CN213473490U - Aircraft wing noise reduction structure based on slat concave cavity corrugated wall - Google Patents
Aircraft wing noise reduction structure based on slat concave cavity corrugated wall Download PDFInfo
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- CN213473490U CN213473490U CN202022520759.6U CN202022520759U CN213473490U CN 213473490 U CN213473490 U CN 213473490U CN 202022520759 U CN202022520759 U CN 202022520759U CN 213473490 U CN213473490 U CN 213473490U
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Abstract
The utility model discloses an aircraft wing noise reduction structure based on slat cavity ripple wall, including deployable leading-edge slat body, main wing and trailing edge flap, at least one cavity ripple wall component of installation of the inside recovery position of deployable leading-edge slat body and the outside expansion position of deployable leading-edge slat body, cavity ripple wall component is for falling the arc ripple wallboard of making an uproar. The optimized element is called a fundamental frequency corrugated wall element, and can promote the rapid evolution of low-frequency large-scale vortex pulsation into a high-frequency small-scale vortex flow structure which is very easy to dissipate. Through the additional effect of fundamental frequency ripple wall element, weaken the vortex flow in leading-edge slat main sound source district, restrain the noise radiation, the utility model discloses can not exert an influence to the aerodynamic performance and the large-scale passenger plane security of high lift device, and be convenient for realize and maintain on engineering application.
Description
Technical Field
The utility model relates to an aerodynamic noise field of aviation, concretely relates to structure of making an uproar falls in aircraft wing based on slat cavity ripple wall for reduce aircraft wing noise.
Background
The low noise is always the aim of cumin in the aviation industry, and even the noise reduction gain of several decibels is still a great deal of effort in academia and industry. In the early design of airplane wings, the aerodynamic performance of the wings, such as the magnitude of lift force, the maximum stall angle of attack, the lift-to-drag ratio efficiency of flight and the like, are of great importance, but with the wide application of advanced technologies such as large-bypass-ratio engines, noise elimination nacelles and acoustic liners, the noise of the engines is greatly reduced, the noise proportion of the airframe is obviously improved, and the requirements for effectively controlling the noise of the wings are increasingly strong due to the concern of passengers of passenger planes and residents near airports on the noise. The noise level of the airframe is reduced, the requirement of the social civil development is met, and the airworthiness evidence obtaining of the large civil airliner in China is facilitated and the airframe occupies a place in the future world aviation field.
In the taking-off and landing stages of modern large passenger aircraft, a three-section wing form is generally adopted to achieve the high lift effect. Wherein the high lift device comprises a leading edge slat and a trailing edge flap. Fig. 1 shows a wing structure of a typical three-section wing configuration, comprising three sections, a leading-edge slat 1, a main wing 2 and a trailing-edge flap 3. The leading edge slat of the high lift device is an important sound source of the noise of a large passenger plane body, and the complicated structure of the slat determines the complexity of the flow and the difficulty of noise reduction. The cavity between the slat and the main wing is both the main source of slat noise and the main component that determines the aerodynamic performance of the high lift device. Research shows that changing the configuration of the slat cavity is an effective means for controlling the noise of the high lift device, and the action principle is to destroy the periodic oscillation of vortex flow in the slat cavity, change the flow state of a shear layer near the slat, and achieve the feedback action of inhibiting the self-oscillation of the cavity, such as cavity filling, a porous trailing edge, a slat sealing plate, a lower trailing edge extension plate and other existing technologies. However, changes in the configuration of the re-entrant cavity can severely affect the aerodynamic performance of the high lift device and also increase the difficulty of slat manufacture. Many noise reduction techniques cannot be applied to engineering practice due to the large aerodynamic losses that result in aircraft, and when the noise suppression effect is not ideal as a result of actual conditions deviating from their design state, the entire slat component needs to be redesigned. It is a challenge for researchers to develop noise control without changing the aerodynamic performance of the high lift devices.
The corrugation of the inner wall of the slat concave cavity is a novel passive noise reduction control method, the flow of the inner wall of the slat concave cavity can be effectively changed by weakly changing the geometric shape of the surface of the inner wall of the slat concave cavity, advance transition is realized, more acoustic energy is dissipated, the wing spreading flow state is improved, and therefore the noise level of the wing is reduced. According to the vortex sound theory, the vortex is flowing sound, and the root of the sounding body is controlled by controlling the vortex. The professor of famous experts in the field of fluid mechanics in China Wu dielectric thinks that the control of noise can be realized through the control of flow field vortex and can also be determined through the control of wave, and researches show that the corrugation on the inner wall of the concave cavity can not only effectively reduce low-frequency noise but also improve the pneumatic performance.
SUMMERY OF THE UTILITY MODEL
The utility model aims at solving above-mentioned difficult problem and shortcoming, provide a structure of making an uproar falls in aircraft wing based on slat cavity ripple wall to reach the target that reduces the noise level when keeping the aerodynamic performance of wing, be convenient for realize moreover in the engineering.
The utility model discloses the following technical scheme of accessible realizes:
the aircraft wing noise reduction structure based on the slat concave-cavity corrugated wall comprises a deployable leading-edge slat body, a main wing and a trailing edge flap, wherein at least one concave-cavity corrugated wall element is installed at a recovery position inside the deployable leading-edge slat body and a deployment position outside the deployable leading-edge slat body, and the concave-cavity corrugated wall element is a noise reduction arc-shaped corrugated wall plate.
Further, the leading-edge slat body is detachably connected with the noise-reducing arc-shaped corrugated wall plate through a connecting piece.
Further, the slat body may be an iso-vertical pull or swept back pull model.
Furthermore, an inner groove for installing the noise reduction arc-shaped corrugated wallboard is arranged on the inner lower surface of the slat cavity along the spanwise direction, two rows of fixing holes are formed in the lower surface of the slat cavity of the leading edge slat body close to the trailing edge and the leading edge sharp corner, N is a positive integer and is more than or equal to 2, the noise reduction arc-shaped corrugated wallboard comprises three sections, the first section is a left smooth arc plate, the middle second section is an inner corrugated outer smooth arc plate, the third section is a right smooth arc plate, the first section, the third section and the second section are integrally formed, the left smooth arc plate and the right smooth arc plate are respectively provided with M through holes, M is a positive integer, the number of the left smooth arc plate through holes and the number of the right smooth arc plate through holes are respectively the same as the number of the two rows of fixing holes, the positions of the left smooth arc plate and the right smooth arc plate are in one-to-one, the wave shape is formed by a wave-shaped arranged wave wall surface, the wave number is k, and k is more than or equal to 2.
Furthermore, the wave shape is one or more than two of sine wave shape, cosine wave shape, half sine wave shape, cosine wave shape, triangle wave shape and triangle wave shape with rounded top.
Furthermore, the specific position of the waveform on the inner side of the noise reduction arc-shaped corrugated wallboard is that the sharp corner of the lower surface of the slat concave cavity curve starts, the curved part of the concave cavity of the leading edge slat body is positioned at 5% -75%, the curved part is parallel to the lower surface of the slat in the spanwise direction, the value range of the wavelength lambda is 0.02L-0.1L, the value range of the amplitude h of the waveform is 0.002L-0.02L, and L is the linear distance from the sharp corner of the leading edge slat body to the trailing edge.
Further, the number of each row N of the two rows of N fixing holes is 2-20, and the arrangement direction of the two rows of fixing holes is the same as the spanwise direction of the leading-edge slat body.
Furthermore, the noise-reducing arc corrugated wallboard is completely and seamlessly embedded with the inner cavity of the leading-edge slat body, and the noise-reducing arc corrugated wallboard and the lower surface of the slat concave cavity are in uniform overall transition after installation.
Further, the connecting piece can be a bolt, a rivet, a hinge, an adhesive or a welding piece, and the three parts of the leading edge slat body, the noise reduction arc-shaped corrugated wallboard and the connecting piece are basically consistent with the leading edge slat structure after being connected, and have no gap or recess.
Furthermore, the lower surface of the leading-edge slat body and the bottom surface of the inner groove are both cambered surfaces, and the depth of the inner groove is more than or equal to 0.
Compared with the prior art, the utility model discloses following beneficial effect has:
the utility model belongs to novel technique of making an uproar falls passively, for current passive noise control technique such as cavity packing, porous trailing edge, the slat closing plate, lower trailing edge extension plate etc, slat cavity ripple wall influences very little to the aerodynamic performance who increases the lift device, need not to change the appearance structure of wing by a wide margin, almost can not bring any extra quality for the slat, simple to operate has, the operation is stable, advantages such as effect is showing, this method is through changing the behavior of vortex drop under the slat cavity, thereby reach the purpose that reduces slat low frequency noise, be favorable to further improving the aerodynamic performance of wing simultaneously, be convenient for in the engineering realize and maintain.
Drawings
FIG. 1 is a schematic illustration of a prior art three-section airfoil configuration;
FIG. 2 is a schematic view of the deployed and retracted positions of the leading-edge slat of the present invention
FIG. 3 is a schematic view of a curved corrugated wall panel of the lower surface of the slat cavity of the present invention;
FIG. 4 is an enlarged, fragmentary view of the corrugated wall connection of FIG. 3;
FIG. 5 is a schematic view of the wave height and amplitude of the curved corrugated wall panel of the slat cavity of the present invention;
fig. 6 is a schematic view of a three-dimensional structure of the smooth arc plate outside the inner side corrugation of the key component of the present invention.
Detailed Description
The following description of the embodiments of the present invention is provided by way of specific examples, and other advantages and effects of the present invention will be readily apparent to those skilled in the art from the disclosure herein.
The utility model discloses use multistage wing 30P30N as the example, introduce an aircraft wing noise reduction structure based on slat cavity ripple wall to make technical personnel in this field can understand the utility model discloses and can implement better. The multi-section wing comprises a leading edge slat, a main wing and a trailing edge flap, wherein in FIG. 1, a mark 1 represents a leading edge slat body, a mark 2 represents a noise reduction arc corrugated wallboard, a mark 3 represents a connecting piece, a mark 4 represents a main wing, and a mark 5 represents a trailing edge flap; in fig. 2, reference numeral 6 denotes a leading-edge tip angle, reference numeral 7 denotes a trailing edge, reference numeral 101 denotes a deployed position schematic diagram of the slat body 1, and reference numeral 102 denotes a retracted position schematic diagram of the slat body 1.
The utility model discloses an aircraft wing noise reduction structure based on slat cavity ripple wall, including deployable leading edge slat body 1, main wing 4 and trailing edge flap 5, at least one cavity ripple wall component of installation in deployable inside recovery position 102 of leading edge slat body 1 and the deployable outside expansion position 101 of leading edge slat body 1, cavity ripple wall component is for falling the arc ripple wallboard 2 of making an uproar.
The specific implementation of using the slat re-entrant corrugated wall to reduce leading-edge slat noise is as follows:
the implementation content is as follows: referring to fig. 1 to 6, in the noise reduction structure for an aircraft wing based on a slat concave-cavity corrugated wall according to the present embodiment, a leading-edge slat body 1 is detachably connected to a noise reduction arc-shaped corrugated wall plate 2 through a connecting member 3, and the installation and the replacement of the corrugated wall type are flexible and convenient, so that the embodiment is convenient and practical in engineering application.
The implementation content is two: referring to fig. 3-4, the leading-edge slat body 1 can be a constant straight-pulling or backward-sweeping tensile model, the inner surface of the slat cavity is provided with an inner groove 1-1 along the extending direction for additionally installing a noise reduction arc-shaped corrugated wallboard 2, the lower surface of the slat cavity 1 cavity is provided with two rows of fixing holes 1-2 near the rear edge 7 and the leading-edge sharp corner 6, each row is provided with N, N is a positive integer and N is more than or equal to 2, the noise reduction arc-shaped corrugated wallboard comprises three sections, the first section is a left side smooth arc-shaped board, the middle second section is an inner side corrugated outer side smooth arc-shaped board 2-2, the third section is a right side smooth arc-shaped board 2-3, the first section, the third section and the second section are integrally formed, the left side smooth arc-shaped board and the right side smooth arc-shaped board are provided with M through holes, M is a positive integer, the number of, the positions of the inner side corrugated smooth arc-shaped plates 2-2 correspond to the positions of the fixing holes 1-2 one by one, the outer side smooth arc-shaped plates 2-2 are corrugated wall plates, the outer side smooth surfaces of the inner side corrugated smooth arc-shaped plates are tightly attached to the inner groove 1-1, the corrugated shape is formed by corrugated wall surfaces which are arranged in a wave shape, the wave number is k, and k is larger than or equal to 2.
The implementation content is three: as shown in fig. 1 to 6, the type of the wave in the present embodiment is one or more than two of sine wave or cosine wave, half sine wave or cosine wave, triangular wave, and triangular wave with rounded tip. The processing of the corrugated shape can be realized by processing and manufacturing technologies such as laser cutting, electric spark cutting, 3D printing and the like. Other components and connections are the same as those described in the detailed description.
The implementation content is four: referring to fig. 1-6, the specific position of the waveform on the inner side of the curved plate of the corrugated wall is that the leading edge sharp corner 6 of the lower surface of the slat concave-cavity curve starts, the curved part of the concave-cavity curve of the leading edge slat body 1 is positioned at 5% -75% and is parallel to the lower surface of the slat in the spanwise direction, the value range of the wavelength lambda is 0.02L-0.1L, the value range of the waveform amplitude h is 0.002L-0.02L, and L is the linear distance from the leading edge sharp corner 6 of the leading edge slat body 1 to the trailing edge 7. The method comprises the steps of obtaining leading edge noise data controlled by slat concave cavity corrugated walls under different flight states when the aircraft is in a take-off state and a landing state by adopting a computational fluid mechanics aerodynamic noise numerical simulation or acoustic wind tunnel test, changing parameters such as wavelength lambda, amplitude h and the like of the arc corrugated wall plate for optimization, establishing noise data, optimizing the wavelength lambda and the amplitude h of the noise reduction arc corrugated wall plate within the reasonable value range, and finally applying the noise data to the design of the corrugated wall in an actual flight state. The optimally designed slat concave cavity corrugated wall structure is called a fundamental frequency corrugated wall and is used for actively controlling the flow direction and the frequency of the most unstable wave of the boundary layer, and the fundamental frequency corrugated wall can be fixed on the lower surface of the slat concave cavity by adopting aviation materials such as aluminum alloy, titanium alloy and the like, so that the low-frequency large-scale vortex pulsation is rapidly evolved into a high-frequency small-scale vortex flow structure which is very easy to dissipate.
The implementation content is five: the number of each row N of the two rows of N fixing holes 1-2 is 2-20, the arrangement direction of the two rows of fixing holes is the same as the spanwise direction of the slat body 1, and other components and connection relations are the same as those of the first, second, third or fourth specific embodiment.
The implementation content is six: the noise-reducing arc-shaped corrugated wallboard 2 is completely and seamlessly embedded with an inner groove 1-1 of the slat body 1, the noise-reducing arc-shaped corrugated wallboard and the lower surface of the slat concave cavity are integrally and uniformly transited after being installed, and other components and connection relations are the same as those of the first to fourth or fifth specific embodiments.
The implementation content is seven: the connecting piece 3 can be a bolt, a rivet, a hinge, an adhesive or a welded part, the three parts of the slat body 1, the noise reduction arc-shaped corrugated wall plate 2 and the connecting piece 3 are basically consistent with a reference slat structure after being connected, no gap, a recess and other parts causing additional noise sources exist, and other components and connection relations are the same as those of the first to fifth or sixth specific embodiments.
The implementation content is eight: the lower surface of the slat body 1 and the bottom surface of the inner groove 1-1 are both cambered surfaces, the depth of the inner groove is more than or equal to 0, and other components and connection relations are the same as those of the first, second, third, fourth, fifth, sixth or seventh specific embodiment.
Example (b):
taking a multi-section wing 30P30N as an example, the chord length is 558.5mm, the spanwise equal straight-pull extension is one-time chord length, the length from the sharp corner of the leading edge of the leading-edge slat to the trailing edge is also 558.5mm, the length from the sharp corner of the leading edge of the leading-edge slat to the trailing edge is 68mm, the noise-reduction corrugated wall plate has the wave amplitude of 0.15mm, the wavelength of 2.72mm, the ratio of the wave amplitude to the wavelength of about 5 percent and the thickness of the wall plate of 4mm after computational fluid mechanics numerical calculation optimization, and is positioned at a reference concave cavity curve part of the slat body which is 5 to 75 percent and is parallel to the lower surface of the slat in the spanwise direction. The depth of the inner groove is 0.4 mm. The connecting piece passes through the rivet with the slat body with fall the arc ripple wallboard seamless connection of making an uproar, two rows of fixed orificess altogether about the ripple wallboard, every row of fixed orificess 4, evenly distributed is to the position in exhibition, and every fixed orifices diameter is 1 mm. Under the condition, the total sound pressure level is predicted to be reduced by 5-6 dB through numerical simulation. Additionally, the utility model discloses also be applicable to the leading edge noise suppression of other multistage wing profiles.
The principle of the utility model is that:
the method for controlling aerodynamic noise by the corrugated wall is based on the theory of eddy dynamics and wave eddy interaction in the field of hydrodynamics. The professor Wu Jie in the field of fluid mechanics in China finds that waves and vortexes in a turbulent flow field always coexist, nonlinear unstable waves prepare for the generation of separation vortexes when low-speed flow is separated, and the formed vortex structure causes shearing in the flow field to create conditions for new-level unstable waves. Therefore, the control of noise can be realized by the control of flow field vortex, and can also be realized by the control of wave. Noise control related to vortices is common, and spoilers and vortex generators on aircraft wings have been used in engineering practice. According to the vortex sound theory, the vortex is flowing sound, and the root of the sounding body is controlled by controlling the vortex. The utility model discloses earlier stage has good suppression effect through the control of a large amount of scientific research experiments and numerical calculation demonstration ripples, the utility model provides a cavity ripple wall not only can effectively reduce low frequency noise but also can reduce resistance, improve lift. The main source of the slat noise is that the airflow forms a free shear layer after flowing out from the slat tip, the shear flow develops downstream until impacting the upper wall surface of the slat cavity to generate noise, and large-scale vortex is generated in the cavity to circulate and return to form a resonant cavity. The utility model discloses a concave cavity arc corrugated wall board can accelerate the boundary layer of slat cavity wall face to transition and beat, and the broken small-scale vortex that is the minor scale vortex of the broken big scale vortex structure that is mixed flow in the cavity fast improves wing exhibition flow state, can effectively reduce slat cavity low frequency noise, restraines the sound source radiation of resonant cavity. Various changes and modifications to the above-described structures and shapes, including other combinations of features, will be apparent to those skilled in the art upon reading the present disclosure. These variants and/or combinations fall within the technical field of the present invention and are intended to be protected by the following claims.
Claims (10)
1. The aircraft wing noise reduction structure based on the slat concave-cavity corrugated wall comprises a deployable leading-edge slat body, a main wing and a trailing edge flap, and is characterized in that at least one concave-cavity corrugated wall element is mounted at a recovery position inside the deployable leading-edge slat body and a deployment position outside the deployable leading-edge slat body, and the concave-cavity corrugated wall element is a noise reduction arc-shaped corrugated wall plate.
2. An aircraft wing noise reduction structure based on a slat reentrant corrugated wall according to claim 1, wherein the leading edge slat body is detachably connected to the noise reducing curved corrugated wall panel by a connector.
3. An aircraft wing noise reduction structure based on a slat reentrant corrugated wall according to claim 2, characterised in that the leading edge slat body may be of equal straight pull or swept back pull model.
4. The aircraft wing noise reduction structure based on the slat concave cavity corrugated wall according to claim 1, wherein an inner groove for installing the noise reduction arc-shaped corrugated wall plate is arranged on the inner lower surface of the slat concave cavity along the spanwise direction, two rows of fixing holes are arranged on the lower surface of the concave cavity of the slat main body close to the rear edge and the front edge sharp corner, N is a positive integer and is more than or equal to 2, the noise reduction arc-shaped corrugated wall plate comprises three sections, the first section is a left smooth arc-shaped plate, the middle second section is an inner corrugated outer smooth arc-shaped plate, the third section is a right smooth arc-shaped plate, the first section, the third section and the second section are integrally formed, the left smooth arc-shaped plate and the right smooth arc-shaped plate are provided with M through holes, M is a positive integer, the number of the left smooth arc-shaped plate and the right smooth arc-shaped plate through holes is, the positions correspond to one another, the smooth arc-shaped plates on the outer sides of the inner corrugations are corrugated wall plates, the smooth surfaces on the outer sides are tightly attached to the inner grooves, the corrugations are formed by corrugated wall surfaces, the wave number is k, and k is larger than or equal to 2.
5. An aircraft wing noise reduction structure based on a slat reentrant corrugated wall according to claim 4, wherein the wave form is one or more of sine wave form, cosine wave form, half sine wave form, cosine wave form, triangular wave form with rounded tip.
6. The aircraft wing noise reduction structure based on the slat reentrant corrugated wall according to claim 4, wherein the specific position of the waveform inside the noise reduction arc-shaped corrugated wall plate is that the sharp corner of the lower surface of the slat reentrant curve starts, the curved part of the slat body reentrant curve is 5% -75%, the curved part is parallel to the lower surface of the slat in the spanwise direction, the wavelength λ ranges from 0.02L to 0.1L, the amplitude h of the waveform ranges from 0.002L to 0.02L, and L is the linear distance from the sharp corner of the leading edge of the slat body to the trailing edge.
7. An aircraft wing noise reduction structure based on a slat reentrant corrugated wall according to claim 4, wherein the number of the two rows of N fixing holes in each row is 2-20, and the arrangement direction of the two rows of fixing holes is the same as the spanwise direction of the leading-edge slat body.
8. The aircraft wing noise reduction structure based on the slat reentrant corrugated wall according to claim 1, wherein the noise reduction arc-shaped corrugated wall plate is completely and seamlessly embedded with an inner cavity of a leading-edge slat body, and is uniformly transited with the lower surface of the slat reentrant integrally after being installed.
9. An aircraft wing noise reduction structure based on a slat reentrant corrugated wall according to claim 2, wherein the connecting piece can be a bolt, a rivet, a hinge, an adhesive or a weld, and the three parts of the leading edge slat body, the noise reduction arc corrugated wall plate and the connecting piece are basically consistent with the leading edge slat structure after being connected without gaps or recesses.
10. The aircraft wing noise reduction structure based on the slat reentrant corrugated wall according to claim 4, wherein the lower surface of the leading edge slat body and the bottom surface of the inner groove are both cambered surfaces, and the depth of the inner groove is greater than or equal to 0.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112173064A (en) * | 2020-11-04 | 2021-01-05 | 上海市应用数学和力学研究所 | Aircraft wing noise reduction structure based on slat concave cavity corrugated wall |
| CN113460285A (en) * | 2021-09-03 | 2021-10-01 | 中国商用飞机有限责任公司 | High lift device for fixed wing aircraft and manufacturing method thereof |
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2020
- 2020-11-04 CN CN202022520759.6U patent/CN213473490U/en not_active Withdrawn - After Issue
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112173064A (en) * | 2020-11-04 | 2021-01-05 | 上海市应用数学和力学研究所 | Aircraft wing noise reduction structure based on slat concave cavity corrugated wall |
| CN112173064B (en) * | 2020-11-04 | 2024-06-18 | 上海市应用数学和力学研究所 | Aircraft wing noise reduction structure based on slat concave cavity corrugated wall |
| CN113460285A (en) * | 2021-09-03 | 2021-10-01 | 中国商用飞机有限责任公司 | High lift device for fixed wing aircraft and manufacturing method thereof |
| CN113460285B (en) * | 2021-09-03 | 2021-11-23 | 中国商用飞机有限责任公司 | High lift device for fixed wing aircraft and manufacturing method thereof |
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