CN215622650U - High-lift noise reduction wing type structure - Google Patents

High-lift noise reduction wing type structure Download PDF

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Publication number
CN215622650U
CN215622650U CN202120745423.1U CN202120745423U CN215622650U CN 215622650 U CN215622650 U CN 215622650U CN 202120745423 U CN202120745423 U CN 202120745423U CN 215622650 U CN215622650 U CN 215622650U
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porous medium
flap
block
main body
concave
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朱卫军
刘嘉颖
顾超杰
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Yangzhou University
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Yangzhou University
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Abstract

The utility model discloses a high-lift noise-reduction wing section structure which comprises a leading edge slat (1), a middle main body section (2) and a trailing edge flap (3), wherein a first porous medium block (11) is arranged at a concave bend on the lower surface of the leading edge slat (1), a second porous medium block (21) is arranged at a concave bend on the upper surface of the middle main body section (2), and the tail part of the trailing edge flap (3) is connected with a gurney flap (4). According to the high-lift noise reduction wing-shaped structure provided by the utility model, the concave bends are filled with the porous medium, so that the cavity oscillation generated at the concave bay of the front and middle sections can be basically eliminated, and the tone noise can be basically eliminated under the condition of improving the integral lift-drag ratio.

Description

High-lift noise reduction wing type structure
Technical Field
The utility model relates to a high-lift noise reduction wing type structure, and belongs to the technical field of wing type of airplane.
Background
For machines which utilize a pressure difference principle to generate a lift-to-drag ratio for working, such as airplane wings, wind turbines and the like, a lift device of the machines often becomes a main noise source while continuously pursuing high lift and high lift-to-drag ratio. When the machinery is close to a residential area and reaches a certain noise level, the normal production and life of residents in nearby communities are influenced to a certain extent. Taking an airplane as an example, in the process of taking off and landing, in order to ensure smooth taking off and stable landing in a fixed-length runway, a device with higher lift force is often required to provide support. However, higher noise levels are also correspondingly produced in this process.
The three-section airfoil profile is composed of a leading edge slat, a middle main body section and a trailing edge flap. According to the schematic diagram of the MDA 30P30N flow field, it can be clearly observed that strong turbulence exists at the concave curve of the similar cavity at the rear part of the leading edge slat and the concave curve of the lower surface at the tail part of the terminal, the eddy intensity in the region is high, and under the condition of strong flow, a strong eddy structure appears in the cavity, cavity oscillation is easily generated, and the instability of the structure and the generation of strong tone noise are caused. In addition, unsteady flow between different airfoil sections and trailing edge vortex shedding of the front airfoil section will cause mid and low frequency noise to rise. Research shows that under the condition of a small attack angle, the leading edge slat is a main noise source; as the attack angle is increased, the sound pressure level of the noise generated by the middle main body section and the trailing edge flap is increased, and the noise levels of the three parts are equivalent.
SUMMERY OF THE UTILITY MODEL
The utility model aims to overcome the defects of the prior art and provide a high-lift noise reduction wing-shaped structure which can basically eliminate tone noise under the condition of meeting the requirement of improving the integral lift-drag ratio.
In order to solve the technical problems, the technical scheme adopted by the utility model is as follows:
the utility model provides a wing section structure of making an uproar falls in high lift, includes leading edge slat, well main part section and trailing edge flap, the concave curve department of leading edge slat lower surface has arranged first porous medium piece, the concave curve department of well main part section upper surface has arranged the second porous medium piece, trailing edge flap afterbody even has the gurney flap.
A sliding rail and a telescopic device are arranged in the concave bend of the upper surface of the middle main body section, a sliding block is arranged on the sliding rail, the second porous medium block is arranged on the sliding block, and the telescopic device is connected with the sliding block.
And the upper surface of the middle main body section is hinged with a panel structure close to the second porous medium block, and the panel structure is used for sealing the concave curve of the lower surface of the leading edge slat.
The trailing edge flap and the gurney flap are in hinged and twistable connection.
The first porous medium block is in a semi-filling type in the concave bend of the lower surface of the leading-edge slat.
The first porous medium block and the second porous medium block are made of aluminum fibers, ceramic foam or nylon.
The utility model has the beneficial effects that: according to the high-lift noise reduction wing section structure provided by the utility model, the first porous medium block is arranged at the concave bend of the lower surface of the leading edge slat, the second porous medium block is arranged at the concave bend of the upper surface of the middle main body section, and the porous medium is used for filling the concave bend, so that the cavity oscillation generated at the concave bend of the front and middle sections can be basically eliminated, and the generation of tone noise is avoided. The porous medium is a sound absorption material, can absorb a part of sound energy, changes the fluid flow condition near the porous area to a certain extent, and reduces the turbulence and the eddy current intensity at the sharp geometric shape of the original airfoil shape, thereby inhibiting the near-field broadband noise. Meanwhile, filling is carried out on the concave bends, so that the sound pressure level of far-field noise can be reduced to a certain extent. In addition, the addition of the gurney flap at the trailing edge flap can further enhance the overall lift-drag ratio of the airfoil. The middle section porous medium module is of a telescopic structure, extends out at a higher attack angle, and retracts at a lower attack angle to obtain a higher lift-drag ratio. The tail gurney flap is also used by being unscrewed when high lift is required and retracted when not required.
Drawings
FIG. 1 is a schematic diagram of an overall structure of a high lift noise reduction airfoil configuration of the present invention;
FIG. 2 is a schematic representation of the multi-hole filling of a leading-edge slat according to the present invention;
FIG. 3 is a schematic view of the movable porous dielectric block of the present invention (a is the second porous dielectric block extending out, b is the second porous dielectric block retracting);
FIG. 4 is a schematic view of a twist-able gurney flap of the trailing edge flap of the present invention (a is the gurney flap being rotated out and b is the gurney flap being rotated back).
The reference numbers in the figures are as follows: 1-leading-edge slats; 2-a middle body section; 3-a trailing edge flap; 4-gurney flaps; 5-a slide rail; 6-panel construction; 11-a first porous dielectric block; 21-a second porous media block.
Detailed Description
The present invention is further described with reference to the accompanying drawings, and the following examples are only for clearly illustrating the technical solutions of the present invention, and should not be taken as limiting the scope of the present invention.
As shown in FIG. 1, the utility model discloses a high-lift noise reduction wing section structure, which comprises a leading-edge slat 1, a middle main body section 2 and a trailing-edge flap 3, wherein the part is a high-lift wing section structure in the prior art. According to the utility model, a first porous medium block 11 is arranged at the concave bend of the lower surface of the leading edge slat 1, and a second porous medium block 21 is arranged at the concave bend of the upper surface of the middle main body section 2. The roles of the first porous dielectric block 11 and the second porous dielectric block 21 are embodied in two aspects. Firstly, the geometrical shape of the wing section at the concave bend is in a non-streamline transition, the turbulence and the vortex intensity at the concave bend are increased, and under the conditions of larger attack angle and larger Reynolds, cavity oscillation is easy to generate, and the porous medium can relieve the non-steady flow in the region. On the other hand, the concave-curved filling can reduce far-field noise, and the porous medium can play a sound absorption role and inhibit near-field pressure fluctuation to a certain extent so as to reduce broadband noise.
A sliding rail 5 and a telescopic device are arranged in the concave curve of the upper surface of the middle main body section 2, a sliding block is arranged on the sliding rail 5, the second porous medium block 21 is arranged on the sliding block, and the telescopic device is connected with the sliding block. The porous medium module can be adjusted in a telescopic way. Under a larger attack angle, when the noise level of the middle section is higher than the whole noise level of the airfoil shape, the porous module is extended out to absorb part of sound energy and restrain the turbulence and vortex intensity at the position, so that noise reduction is realized; at lower angles of attack, the module retracts inside the airfoil to obtain a higher lift-to-drag ratio. The upper surface of the middle main body section 2 is hinged with a panel structure 6 close to the second porous medium block 21, the panel structure 6 is used for sealing the concave curve of the lower surface of the leading edge slat 1, and the panel structure is mainly used for being retracted along with the porous module when the porous module is retracted and enabling the middle section airfoil to be in a closed state integrally.
The first porous medium block 11 is in a semi-filling type in the concave curve of the lower surface of the leading edge slat 1. The concave-curved half-filling type has better pneumatic performance than the full-filling type, but the noise reduction capability is slightly insufficient; for the porous medium module at the lower part of the tail edge of the middle section, the filling shape of the porous medium module also has plasticity, generally speaking, the turbulent flow formation can be better inhibited by keeping a smooth streamline design, and the noise sound pressure level is reduced.
The first porous medium block 11 and the second porous medium block 21 are made of metal type and nonmetal type, including aluminum fiber, ceramic foam or nylon. Firstly, the material is a sound absorption material and has certain permeability, when airflow flows through the area, partial energy of fluid is converted into heat energy in friction and collision for dissipation, and acoustic energy generates loss; meanwhile, the porous medium can change the condition of the original flow field, the development of turbulence and vortex can be restrained to a certain extent, and the broadband noise reduction of the blade can be effectively realized.
As shown in FIG. 4, the tail part of the trailing edge flap 3 is connected with a gurney flap 4, and the gurney flap 4 mainly functions to further improve the overall lift of the airfoil profile and reduce the resistance. The trailing edge flap 3 and the gurney flap 4 are in hinged and twistable connection, so that the gurney flap can be flexibly twisted at the rear part of the trailing edge flap. Under conditions of high lift demand (such as during take-off and landing of the aircraft), the gurney flap can be extended to achieve a higher lift-to-drag ratio. Typically, the gurney flap is twisted to merge with the trailing edge flap main section into a unitary body with a smooth structure in order to avoid its sharp and non-smooth transition geometry leading to unnecessary turbulence and vortex structures.
The above description is only of the preferred embodiments of the present invention, and it should be noted that: it will be apparent to those skilled in the art that various modifications and adaptations can be made without departing from the principles of the utility model and these are intended to be within the scope of the utility model.

Claims (6)

1. A high-lift noise reduction airfoil structure is characterized in that: the novel multi-hole medium-block-type wing slat is characterized by comprising a leading edge slat (1), a middle main body section (2) and a trailing edge flap (3), wherein a first porous medium block (11) is arranged at a concave bend on the lower surface of the leading edge slat (1), a second porous medium block (21) is arranged at a concave bend on the upper surface of the middle main body section (2), and the tail of the trailing edge flap (3) is connected with a gurney flap (4).
2. A high lift noise reducing airfoil configuration as defined in claim 1 wherein: the middle main body section (2) is characterized in that a sliding rail (5) and a telescopic device are arranged in the concave curve of the upper surface of the middle main body section, a sliding block is arranged on the sliding rail (5), the second porous medium block (21) is arranged on the sliding block, and the telescopic device is connected with the sliding block.
3. A high lift noise reducing airfoil configuration as defined in claim 2 wherein: and the upper surface of the middle main body section (2) is hinged with a panel structure (6) close to the second porous medium block (21), and the panel structure (6) is used for sealing the concave curve of the lower surface of the leading edge slat (1).
4. A high lift noise reducing airfoil configuration as defined in claim 1 wherein: the trailing edge flap (3) and the gurney flap (4) are connected in a hinged and twistable manner.
5. A high lift noise reducing airfoil configuration as defined in claim 1 wherein: the first porous medium block (11) is in a semi-filling type in the concave curve of the lower surface of the leading-edge slat (1).
6. A high lift noise reducing airfoil configuration as defined in claim 1 wherein: the first porous medium block (11) and the second porous medium block (21) are made of aluminum fibers, ceramic foam or nylon.
CN202120745423.1U 2021-04-13 2021-04-13 High-lift noise reduction wing type structure Active CN215622650U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202120745423.1U CN215622650U (en) 2021-04-13 2021-04-13 High-lift noise reduction wing type structure

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202120745423.1U CN215622650U (en) 2021-04-13 2021-04-13 High-lift noise reduction wing type structure

Publications (1)

Publication Number Publication Date
CN215622650U true CN215622650U (en) 2022-01-25

Family

ID=79935694

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202120745423.1U Active CN215622650U (en) 2021-04-13 2021-04-13 High-lift noise reduction wing type structure

Country Status (1)

Country Link
CN (1) CN215622650U (en)

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