CN219366387U

CN219366387U - Fan structure, ducted fan and aircraft

Info

Publication number: CN219366387U
Application number: CN202221672913.4U
Authority: CN
Inventors: 胡华智
Original assignee: Ehang Intelligent Equipment Guangzhou Co Ltd
Current assignee: Ehang Intelligent Equipment Guangzhou Co Ltd
Priority date: 2022-06-30
Filing date: 2022-06-30
Publication date: 2023-07-18
Anticipated expiration: 2032-06-30

Abstract

The embodiment of the application discloses fan structure is applied to the duct fan, includes: the blade assembly and the outer annular wall arranged on the periphery of the blade assembly, and a plurality of turbine blades are circumferentially distributed on the outer side of the outer annular wall. The application also discloses a corresponding ducted fan and an aircraft. The propulsion efficiency can be greatly improved, the size is reduced, the speed regulation characteristic is improved, the propulsion force can be generated, and the effect of directly generating the attitude control force can be achieved as long as the thrust speed of each ducted fan is independently controlled for the aircrafts driven by a plurality of ducted fans.

Description

Fan structure, ducted fan and aircraft

Technical Field

Embodiments of the present application relate to aircraft technology, and in particular, to a fan structure, a ducted fan, and an aircraft.

Background

The ducted fan is a propeller which is provided with a duct on the periphery of a fan-type propeller to generate propulsion, and is also called a ducted propeller. Compared with the traditional propeller, the ducted propeller has the advantages of small eddy current loss, compact structure and low noise, and has obvious advantages in the application of the small vertical take-off and landing unmanned aerial vehicle.

Ducted fans of the prior art are commonly used in turbine engines to generate propulsion by driving blades in a central axial direction. The ducted fan with the structure has the advantages of larger stress born by the slurry root, larger flow resistance, more disturbance loss in flow, low propulsion efficiency, large size, low speed regulation property, thrust generation only, and incapability of directly generating attitude control force.

Disclosure of Invention

The embodiment of the application provides a fan structure, a ducted fan and an aircraft, so as to increase the propulsion efficiency of the ducted fan, reduce the size and directly generate attitude control force.

In a first aspect, an embodiment of the present application discloses a fan structure, applied to a ducted fan, including:

the blade assembly and the outer annular wall arranged on the periphery of the blade assembly, and a plurality of turbine blades are circumferentially distributed on the outer annular wall.

In some possible embodiments, the turbine blades are arranged as semi-annular shrouds opening tangentially to the outer annular wall.

In some possible embodiments, the top of the semi-annular shroud is configured as a hollow quarter sphere.

In some possible embodiments, the blade assembly further comprises an inner annular wall arranged on the inner periphery of the blade assembly, and the blade assembly comprises a plurality of blades uniformly and radially spirally extending from the outer side of the inner annular wall to the inner side of the outer annular wall.

In some possible embodiments, the inner ends of the blades are longitudinally and obliquely distributed on the inner annular wall, and the outer ends of the blades are transversely and obliquely distributed on the outer annular wall, so that a structure with the axial thickness of the inner annular wall being larger than that of the outer annular wall is formed.

In some possible embodiments, the plurality of paddles are densely arranged and a gap is formed between adjacent paddles.

In some possible embodiments, the slit is S-shaped.

In some possible embodiments, each blade corresponds to at least two turbine blades.

In a second aspect, embodiments of the present application disclose a ducted fan including a fan structure as described above.

In a third aspect, embodiments of the present application disclose an aircraft comprising an airframe and a ducted propeller disposed outside the airframe, the ducted propeller comprising at least two ducted fans as described above.

In some possible embodiments, the body adopts a missile type shell structure.

The beneficial effects of this application are:

according to the embodiment of the application, the outer annular wall is arranged on the periphery of the blade assembly, the air jet holes are formed in the outer annular wall, the blade assembly is driven to rotate by utilizing the radial driving force generated by air flow passing through the air jet holes from the outside to the blade, the air is pushed to form thrust, and lift force is generated for an aircraft.

Drawings

In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, a brief description will be given below of the drawings required for the embodiments or the description of the prior art, and it is obvious that the drawings in the following description are some embodiments of the present application, and that other drawings may be obtained according to these drawings without the need for inventive effort for a person skilled in the art.

Fig. 1 is a schematic perspective view of a fan structure according to an embodiment of the present application.

Fig. 2 is a schematic plan view of a fan structure according to an embodiment of the present application.

Fig. 3 is another schematic plan view of a ducted fan according to an embodiment of the present application.

Fig. 4 is a schematic structural diagram of a ducted fan according to an embodiment of the present application.

Fig. 5 is a schematic structural view of an aircraft according to an embodiment of the present application.

Reference numerals illustrate:

100-organism; 200-ducted fans; 300-fan configuration;

1-blade assembly, 2-outer annular wall, 3-turbine blade, 4-inner annular wall, 10-blade, 11-gap.

Detailed Description

In order to make the objects, technical solutions and advantages of the present application more apparent, the technical solutions of the present application will be described in detail by way of embodiments with reference to the accompanying drawings in the examples of the present application. Obviously, embodiments and features of embodiments in this application may be combined with each other without conflict.

It should be noted that: in the drawings, like or similar reference numerals refer to like or similar elements throughout or elements having like or similar functions; in the description of the present application, the terms "center," "longitudinal," "transverse," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate or are based on the orientation or positional relationship shown in the drawings, merely to facilitate description of the present application and simplify description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be configured and operated in a particular orientation, and therefore should not be construed as limiting the scope of protection of the present application; in the description of the present application, "first", "second", etc. are used merely for distinguishing one from another, and do not denote their importance or order or the like.

In the description of the present application, unless explicitly stated and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, movably connected, or detachably connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, can be communicated with the inside of two elements, and the like. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art in a specific context.

Referring to fig. 1-5, a fan structure 300 disclosed in an embodiment of the present application is applied to a ducted fan 200, and includes:

the blade assembly 1 and the outer annular wall 2 arranged on the periphery of the blade assembly 1, and a plurality of turbine blades 3 are circumferentially distributed on the outer side of the outer annular wall 2.

In some possible embodiments, the turbine blade 3 is arranged as a semi-annular shroud opening tangentially along the outer side wall 2.

In some possible embodiments, the top of the semi-annular cover 3 is provided as a hollow quarter sphere.

In some possible embodiments, the blade assembly 1 further comprises an inner annular wall 4 arranged on the inner periphery of the blade assembly 1, and the blade assembly 1 comprises a plurality of blades 10 which uniformly and radially spirally extend from the outer side of the inner annular wall 4 to the inner side of the outer annular wall 2.

In some possible embodiments, the inner ends of the blades 10 are longitudinally and obliquely distributed on the inner annular wall 4, and the outer ends of the blades are transversely and obliquely distributed on the outer annular wall 2, so that a structure that the axial thickness of the inner annular wall 4 is larger than that of the outer annular wall 2 is formed.

In some possible embodiments, the plurality of paddles 10 are densely arranged and a gap 11 is formed between adjacent paddles.

In some possible embodiments, the slit 11 is S-shaped.

In some possible embodiments, each blade 10 corresponds to at least two turbine blades 3.

Referring to fig. 4, the ducted fan 200 disclosed in the embodiment of the present application includes the fan structure 300 as described in the previous embodiment.

Referring to fig. 5, an embodiment of the present application discloses an aircraft, which includes an engine body 100 and a ducted propeller disposed outside the engine body 100, wherein the ducted propeller includes at least two ducted fans 200 according to the previous embodiment.

In some possible embodiments, the body 100 employs a missile type housing structure.

Note that the above is only a preferred embodiment of the present application and the technical principle applied. Those skilled in the art will appreciate that the present application is not limited to the particular embodiments described herein, but is capable of numerous obvious changes, rearrangements and substitutions as will now become apparent to those skilled in the art without departing from the scope of the present application. Therefore, while the present application has been described in connection with the above embodiments, the present application is not limited to the above embodiments, but may include many other equivalent embodiments without departing from the spirit of the present application, the scope of which is defined by the scope of the appended claims.

Claims

1. A fan structure, applied to a ducted fan, comprising:

the blade assembly and the outer annular wall arranged on the periphery of the blade assembly, and a plurality of turbine blades are circumferentially distributed on the outer side of the outer annular wall.

2. The fan structure of claim 1, wherein: the turbine blades are arranged as semi-annular shrouds opening tangentially to the outer annular wall.

3. The fan structure of claim 2, wherein: the top of the semi-annular cover body is arranged to be hollow and quarter spherical.

4. A fan structure as claimed in any one of claims 1 to 3, wherein:

the inner annular wall is arranged on the inner periphery of the blade assembly, and the blade assembly comprises a plurality of blades which uniformly and radially spirally extend to the inner side of the outer annular wall from the outer side of the inner annular wall.

5. The fan structure of claim 4, wherein:

the inner ends of the blades are longitudinally and obliquely distributed on the inner annular wall, and the outer ends of the blades are transversely and obliquely distributed on the outer annular wall, so that a structure with the axial thickness of the inner annular wall being greater than that of the outer annular wall is formed.

6. The fan structure of claim 5, wherein: the paddles are densely arranged, and gaps are formed between the adjacent paddles.

7. The fan structure of claim 4, wherein: each blade corresponds to at least two turbine blades.

8. The fan structure of claim 6, wherein: the gap is S-shaped.

9. A ducted fan, characterized in that: a fan construction comprising a fan structure according to any of claims 1-8.

10. An aircraft, includes organism and locates the duct propeller in the organism outside, its characterized in that: the ducted propeller comprising at least two ducted fans as claimed in claim 9.

11. The aircraft of claim 10, wherein: the machine body adopts a missile type shell structure.