Ducted piston jet engine

Abstract

The utility model relates to the field of jet engines, in particular to a ducted piston jet engine which comprises a fairing, an air inlet is formed in the front of the fairing, an air jet opening is formed in the rear of the fairing, an engine is arranged in the fairing, and a propeller for controlling air to enter the fairing is arranged in front of the fairing. The front portion of the engine is in transmission connection with the propeller, the rear portion of the engine is in transmission connection with a compressed air axial flow blade device and a tail axial flow cover which are located in the fairing, the tail axial flow cover is arranged behind the compressed air axial flow blade device, and the distance between the middle of the tail axial flow cover and the inner wall of the fairing is smaller than the distance between the two ends of the tail axial flow cover and the inner wall of the fairing in the axis direction of the fairing. The front output shaft and the rear output shaft of the engine are output straight shafts penetrating through the engine. The engine is reasonable in structure, the propeller is driven by the engine to achieve high-speed entering of airflow, the airflow is pressurized through the compressed air axial flow blade device and the tail axial flow cover and sprayed out of the nozzle, efficient rear thrust is obtained, and the energy efficiency is effectively improved.

Description

Technical Field

[0001] The utility model relates to the field of jet engines, in particular to a ducted piston jet engine. Background Art

[0002] The scale of global aircraft use is getting larger and larger, and the requirements for aircraft power technology are naturally progressive. The various types of aircraft engines currently in common use have the same fundamental characteristics, namely, complex processes, high prices, low thermal efficiency, high fuel consumption, and high maintenance costs. Driven by the huge amount of research and development funds invested by various countries, engineers in the industry have been committed to iterating and tapping the potential of existing types of aircraft engines, seeking aircraft engines with greater power, greater reliability, and lower fuel consumption.

[0003] In the process of jet engine development, generating thrust through shaft-rotating air intake, compression, combustion gas and jet has been the mainstream development technology of aviation engines in the past few decades. Aviation power manufacturing companies have invested a lot of manpower and material resources to optimize product principles at a higher level of technology, which is naturally reflected in the high purchase cost, use cost and maintenance cost on the market application end.

[0004] Based on market application considerations, we seek to develop a new type of power that combines the opposed piston engine, propeller and exhaust gas kinetic energy, so that it has an unparalleled low-cost, low-fuel-consumption, and highly reliable aviation power product to adapt to the ever-evolving aviation application market. Utility Model Content

[0005] The technical problem to be solved by the utility model is to overcome the defects of the above-mentioned technology and provide a ducted piston jet engine, which provides an aviation engine with high reliability, high power-to-weight ratio, extremely low fuel consumption, low manufacturing cost and low maintenance cost for aircraft.

[0006] A ducted piston jet engine comprises a fairing, an air inlet is arranged in front of the fairing, and an air jet is arranged in the rear, an engine is arranged in the fairing, a propeller for controlling air entering the fairing is arranged in front of the fairing, the front of the engine is connected to the propeller by transmission, and the rear of the engine is connected to a compressor axial flow blade device and a tail axial flow cover in the fairing by transmission, the tail axial flow cover is arranged behind the compressor axial flow blade device, and the distance between the middle position of the tail axial flow cover and the inner wall of the fairing along the axial direction of the fairing is smaller than the distance between the two end positions and the inner wall of the fairing;

[0007] An air flow channel is provided in the fairing from the air inlet to the jet outlet. When the engine is running, the propeller rotates to blow high-speed air into the fairing through the air inlet. The high-speed air cools down the engine cylinder temperature and mixes with the exhaust gas of the engine. The air passes through the compressor axial flow blade device and the tail axial flow cover and is ejected from the jet outlet to form a rear thrust.

[0008] Furthermore, the front output shaft of the engine extends out of the fairing and is connected to a propeller sleeve for mounting a propeller.

[0009] Furthermore, the fairing is provided at the compressor axial flow blade device position.

[0010] Furthermore, a mounting frame for mounting the engine without affecting air flow is provided in the fairing.

[0011] Furthermore, the engine adopts a piston-type opposed engine structure.

[0012] Furthermore, the front end of the fairing is connected to a guide cover irradiating the outside of the propeller through a rib plate.

[0013] Furthermore, a post-burner is provided in the fairing between the compressor axial flow blade device and the tail axial flow cover.

[0014] Furthermore, the front output shaft and the rear output shaft of the engine are straight output shafts that pass through the engine.

[0015] Advantages of the utility model: The utility model has a reasonable structure, realizes high-speed airflow entry through the engine to the propeller, and then pressurizes the airflow through the compressed air axial flow blade device and the tail axial flow cover to eject the airflow from the nozzle, thereby obtaining efficient rear thrust;

[0016] In addition, a post-burner is arranged between the compressor axial flow blade device and the tail axial flow cover to increase the air flow velocity through deflagration work to increase the jet thrust, so that the engine obtains additional thrust. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of a ducted piston jet engine of the utility model;

[0018] Figure 2 This is a schematic diagram of the internal structure of a ducted piston jet engine of the utility model;

[0019] Figure 3 It is a schematic diagram of a propeller configuration shroud of a ducted piston jet engine of the utility model;

[0020] Figure 4 The utility model is a schematic diagram of the internal air flow of a ducted piston jet engine.

[0021] As shown in the figure: 1. Fairing; 2. Air inlet; 3. Jet nozzle; 4. Engine; 5. Propeller; 6. Compressor axial flow blade device; 7. Tail axial flow cover; 8. Propeller sleeve; 9. Mounting frame; 10. Rib plate; 11. Guide cover; 12. Afterburner. DETAILED DESCRIPTION

[0022] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0023] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present utility model, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0024] In the description of the embodiments of the present utility model, if a feature is referred to as being "set", "fixed", "connected" or "installed" on another feature, it may be directly set, fixed, connected to another feature, or indirectly set, fixed, connected, or installed on another feature.

[0025] In the description of the embodiments of the present utility model, if "several" is involved, it means more than one, if "multiple" is involved, it means more than two, if "greater than", "less than" or "exceed" is involved, it should be understood as not including the number itself, if "above", "below" or "within" is involved, it should be understood as including the number itself. If "first" or "second" is involved, it should be understood as being used to distinguish technical features, and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features or implicitly indicating the order of the indicated technical features.

[0026] The utility model is further described in detail below in conjunction with the accompanying drawings.

[0027] like Figure 1 and 2As shown, a ducted piston jet engine comprises a fairing 1, an air inlet 2 is arranged in front of the fairing 1, and an air jet 3 is arranged in the rear, an engine 4 is arranged in the fairing 1, and a propeller 5 for controlling air entering the fairing 1 is arranged in front of the fairing 1, the front output shaft of the engine 4 is drivingly connected with the propeller 5, and the rear output shaft is drivingly connected with a compressor axial flow blade device 6 and a tail axial flow cover 7 located in the fairing 1, the tail axial flow cover 7 is arranged behind the compressor axial flow blade device 6, and the distance between the middle position of the tail axial flow cover 7 and the inner wall of the fairing 1 along the axis direction of the fairing 1 is smaller than the distance between the two end positions and the inner wall of the fairing 1;

[0028] The output shaft in front of the engine 4 extends out of the fairing 1 and is connected to a propeller sleeve 8 for mounting a propeller 5;

[0029] The fairing 1 is provided with a mounting frame 9 for mounting the engine 4 without affecting the air flow;

[0030] The front end of the fairing 1 is connected to a deflector 11 irradiating the outside of the propeller 5 through a rib plate 10. Figure 3 shown.

[0031] An afterburner 1 is provided between the compressor axial flow blade device 6 and the tail axial flow cover 7 in the fairing 1. The afterburner is an additional thrust obtained by the engine by igniting the fuel flowing through the cavity vortex and increasing the airflow velocity through explosion to increase the jet thrust. It is usually used for the power needs of aircraft take-off or maneuvering.

[0032] The engine 4 adopts a piston-type opposed engine structure.

[0033] The front output shaft and the rear output shaft of the engine 4 are straight output shafts that penetrate the engine.

[0034] The working principle of the utility model is as follows: the piston-type opposed engine is the power source, and the engine has 4 power sources, which are provided with output shafts at the front and rear to provide power for the entire power group. The propeller 5 works as a pulling force and blows high-speed air into the fairing 1. The high-speed air takes away the cylinder temperature of the piston engine and merges with the exhaust gas, and enters the airway through the compressed air axial flow blade device 6 on the rear output shaft. Under the action of the Laval effect, it passes through the tail axial flow cover 7 and is ejected from the jet port 3 of the fairing 1 at a very high rate as the rear thrust power, such as Figure 4 shown.

[0035] The shape and size declared this time can be adjusted according to the use requirements of the aircraft, but the internal structure and principle remain unchanged.

[0036] The above description of the utility model and its implementation methods is not restrictive. The drawings show only one implementation method of the utility model, and the actual structure is not limited thereto. In short, if ordinary technicians in this field are inspired by it and design structural methods and embodiments similar to the technical solution without creativity without departing from the purpose of the invention of the utility model, they should all fall within the protection scope of the utility model.

Claims

1. A ducted piston jet engine, characterized in that: The invention comprises a fairing (1), wherein an air inlet (2) is arranged in front of the fairing (1), and an air jet (3) is arranged in the rear. An engine (4) is arranged in the fairing (1), and a propeller (5) is arranged in front of the fairing (1) to control the air to enter the fairing (1). The front output shaft of the engine (4) is transmission-connected with the propeller (5), and the rear output shaft is transmission-connected with a compressor axial flow blade device (6) and a tail axial flow cover (7) located in the fairing (1). The tail axial flow cover (7) is arranged behind the compressor axial flow blade device (6). Along the axis direction of the fairing (1), the distance between the middle position of the tail axial flow cover (7) and the inner wall of the fairing (1) is smaller than the distance between the two end positions and the inner wall of the fairing (1). An air flow channel is provided in the fairing (1) from the air inlet (2) to the air jet (3). When the engine (4) is working, the propeller (5) rotates to blow high-speed air into the fairing (1) through the air inlet (2). The high-speed air cools down the engine cylinder and mixes with the exhaust gas of the engine (4). The high-speed air passes through the compressor axial flow blade device (6) and the tail axial flow cover (7) and is ejected from the air jet (3) to form a rearward driving force.

2. A ducted piston jet engine according to claim 1, characterized in that: The front output shaft of the engine (4) extends out of the fairing (1) and is connected to a propeller sleeve (8) for mounting a propeller (5).

3. A ducted piston jet engine according to claim 1, characterized in that: A mounting frame (9) for mounting the engine (4) without affecting the air flow is provided in the fairing (1).

4. A ducted piston jet engine according to claim 1, characterized in that: The engine (4) adopts a piston-type opposed engine structure.

5. A ducted piston jet engine according to claim 1, characterized in that: The front end of the fairing (1) is connected to a fairing (11) irradiating the outside of the propeller (5) via a rib plate (10).

6. A ducted piston jet engine according to claim 1, characterized in that: A post-burner (12) is provided in the fairing (1) between the compressor axial flow blade device (6) and the tail axial flow cover (7).

7. A ducted piston jet engine according to claim 1, characterized in that: The front output shaft and the rear output shaft of the engine (4) are straight output shafts that pass through the engine.

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