Outlet guide vane, power propulsion system and noise reduction method of power propulsion system

Abstract

The invention relates to an outlet guide vane, a power propulsion system and a noise reduction method of the power propulsion system. The outlet guide vane comprises a vane body, and the vane body comprises an acoustic lining part; the acoustic liner part is at least provided with a plurality of acoustic liner areas in the direction from the front edge to the tail edge of the outlet guide vane, and the acoustic liner areas at least comprise the first acoustic liner area and the second acoustic liner area located on the upstream of the first acoustic liner area. Wherein the first acoustic liner region comprises a plurality of first resonant cavities, the second acoustic liner region comprises a plurality of second resonant cavities, and the area of a single first resonant cavity is larger than that of a single second resonant cavity.

Description

Technical Field

[0001] The invention relates to an outlet guide vane, a power propulsion system and a noise reduction method thereof. Background Art

[0002] With the rapid iteration of civil aviation engine products and increasingly fierce market competition, high noise and heavy weight issues have become unavoidable problems for all research companies. Whether the engine can reasonably reduce weight involves the core competitive standard of fuel consumption, and the sound radiation level of the engine to the airport during takeoff and landing is limited by the stringent requirements of the International Civil Aviation Organization (ICAO). The latest airworthiness noise clauses require new civil aircraft to adopt more stringent fifth-stage noise airworthiness standards, which further reduce the cumulative noise margin by 7dB compared to the fourth stage. Low-noise design and lightweight design that take into account aerodynamic efficiency are becoming increasingly important in the design stage of new-generation aircraft engine products.

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

[0004] In order to solve the above problems, existing solutions such as Figure 1 As shown, the fan of the gas turbine engine includes fan rotor blades 1001 and outlet guide vanes 1002, and acoustic liners 1004 are arranged on the inner wall surfaces of the air inlet, the fan casing and the outer duct to absorb and attenuate the sound energy of the above-mentioned single-tone noise, while broadening the sound absorption frequency band as much as possible to take into account broadband.

[0005] Acoustic lining is the most important propagation noise reduction technology that has been widely used, especially for civil turbofan engines with large bypass ratio. The structure of the existing acoustic lining 1004 is as follows: Figure 2A as well as Figure 2B As shown, it generally includes a perforated plate 1005, a honeycomb cavity 1006 and a rigid back plate 1007. Figure 2A as well as Figure 2B As shown (taking a single layer, i.e., a single degree of freedom acoustic lining structure as an example), it can be regarded as a large number of permutations and combinations of Helmholtz resonant cavities. The acoustic resistance is determined by the micropores, and the size of the resonant cavity determines its resonant frequency, i.e., the acoustic reactance. After the sound wave of a specific frequency passes through the small hole 10051 on the perforated plate 1005 and enters the honeycomb cavity 1006, it will resonate, 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 parameter design of the hole and cavity generally requires a multi-parameter optimized forward design to find the best noise reduction effect.

[0006] The solutions introduced above still need to further improve the lightweight performance so as to meet the lightweight requirements of gas turbine engines on the basis of achieving noise reduction. Summary of the invention

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

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

[0009] Another object of the present invention is to provide a noise reduction method for a power propulsion system.

[0010] According to a first aspect of the present invention, an outlet guide vane comprises a blade body, wherein the blade body comprises an acoustic lining portion; the acoustic lining portion is provided with at least a plurality of acoustic lining areas along a direction from a leading edge to a trailing edge of the outlet guide vane, comprising at least a first acoustic lining area and a second acoustic lining area located upstream of the first acoustic lining area; wherein the first acoustic lining area comprises a plurality of first resonance cavities, the second acoustic lining area comprises a plurality of second resonance cavities, and the area of ​​a single first resonance cavity is larger than that of a single second resonance cavity.

[0011] In one or more embodiments of the outlet guide vane, in the direction from the leading edge to the trailing edge, among adjacent acoustic liner regions, an area of ​​a single resonance cavity of an acoustic liner region located relatively downstream is larger than an area of ​​a single resonance cavity of an acoustic liner region located relatively upstream.

[0012] In one or more embodiments of the outlet guide vane, in the direction from the leading edge to the trailing edge, in adjacent acoustic liner areas, the number of rows of arrangement of resonance cavities and the number of resonance cavities in each row of the acoustic liner area located relatively downstream are both smaller than the area of ​​the resonance cavities of the acoustic liner area relatively upstream.

[0013] In one or more embodiments of the outlet guide vane, the multiple acoustic lining areas are a sixth acoustic lining area, a fifth acoustic lining area, a fourth acoustic lining area, a third acoustic lining area, a second acoustic lining area, and a first acoustic lining area, which are sequentially distributed from the leading edge to the trailing edge, and the corresponding target attenuation frequencies are the second-order fundamental frequency and the first-order fundamental frequency of the single-tone noise of the edge condition of the aircraft engine's airworthiness condition, the second-order fundamental frequency and the first-order fundamental frequency of the single-tone noise of the flyover condition of the aircraft engine's airworthiness condition, and the second-order fundamental frequency and the first-order fundamental frequency of the single-tone noise of the approach condition of the aircraft engine's airworthiness condition.

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

[0015] In one or more embodiments of the outlet guide vane, the connection region of adjacent acoustic liner sections comprises a glued 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, the surface of the acoustic lining has perforations, each perforation is arranged corresponding to each resonant cavity, and the corresponding target attenuation frequency of the resonant 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 the area of ​​the perforation, L is the length of the resonance cavity, and V is the 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 invention comprises the outlet guide vane as described in the first aspect.

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

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

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

[0025] By integrating the structure of the acoustic liner in the outlet guide vane, that is, the blade body serves as the rigid back plate of the acoustic liner, the lightweight of the noise reduction structure is achieved. At the same time, through the structure of multiple acoustic liner zones, the area of ​​a single resonance cavity of the acoustic liner zone located relatively upstream is smaller than the area of ​​the resonance cavity of the acoustic liner zone located relatively downstream. On the basis of achieving the lightweight of the noise reduction structure, the influence of the integrated acoustic liner structure on the aerodynamic efficiency of the outlet guide vane is reduced, so that the outlet guide vane achieves the lightweight of the noise reduction structure on the basis of the basic function of having high aerodynamic efficiency. In addition, multiple acoustic liner zones are provided to take into account the noise reduction of noises of different airworthiness conditions and / or fundamental frequencies of different orders, thereby optimizing the noise reduction effect of the noise reduction structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which:

[0027] Figure 1 The present invention is a schematic diagram of the structure of a gas turbine engine of an existing scheme.

[0028] Figure 2A as well as Figure 2B The present invention is a schematic diagram of the structure of a sound liner of an existing solution.

[0029] Figure 3 It is a schematic diagram of the structure of the outlet guide vane of a comparison scheme.

[0030] Figure 4 It is a schematic diagram of the structure of the surface of an outlet guide vane in one embodiment.

[0031] Figure 5 It is a schematic diagram of the structure of the resonance cavity of multiple acoustic liner areas of an outlet guide vane according to one embodiment.

[0032] Reference numerals:

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

[0034] 101-front edge,

[0035] 102 - trailing edge,

[0036] 1- Blade body,

[0037] 11- Acoustic lining,

[0038] 111-Piercing,

[0039] 12-sound lining area,

[0040] 121-first sound lining area,

[0041] 1211-First resonant cavity,

[0042] 122-second sound lining area,

[0043] 1221-second resonance cavity,

[0044] 123-third sound lining area,

[0045] 124-the fourth sound lining area,

[0046] 125-Fifth tone lining area,

[0047] 126-second sound lining area,

[0048] 13- Connection area,

[0049] 1001-Fan rotor blades,

[0050] 1004- Acoustic Lining,

[0051] 1005-perforated plate,

[0052] 10051-small hole,

[0053] 1006-honeycomb cavity,

[0054] 1007 - Rigid back panel. DETAILED DESCRIPTION

[0055] The present invention is further described below in conjunction with specific embodiments and drawings. More details are elaborated in the following description to facilitate a full understanding of the present invention. However, the present invention can obviously be implemented in a variety of other ways different from the description herein. Those skilled in the art can make similar generalizations and deductions based on actual application situations without violating the connotation of the present invention. Therefore, the protection scope of the present invention should not be limited by the content of this specific embodiment.

[0056] At the same time, the present application uses specific words to describe the embodiments of the present application, such as "one embodiment", "an embodiment", and / or "some embodiments" to refer to a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" mentioned twice or more in different locations in this specification does not necessarily refer to the same embodiment. In addition, certain features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0057] The outlet guide vane 10 described in the following embodiment is applied to a gas turbine engine, specifically, a fan of a turbofan engine is taken as an example, the gas turbine engine includes a fan and / or a compressor, and an outlet guide vane is provided at the outlet end of the fan and / or the compressor. However, it is not limited to this, and can be applied to any power propulsion system, including a power propulsion system with a fan, blades, propeller fan, etc., and is not limited to a gas turbine engine. For example, it can be a hybrid propulsion system including a gas turbine engine, or a pure electric drive power propulsion system with a fan, blades, and propeller fan, so as to reduce the fan noise and / or the intake noise of the compressor.

[0058] Existing solutions include Figure 1 As shown, acoustic liners 1004 are provided on the inner wall surfaces of the air inlet 1001, the fan casing 1002 and the outer duct 1003 of the gas turbine engine to absorb and attenuate the sound energy of the above-mentioned single-tone noise, while broadening the sound absorption frequency band as much as possible to take into account broadband.

[0059] Acoustic lining is the most important propagation noise reduction technology that has been widely used, especially for civil turbofan engines with large bypass ratio. The structure of the existing acoustic lining 1004 is as follows: Figure 2A as well as Figure 2B As shown, it generally includes a perforated plate 1005, a honeycomb cavity 1006 and a rigid back plate 1007. After a sound wave of a certain frequency enters the honeycomb cavity 1006 through a small hole 10051 on the perforated plate 1005, resonance is generated to form a resonant cavity with an open top and a closed bottom. A common resonant cavity is a Helmholtz resonator. After the sound enters the resonant cavity through the small hole on the surface of the sound liner, it resonates in the resonant cavity and dissipates the sound energy. Its damping mechanism is usually mainly due to the dissipation of the vibration jet at the resonator orifice.

[0060] In order to achieve the lightness of the gas turbine engine with the acoustic liner structure, in a comparative scheme, as Figure 3 As shown, an acoustic lining structure is integrated into an outlet guide vane 100 of the fan. Specifically, the outlet guide vane 100 includes a blade body 1 , and an acoustic lining portion 11 is provided on the blade body 1 . Figure 3 In the structure shown, the acoustic lining portion 11 can be a groove-shaped area opened in the blade body 1, the blade body 1 serves as a rigid backing plate of the acoustic lining, a porous structure is arranged on the surface of the blade body 1 to form a perforated plate, and a honeycomb cavity is arranged in the thickness extending from the surface of the blade body 1 to the inside. It can be understood that although Figure 3 The form is similar to a decomposed exploded diagram, which is to more clearly show the guide vane integrated acoustic liner structure. In fact, an one-piece molding manufacturing process is generally adopted, such as an additive manufacturing process to obtain the outlet guide vane, in order to improve the yield rate of complex structure molding.

[0061] But the inventors found that Figure 3 The outlet guide vane 100 of the comparative solution shown in the figure can play a certain role in weight reduction, but the function of the outlet guide vane itself is to rectify the tail flow of the fan rotor blade and convert it into axial air outlet. Figure 3 The structure of the outlet guide vane 100 will have a large aerodynamic loss.

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

[0063] refer to Figure 4 as well as Figure 5 As shown, in some embodiments, the outlet guide vane 10 includes a blade body 1, and the blade body 1 includes an acoustic lining portion 11; the acoustic lining portion 11 is provided with at least a plurality of acoustic lining areas 12 along the direction from the leading edge 101 to the trailing edge 102 of the outlet guide vane 10, including at least 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 includes a plurality of first resonance cavities 1211, and the second acoustic lining area 122 includes a plurality of second resonance cavities 1221, and the area of ​​a single first resonance cavity 1211 is larger than that of a single second resonance cavity 1221. The structure of the outlet guide vane 10 integrating the acoustic lining, that is, the way of integrating the resonance cavity, the perforated plate, and the rigid back plate, is similar to Figure 3 The structure of the outlet guide vane 100 shown is similar and will not be described here in detail. It can be understood that the area of ​​a single resonance cavity here refers to the cross-sectional area of ​​a single resonance cavity, and the dimension of the cross-sectional area generally needs to be much smaller than the wavelength of the sound wave corresponding to the noise reduction.

[0064] The division of different acoustic lining areas here is based on the area size of the single resonance cavity corresponding to the different acoustic lining areas, so as to deal with noises of different frequencies. For the same shape, such as a honeycomb resonance cavity of a regular hexagon, different areas correspond to noises of different specific frequencies. For example, the surface of the acoustic lining portion 11 has a perforation 111, each perforation 111 is arranged corresponding to each resonance cavity, and generally the perforation 111 is located at the center of each resonance cavity. The corresponding target attenuation frequency of the resonance 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 resonance cavity, and V is the volume of the resonance cavity.

[0067] For a hexagonal resonant cavity, the formula for calculating the area of ​​the parallelepiped is:

[0068] Where A is the area of ​​the side length.

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

[0070]

[0071] The area A of the hexagonal resonance cavity is the side length area, and the volume of the resonance cavity can be approximated as P*H, where H is the cavity depth. Since the cavity depth and perforation shape of the resonance cavities in different acoustic liner areas are the same inside the outlet guide vane 10, it can be simply considered that F is inversely proportional to A, that is, the longer the side length of a single resonance 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 liner area 121 and the second acoustic liner area 122 is only for describing adjacent acoustic liner areas, and does not mean that the blade has only two acoustic liner areas. Figure 4 as well as Figure 5 As shown, the number of acoustic lining areas may be 6. For details, please refer to the following introduction.

[0073] Preferably, if Figure 4 as well as Figure 5 As shown, in some embodiments, in the direction from the leading edge 101 to the trailing edge 102, in adjacent acoustic liner areas 12, the area of ​​a single resonant cavity in the relatively downstream acoustic liner area is larger than the area of ​​a single resonant cavity in the relatively upstream acoustic liner area. That is, in adjacent acoustic liner areas 12, the number of rows of resonant cavities in the relatively downstream acoustic liner area and the number of resonant cavities in each row are smaller than the area of ​​resonant cavities in the relatively upstream acoustic liner area. Such a beneficial effect is that, Figure 5 As shown, the cross-sectional area of ​​a single resonance 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 changes from sparse to dense, especially at the trailing edge where the flow loss is more obvious, the loosest arrangement is used. The inventors have found that such a structure can minimize the impact of the addition of the acoustic liner on the aerodynamic efficiency, thereby ensuring the aerodynamic efficiency of the outlet guide vane.

[0074] In some embodiments, reference Figure 5 As shown, the connection area 13 of adjacent acoustic lining areas can be a glued structure. However, this is not a limitation. For example, if the noise scattering problem caused by the joint is taken into consideration, it can also be processed into a cavity in each area and supplemented with perforations to form an irregular acoustic lining unit. However, the inventors found that the area of ​​the connection area 13 is very small and the optimization effect is limited. Therefore, a glued structure can be used. Such a structure is relatively light and stable. It can be understood that other light and stable connection methods can also be used.

[0075] refer to Figure 4 , Figure 5As shown, in some embodiments, according to the current airworthiness regulations, the outlet guide vane 10 can be set to take into account 6 specific frequencies, namely, the first two fundamental frequencies corresponding to the three airworthiness conditions of approach, flyover and sideline. Because the noise reduction of the acoustic liner is generally aimed at the first two fundamental frequencies, the airworthiness noise assessment is aimed at the three airworthiness conditions of approach, flyover and sideline, and each condition corresponds to a different rotation speed, that is, a different fundamental frequency, so the ideal situation is to be able to reduce the noise of the above 6 frequencies. 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, which are sequentially distributed from the leading edge 101 to the trailing edge 102, and the corresponding target attenuation frequencies are the second-order fundamental frequency and the first-order fundamental frequency of the single-tone noise of the sideline working condition of the aircraft engine airworthiness working condition, the second-order fundamental frequency and the first-order fundamental frequency of the single-tone noise of the flyover working condition of the aircraft engine airworthiness working condition, and the second-order fundamental frequency and the first-order fundamental frequency of the single-tone noise of the approach working condition of the aircraft engine airworthiness working condition. In some embodiments, the specific structure may be that the side length of the resonance cavity of the first acoustic liner area 121 is a, and the corresponding target attenuation frequency is the first-order fundamental frequency f of the single-tone noise of the approach condition of the aircraft engine airworthiness condition; the side length of the resonance cavity of the second acoustic liner area 122 is 1 / 2a, and the corresponding target attenuation frequency is the second-order fundamental frequency 2f of the single-tone noise of the approach condition; the side length of the resonance cavity of the third acoustic liner area 123 is 2 / 3a, and the corresponding target attenuation frequency is the first-order fundamental frequency 1.5f of the single-tone noise of the flyover condition of the aircraft engine airworthiness condition; The side length of the resonance cavity of the fourth acoustic lining area 124 is 1 / 3a, and the corresponding target attenuation frequency is 3f, the second-order fundamental frequency of the single-tone noise in the flyover condition of the aircraft engine's airworthiness condition; the side length of the resonance cavity of the fifth acoustic lining area 125 is 5 / 9a, and the corresponding target attenuation frequency is 1.8f, the first-order fundamental frequency of the single-tone noise in the sideline condition of the aircraft engine's airworthiness condition; the side length of the resonance cavity of the sixth acoustic lining area 126 is 5 / 18a, and the corresponding target attenuation frequency is 3.6f, the second-order fundamental frequency of the single-tone noise in the sideline condition of the aircraft engine's airworthiness condition.

[0076] As introduced above, the present application also provides a noise reduction method for a power propulsion system, the power propulsion system includes a fan and / or a compressor, and the noise reduction method includes setting an outlet guide vane 10 as described in the above embodiment at the outlet end of the fan and / or the compressor to achieve a lightweight noise reduction solution, while taking into account multiple noise reduction frequencies, also ensuring that the aerodynamic efficiency of the outlet guide vane is high.

[0077] In summary, the beneficial effects of the outlet guide vane, power propulsion system and noise reduction method thereof introduced in the above embodiments include but are not limited to: by integrating the structure of the acoustic liner in the outlet guide vane, that is, the blade body serves as the rigid back plate of the acoustic liner, thereby achieving lightweight noise reduction structure; at the same time, through the structure of multiple acoustic liner zones, the area of ​​a single resonance cavity of the acoustic liner zone located relatively upstream is smaller than the area of ​​the resonance cavity of the acoustic liner zone located relatively downstream, so that on the basis of achieving lightweight noise reduction structure, the influence of the integrated acoustic liner structure on the aerodynamic efficiency of the outlet guide vane is reduced, so that the outlet guide vane achieves lightweight noise reduction structure on the basis of having the basic function of high aerodynamic efficiency; in addition, multiple acoustic liner zones are provided to take into account the noise reduction of noises of different airworthiness conditions and / or fundamental frequencies of different orders, thereby optimizing the noise reduction effect of the noise reduction structure.

[0078] Although the present invention is disclosed as above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope defined by the claims of the present invention.

Claims

1. An outlet guide vane (10), characterized in that: include: A blade body (1), the blade body (1) comprising an acoustic lining portion (11); The acoustic lining portion (11) is provided with at least a plurality of acoustic lining areas (12) along a direction from a leading edge (101) to a trailing edge (102) of the outlet guide vane (10), including at least a first acoustic lining area (121) and a second acoustic lining area (122) located upstream of the first acoustic lining area (121); The first acoustic liner area (121) includes a plurality of first resonance cavities (1211), the second acoustic liner area (122) includes a plurality of second resonance cavities (1221), and the area of ​​a single first resonance cavity (1211) is larger than that of a single second resonance cavity (1221).

2. The outlet guide vane (10) according to claim 1, characterized in that: In the direction from the leading edge (101) to the trailing edge (102), in adjacent acoustic liner areas (12), the area of ​​a single resonance cavity of the acoustic liner area located relatively downstream is larger than the area of ​​a single resonance cavity of the acoustic liner area located relatively upstream.

3. The outlet guide vane (10) according to claim 1, characterized in that: In the direction from the leading edge (101) to the trailing edge (102), in the adjacent acoustic liner areas (12), the number of rows of resonant cavities in the relatively downstream acoustic liner area and the number of resonant cavities in each row are both smaller than the resonant cavity area of ​​the relatively upstream acoustic liner area.

4. The outlet guide vane (10) according to claim 1, characterized in that: 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) which are sequentially distributed in a direction from a leading edge (101) to a trailing edge (102), and the corresponding target attenuation frequencies are respectively and sequentially corresponding to the second-order fundamental frequency and the first-order fundamental frequency of the single-tone noise of the sideline working condition of the aircraft engine airworthiness working condition, the second-order fundamental frequency and the first-order fundamental frequency of the single-tone noise of the flyover working condition of the aircraft engine airworthiness working condition, and the second-order fundamental frequency and the first-order fundamental frequency of the single-tone noise of the approach working condition of the aircraft engine airworthiness working condition.

5. The outlet guide vane (10) according to claim 4, characterized in that: The side length of the resonance cavity of the first acoustic lining area (121) is a, and the corresponding target attenuation frequency is the first-order fundamental frequency f of the single-tone noise of the approach condition of the aircraft engine airworthiness condition; the side length of the resonance cavity of the second acoustic lining area (122) is 1 / 2a, and the corresponding target attenuation frequency is the second-order fundamental frequency 2f of the single-tone noise of the approach condition; the side length of the resonance cavity of the third acoustic lining area (123) is 2 / 3a, and the corresponding target attenuation frequency is the first-order fundamental frequency 1.5f of the single-tone noise of the flyover condition of the aircraft engine airworthiness condition; and the side length of the resonance cavity of the fourth acoustic lining area (1 The side length of the resonance cavity of the fifth acoustic lining area (125) is 5 / 9a, and the corresponding target attenuation frequency is 1.8f, which is the first order fundamental frequency of the single-tone noise of the sideline condition of the aircraft engine airworthy working condition. The side length of the resonance cavity of the sixth acoustic lining area (126) is 5 / 18a, and the corresponding target attenuation frequency is 3.6f, which is the second order fundamental frequency of the single-tone noise of the sideline condition of the aircraft engine airworthy working condition.

6. The outlet guide vane (10) according to claim 1, characterized in that: The connection area (13) of adjacent acoustic liner zones comprises an adhesive bond.

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

8. The outlet guide vane (10) according to claim 1, characterized in that: The surface of the acoustic lining portion (11) has perforations (111), each perforation (111) is arranged corresponding to each resonance cavity, and the corresponding target attenuation frequency of the resonance cavity is obtained by the following formula: 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 resonance cavity, and V is the volume of the resonance cavity.

9. The outlet guide vane (10) according to any one of claims 1 to 8, characterized in that: The outlet guide vane (10) is integrally formed by additive manufacturing.

10. A power propulsion system, characterized in that: It comprises the outlet guide vane (10) as claimed in any one of claims 1 to 9.

11. The propulsion system according to claim 10, characterized in that: The power propulsion system is a gas turbine engine, which includes a fan and / or a compressor, and the outlet end of the fan and / or the compressor is provided with the outlet guide vane (10).

12. A method for reducing noise of a power propulsion system, the power propulsion system comprising a fan and / or a compressor, characterized in that: The noise reduction method comprises providing an outlet guide vane (10) as claimed in any one of claims 1 to 9 at the outlet end of the fan and / or compressor.

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