Supercharged turbofan aviation power device

Abstract

A supercharged turbofan aviation power device comprises a transmission shaft (5), a first-stage driving compression bin (1), at least one second-stage supercharging bin (2) and a third-stage driven compression bin (4) are sequentially arranged on the transmission shaft (5) from front to back, and the first-stage driving compression bin (1), the second-stage supercharging bins (2) and the third-stage driven compression bin (4) are all of a Laval nozzle structure. The device has the advantages that the overall design of the device conforms to the aerodynamics principle, the aerodynamics characteristics and the air multiplication technology are fully utilized, the structural design and the overall structure are ingenious, and the maximum thrust is obtained with the minimum energy consumption. The structure is simple, scientific and stable, and plasticity is strong. A multi-stage pressurizing compression bin can be additionally arranged according to needs, so that the minimum power is used, and larger thrust is generated. The device is easy to produce, machine and install, few in quick-wear parts, low in external repair cost, wide in application and extremely high in development and utilization value.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation aircraft engines, and in particular to a supercharged turbofan aviation power device. Background Art

[0002] At present, the power principle of aviation vehicles is basically to compress air and inject air to generate thrust. The main technologies are fuel-powered and electric-powered. The fuel-powered route mainly includes turbojets, turboprops, turboshafts, explosive vibration ramjet, etc. The characteristics are that solid or liquid fuel is burned to generate gas expansion, and thrust is generated through a special air circulation structure, using high fuel consumption for high thrust. In terms of electric power drive, there are two types: Hall electric propulsion and electric motors, both of which are relatively environmentally friendly. The thrust of the Hall motor is relatively small, and the electric motor drives the propeller to drive the aircraft. The main reason is that the working propeller is exposed to the outside, which is unsafe. In addition, it is difficult to store electricity, and endurance is a problem. Summary of the invention

[0003] The purpose of the present invention is to provide a supercharged turbofan aviation power unit to address the above-mentioned deficiencies.

[0004] The present invention comprises a transmission shaft, on which a first-stage active compression chamber, at least one second-stage boosting chamber and a third-stage driven compression chamber are arranged in sequence from front to back. The first-stage active compression chamber, the second-stage boost chamber and the third-stage passive compression chamber all have Laval nozzle structures. A group of turbofan blades fixed on the transmission shaft are arranged in the first-stage active compression chamber and the third-stage driven compression chamber, and a power motor for driving the transmission shaft to rotate is arranged in the first-stage active compression chamber; A set of free turbofans movably connected to the transmission shaft are provided in the second-stage booster compartment.

[0005] The outer walls of the air outlet ends of the first-stage active compression chamber, the second-stage boost chamber and the third-stage driven compression chamber all have a group of reinforcing ribs in a circular array, and the reinforcing ribs of the first-stage active compression chamber, the second-stage boost chamber and the third-stage driven compression chamber are fixedly connected by a group of strip-shaped special-shaped components, and gaps are provided between the first-stage active compression chamber, a group of second-stage boost chambers and the third-stage driven compression chamber.

[0006] The free turbofan is mounted on the drive shaft via tapered roller bearings.

[0007] A bearing support frame is provided on the front air inlet of the second-stage boost chamber and the third-stage driven compression chamber, and the bearing support frame is movably connected to the transmission shaft through a bearing.

[0008] An air intake hood is provided on the front air intake of the first-stage active compression chamber. One axial end bearing of the power motor is fixedly sleeved on the air intake hood, and the other end is sleeved on the transmission shaft. The body of the power motor is fixed on the chamber wall of the first-stage active compression chamber through a group of connecting components.

[0009] Air rectification structural parts are arranged on the air outlets in the first-stage active compression chamber, the second-stage boosting chamber and the third-stage passive compression chamber.

[0010] The advantages of the present invention are: the overall design of the device conforms to the principle of aerodynamics, makes full use of aerodynamic characteristics and air multiplication technology, and has ingenious structural design and overall architecture, so as to obtain the maximum thrust with the minimum energy consumption. The structure is simple, scientific and stable, and has strong plasticity. Multi-stage booster compression chambers can be added as needed, so as to achieve the goal of using the minimum power and generating greater thrust. The device is simple to produce, process and install, has few wearing parts, low external repair cost, wide application, and extremely high development and utilization value. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 It is a schematic diagram of the structure of the present invention.

[0012] Figure 2 It is a schematic diagram of the internal structure of the present invention.

[0013] Figure 3 This is a schematic diagram of the internal installation structure of the first-stage active compression chamber.

[0014] Figure 4 It is a schematic diagram of the installation structure of air rectification structural parts. Implementation

[0015] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0016] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely represents selected embodiments of the present invention. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments of the present invention without creative work are within the scope of protection of the present invention. It should be noted that similar reference numerals and letters represent similar items in the following drawings, so once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings.

[0017] In the description of the embodiments of the present invention, it should be noted that if the terms "upper", "lower", "inner", "outer", etc. appear, the orientation or position relationship indicated is based on the orientation or position relationship shown in the drawings, or the orientation or position relationship in which the product of the invention is usually placed when in use. This is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, if the terms "first", "second", etc. appear in the description of the present invention, they are only used to distinguish the description and cannot be understood as indicating or implying relative importance.

[0018] In the description of the embodiments of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "setting" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0019] As shown in the accompanying drawings, the present invention comprises a transmission shaft 5, on which a first-stage active compression chamber 1, at least one second-stage boosting chamber 2 and a third-stage driven compression chamber 4 are arranged in sequence from front to back. The first-stage active compression chamber 1, the second-stage boost chamber 2 and the third-stage passive compression chamber 4 all have a Laval nozzle structure, that is, the chamber body is in the shape of a cylindrical funnel, with a large air inlet, a smaller air outlet, and a trumpet-shaped tail of the air outlet.

[0020] The air rectification structure 21 is located on the compression portion of the air outlet.

[0021] A group of turbofan blades 7 fixed on the transmission shaft 5 are provided in the first-stage active compression chamber 1 and the third-stage driven compression chamber 4, and a power motor 17 for driving the transmission shaft 5 to rotate is provided in the first-stage active compression chamber 1; A group of free turbofans 6 movably connected to the transmission shaft 5 are arranged in the secondary booster compartment 2 .

[0022] The outer walls of the air outlet ends of the first-stage active compression chamber 1, the second-stage boost chamber 2 and the third-stage driven compression chamber 4 are all provided with a group of reinforcing ribs in a circular array, and the reinforcing ribs of the first-stage active compression chamber 1, the second-stage boost chamber 2 and the third-stage driven compression chamber 4 are fixedly connected by a group of strip-shaped special-shaped components 11, and gaps are provided between the first-stage active compression chamber 1, a group of second-stage boost chambers 2 and the third-stage driven compression chamber 4.

[0023] The first-stage active compression chamber 1, the second-stage boost chamber 2 and the third-stage passive compression chamber 4 are coaxially arranged in series to form a multi-stage air boosting aviation power device. The jet port of the first-stage compression chamber is located on the air inlet of the second-stage compression chamber, and a certain gap is maintained, and the gap serves as a free air inlet.

[0024] The free turbofan 6 is mounted on the transmission shaft 5 via a tapered roller bearing.

[0025] A bearing support frame 22 is provided on the front air inlet of the second-stage boost chamber 2 and the third-stage driven compression chamber 4, and the bearing support frame 22 is movably connected to the transmission shaft 5 through a bearing.

[0026] An air intake hood 23 is provided on the front air intake of the first-stage active compression chamber 1. One axial end bearing of the power motor 17 is fixedly sleeved on the air intake hood 23, and the other end is sleeved on the transmission shaft 5. The body of the power motor 17 is fixed to the chamber wall of the first-stage active compression chamber 1 through a group of connecting components.

[0027] That is, the stator of the power motor 17 is fixedly connected to the wall of the first-stage active compression chamber 1 , and the rotor of the power motor 17 is fixedly connected to the transmission shaft 5 .

[0028] Working mode: The power motor 17 rotates in the first-stage active compression chamber 1, driving the transmission shaft 5 to rotate, and at the same time, the turbofan blades 7 in the first-stage active compression chamber 1 and the third-stage driven compression chamber 4 rotate synchronously. The first-stage active compression chamber 1 sucks air into the compression chamber and undergoes multi-stage compression, and ejects air from the Laval nozzle-shaped narrow mouth. The trumpet-shaped nozzle quickly increases the air flow rate of the nozzle, thereby increasing the air flow field. At this time, the nozzle is aligned with the air inlet of the second-stage boost chamber 2, and a gap is maintained with the air inlet, generating an air low-pressure area around it. According to the Coanda effect, after completely accepting the air ejected from the first-stage active compression chamber 1, the air in the low-pressure area outside the air inlet is forcefully sucked into the second-stage boost chamber 2, and the free turbofan 6 in the second-stage boost chamber 2 is blown to rotate at a high speed for secondary compression, thereby improving the air jet in the device. Similarly, the secondary boost chamber 2 further pressurizes the tertiary driven compression chamber 4, and blows a group of turbofan blades 7 in the tertiary driven compression chamber 4 to rotate at a higher speed, and reversely pushes the acceleration force through the transmission shaft 5 to drive a group of turbofan blades 7 in the primary active compression chamber 1 to rotate, and ejects the pressurized incremental air flow through the Laval nozzle at high speed, achieving strong thrust with lower energy consumption.

[0029] The number of secondary boost chambers 2 in the middle section is set according to the thrust requirements of the entire power unit.

Claims

1. A supercharged turbofan aviation power unit, Features The transmission shaft (5) comprises a first-stage active compression chamber (1), at least one second-stage boost chamber (2) and a third-stage driven compression chamber (4) which are arranged on the transmission shaft (5) in sequence from front to back. The first-stage active compression chamber (1), the second-stage boost chamber (2) and the third-stage passive compression chamber (4) all have a Laval nozzle structure. A group of turbofan blades (7) fixed on the transmission shaft (5) are provided in both the first-stage active compression chamber (1) and the third-stage driven compression chamber (4), and a power motor (17) for driving the transmission shaft (5) to rotate is provided in the first-stage active compression chamber (1); A group of free turbofans (6) movably connected to the transmission shaft (5) are provided in the secondary boost chamber (2).

2. A supercharged turbofan aviation power plant according to claim 1, Features The outer walls of the air outlet ends of the first-stage active compression chamber (1), the second-stage boost chamber (2) and the third-stage driven compression chamber (4) are all provided with a group of reinforcing ribs in a circular array; the reinforcing ribs of the first-stage active compression chamber (1), the second-stage boost chamber (2) and the third-stage driven compression chamber (4) are fixedly connected by a group of strip-shaped special-shaped components (11); and gaps are provided between the first-stage active compression chamber (1), the group of second-stage boost chambers (2) and the third-stage driven compression chamber (4).

3. A supercharged turbofan aviation power plant according to claim 1, Features The free turbofan (6) is mounted on the transmission shaft (5) via a tapered roller bearing.

4. A supercharged turbofan aviation power plant according to claim 1, Features A bearing support frame (22) is provided on the front air inlet of the second-stage boost chamber (2) and the third-stage driven compression chamber (4), and the bearing support frame (22) is movably connected to the transmission shaft (5) via a bearing.

5. A supercharged turbofan aviation power plant according to claim 1, Features An air intake cover (23) is provided on the front air intake of the first-stage active compression chamber (1); one axial end bearing of the power motor (17) is fixedly sleeved on the air intake cover (23), and the other end is sleeved on the transmission shaft (5); the body of the power motor (17) is fixed to the chamber wall of the first-stage active compression chamber (1) via a group of connecting components.

6. A supercharged turbofan aviation power plant according to claim 1, Features Air rectification structural components (21) are provided on the air outlets in the first-stage active compression chamber (1), the second-stage boost chamber (2) and the third-stage passive compression chamber (4).

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