CN119532247B - Outlet guide vane, power propulsion system and noise reduction method thereof - Google Patents
Outlet guide vane, power propulsion system and noise reduction method thereofInfo
- Publication number
- CN119532247B CN119532247B CN202311117943.8A CN202311117943A CN119532247B CN 119532247 B CN119532247 B CN 119532247B CN 202311117943 A CN202311117943 A CN 202311117943A CN 119532247 B CN119532247 B CN 119532247B
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- China
- Prior art keywords
- acoustic liner
- resonant cavity
- region
- acoustic
- guide vane
- Prior art date
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/663—Sound attenuation
- F04D29/665—Sound attenuation by means of resonance chambers or interference
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
本发明涉及一种出口导流叶片、动力推进系统及其降噪方法。其中，出口导流叶片包括叶片本体，所述叶片本体包括声衬部；所述声衬部沿所述出口导流叶片的前缘至尾缘的方向至少设置有多个声衬区，至少包括第一声衬区，以及位于所述第一声衬区上游的第二声衬区；其中，第一声衬区包括多个第一共振腔、第二声衬区包括多个第二共振腔，单个所述第一共振腔的面积大于单个所述第二共振腔。
This invention relates to an outlet guide vane, a propulsion system, and a noise reduction method thereof. The outlet guide vane includes a vane body, which includes an acoustic liner. The acoustic liner has at least a plurality of acoustic liner regions along the direction from the leading edge to the trailing edge of the outlet guide vane, including at least a first acoustic liner region and a second acoustic liner region located upstream of the first acoustic liner region. The first acoustic liner region includes a plurality of first resonant cavities, and the second acoustic liner region includes a plurality of second resonant cavities, wherein the area of a single first resonant cavity is larger than that of a single second resonant cavity.
Description
Technical Field
The invention relates to an outlet guide vane, a power propulsion system and a noise reduction method thereof.
Background
With the trend of rapid iteration of civil aviation engine products and market competition, the problems of high noise and heavy weight become the problem that all research enterprises cannot bypass, whether an engine can reasonably reduce weight, the core competition standard of oil consumption is involved, and the sound radiation level of the engine to an airport in the take-off and landing stages is limited by the severe requirements of the International Civil Aviation Organization (ICAO), the latest airworthiness noise clause at present requires a novel civil airliner to adopt a harsher fifth-stage noise airworthiness standard, and the accumulated noise margin of the fourth stage is further reduced by 7dB. Low noise designs and lightweight designs that compromise aerodynamic efficiency are becoming increasingly important in the design phase of new generation aircraft engine products.
For low noise designs, large bypass is most contributing to fan/compressor noise than high speed turbofan engines in general, where the static-rotating interference noise is an important component of it, which occurs spectrally at an integer multiple of the BPF (Blade passing Frequency, the product of the number of blades and the rotational frequency, also known as the fundamental frequency), and is therefore also known as single tone noise.
In order to solve the above problems, as shown in fig. 1, a fan of a gas turbine engine includes a fan rotor blade 1001 and an outlet guide vane 1002, and an acoustic liner 1004 is provided on the inner wall surfaces of an intake duct, a fan casing, and an outer duct, so that the noise energy absorption and attenuation are performed for the single noise, and the sound absorption frequency band is widened as much as possible to achieve a broad frequency.
Acoustic liners are the most widely used technology for noise reduction by propagation, and are particularly suitable for large-bypass-ratio civil turbofan engines, and the structure of the existing acoustic liner 1004, as shown in fig. 2A and 2B, generally comprises a perforated plate 1005, a honeycomb cavity 1006 and a rigid back plate 1007, as shown in fig. 2A and 2B (a single-layer, i.e., single-degree-of-freedom acoustic liner structure is taken as an example), and can be regarded as an arrangement combination of a large number of helmholtz resonance cavities. The acoustic resistance is determined by the micro-holes, the size of the resonant cavity determines the resonant frequency, namely the acoustic reactance, and the acoustic wave with specific frequency can generate resonance after entering the honeycomb cavity 1006 through the small holes 10051 on the perforated plate 1005, so that the acoustic energy is converted into energy which is consumed, and the two are matched, thereby achieving the purpose of noise reduction under specific frequency. The specific parameter design of the hole and the cavity generally needs to be forward-direction design with multi-parameter optimization at present so as to find the optimal noise reduction effect.
The solution described above still needs to further improve the light-weight performance to meet the light-weight requirements of the gas turbine engine on the basis of achieving noise reduction.
Disclosure of Invention
It is an object of the present invention to provide an outlet guide vane.
It is another object of the present invention to provide a powered propulsion system.
It is yet another object of the present invention to provide a method of reducing noise in a power propulsion system.
According to the first aspect of the invention, the outlet guide vane comprises a vane body, wherein the vane body comprises a sound lining part, the sound lining part is at least provided with a plurality of sound lining areas along the direction from the front edge to the tail edge of the outlet guide vane, the sound lining part at least comprises a first sound lining area and a second sound lining area positioned upstream of the first sound lining area, the first sound lining area comprises a plurality of first resonant cavities, the second sound lining area comprises a plurality of second resonant cavities, and the area of each first resonant cavity is larger than that of each second resonant cavity.
In one or more embodiments of the outlet guide vane, in the direction of the leading edge to the trailing edge, in the adjacent acoustic liner region, the area of the individual resonant cavity of the acoustic liner region located relatively downstream is larger than the area of the individual resonant cavity of the acoustic liner region located relatively upstream.
In one or more embodiments of the outlet guide vane, in the direction from the leading edge to the trailing edge, in the adjacent acoustic liner region, the number of columns of arranged resonant cavities of the acoustic liner region located relatively downstream, the number of resonant cavities of each column, are smaller than the resonant cavity area of the acoustic liner region located relatively upstream.
In one or more embodiments of the outlet guide vane, the plurality of acoustic liner regions are a sixth acoustic liner region, a fifth acoustic liner region, a fourth acoustic liner region, a third acoustic liner region, a second acoustic liner region and a first acoustic liner region which are sequentially distributed from the leading edge to the trailing edge, and the corresponding target attenuation frequencies are a second-order fundamental frequency, a first-order fundamental frequency, a second-order fundamental frequency, and a first-order fundamental frequency of edge operating mode single sound noise of aeroengine navigable operating mode, which are sequentially corresponding to aeroengine navigable operating mode respectively.
In one or more embodiments of the outlet guide vane, the resonant cavity side length of the first acoustic liner region is a, the resonant cavity side length of the second acoustic liner region is 1/2a, the resonant cavity side length of the second acoustic liner region is 2/3a, the resonant cavity side length of the third acoustic liner region is 1.5f, the resonant cavity side length of the fourth acoustic liner region is 1/3a, the resonant cavity side length of the target attenuation region is 3f, the resonant cavity side length of the fifth acoustic liner region is 5/9a, the resonant cavity side length of the target attenuation region is 1.8f, the resonant cavity side length of the sixth acoustic liner region is 5/18a, and the resonant cavity side length of the target attenuation region is 3.6f.
In one or more embodiments of the outlet guide vane, the connection region of adjacent acoustic liner regions comprises a glued joint.
In one or more embodiments of the outlet guide vane, the resonant cavity is a hexagonal honeycomb resonant cavity.
In one or more embodiments of the outlet guide vane, the surface of the acoustic liner has perforations, each perforation being provided for each resonant cavity, the corresponding target attenuation frequency of the resonant cavity being 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 resonant cavity, and V is the volume of the resonant cavity.
In one or more embodiments of the exit guide vane, the exit guide vane is integrally formed by additive manufacturing.
A power propulsion system according to a second aspect of the invention comprises an outlet guide vane as described in the first aspect.
In one or more embodiments of the power propulsion system, the power propulsion system is a gas turbine engine comprising a fan and/or a compressor, the outlet end of which is provided with the outlet guide vane.
A method of noise reduction in a power propulsion system according to a third aspect of the invention, the power propulsion system comprising a fan and/or a compressor, the method comprising providing an outlet guide vane according to the first aspect at an outlet end of the fan and/or the compressor.
The beneficial effects of the invention include, but are not limited to:
Through the structure of the integrated acoustic liner of export guide vane, namely the blade body is as the rigidity backplate of acoustic liner, the lightweight of structure of making an uproar falls has been realized, simultaneously, through a plurality of acoustic liner district, the area of the single resonant cavity of the acoustic liner district that is located relative upper reaches is less than the structure of the resonant cavity of the acoustic liner district that is located relative low reaches, make on the basis of realizing the lightweight of structure of making an uproar falls, the influence of integrated acoustic liner structure to the aerodynamic efficiency of export guide vane has been reduced, make the export guide vane on the basis of having the basic function of higher aerodynamic efficiency, the lightweight of structure of making an uproar falls has been realized, in addition, set up the noise of making an uproar of a uproar district compromise the noise of the fundamental frequency of different seaworthiness operating modes and/or different orders in a plurality of acoustic liner district, optimize the noise reduction effect of structure of making an uproar falls.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description in conjunction with the accompanying drawings and embodiments, in which:
FIG. 1 is a schematic structural view of a prior art solution gas turbine engine.
Fig. 2A and 2B are schematic structural views of an acoustic liner of a prior art design.
FIG. 3 is a schematic view of a comparative outlet guide vane.
FIG. 4 is a schematic view of the surface of an embodiment of an exit guide vane.
FIG. 5 is a schematic structural view of a resonant cavity of a plurality of acoustic liner regions of an outlet guide vane of an embodiment.
Reference numerals:
10. 100, 1002-an outlet guide vane,
101-The front edge of the wafer,
102-The trailing edge of the strip,
1-A blade body, wherein the blade body is provided with a plurality of blades,
An 11-sound liner portion, the sound liner portion,
The hole is formed in the shape of a 111-hole,
A 12-acoustic liner region,
121-A first acoustic liner region,
1211-A first resonant cavity,
122-A second acoustic backing region,
1221-A second resonant cavity, the second resonant cavity,
123-A third acoustic liner region,
124-A fourth acoustic liner region,
125-A fifth acoustic liner region,
126-A second acoustic backing region,
A 13-connection region, which is provided in the region of the first connecting member,
1001-The fan rotor blade(s),
1004-An acoustic liner of the type described above,
1005-A perforated plate,
10051-The small holes are formed in the glass,
1006-A honeycomb cavity,
1007-Rigid back plate.
Detailed Description
The present invention will be further described with reference to specific embodiments and drawings, in which more details are set forth in the following description in order to provide a thorough understanding of the present invention, but it will be apparent that the present invention can be embodied in many other forms than described herein, and that those skilled in the art may make similar generalizations and deductions depending on the actual application without departing from the spirit of the present invention, and therefore should not be construed to limit the scope of the present invention in terms of the content of this specific embodiment.
Meanwhile, the present application uses specific words to describe embodiments of the present application, such as "one embodiment," "an embodiment," and/or "some embodiments" means that a certain feature, structure, or characteristic is associated with at least one embodiment of the present application. Thus, it should be emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" in various positions in this specification are not necessarily referring to the same embodiment. Furthermore, certain features, structures, or characteristics of one or more embodiments of the application may be combined as suitable.
The following embodiments describe the outlet guide vane 10 as applied to a gas turbine engine, in particular, a fan of a turbofan engine, for example, 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. However, the present invention is not limited thereto, and the power propulsion system may be applied to a power propulsion system having a fan, a blade, a propeller, etc., and may also be applied to a gas turbine engine, for example, a hybrid power propulsion system including a gas turbine engine, or a power propulsion system having a fan, a blade, a propeller, etc., which is driven purely to reduce fan noise and/or intake noise of a compressor.
As shown in fig. 1, in the conventional art, acoustic liners 1004 are provided on inner wall surfaces of an intake duct 1001, a fan casing 1002, and an outer duct 1003 of a gas turbine engine, and acoustic energy absorption and attenuation are performed for the single noise, and the sound absorption frequency band is widened as much as possible to achieve both of the wide frequency band.
Acoustic liners are the most widely used propagation noise reduction technology, and are particularly suitable for large bypass ratio civil turbofan engines, and the structure of the existing acoustic liner 1004 is shown in fig. 2A and 2B, and generally comprises a perforated plate 1005, a honeycomb cavity 1006 and a rigid back plate 1007. After the sound wave with fixed frequency enters the honeycomb cavity 1006 through the small holes 10051 on the perforated plate 1005, resonance is generated, so that a resonance cavity (resonance cavity) with an open top and a closed bottom is formed, a common resonance cavity is provided with a Helmholtz type resonator, and after the sound enters the resonance cavity through the small holes on the surface of the sound liner, the sound is resonated in the resonance cavity to dissipate sound energy. Its damping mechanism is usually mainly due to the dissipation of the vibration jet accompanying the resonator orifice.
In order to achieve the light weight of the gas turbine engine having the acoustic liner structure, in a comparative example, as shown in fig. 3, the acoustic liner structure is integrated in the outlet guide vane 100 of the fan, specifically, the outlet guide vane 100 includes the vane body 1, and the acoustic liner portion 11 is provided in the vane body 1. In the structure illustrated in fig. 3, the acoustic liner 11 may be a groove-shaped region formed in the blade body 1, the blade body 1 is a rigid back plate of the acoustic liner, a porous structure is provided on the surface of the blade body 1 to form a perforated plate, and a honeycomb cavity is provided in a thickness extending from the surface of the blade body 1 to the inside. It will be appreciated that although the form of fig. 3 is similar to an exploded view, for the sake of more clarity in showing the integrated acoustic liner structure of the guide vane, it is generally practical to use an integrally formed manufacturing process, such as an additive manufacturing process, to obtain the outlet guide vane, so as to improve the yield of complex structural formation.
However, the inventor has found that although the comparative outlet guide vane 100 shown in fig. 3 may perform a certain light weight function, the outlet guide vane itself functions to rectify and convert the wake of the fan rotor blade into axial air, and with the structure of fig. 3, there is a large aerodynamic loss of the outlet guide vane 100.
Based on the above, the inventor has invented a new structure of the outlet guide vane, which not only has better noise reduction and light weight effects, but also can ensure better aerodynamic efficiency of the outlet guide vane.
Referring to fig. 4 and 5, in some embodiments, the outlet guide vane 10 includes a vane body 1, the vane body 1 including an acoustic liner 11, the acoustic liner 11 being provided with at least a plurality of acoustic liner regions 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 liner region 121, and a second acoustic liner region 122 located upstream of the first acoustic liner region 121, wherein the first acoustic liner region 121 includes a plurality of first resonant cavities 1211, the second acoustic liner region 122 includes a plurality of second resonant cavities 1221, and the area of the single first resonant cavity 1211 is larger than the area of the single second resonant cavity 1221. The structure of the outlet guide vane 10 integrated with the acoustic liner, i.e. the resonant cavity, the perforated plate, and the rigid back plate, is similar to the structure of the outlet guide vane 100 shown in fig. 3, and will not be described again. It will be appreciated that the area of an individual resonant cavity, referred to herein as the cross-sectional area of the individual resonant cavity, the extent of the cross-sectional area, generally needs to be much smaller than the wavelength of its corresponding noise reducing acoustic wave.
The different acoustic liner regions are divided according to the area of the single resonant cavity corresponding to the different acoustic liner regions, so as to correspondingly process noise with different frequencies. For a same shape, e.g. a honeycomb-shaped resonant cavity, typically a regular hexagon, different areas correspond to different specific frequencies of noise. For example, the surface of the acoustic liner 11 has perforations 111, each perforation 111 being disposed corresponding to each resonant cavity, typically the perforation 111 being located at the center of each resonant cavity, the corresponding target attenuation frequency of the resonant cavity being obtained by the following equation:
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.
For a hexagonal resonant cavity, the parallel hexagonal area calculation formula is:
wherein A is the side length area.
The relationship between the resonant frequency (i.e., the target attenuation frequency) F and a is:
The hexagonal area A of the resonant cavity is the side length area, the volume of the resonant cavity can be approximately P.H, and H is the cavity depth. Since the cavity depths, perforations, of the resonant cavities of the different acoustic liner regions are identical inside the outlet guide vane 10, it can be simply considered that F is inversely related 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.
It will be appreciated that the description of the first acoustic backing region 121, the second acoustic backing region 122 above is for the purpose of describing adjacent acoustic backing regions only, and does not mean that the vane has only two acoustic backing regions, for example, the acoustic backing regions may be 6 as shown in fig. 4 and 5. Particularly as described below.
Preferably, as shown in fig. 4 and 5, in some embodiments, in the direction of the leading edge 101 to the trailing edge 102, in adjacent acoustic liner regions 12, the area of the individual resonant cavities of the acoustic liner regions located relatively downstream is greater than the area of the individual resonant cavities of the acoustic liner regions located relatively upstream. That is, in the adjacent acoustic liner region 12, the number of columns of the arrangement of the resonant cavities in the acoustic liner region located relatively downstream and the number of resonant cavities in each column are smaller than the resonant cavity area of the acoustic liner region located relatively upstream. The beneficial effects are that as shown in fig. 5, the cross-sectional area of the single resonant cavity gradually increases from the front edge to the tail edge, and the perforations are always in the center of the cross-sectional area, so that the perforation arrangement is from sparse to dense, especially the most loose arrangement is used at the tail edge with obvious flow loss, and the inventor finds that the structure can reduce the influence on the aerodynamic efficiency caused by adding an acoustic liner to the greatest extent, and ensures the aerodynamic efficiency of the outlet guide vane.
In some embodiments, as shown with reference to fig. 5, the connection region 13 of adjacent acoustic liner regions may be a glued structure. However, the present invention is not limited thereto, and for example, if considering the problem of noise scattering caused by the joint, it is possible to process the joint into a divided cavity and use the perforated hole as an irregular acoustic liner unit, but the inventors have found that the area of the connection region 13 is small and the optimum effect is limited, and thus, a glued structure is adopted, and the structure is light and stable, and it is understood that other light and stable connection methods may be adopted.
Referring to fig. 4 and 5, in some embodiments, for the current airworthiness regulations, the provision of the outlet guide vane 10 may consider 6 specific frequencies, namely, the first two fundamental frequencies corresponding to the three airworthiness conditions of approach, fly-over and side line. Because acoustic liner noise reduction is generally aimed at the first two-order fundamental frequency, and airworthiness noise evaluation is aimed at three airworthiness working conditions of approach, fly-over and side line, each working condition corresponds to different rotation speeds, namely corresponds to different fundamental frequency, the ideal situation is that the above 6 frequencies can be subjected to noise reduction. The plurality of acoustic liner regions 12 are a sixth acoustic liner region 126, a fifth acoustic liner region 125, a fourth acoustic liner region 124, a third acoustic liner region 123, a second acoustic liner region 122, and a first acoustic liner region 121 sequentially distributed in a direction from the leading edge 101 to the trailing edge 102, and the corresponding target attenuation frequencies are a second-order fundamental frequency, a first-order fundamental frequency, a second-order fundamental frequency, and a first-order fundamental frequency of a single-tone noise of a flying condition corresponding to an aeroengine airiness condition, respectively. In some embodiments, the specific structure may be that the resonant cavity side length of the first acoustic liner 121 is a, the resonant cavity side length of the second acoustic liner 122 is 1/2a, the resonant cavity side length of the first acoustic liner 121 is 2/3a, the resonant cavity side length of the third acoustic liner 123 is 1.5f, the resonant cavity side length of the fourth acoustic liner 124 is 1/3a, the resonant cavity side length of the fifth acoustic liner 125 is 5/9a, the resonant cavity side length of the sixth acoustic liner 126 is 5/18a, and the resonant cavity side length of the fourth acoustic liner 124 is 1/3a, the resonant cavity side length of the fifth acoustic liner 125 is 5/9a, the resonant cavity side length of the sixth acoustic liner is 5.8 f, and the resonant cavity side length of the sixth acoustic liner 126 is 3.6f.
In light of the foregoing, the present application further provides a noise reduction method for a power propulsion system, where the power propulsion system includes a fan and/or a compressor, and the noise reduction method includes providing the outlet guide vane 10 as described in the foregoing embodiment at the outlet end of the fan and/or the compressor, so as to implement a light noise reduction scheme, and ensure that the aerodynamic efficiency of the outlet guide vane is higher while taking into account a plurality of noise reduction frequencies.
In summary, the beneficial effects of the outlet guide vane, the power propulsion system and the noise reduction method thereof described in the above embodiments include, but are not limited to, the structure of integrating the acoustic liner on the outlet guide vane, that is, the rigid back plate of the vane body as the acoustic liner, realizing the light weight of the noise reduction structure, meanwhile, through the plurality of acoustic liner areas, the area of the single resonant cavity of the acoustic liner area located relatively upstream is smaller than that of the resonant cavity of the acoustic liner area located relatively downstream, so that on the basis of realizing the light weight of the noise reduction structure, the influence of the integrated acoustic liner structure on the aerodynamic efficiency of the outlet guide vane is reduced, on the basis of having the basic function of higher aerodynamic efficiency, the light weight of the noise reduction structure is realized, and in addition, the plurality of acoustic liner areas are provided to give consideration to the noise reduction of different navigable working conditions and/or fundamental frequencies of different orders, and the noise reduction effect of the noise reduction structure is optimized.
While the invention has been described in terms of preferred embodiments, it is not intended to be limiting, but rather to the invention, as will occur to those skilled in the art, without departing from the spirit and scope of the invention. Therefore, any modification, equivalent variation and modification of the above embodiments according to the technical substance of the present invention fall within the protection scope defined by the claims of the present invention.
Claims (9)
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| CN111706433A (en) * | 2020-05-11 | 2020-09-25 | 中国航发沈阳发动机研究所 | Sound lining combined structure |
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| GB2026622A (en) * | 1978-07-08 | 1980-02-06 | Rolls Royce | Blade for Fluid Flow Machine |
| US7901189B2 (en) * | 2007-05-14 | 2011-03-08 | General Electric Company | Wind-turbine blade and method for reducing noise in wind turbine |
| US10677163B2 (en) * | 2017-12-06 | 2020-06-09 | General Electric Company | Noise attenuation structures |
| CN109356802B (en) * | 2018-12-29 | 2019-10-01 | 南京航空航天大学 | A kind of pneumatic equipment bladess with denoising structure |
| CN113123875B (en) * | 2019-12-31 | 2022-07-08 | 中国航发商用航空发动机有限责任公司 | Aeroengine sound absorption device and aeroengine |
| US11339720B2 (en) * | 2020-02-21 | 2022-05-24 | Raytheon Technologies Corporation | Acoustic liner with non-uniform volumetric distribution |
| CN113803296A (en) * | 2020-06-16 | 2021-12-17 | 中国航发商用航空发动机有限责任公司 | Aircraft engine, acoustic lining pore plate and manufacturing method of acoustic lining pore plate |
| CN113958415B (en) * | 2020-07-20 | 2023-02-28 | 中国航发商用航空发动机有限责任公司 | Noise reduction lining and aircraft engine |
| CN112069657B (en) * | 2020-08-13 | 2024-03-12 | 株洲时代新材料科技股份有限公司 | Pipeline acoustic liner design method and pipeline acoustic liner suitable for air flow environment |
| CN115823020B (en) * | 2021-09-14 | 2026-01-16 | 中国航发商用航空发动机有限责任公司 | Flow guide stator blade assembly and turbofan engine comprising same |
| CN116292399A (en) * | 2022-12-31 | 2023-06-23 | 中国航发沈阳发动机研究所 | Low-noise fan rotor blade |
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| CN111706433A (en) * | 2020-05-11 | 2020-09-25 | 中国航发沈阳发动机研究所 | Sound lining combined structure |
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