Turbine-free ramjet engine

Abstract

The invention relates to the technical field of aero-engines, in particular to a turbo-free ramjet engine which comprises an inner shell and an outer shell, a rectifying body is arranged in the inner shell, an inner air inlet channel and a main air injection channel are arranged on the two sides of the rectifying body, the outer shell is arranged on the outer side of the inner shell, and the inner shell extends out of the outer shell. An outer air inlet channel and a heat dissipation channel are arranged between the inner shell and the outer shell, a fan and an air compressor are arranged on the outer side of the inner shell, a plurality of side air spraying pipes are arranged on the inner shell and located on the outer side of the main air spraying channel, and the side air spraying pipes are annularly arranged outside the outer shell at equal intervals. The jet engine is simpler and more compact in structure, easy to manufacture and produce and convenient to maintain, the size of the engine is smaller, a large amount of precious metal is prevented from being used, the production cost of the engine is greatly saved, the side jet pipe is arranged, the rotating speed of the inner shell is rapidly increased, and the efficiency of the engine is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation engines, and in particular to a turbine-free ramjet engine. Background Art

[0002] Currently, commonly used jet engines are mainly turbine-structured jet engines. Turbojets, turbofans, turboprops, turboshafts or variable cycle engines all use turbines as core components. Turbines are in high-temperature working environments for a long time. In order to always maintain the stability of the turbine structure and ensure long-term reliable operation of the turbine, the production materials of the turbine usually require a large amount of precious metals, which greatly increases the production cost of the turbine. In addition, the structure of the turbine is complex and the technical difficulty is high, resulting in a complex production process, difficult manufacturing and difficult maintenance of the turbine. Summary of the invention

[0003] In view of the above problems, the present invention provides a turbine-free ramjet engine to solve the problems of high production cost, complex structure, high technical difficulty, complex production process, difficult manufacturing and difficult maintenance of turbojet engines in the prior art.

[0004] To achieve the above-mentioned object, the present invention provides a turbine-free ramjet engine, comprising an inner casing and an outer casing, wherein a rectifier body is arranged in the inner casing, the rectifier body is ellipsoidal, an inner air inlet duct and a main jet duct are arranged on both sides of the rectifier body respectively, the outer casing is arranged on the outer side of the inner casing, and one end of the inner casing on which the main jet duct is arranged extends out of the outer casing, an outer air inlet duct and a heat dissipation duct are arranged between the inner casing and the outer casing, the outer air inlet duct is arranged on the outer side of the inner air inlet duct, the heat dissipation duct is arranged on the outer side of the main jet duct, a fan and a compressor are arranged on the outer side of the inner casing in sequence, the fan and the compressor are both arranged in the outer air inlet duct, a plurality of side jet pipes are connected to the outer wall of the inner casing, the side jet pipes are arranged on the outer side of the main jet duct, and the side jet pipes are arranged outside the outer casing, and the side jet pipes are arranged equidistantly in a ring along the inner casing.

[0005] Furthermore, a plurality of combustion chambers are arranged around the outer side of the rectifying body, and the combustion chambers are connected with the inner air intake passage, the main jet passage and the outer air intake passage at the same time, and each of the combustion chambers is provided with a fuel injector and a spark plug.

[0006] Furthermore, one-way intake valves are provided at the connection points between the combustion chamber and the inner intake duct and the outer intake duct, and the one-way intake valves are used to control the intake rate of the inner intake duct and the outer intake duct into the combustion chamber.

[0007] Furthermore, a plurality of annular shafts are arranged on the outside of the inner shell, and a plurality of support rods are connected to each of the annular shafts, and the support rods are connected to the outer shell.

[0008] Furthermore, the side air jet adopts vector control.

[0009] Furthermore, the plurality of side air jet pipes are respectively arranged in planes tangent to the inner shell, and the side air jet pipes can rotate in planes tangent to the inner shell, and the angle between the jet direction of the side air jet pipe and the jet direction of the main jet channel is 0 to 90 degrees.

[0010] Beneficial effects of the present invention:

[0011] The main structure of the jet engine in the present invention is an inner shell and an outer shell, wherein only a rectifying body and a combustion chamber are arranged in the inner shell, and only a fan and a compressor are arranged between the inner shell and the outer shell, and the engine is not provided with a turbine structure, so that the structure of the engine is simpler and more compact, and it is easy to manufacture and produce, and is also convenient for maintenance, so that the volume of the engine is smaller, and a large amount of precious metals are avoided, thereby greatly saving the production cost of the engine;

[0012] In the present invention, a plurality of side jet pipes are provided at the end of the inner casing of the jet engine. When the engine rotates at a low speed, the side jet pipes are opened, and the jet is ejected obliquely rearward from the side jet pipes, which can quickly increase the rotation speed of the inner casing, so as to quickly increase the rotation speed of the fan and the compressor, and quickly improve the air compression efficiency. When the side jet pipes are closed, the jet engine enters a ramjet state, so that the engine quickly reaches a state of high-speed and efficient operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] In order to more clearly illustrate the technical solution of the present invention, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0014] Figure 1 The overall structure diagram of the engine;

[0015] Among them: 1-inner shell, 2-outer shell, 3-rectifier, 4-inner air inlet, 5-main jet, 6-outer air inlet, 7-cooling duct, 8-fan, 9-compressor, 10-side jet pipe, 11-combustion chamber, 12-injector nozzle, 13-spark plug, 14-one-way air inlet valve, 15-annular shaft, 16-support rod. DETAILED DESCRIPTION

[0016] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0017] In a specific embodiment of the present invention, Figure 1 As shown, a turbine-free ramjet engine comprises an inner casing 1 and an outer casing 2. A rectifier body 3 is arranged in the inner casing 1, and the rectifier body is ellipsoidal. An inner air inlet duct 4 and a main jet duct 5 are arranged on both sides of the rectifier body 3 respectively. The outer casing 2 is arranged on the outer side of the inner casing 1, and one end of the inner casing 1 where the main jet duct 5 is arranged extends out of the outer casing 2. An outer air inlet duct 6 and a heat dissipation duct 7 are arranged between the inner casing 1 and the outer casing 2. The outer air inlet duct 6 is arranged on the outer side of the inner air inlet duct 4, and the heat dissipation duct 7 is arranged on the outer side of the main jet duct 5. A fan 8 and a compressor 9 are arranged on the outer side of the inner casing 1 in sequence, and both the fan 8 and the compressor 9 are arranged in the outer air inlet duct 6. A plurality of side jet pipes 10 are connected to the outer wall of the inner casing 1, and the side jet pipes 10 are arranged on the outer side of the main jet duct 5, and the side jet pipes 10 are arranged on the outer side of the outer casing 2. The side jet pipes 10 are arranged equidistantly in a ring along the inner casing 1.

[0018] A plurality of combustion chambers 11 are arranged around the outer side of the rectifying body 3. The combustion chambers 11 are connected with the inner air intake duct 4, the main jet duct 5 and the outer air intake duct 6 at the same time. A fuel injector 12 and a spark plug 13 are arranged in each combustion chamber 11. A one-way intake valve 14 is arranged at the connection between the combustion chamber 11 and the inner air intake duct 4 and the outer air intake duct 6. The one-way intake valve 14 is used to control the intake rate of the inner air intake duct 4 and the outer air intake duct 6 to the combustion chamber 11.

[0019] A plurality of annular shafts 15 are arranged on the outside of the inner shell 1 , and a plurality of support rods 16 are connected to each of the annular shafts 15 . The support rods 16 are connected to the outer shell 2 .

[0020] The side jet pipe 10 adopts vector control, and several side jet pipes 10 are respectively arranged in planes tangent to the inner shell 1, and the side jet pipe 10 can rotate in the plane tangent to the inner shell 1, and the angle between the jet direction of the side jet pipe 10 and the jet direction of the main jet channel 5 is 0 to 90°.

[0021] The use process of the present invention:

[0022] When the engine is started, the inner casing 1 rotates, driving the fan 8 and the compressor 9 on the outside of the inner casing 1 to rotate. At this time, the rotation speed of the inner casing 1 of the engine is relatively low, and air enters from the outer air inlet 6, and enters the combustion chamber 11 after being compressed by the fan 8 and the compressor 9. The fuel injector 12 injects fuel into the combustion chamber 11 and the fuel-air mixture is ignited by the spark plug 13. The jet is ejected from the main jet passage 5. The angle of the side jet pipe 10 is vector-controlled to increase the jet angle of the side jet pipe 10 and the jet angle of the main jet passage 5, which can reach 90° at most. At this time, the thrust of the side jet pipe 10 is used to accelerate the rotation speed of the inner casing 1, so that air can be sucked into the engine faster.

[0023] When the engine inner casing 1 rotates at high speed, the head-on air pressure increases, air enters from the inner intake duct 4, and after being compressed by the rectifying body 3, pushes the one-way intake valve 14 and then enters the combustion chamber 11, and burns together with the air entering from the outer intake duct 6. At this time, the angle of the side jet pipe 10 is controlled by vector control, so that the jet angle of the side jet pipe 10 and the jet angle of the main jet duct 5 are reduced, and the minimum can reach 0°. At this time, the side jet pipe 10 reduces the thrust that drives the inner casing 1 to rotate, and increases the thrust of the engine to the rear. When the angle is 0°, the side jet pipe 10 only applies thrust to the rear.

[0024] Part of the compressed air enters the heat dissipation channel 7 after passing through the fan 8 and the compressor 9, and cools down the main jet channel 5 of the inner shell 1, so that the inner shell 1 can meet the long-term operation requirements.

[0025] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, it is still possible for those skilled in the art to modify the technical solutions described in the aforementioned embodiments or to make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A turbine-less ramjet engine, characterized in that: The invention comprises an inner shell (1) and an outer shell (2), wherein a rectifier (3) is arranged in the inner shell (1), the rectifier is ellipsoidal, an inner air inlet passage (4) and a main jet passage (5) are arranged on both sides of the rectifier (3), the outer shell (2) is arranged outside the inner shell (1), and one end of the inner shell (1) where the main jet passage (5) is arranged extends out of the outer shell (2), an outer air inlet passage (6) and a heat dissipation passage (7) are arranged between the inner shell (1) and the outer shell (2), and the outer air inlet passage (6) is arranged on the inner air inlet passage (4). The heat dissipation channel (7) is arranged on the outside of the main jet channel (5), and a fan (8) and a compressor (9) are arranged on the outside of the inner shell (1) in sequence. The fan (8) and the compressor (9) are both arranged in the outer air inlet channel (6). A plurality of side jet pipes (10) are connected to the outer wall of the inner shell (1), and the side jet pipes (10) are arranged on the outside of the main jet channel (5). The side jet pipes (10) are arranged outside the outer shell (2), and the side jet pipes (10) are arranged equidistantly in a ring shape along the inner shell (1).

2. A turbine-less ramjet engine according to claim 1, characterized in that: A plurality of combustion chambers (11) are arranged around the outer side of the rectifying body (3), and the combustion chambers (11) are connected with the inner air intake passage (4), the main jet passage (5) and the outer air intake passage (6) at the same time. A fuel injection nozzle (12) and a spark plug (13) are arranged in each of the combustion chambers (11).

3. A turbine-less ramjet engine according to claim 2, characterized in that: A one-way intake valve (14) is provided at the connection between the combustion chamber (11) and the inner intake duct (4) and the outer intake duct (6). The one-way intake valve (14) is used to control the intake rate of the inner intake duct (4) and the outer intake duct (6) into the combustion chamber (11).

4. A turbine-less ramjet engine according to claim 1, characterized in that: A plurality of annular shafts (15) are arranged on the outside of the inner shell (1), and a plurality of support rods (16) are connected to each of the annular shafts (15), and the support rods (16) are connected to the outer shell (2).

5. A turbine-less ramjet engine according to claim 1, characterized in that: The side air jet pipe (10) adopts vector control.

6. A turbine-less ramjet engine according to claim 5, characterized in that: The plurality of side jet pipes (10) are respectively arranged in a plane tangent to the inner shell (1), and the side jet pipes (10) can rotate in a plane tangent to the inner shell (1), and the jet direction of the side jet pipe (10) and the jet direction of the main jet channel (5) form an angle of 0 to 90 degrees.

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