CN217598824U

CN217598824U - Vortex generator

Info

Publication number: CN217598824U
Application number: CN202221089571.3U
Authority: CN
Inventors: 李艳; 蔡锦阳; 郑隆乾; 李东坡; 褚容宇; 张润东
Original assignee: Comac Shanghai Aircraft Design & Research Institute; Commercial Aircraft Corp of China Ltd
Current assignee: Comac Shanghai Aircraft Design & Research Institute; Commercial Aircraft Corp of China Ltd
Priority date: 2022-04-27
Filing date: 2022-04-27
Publication date: 2022-10-18
Anticipated expiration: 2032-04-27

Abstract

The utility model relates to a vortex generator, this vortex generator include first section, second section and mid-section, and the mid-section is located between first section and the second section to the maximum height of mid-section is less than first section with the maximum height of second section.

Description

Vortex generator

Technical Field

The utility model relates to an aircraft design field, concretely relates to vortex generator on aircraft.

Background

The aerodynamic characteristics of the airplane are very important for the safety, economy, comfort and environmental protection of civil airplanes, and the vortex generators can improve the aerodynamic characteristics of the airplane, so that the design of the vortex generators of the airplane plays an important role in the design of the airplane.

Under the condition of a large attack angle of an airplane, the phenomenon of airflow separation can occur on wings, and the phenomenon of airflow separation can generally cause a large amount of turbulence, so that a large amount of lift force is lost, and dangers are caused. FIG. 1A illustrates a polar flow restriction map of the effect of a conventional vortex generator on airfoil flow control.

To reduce this separation, vortex generators are typically mounted on the nacelle of a lower uniwing, engine winged aircraft to reduce the separation of the flow over the upper surface of the aircraft wing at high angles of attack. Meanwhile, a vortex generator can be arranged on the wing flap of the airplane to control the airflow separation on the wing flap.

SUMMERY OF THE UTILITY MODEL

In order to distinguish traditional vortex generator, increase vortex generator's the controllability to air flow separation, the utility model provides a novel vortex generator under the complicated prerequisite of mechanism not increasing, fully excavate vortex generator's ability, the increase is to the controllability of separation air current.

In particular, the vortex generator comprises a first section, a second section and an intermediate section, the intermediate section being located between the first section and the second section and having a maximum height that is smaller than a maximum height of the first section and a maximum height of the second section.

Preferably, the first segment and/or the second segment is an arc-shaped segment.

In an embodiment of the invention, the intermediate section is a linear section.

In an embodiment of the invention, the length of the intermediate section is between 0% and 20% of the total length of the vortex generator.

Preferably, the ratio of the maximum height of the second section to the maximum height of the first section is between 1 and 1.5.

Preferably, the ratio of the maximum height of the first section to the maximum height of the intermediate section is between 1.5 and 3.

Additional features and advantages of the described vortex generators will be set forth in the detailed description which follows, and in part will be readily apparent to those skilled in the art from that description or recognized by practicing the embodiments described herein, including the detailed description which follows and the accompanying drawings.

Drawings

With reference to the above purposes, the technical features of the invention are clearly described in the claims below, and its advantages are apparent from the following detailed description with reference to the accompanying drawings, which illustrate by way of example a preferred embodiment of the invention, without limiting the scope of the inventive concept.

FIG. 1A illustrates a polar flow plot of the effect of a conventional vortex generator on airfoil flow control;

FIG. 1B illustrates a polar restriction map of the effect of a vortex generator on airfoil flow control in accordance with an embodiment of the present invention; and

fig. 2 shows a plan view of a vortex generator according to an embodiment of the invention.

Reference numerals

1 vortex generator

10 first section

20 second section

30 middle section

Detailed Description

The preferred embodiments of the present invention will be described in detail below with reference to the accompanying drawings so that the objects, features and advantages of the invention can be more clearly understood.

The terms "length" and "height" as used herein are defined with reference to the position of the vortex generator in the drawings, in particular, "length" refers to the length in the horizontal direction in the drawings, and "height" refers to the length in the vertical direction in the drawings; further "maximum height" refers to the maximum of height in a section.

Fig. 1B shows a vortex generator 1 and its polar restriction map of the effect of the vortex generator on airfoil flow control according to an embodiment of the invention. Compared with the existing vortex generators, the vortex generator of the utility model can improve the original design basis to the minimum. Through the emulation calculation, the result shows, the utility model discloses a vortex generator compares with traditional vortex generator, has stronger vortex emergence ability, can obviously reduce the size of the flow separation district on the airfoil, weakens the air current separation on the wing, can produce favorable effect to the aerodynamic characteristic of aircraft.

In particular, fig. 2 shows a plan profile view of a vortex generator 1 according to an embodiment of the invention. For simplicity, the vortex generator 1 is shown in plan view, in practice the vortex generator 1 has a certain thickness. The side of the vortex generator 1 intended for mounting is shown as horizontal, but in practice the side of the vortex generator 1 intended for mounting may be conformed to the contour of the mounted component, depending on the location of mounting.

The vortex generator 1 comprises a first section 10, a second section 20. In the preferred embodiment, the first section 10 and/or the second section 20 are sections having an arcuate shape, which makes it easier for the air flow to pass along the vortex generator 1, but can be any other shape that is advantageous for controlling the air flow. Further, to facilitate directing the airflow, the maximum height H1 of the first section 10 is less than the maximum height H2 of the second section 20 (labeled H1 and H2 in fig. 2). In the preferred embodiment, the ratio of the maximum height of the second section H2 to the maximum height H1 of the first section is between 1 and 1.5, although in other embodiments the ratio of the maximum height of the second section H2 to the maximum height H1 of the first section is not limited thereto.

The vortex generator 1 further comprises an intermediate section 30, which intermediate section 30 is located between the first section 10 and the second section 20. The length of the intermediate section 30 is between 0% and 20% of the total length of the vortex generator 1, but longer intermediate sections 30 are conceivable.

In the present embodiment, the intermediate section 30 is a straight section, but this is merely an example and not a limitation. In other embodiments, the intermediate section 30 may, for example, have a curvilinear profile.

Preferably, the maximum height H3 of the intermediate section 30 is smaller than the maximum height H1 of the first section 10 and the maximum height H2 of the second section 20. In the present embodiment, the ratio of the maximum height H1 of the first section 10 to the maximum height H3 of the intermediate section 30 is between 1.5 and 3, although in other embodiments, the ratio of the maximum height of the second section H2 to the maximum height H1 of the first section is not limited thereto.

Compared with the prior vortex generator, the utility model discloses can improve original design basis on the minimum, and then reinforcing air flow separation control can produce favorable effect to the aerodynamic characteristic of aircraft.

While the structure and method of installation of the present invention has been described above in connection with preferred embodiments, it will be understood by those of ordinary skill in the art that the above examples are intended to be illustrative only and are not intended to be limiting. Thus, modifications and variations may be made to the present invention which fall within the scope of the appended claims.

Claims

1. A vortex generator comprising a first section, a second section and an intermediate section, the intermediate section being located between the first section and the second section and having a maximum height less than the maximum height of the first section and the second section.

2. The vortex generator of claim 1,

the first segment and/or the second segment is an arcuate segment.

3. The vortex generator of claim 2,

the intermediate section is a linear section.

4. The vortex generator of claim 1,

the length of the intermediate section is between 0% and 20% of the total length of the vortex generator.

5. The vortex generator of claim 1,

the ratio of the maximum height of the second section to the maximum height of the first section is between 1 and 1.5.

6. The vortex generator of claim 5,

the ratio of the maximum height of the first section to the maximum height of the intermediate section is between 1.5 and 3.