole. DETAILED DESCRIPTION

[0033] The present application will be described in detail below with reference to the drawings and specific embodiments. It should be noted that, in order to make the embodiments more detailed, the following embodiments are the best, preferred embodiments, and other alternative ways can also be used by those skilled in the art to implement them; and the drawings are only used to more specifically describe the embodiments, and are not intended to specifically limit the present application.

[0034] It should be noted that in the specification, "one embodiment", "embodiment", "exemplary embodiment", "some embodiments" and the like indicate that the described embodiments can include a specific feature, structure or property, but not necessarily every embodiment includes the specific feature, structure or property. In addition, when a specific feature, structure or property is described in combination with an embodiment, it should be within the knowledge of those skilled in the art to implement such a feature, structure or property in combination with other embodiments, whether or not it is explicitly described.

[0035] ​​​​​In general, terminology can be understood at least in part from the usage in context. For example, the term "one or more" as used herein, depending at least in part upon context, can be used to describe any feature, structure, or characteristic in a singular sense or can be used to describe combinations of features, structures or characteristics in a plural sense. Additionally, the term "based on" can be understood as not necessarily being confined to factors that are strictly descriptive in nature, but can instead be broadly understood as based at least in part on a factor that can not be strictly descriptive in nature.

[0036] It will be understood that the terms "on", "over", and "above", in the present invention, are to be interpreted in the broadest possible sense to mean not only "directly on" something, but also to include the meaning of being "on" something with intervening features or layers therebetween, and "over" or "above" something not only means "over" or "above" something, but can also include the meaning of being "over" or "above" something with no intervening features or layers therebetween.

[0037] In addition, spatially relative terms, such as "beneath", "below", "lower", "above", "upper" and the like, can be used herein for ease of description to describe one element or feature's relationship to another element(s) or feature(s) as illustrated in the figures. The spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientations depicted in the figures. The devices can be otherwise oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein can similarly be interpreted accordingly.

[0038] DETAILED DESCRIPTION Figures 1-4 The present application provides a technical solution: a cross-medium scramjet engine, comprising an engine body 1, a circumferential outer side of a tail end injection port of the engine body 1 is fixedly installed with a flow guide vane 2, an inner part of an end of the engine body 1 away from the flow guide vane 2 is provided with an air inlet channel, an outer side of the air inlet channel of the end of the engine body 1 is fixedly provided with a butt joint seat 10, an end of the butt joint seat 10 is fixedly provided with an air inlet cylinder 3, the circumferential outer wall of the air inlet cylinder 3 is provided with an air inlet hole 31, and the circumferential outer side of the air inlet cylinder 3 is fixedly provided with a flow-through vane 32; a turbine 11 is arranged at a place close to the injection port in the inner part of the engine body 1, and a compressor 14 is arranged at a place close to the air inlet channel in the inner part of the engine body 1; a combustion assembly 13 is installed between the compressor 14 and the turbine 11.

[0039] As Figure 1 , Figure 2 and Figure 3As shown, the second specific implementation is a further limitation of the first specific implementation. Four sets of guide vanes 2 are evenly arranged along the outer 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, the third specific embodiment is a further limitation of the first specific embodiment. The engine body 1 includes a docking seat 10, a turbine 11, turbine blades 12, a combustion assembly 13 and a compressor 14. The combustion assembly 13 has a combustion chamber inside. 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. Multiple sets of turbine blades 12 are evenly arranged on the outer circumference of the turbine 11.

[0041] like Figure 1 , Figure 4 and Figure 5 As shown, the fourth specific embodiment is a further limitation of the first specific embodiment. The air intake cylinder 3 includes an air intake hole 31, a flow-through plate 32, a flow-piercing part 33, a connecting piece 34, a retarder cylinder 35, and a guide shroud 36. The air intake cylinder 3 is bullet-shaped, and the flow-piercing part 33 is provided at the end of the air intake cylinder 3 away from the engine body 1. The external airflow impacts the retarder cylinder 35 through the air intake hole 31 and is decelerated before being filtered by the guide shroud 36 and entering the engine air passage.

[0042] like Figure 1 , Figure 2 , Figure 5 , Figure 6 and Figure 7 As shown, in the fifth specific embodiment: This embodiment is a further limitation of the fourth specific embodiment. Four sets of flow-through vanes 32 are evenly arranged on the outer circumference of the air inlet cylinder 3. The flow-through vanes 32 are arranged in a fan shape and the outer surface of the flow-through vanes 32 is streamlined. The end of the air inlet cylinder 3 away from the piercing part 33 is screwed and fixed to the docking seat 10.

[0043] like Figure 5 , Figure 6 and Figure 7 As shown, in specific embodiment six: This embodiment is a further limitation of specific embodiment four. The air intake cylinder 3 is provided with a retarder cylinder 35 inside. The retarder cylinder 35 is bullet-shaped. Multiple sets of connecting pieces 34 are evenly arranged on the outer side of the retarder cylinder 35. The end of the connecting piece 34 away from the retarder cylinder 35 is fixedly arranged on the inner wall of the air intake cylinder 3. Multiple sets of air intake holes 31 are evenly opened on the outer circumference of the air intake cylinder 3. The air intake holes 31 are strip-shaped. The axial cross-section of the air intake cylinder 3 and the retarder cylinder 35 inside it is a concentric circle structure.

[0044] As Figure 9 , Figure 10 and Figure 11 shown, the seventh embodiment is a further limitation of the first embodiment, the inside of the intake cylinder 3 is screw-mounted with a flow guide cover 36, which covers the air passage of the engine body 1, and the flow guide cover 36 includes a fixed seat 361, an intake outer cover 362 and an intake inner cover 363.

[0045] As Figure 9 , Figure 10 and Figure 11 shown, the eighth embodiment is a further limitation of the seventh embodiment, the top of the flow guide cover 36 is fixedly mounted with the fixed seat 361, the bottom of the fixed seat 361 is fixedly connected with the intake outer cover 362, and the bottom of the intake outer cover 362 is fixedly mounted with the intake inner cover 363; the axial section of the fixed seat 361, the intake outer cover 362 and the 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 of the engine body 1 at a very high speed; the air inlet adopts shock wave compression to make the high-speed airflow generate a series of shock waves; when the airflow passes through the shock wave, the speed is reduced, and the pressure and temperature are increased, realizing the preliminary compression of the air; the combustion assembly 13 includes a combustion chamber, which is the place where fuel and air are mixed and burned; after the subsonic air is compressed and stabilized, the fuel is injected into the combustion chamber through a special nozzle in a suitable way; the fuel is rapidly 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 airflow, the combustion process is carried out in the low-speed high-pressure airflow, which can improve the gas static pressure and improve the combustion efficiency, producing high-temperature and high-pressure gas; the high-temperature and high-pressure gas produced by combustion enters the tail nozzle; the shape and structure design of the tail nozzle make the gas expand and accelerate in it; according to the law of conservation of momentum, the gas is ejected backward at high speed, generating a backward force, i.e. thrust, to push the aircraft forward; when the air inlet of the engine body 1 is in the process of air intake, the front of the air inlet is provided with an air inlet cylinder 3, which is bullet-shaped and uniformly provided with multiple groups of air inlet holes 31 on the circumferential outer side; the outside airflow can enter the inside of the air inlet from the air inlet holes 31, avoiding the entry of birds into the air inlet; the bullet-shaped air inlet cylinder 3 can make the oncoming airflow more smoothly converge to the air inlet, increase the air intake coefficient, and provide sufficient air for the engine to burn; the air inlet holes 31 on the circumferential outer wall can guide part of the airflow, making the airflow more uniformly enter the air inlet, improving the air intake efficiency, and ensuring that the engine can stably obtain the required air volume under different flight attitudes and working conditions; the bullet-shaped air inlet cylinder 3 will generate a shock wave in the high-speed airflow, which can preliminarily compress the incoming air, increase the pressure and temperature of the air, and be beneficial to the subsequent combustion process; the existence of the slot hole can further adjust the strength and position of the shock wave, make the pre-compression effect more ideal, and make the air state entering the combustion chamber more meet the combustion demand, improve the overall performance of the engine; at the same time, when the airflow passes through the air inlet holes 31 and impacts on the circumferential outer side of the speed reduction cylinder 35, it can slow down the gas about to enter the inside of the air inlet; according to the principle of ramjet engine, during the gas speed reduction process, the kinetic energy is converted into pressure energy, which makes the gas static pressure increase; this provides a suitable pressure environment for the subsequent combustion, so that the fuel and air can be more fully and efficiently mixed and burned, thereby improving the thermal efficiency and thrust output of the engine; the combustion chamber of the scramjet engine needs air with a certain pressure to ensure stable and efficient combustion of fuel; the air is slowed down and pressurized before air intake, which can ensure that the air pressure entering the combustion chamber meets the combustion requirements, maintains a stable combustion process, and prevents problems such as unstable combustion and flameout; after the gas is slowed down, the flow rate in the engine is relatively reduced, which prolongs the residence time of the fuel and air in the combustion chamber;This facilitates more thorough mixing of fuel and air and chemical reactions, improves combustion efficiency, and converts more of the fuel's chemical energy into heat energy, thereby enhancing engine performance; the airflow after deceleration impacts on the fairing 36;

[0047] The fairing 36 covers the air passage of the engine body 1, and includes a fixing seat 361, an air inlet outer cover 362, and an air inlet inner cover 363. The air inlet inner cover 363 covers the outer side of the compressor 14, and the fairing 36 is uniformly provided with multiple groups of flow guide holes. The arrangement of the fairing 36 allows the airflow entering the air passage to be uniformly distributed, and the airflow about to enter the air passage to be divided and rectified, thereby reducing the turbulence of the airflow and making the velocity and pressure distribution of the airflow entering the engine more uniform in cross section. This helps to improve the uniformity of fuel and air mixing in the combustion chamber, achieve more stable and efficient combustion, reduce problems such as local overheating or insufficient combustion, and improve the reliability and thrust output stability of the engine. The airflow forms a specific flow pattern after entering the air passage, which facilitates more thorough mixing of fuel and air before entering the combustion chamber. A more uniform fuel-air mixture ratio enables combustion to be closer to the ideal state, improves combustion efficiency, releases more energy, and thus increases the thrust of the engine. The airflow entering the combustion chamber is more stable and orderly, providing a more stable environment for combustion. This helps to maintain the stability of combustion, prevents flameout or unstable combustion phenomena such as oscillating combustion, and ensures that the engine can reliably work under various flight conditions, especially under high Mach number flight or complex airflow conditions. The four groups of guide vanes 2 are uniformly arranged along the outer side of the circumference of the tail end injection port of the engine body 1, which makes the high-speed airflow ejected from the tail end injection port more stable and orderly. This prevents airflow from being turbulent and fluctuating, and ensures that the engine can maintain stable thrust output under different flight conditions and working conditions, thereby improving the stability and controllability of the aircraft in flight.

[0048] As shown in Figure 10 and Figure 11 , the specific embodiment nine is a further limitation of the specific embodiment eight. The cross sections of the air inlet outer cover 362 and the air inlet inner cover 363 are isosceles trapezoidal, the air inlet inner cover 363 covers the outer side of the compressor 14, and the fairing 36 is uniformly provided with multiple groups of flow guide holes.

[0049] As shown in Figure 4 , Figure 5 , Figure 6 , Figure 7 andFigure 8 Specific embodiment ten: this embodiment is a further limitation of specific embodiment four or eight, the bottom of the air inlet cylinder 3 is uniformly provided with multiple groups of inclined holes 200 and threaded holes 300, the circumferential inner wall of the fixing seat 361 is uniformly provided with multiple groups of connecting holes 400, the surface of the butt joint seat 10 is uniformly provided with multiple groups of inclined threaded holes 100, the inclined threaded holes 100 and the inclined holes 200 are oppositely arranged, the first fixing bolt is screwed in the inclined threaded hole 100 through the inclined hole 200, and the second fixing bolt is screwed in the threaded hole 300 through the connecting hole 400.

[0050] The present application encompasses any alternatives, modifications, equivalent methods and solutions made on the essence and scope of the present application. In order to make the public have a thorough understanding of the present application, specific details are described in the following preferred embodiments of the present application, and the present application can also be fully understood without the description of these details by those skilled in the art. In addition, in order to avoid unnecessary confusion to the essence of the present application, well-known methods, processes, procedures, elements and circuits, etc. are not described in detail.

[0051] The above is only the preferred embodiment of the present application, and it should be pointed out that for ordinary skilled in the art, without departing from the principles of the present application, a number of improvements and refinements can also be made, which should be considered as the protection scope of the present application.

Claims

1. A scramjet engine across the medium, comprising an engine body (1), characterized by: The engine body (1) tail end injection port circumferential outside fixed installation has guide vane (2), engine body (1) is away from guide vane (2) one end inside and is provided with air inlet, engine body (1) end air inlet outside fixedly arranged with butt joint seat (10), butt joint seat (10) end fixedly arranged with air inlet cylinder (3), air inlet cylinder (3) circumferential outer wall is provided with air inlet hole (31), air inlet cylinder (3) circumferential outside fixedly arranged with through flow piece (32);Engine body (1) inside is close to the place of injection port and is provided with turbine (11), engine body (1) inside is close to the place of air inlet and is provided with compressor (14);Compressor (14) and turbine (11) between installation has combustion assembly (13).

2. The cross- medium scramjet engine of claim 1, wherein: The guide vane (2) is evenly provided with four groups along the circumferential outside of the tail end injection port of the engine body (1), the cross section of the guide vane (2) is provided in trapezoidal shape, the outside surface of the engine body (1) is provided in streamline shape, and the engine body (1) is provided in spherical shape as a whole.

3. The cross- medium scramjet engine of claim 1, wherein: The engine body (1) includes butt joint seat (10), turbine (11), turbine blade (12), combustion assembly (13) and compressor (14), the inside of the combustion assembly (13) is provided with a combustion chamber, the combustion assembly (13) is evenly provided with six groups between the turbine (11) and the compressor (14), and the inner wall of the engine body (1) is provided with cooling jacket on both sides; The circumferential outside of the turbine (11) is evenly provided with a plurality of turbine blades (12).

4. The cross- medium scramjet engine of claim 1, wherein: The air inlet cylinder (3) includes air inlet hole (31), through flow piece (32), flow part (33), connecting piece (34), speed reduction cylinder (35) and flow cover (36), the air inlet cylinder (3) is provided in bullet shape, and the end of the air inlet cylinder (3) away from the engine body (1) is provided with flow part (33); The outside air flow impacts on the speed reduction cylinder (35) through the air inlet hole (31) and slows down, then filters through the flow cover (36) and enters the engine air inlet.

5. The cross- medium scramjet engine of claim 4, wherein: The circumferential outside of the air inlet cylinder (3) is evenly provided with four groups of through flow pieces (32), the through flow pieces (32) are provided in fan shape, and the outside surface of the through flow pieces (32) is provided in streamline shape; The end of the air inlet cylinder (3) away from the flow part (33) is screw fixed with the butt joint seat (10).

6. The cross- medium scramjet engine of claim 4, wherein: The inside of the air inlet cylinder (3) is provided with speed reduction cylinder (35), the speed reduction cylinder (35) is provided in bullet shape, a plurality of connecting pieces (34) are evenly provided on the outside of the speed reduction cylinder (35), and the end of the connecting piece (34) away from the speed reduction cylinder (35) is fixedly arranged on the inner wall of the air inlet cylinder (3); A plurality of air inlet holes (31) are evenly provided on the circumferential outer wall of the air inlet cylinder (3), and the air inlet holes (31) are provided in strip shape; The axial section of the air inlet cylinder (3) and the speed reduction cylinder (35) inside it is concentric circular structure.

7. The cross- medium scramjet engine of claim 1, wherein: The flow cover (36) is screw installed on the inside of the air inlet cylinder (3), the flow cover (36) covers the air inlet of the engine body (1), and the flow cover (36) includes fixed seat (361), air inlet outer cover (362) and air inlet inner cover (363).

8. The cross- medium scramjet engine of claim 7, wherein: The top of the fairing (36) is fixedly provided with a fixed seat (361), the bottom of the fixed seat (361) is fixedly connected with an air inlet outer cover (362), and the bottom of the air inlet outer cover (362) is fixedly provided with an air inlet inner cover (363); the axial section of the fixed seat (361), the air inlet outer cover (362) and the air inlet inner cover (363) is a concentric circle structure.

9. The cross- medium scramjet engine of claim 8, wherein: The section of the air inlet outer cover (362) and the air inlet inner cover (363) is an isosceles trapezoid, the air inlet inner cover (363) covers the outer side of the air compressor (14), and a plurality of groups of flow guide holes are uniformly formed in the fairing (36).

10. The cross- medium scramjet engine according to any one of claims 4 or 8, wherein: The bottom of the air inlet cylinder (3) is uniformly provided with a plurality of groups of inclined through holes (200) and screw holes (300), a plurality of groups of connecting holes (400) are uniformly formed in the circumferential inner wall of the fixed seat (361), and the surface of the butt joint seat (10) is uniformly provided with a plurality of groups of inclined screw holes (100); the inclined screw holes (100) and the inclined through holes (200) are oppositely arranged, the first fixing bolt is screwed in the inclined screw holes (100) through the inclined through holes (200), and the second fixing bolt is screwed in the screw holes (300) through the connecting holes (400).

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