Outlet guide vanes, power propulsion system and noise reduction method thereof

Abstract

The application relates to an outlet guide vane, a power propulsion system and a noise reduction method thereof. The outlet guide vane comprises a vane body, the vane body comprises a sound lining part; the sound lining part is provided with at least a plurality of sound lining areas in the direction from the leading edge to the trailing edge of the outlet guide vane, at least comprising a first sound lining area and a second sound lining area located upstream of the first sound lining area; wherein the first sound lining area comprises a plurality of first resonance cavities, the second sound lining area comprises a plurality of second resonance cavities, and the area of a single first resonance cavity is greater than that of a single second resonance cavity.

Description

TECHNICAL FIELD

[0001] The present application relates to an outlet guide vane, a power propulsion system and a noise reduction method thereof. BACKGROUND

[0002] With the rapid iteration of civil aviation engine products and the increasingly fierce market competition, the problems of high noise and large weight have become unavoidable for all research enterprises. Whether the engine can be reasonably lightened relates to the core competitive standard of fuel consumption. The sound radiation level of the engine during the take-off and landing stages of the airport is limited by the strict requirements of the International Civil Aviation Organization (ICAO). The latest noise regulation requires new civil aircraft to adopt the more stringent fifth stage noise regulation, which further reduces the cumulative noise margin by 7dB compared with the fourth stage. The low-noise design and lightweight design considering aerodynamic efficiency become more and more important in the design stage of the new generation of aviation engine products.

[0003] For low-noise design, the fan / compressor noise of a large-bypass-ratio high-speed turbine fan engine contributes the most, among which the rotor-stator interaction noise is an important part, which appears at the integer multiples of BPF (Blade passing Frequency, the product of the number of blades and the rotational speed frequency, also known as the fundamental frequency) in the frequency spectrum, so it is also called single-tone noise.

[0004] In order to solve the above problems, the existing scheme as shown in Figure 1 , the fan of the gas turbine engine includes fan rotor blades 1001 and outlet guide vanes 1002, and a sound lining 1004 is arranged on the inner wall surface of the inlet duct, fan case and outer duct, so as to absorb and attenuate the sound energy of the above-mentioned single-tone noise, and at the same time, to widen the sound absorption frequency band as much as possible to take into account the broadband.

[0005] The sound lining is the most important propagation noise reduction technology that has been widely used, especially for large-bypass-ratio civil turbofan engines. The structure of the existing sound lining 1004 is as shown in Figure 2A and Figure 2B , which generally includes a perforated plate 1005, a honeycomb cavity 1006 and a rigid back plate 1007, as shown in Figure 2A and Figure 2B (taking a single layer, i.e. a single-degree-of-freedom sound lining structure as an example), which can be regarded as an arrangement of a large number of Helmholtz resonant cavities. The acoustic resistance is determined by the micro-holes, and the resonant frequency of the resonant cavity determines the acoustic reactance. The sound wave of a specific frequency enters the honeycomb cavity 1006 through the small holes 10051 on the perforated plate 1005 and produces resonance, so that the sound energy is converted into internal energy and consumed. In this way, the two cooperate to achieve the purpose of noise reduction at a specific frequency. The specific parameters of the holes and cavities are now generally required to be optimized in a multi-parameter forward design to find the best noise reduction effect.

[0006] The above scheme still needs to be further improved in terms of lightweight performance to meet the lightweight demand of the gas turbine engine on the basis of noise reduction. SUMMARY

[0007] An object of the present application is to provide an outlet guide vane.

[0008] Another object of the present application is to provide a power propulsion system.

[0009] Still another object of the present application is to provide a noise reduction method for a power propulsion system.

[0010] An outlet guide vane according to a first aspect of the present application comprises a vane body, the vane body comprising a sound lining portion; the sound lining portion is provided with at least a plurality of sound lining zones in a direction from a leading edge to a trailing edge of the outlet guide vane, at least comprising a first sound lining zone and a second sound lining zone upstream of the first sound lining zone; wherein the first sound lining zone comprises a plurality of first resonant cavities, and the second sound lining zone comprises a plurality of second resonant cavities, and an area of a single first resonant cavity is greater than an area of a single second resonant cavity.

[0011] In one or more embodiments of the outlet guide vane, in a direction from the leading edge to the trailing edge, in adjacent sound lining zones, an area of a single resonant cavity in a sound lining zone located relatively downstream is greater than an area of a single resonant cavity in a sound lining zone located relatively upstream.

[0012] In one or more embodiments of the outlet guide vane, in a direction from the leading edge to the trailing edge, in adjacent sound lining zones, a number of columns of resonant cavities and a number of resonant cavities per column in a sound lining zone located relatively downstream are both less than those in a sound lining zone located relatively upstream.

[0013] In one or more embodiments of the outlet guide vane, the plurality of sound lining zones are a sixth sound lining zone, a fifth sound lining zone, a fourth sound lining zone, a third sound lining zone, a second sound lining zone, and a first sound lining zone distributed in sequence from the leading edge to the trailing edge, and corresponding target attenuation frequencies are respectively corresponding to sideline single tone noise second-order fundamental frequency, first-order fundamental frequency in an air engine airworthiness operating condition, flyover single tone noise second-order fundamental frequency, first-order fundamental frequency in an air engine airworthiness operating condition, approach single tone noise second-order fundamental frequency, first-order fundamental frequency in an air engine airworthiness operating condition in sequence.

[0014] In one or more embodiments of the outlet guide vane, a resonance cavity of the first acoustic lining region has a side length a, a corresponding target attenuation frequency is a first order fundamental frequency f of an approach condition single tone noise of an aeroengine in a flight condition, a resonance cavity of the second acoustic lining region has a side length 1 / 2a, a corresponding target attenuation frequency is a second order fundamental frequency 2f of the approach condition single tone noise, a resonance cavity of the third acoustic lining region has a side length 2 / 3a, a corresponding target attenuation frequency is a first order fundamental frequency 1.5f of a flyover condition single tone noise of the aeroengine in the flight condition, a resonance cavity of the fourth acoustic lining region has a side length 1 / 3a, a corresponding target attenuation frequency is a second order fundamental frequency 3f of the flyover condition single tone noise of the aeroengine in the flight condition, a resonance cavity of the fifth acoustic lining region has a side length 5 / 9a, a corresponding target attenuation frequency is a first order fundamental frequency 1.8f of an sideline condition single tone noise of the aeroengine in the flight condition, a resonance cavity of the sixth acoustic lining region has a side length 5 / 18a, a corresponding target attenuation frequency is a second order fundamental frequency 3.6f of the sideline condition single tone noise of the aeroengine in the flight condition.

[0015] In one or more embodiments of the outlet guide vane, a connecting region of adjacent acoustic lining regions comprises a glue joint structure.

[0016] In one or more embodiments of the outlet guide vane, the resonance cavity is a hexagonal honeycomb resonance cavity.

[0017] In one or more embodiments of the outlet guide vane, a surface of the acoustic lining portion has perforations, each perforation corresponds to each resonance cavity, a corresponding target attenuation frequency of the resonance cavity is obtained by the following formula:

[0018]

[0019] wherein F is the target attenuation frequency, k is an empirical coefficient greater than 0, S is an area of the perforation, L is a length of the resonance cavity, V is a volume of the resonance cavity.

[0020] In one or more embodiments of the outlet guide vane, the outlet guide vane is integrally formed by additive manufacturing.

[0021] A power propulsion system according to a second aspect of the present application comprises the outlet guide vane according to the first aspect.

[0022] In one or more embodiments of the power propulsion system, the power propulsion system is a gas turbine engine, the gas turbine engine comprises a fan and / or a compressor, an outlet end of the fan and / or the compressor is provided with the outlet guide vane.

[0023] According to the third aspect of the present application, a noise reduction method of a power propulsion system, the power propulsion system comprising a fan and / or a compressor, the noise reduction method comprising, at an outlet end of the fan and / or the compressor, arranging an outlet guide vane as described in the first aspect.

[0024] The beneficial effects of the present application include, but are not limited to:

[0025] By integrating the structure of the sound lining in the outlet guide vane, that is, the vane body as the rigid back plate of the sound lining, the lightweight of the noise reduction structure is realized, and at the same time, through the structure that the area of a single resonance cavity of the sound lining area located at the relatively upstream is smaller than the area of the resonance cavity of the sound lining area located at the relatively downstream, on the basis of realizing the lightweight of the noise reduction structure, the influence of the integrated sound lining structure on the aerodynamic efficiency of the outlet guide vane is reduced, so that the outlet guide vane realizes the lightweight of the noise reduction structure on the basis of the basic function of having relatively high aerodynamic efficiency, in addition, the arrangement of multiple sound lining areas takes into account the noise reduction of different flight conditions and / or different orders of fundamental frequency, and optimizes the noise reduction effect of the noise reduction structure. BRIEF DESCRIPTION OF DRAWINGS

[0026] The above and other features, properties, and advantages of the present application will become more apparent by referring to the following description in conjunction with the accompanying drawings, in which:

[0027] Figure 1 is a structural schematic diagram of a gas turbine engine of an existing scheme.

[0028] Figure 2A and Figure 2B is a structural schematic diagram of a sound lining of an existing scheme.

[0029] Figure 3 is a structural schematic diagram of an outlet guide vane of a comparative scheme.

[0030] Figure 4 is a structural schematic diagram of a surface of an outlet guide vane of an embodiment.

[0031] Figure 5 is a structural schematic diagram of resonance cavities of multiple sound lining areas of an outlet guide vane of an embodiment.

[0032] REFERENCE SIGNS:

[0033] 10, 100, 1002 - outlet guide vane,

[0034] 101 - leading edge,

[0035] 102 - trailing edge,

[0036] 1 - vane body,

[0037] 11 - sound lining part,

[0038] 111 - perforations,

[0039] 12 - acoustic liner region,

[0040] 121 - first acoustic liner region,

[0041] 1211 - first resonant cavity,

[0042] 122 - second acoustic liner region,

[0043] 1221 - second resonant cavity,

[0044] 123 - third acoustic liner region,

[0045] 124 - fourth acoustic liner region,

[0046] 125 - fifth acoustic liner region,

[0047] 126 - second acoustic liner region,

[0048] 13 - connecting region,

[0049] 1001 - fan rotor blade,

[0050] 1004 - acoustic liner,

[0051] 1005 - perforated plate,

[0052] 10051 - perforation,

[0053] 1006 - honeycomb cavity,

[0054] 1007 - rigid backplate. DETAILED DESCRIPTION

[0055] The application is further described in connection with the following embodiments and drawings, in which more details are set forth in order to provide a thorough understanding of the application. However, it will be apparent to those skilled in the art that the application can be practiced in a variety of ways without departing from the spirit and scope of the application as set forth in the claims. Accordingly, the detailed description is not intended to limit the scope of the application as set forth in the claims.

[0056] Also, the use of "one embodiment," "an embodiment," or "some embodiments” in this specification, is not a limitation on the scope or application of the application. The phrase "one embodiment,” "an embodiment,” or "some embodiments” does not mean the same embodiment or embodiments. Further, many of the features of one or more embodiments of the application can be combined with some or all of the features of other one or more embodiments. Therefore, the description of one or more embodiments of the application should not be construed as limiting the scope of the application.

[0057] The following embodiments introduce an outlet guide vane 10 to be applied to a gas turbine engine, in particular to a fan of a turbofan engine, the gas turbine engine comprising a fan and / or a compressor, the outlet guide vane being arranged at an outlet end of the fan and / or the compressor. However, this is not limiting, the outlet guide vane can be applied to any kind of power propulsion system, for example to a fan, a propeller, a propfan, etc. Also, this is not limiting to a gas turbine engine, for example, the outlet guide vane can be applied to a hybrid power propulsion system comprising a gas turbine engine, or to an electrically driven power propulsion system, for example to a fan, a propeller, a propfan, etc., in order to reduce fan noise and / or intake noise of the compressor.

[0058] As shown in the prior art, Figure 1 An acoustic lining 1004 is arranged at inner walls of an inlet duct 1001, a fan case 1002, and an outer duct 1003 of the gas turbine engine, in order to absorb and attenuate sound energy of the above-mentioned single tone noise, and to broaden the sound absorption frequency band as much as possible.

[0059] The acoustic lining is the most important propagation noise reduction technology that has been widely used, especially for large bypass ratio civil turbofan engines. The structure of the prior art acoustic lining 1004 is shown in Figure 2A and Figure 2B Generally, the acoustic lining 1004 comprises a perforated panel 1005, a honeycomb cavity 1006, and a rigid back plate 1007. A sound wave with a certain frequency enters the honeycomb cavity 1006 through the small holes 10051 of the perforated panel 1005, and then resonates to form a resonant cavity with an open top and a closed bottom. The common resonant cavity is a Helmholtz resonator. After the sound enters the resonant cavity through the small holes of the acoustic lining surface, it resonates in the resonant cavity and dissipates sound energy. The damping mechanism is usually mainly due to the dissipation of the vibration jet accompanied by the resonator orifice.

[0060] In order to realize the lightweight of the gas turbine engine with the acoustic lining structure, in a comparative scheme, as shown in Figure 3 The outlet guide vane 100 of the fan is integrated with the acoustic lining structure. Specifically, the outlet guide vane 100 comprises a vane body 1, and an acoustic lining portion 11 is arranged at the vane body 1. Figure 3 The structure shown in the figure is sufficient. The acoustic lining portion 11 can be a groove-shaped area formed in the vane body 1. The vane body 1 serves as a rigid back plate of the acoustic lining. A perforated panel is arranged on the surface of the vane body 1. A honeycomb cavity is arranged in the thickness of the vane body 1 extending from the surface to the inside. It can be understood that, although Figure 3 the form is similar to an exploded view, this is to more clearly show the outlet guide vane integrated with the acoustic lining structure. In fact, an integrated manufacturing process is generally used, for example, an additive manufacturing process is used to obtain the outlet guide vane, in order to improve the yield of the complex structure.

[0061] But the inventors found that, Figure 3 The outlet guide vane 100 of the comparative scheme shown can play a certain role in lightening, but the outlet guide vane itself has the role of rectifying and converting the fan rotor blade wake into axial outflow. The structure of the outlet guide vane 100 will have a large aerodynamic loss. Figure 3

[0062] Based on the above, the inventors have invented a new structure of the outlet guide vane, which can not only have good noise reduction and lightening effects, but also can ensure good aerodynamic efficiency of the outlet guide vane.

[0063] Referring to Figure 4 and Figure 5 In some embodiments, the outlet guide vane 10 includes a vane body 1, and the vane body 1 includes a sound lining portion 11. The sound lining portion 11 is provided with at least a plurality of sound lining zones 12 in the direction from the leading edge 101 to the trailing edge 102 of the outlet guide vane 10, and at least includes a first sound lining zone 121 and a second sound lining zone 122 located upstream of the first sound lining zone 121. The first sound lining zone 121 includes a plurality of first resonant cavities 1211, and the second sound lining zone 122 includes a plurality of second resonant cavities 1221. The area of a single first resonant cavity 1211 is greater than that of a single second resonant cavity 1221. The structure of the outlet guide vane 10 integrated with the sound lining, i.e., integrated with the resonant cavities, perforated plates, and rigid back plates, is similar to that of the outlet guide vane 100 shown in Figure 3 , and details are not repeated here. It can be understood that the area of a single resonant cavity here refers to the cross-sectional area of a single resonant cavity, and the linearity of the cross-sectional area is generally required to be much smaller than the wavelength of the corresponding noise to be reduced.

[0064] The division of different sound lining zones here is based on the size of the area of a single resonant cavity constituting different sound lining zones to correspondingly process different frequency noises. For the same shape, such as a honeycomb-shaped resonant cavity with a regular hexagonal shape, different areas correspond to different specific frequency noises. For example, the surface of the sound lining portion 11 has perforations 111, each perforation 111 is provided with each resonant cavity, and the perforation 111 is generally located at the center position of each resonant cavity. The corresponding target attenuation frequency of the resonant cavity is obtained by the following formula:

[0065]

[0066] Wherein, F is the target attenuation frequency, k is an empirical coefficient greater than 0, S is the area of the perforation, L is the length of the resonant cavity, and V is the volume of the resonant cavity.

[0067] For a hexagonal resonant cavity, the area calculation formula of a parallelogram is: ​

[0068] wherein A is the side length area.

[0069] The relationship between the resonance frequency (i.e. target attenuation frequency) F and A is:

[0070]

[0071] wherein the area A of the hexagonal resonant cavity is the side length area, and the resonant cavity volume can be approximated as P*H, H being the cavity depth. Since the cavity depth and the perforation shape of the resonant cavities in different acoustic lining zones are the same inside the outlet guide vane 10, it can be simply considered that F is inversely proportional to A, i.e. the longer the side length of a single resonant cavity, the larger the side length area, and the lower the frequency.

[0072] It can be understood that the above description of the first acoustic lining zone 121 and the second acoustic lining zone 122 is only for describing adjacent acoustic lining zones, and does not mean that the vane has only two acoustic lining zones. For example, as shown in Figure 4 and Figure 5 , the acoustic lining zones can be six. Details are described below.

[0073] Preferably, as shown in Figure 4 and Figure 5 , in some embodiments, in the direction from the leading edge 101 to the trailing edge 102, in adjacent acoustic lining zones 12, the area of a single resonant cavity in the relatively downstream acoustic lining zone is greater than the area of a single resonant cavity in the relatively upstream acoustic lining zone. That is, in adjacent acoustic lining zones 12, the number of columns of resonant cavities and the number of resonant cavities per column in the relatively downstream acoustic lining zone are both less than the resonant cavity area in the relatively upstream acoustic lining zone. The beneficial effect of this is that, as shown in Figure 5 , the cross-sectional area of a single resonant cavity gradually increases from the leading edge to the trailing edge, and the perforation is always at the center of the cross-sectional area, so the perforation arrangement is from sparse to dense, and especially at the trailing edge where the flow loss is more obvious, the sparsest arrangement is used. The inventors have found that such a structure can minimize the impact on aerodynamic efficiency caused by the addition of acoustic lining, and ensure the aerodynamic efficiency of the outlet guide vane.

[0074] In some embodiments, as shown in Figure 5 , the connecting area 13 of adjacent acoustic lining zones can be a glue joint structure. However, this is not a limitation, for example, if the noise scattering problem caused by the joint is considered, it can also be processed into a cavity in sub-areas and supplemented with perforations as irregular acoustic lining unit bodies, but the inventors have found that the area of the connecting area 13 is very small, and the optimization effect is limited, so the glue joint structure can be used. Such a structure is relatively lightweight and stable, and it can be understood that other lightweight and stable connection methods can also be used.

[0075] As shown in Figure 4 , Figure 5As shown, in some embodiments, for the current airworthiness regulation requirements, the setting of the outlet guide vane 10 can take into account 6 specific frequencies, namely the first two order base frequencies corresponding to the approach, flyover and sideline three airworthiness operating conditions. Because the acoustic lining noise reduction is generally for the first two order base frequencies, the airworthiness noise evaluation is for the approach, flyover and sideline three airworthiness operating conditions, each operating condition corresponds to a different rotating speed, that is, corresponds to a different base frequency, so the ideal condition is to reduce noise for the above 6 frequencies. The plurality of acoustic lining areas 12 are the sixth acoustic lining area 126, the fifth acoustic lining area 125, the fourth acoustic lining area 124, the third acoustic lining area 123, the second acoustic lining area 122, and the first acoustic lining area 121 distributed in the direction from the leading edge 101 to the trailing edge 102 in turn, and the corresponding target attenuation frequencies are the sideline condition single tone noise second order base frequency, the first order base frequency of the aviation engine airworthiness condition, the flyover condition single tone noise second order base frequency, the first order base frequency of the aviation engine airworthiness condition, the approach condition single tone noise second order base frequency, the first order base frequency of the aviation engine airworthiness condition, in turn. In some embodiments, the specific structure can be that the side length of the resonant cavity of the first acoustic lining area 121 is a, the corresponding target attenuation frequency is the first order base frequency f of the approach condition single tone noise of the aviation engine airworthiness condition, the side length of the resonant cavity of the second acoustic lining area 122 is 1 / 2a, the corresponding target attenuation frequency is the second order base frequency 2f of the approach condition single tone noise, the side length of the resonant cavity of the third acoustic lining area 123 is 2 / 3a, the corresponding target attenuation frequency is the first order base frequency 1.5f of the flyover condition single tone noise of the aviation engine airworthiness condition, the side length of the resonant cavity of the fourth acoustic lining area 124 is 1 / 3a, the corresponding target attenuation frequency is the second order base frequency 3f of the flyover condition single tone noise of the aviation engine airworthiness condition, the side length of the resonant cavity of the fifth acoustic lining area 125 is 5 / 9a, the corresponding target attenuation frequency is the first order base frequency 1.8f of the sideline condition single tone noise of the aviation engine airworthiness condition, and the side length of the resonant cavity of the sixth acoustic lining area 126 is 5 / 18a, the corresponding target attenuation frequency is the second order base frequency 3.6f of the sideline condition single tone noise of the aviation engine airworthiness condition.

[0076] Based on the above introduction, the application further provides a noise reduction method of a power propulsion system, the power propulsion system comprising a fan and / or a compressor, the noise reduction method comprising: setting an outlet guide vane 10 as introduced in the above embodiments at the outlet end of the fan and / or the compressor, to realize a lightweight noise reduction scheme, taking into account multiple noise reduction frequencies, while also ensuring that the aerodynamic efficiency of the outlet guide vane is relatively high.

[0077] In summary, the beneficial effects of the outlet guide vane, the power propulsion system and the noise reduction method introduced by the above embodiments include but are not limited to the following: through the structure of integrating the sound lining in the outlet guide vane, i.e. the vane body as the rigid back plate of the sound lining, the light weight of the noise reduction structure is realized, at the same time, through the structure that the area of the single resonance cavity of the sound lining area located in the relatively upstream is smaller than the area of the resonance cavity of the sound lining area located in the relatively downstream, the influence of the integrated sound lining structure on the aerodynamic efficiency of the outlet guide vane is reduced on the basis of realizing the light weight of the noise reduction structure, so that the outlet guide vane realizes the light weight of the noise reduction structure on the basis of having the basic function of higher aerodynamic efficiency, in addition, the multiple sound lining areas are arranged to reduce the noise of different flight conditions and / or different orders of fundamental frequency, and the noise reduction effect of the noise reduction structure is optimized.

[0078] Although the present application is disclosed with the preferred embodiments as above, it is not intended to limit the present application, and any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the present application. Therefore, any modification, equivalent change and modification made to the above embodiments according to the technical essence of the present application, which does not depart from the technical solutions of the present application, falls within the protection scope defined by the claims of the present application.

Claims

1. An outlet guide vane (10) characterized by, Comprise: A blade body (1) comprising an acoustic lining (11); The acoustic lining (11) is provided with at least a plurality of acoustic lining areas (12) in the direction from the leading edge (101) to the trailing edge (102) of the outlet guide vane (10), at least comprising a first acoustic lining area (121), and a second acoustic lining area (122) located upstream of the first acoustic lining area (121); Wherein the first acoustic lining area (121) comprises a plurality of first resonant cavities (1211), the second acoustic lining area (122) comprises a plurality of second resonant cavities (1221), the area of a single first resonant cavity (1211) is greater than that of a single second resonant cavity (1221); In the direction from the leading edge (101) to the trailing edge (102), in adjacent acoustic lining areas (12), the area of a single resonant cavity in the relatively downstream acoustic lining area is greater than that of a single resonant cavity in the relatively upstream acoustic lining area; In the direction from the leading edge (101) to the trailing edge (102), in adjacent acoustic lining areas (12), the number of columns of resonant cavities and the number of resonant cavities per column in the relatively downstream acoustic lining area are less than those in the relatively upstream acoustic lining area; The plurality of acoustic lining areas (12) are a sixth acoustic lining area (126), a fifth acoustic lining area (125), a fourth acoustic lining area (124), a third acoustic lining area (123), a second acoustic lining area (122), and a first acoustic lining area (121) distributed in the direction from the leading edge (101) to the trailing edge (102) in turn, and the corresponding target attenuation frequencies are the second order fundamental frequency of the sideline condition single tone noise, the first order fundamental frequency of the sideline condition single tone noise, the second order fundamental frequency of the flyover condition single tone noise, the first order fundamental frequency of the flyover condition single tone noise, the second order fundamental frequency of the approach condition single tone noise, and the first order fundamental frequency of the approach condition single tone noise of the aero-engine in flight condition respectively.

2. Outlet guide vane (10) according to claim 1, characterized in that The resonant cavity side length of the first acoustic lining area (121) is a, the corresponding target attenuation frequency is the first order fundamental frequency f of the approach condition single tone noise of the aero-engine in flight condition, the resonant cavity side length of the second acoustic lining area (122) is 1 / 2a, the corresponding target attenuation frequency is the second order fundamental frequency 2f of the approach condition single tone noise, the resonant cavity side length of the third acoustic lining area (123) is 2 / 3a, the corresponding target attenuation frequency is the first order fundamental frequency 1.5f of the flyover condition single tone noise of the aero-engine in flight condition, the resonant cavity side length of the fourth acoustic lining area (124) is 1 / 3a, the corresponding target attenuation frequency is the second order fundamental frequency 3f of the flyover condition single tone noise of the aero-engine in flight condition, the resonant cavity side length of the fifth acoustic lining area (125) is 5 / 9a, the corresponding target attenuation frequency is the first order fundamental frequency 1.8f of the sideline condition single tone noise of the aero-engine in flight condition, and the resonant cavity side length of the sixth acoustic lining area (126) is 5 / 18a, the corresponding target attenuation frequency is the second order fundamental frequency 3.6f of the sideline condition single tone noise of the aero-engine in flight condition.

3. The outlet guide vane (10) according to claim 1, characterized in that The connecting area (13) of adjacent acoustic lining areas comprises a cementing structure.

4. The outlet guide vane (10) according to claim 1, characterized in that The resonant cavity is a hexagonal honeycomb resonant cavity.

5. The outlet guide vane (10) according to claim 1, characterized in that The surface of the acoustic baffle (11) has perforations (111), each perforation (111) corresponding to each resonant cavity, the corresponding target attenuation frequency of the resonant cavity being obtained by the following formula: ； where F is the target attenuation frequency, k is an empirical coefficient greater than 0, S is the area of the perforation, L is the length of the resonant cavity, and V is the volume of the resonant cavity.

6. Outlet guide vane (10) according to any one of claims 1 to 5, characterized in that The outlet guide vane (10) is integrally formed by additive manufacturing.

7. A power propulsion system characterized by, An aircraft comprising the outlet guide vane (10) according to any one of claims 1-6.

8. The power propulsion system of claim 7, wherein, The power propulsion system is a gas turbine engine, the gas turbine engine comprising a fan and / or a compressor, the outlet end of the fan and / or the compressor being provided with the outlet guide vane (10).

9. A method of noise reduction for a power propulsion system comprising a fan and / or compressor, characterized in that, The noise reduction method comprises providing the outlet end of the fan and / or the compressor with the outlet guide vane (10) according to any one of claims 1-6.

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