CN115807790A - Guide stator blade and turbofan engine comprising same - Google Patents
Guide stator blade and turbofan engine comprising same Download PDFInfo
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- CN115807790A CN115807790A CN202111075344.5A CN202111075344A CN115807790A CN 115807790 A CN115807790 A CN 115807790A CN 202111075344 A CN202111075344 A CN 202111075344A CN 115807790 A CN115807790 A CN 115807790A
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- stator blade
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Abstract
The invention discloses a guide stator blade and a turbofan engine comprising the same. The outer surface of the guide stator blade is of an arc-shaped structure, and a plurality of first through holes are formed in the outer surface of the guide stator blade. After the guide stator blade is applied to the turbofan engine, the tail track which is fallen off by the rotation of the upstream fan rotor is beaten to the outer duct guide stator blade, and the surface of the stator blade is of an arc-shaped structure, so that the air flow can move downstream along the surface of the stator blade, the noise can enter the first through hole on the arc-shaped surface, and the first through hole is used for increasing air damping attenuation noise, so that the problems of smooth air flow and noise reduction can be solved, and the noise reduction effect of the first layer is realized. Compared with the prior art, the scheme has the advantages of simple structure and better noise reduction effect.
Description
Technical Field
The invention relates to the field of turbofan engines, in particular to a guide stator blade and a turbofan engine comprising the same.
Background
The main noise sources for civil aircraft fall into the following general categories: engine noise, body noise, and interference noise of the power system and the body. The engine noise includes fan noise, jet noise, turbine noise, core noise, and the like. Body noise includes high lift device noise, landing gear noise, and power system and body interference noise.
For modern large bypass ratio turbofan engines, fan noise is the dominant noise source, radiating forward through the intake duct and backward through the engine overboard duct. The noise generated by the fan can be divided into 3 parts:
(1) Pure tone, which consists of a Blade Passing Frequency (BPF) tone and its harmonics. Pure tones have 2 generation mechanisms: rotor-generated noise and rotor-stator interaction-generated noise. In rotor tone, noise generation is related to blade loading and thickness. The sound field generated by the rotor will rotate at the same speed as at the fan. In rotor-stator interaction, noise is generated by wake vortices shed by rotor blades and downstream stator blade interaction;
(2) The axis level tones, i.e., the saw-tooth noise occurring at the fundamental frequency, which is the axis rotation frequency, are also referred to as multiple tones. The saw-tooth noise is essentially shock noise that is generated only when the blade tips reach supersonic speeds. At supersonic fan tip speeds, a sawtooth tone is produced at double the shaft rotational frequency due to the difference in blade-to-blade cascade setting angle.
(3) Broadband noise, which is mainly generated due to the interaction of random turbulence disturbances with the fan surface.
Fan noise, among other things, is a major source of noise during modern aircraft engine fly-through and approach phases. For aircraft engine fan noise, the main noise components include rotor-stator interference tones, multiple tone shock noise, and wide-band noise. Among them, as one of the main components of fan noise, fan rotor and stator interference tones are discrete noise generated due to the interference of the fan rotor and stator with each other.
Rotor/stator interference noise in large bypass ratio turbofan engines mainly includes fan and outlet guide vane interference noise. The physical mechanism for generating the discrete single-tone noise of the fan/compressor can be summarized as follows: monopole noise due to volume displacement of the blade, dipole noise due to steady force of the blade on the fluid, and dipole noise due to unsteady force of the blade on the fluid
In the prior art, in order to reduce fan noise, usually, on the basis of the position of the outer-duct outlet stator guide blade, the blade tip position is shifted along the rotation direction of the fan rotor blade, that is, the circumferential positive inclination angle of the outer-duct outlet stator guide blade is increased, so as to optimize the outer-duct outlet stator guide blade, reduce the noise generated by the trailing trace of the fan rotor blade sweeping the outer-duct outlet stator guide blade, and at the same time, the root position of the outer-duct outlet stator guide blade is fixed, and only the blade root position is inclined in the reverse direction of the rotation direction of the fan rotor blade, so as to ensure that the aerodynamic performance of the fan is not deteriorated. But the noise reduction effect among the prior art is more limited, and the noise reduction effect is lower.
Disclosure of Invention
The invention aims to overcome the defects in the prior art and provides a guide stator blade and a turbofan engine comprising the same.
The invention solves the technical problems through the following technical scheme:
the utility model provides a water conservancy diversion stator blade, the surface of water conservancy diversion stator blade is the arc structure, just be equipped with a plurality of first perforation on the surface of water conservancy diversion stator blade.
In this scheme, after the turbofan engine was applied to the water conservancy diversion stator blade, the wake that the upper reaches fan rotor rotation drops beat this outer duct water conservancy diversion stator blade after, because stator blade surface is the arc structure, the air current can be followed its surface and moved downstream, and the noise can get into the first perforation on arc surface, and first perforation increases air damping decay noise, consequently can solve smooth air current and noise reduction problem, realizes the effect of making an uproar that falls in first layer. Compared with the prior art, the scheme has the advantages of simple structure and better noise reduction effect.
Preferably, a plurality of layers of noise reduction devices are arranged inside the guide stator blade, each layer of noise reduction device comprises a plurality of honeycomb assemblies along the spanwise direction, and each honeycomb assembly comprises a plurality of honeycomb structures arranged at intervals along the extending direction different from the spanwise direction.
In this scheme, the noise gets into the honeycomb cavity after, can rub in the honeycomb cavity and by the decay, can realize the effect of making an uproar falls in the second floor. Wherein, the distribution of honeycomb subassembly makes stator guide vane's inside divide into a plurality of regions, is favorable to improving noise reduction.
Preferably, for any one honeycomb assembly, the gap between two adjacent honeycomb structures is filled with a porous material;
and/or the inner pore space of at least one honeycomb structure is filled with a porous material.
In this scheme, porous material has the wide advantage of sound absorption frequency band, and the clearance between the honeycomb or the hole intussuseption of honeycomb packs porous material, and the bandwidth of making an uproar effectively falls in the multiplicable, realizes the effect of making an uproar of third layer.
Preferably, the porous material is a metal foam.
Preferably, a noise reduction plate is arranged at the downstream of at least one honeycomb assembly, and a plurality of second perforations are arranged on the noise reduction plate.
In the scheme, the second through holes in the noise reduction plate have the functions of increasing air damping and attenuating noise energy. The rear side of the honeycomb structure is provided with a perforated noise reduction plate, the second perforation is utilized to continuously attenuate noise for the second time and provide a lower-layer channel for the noise, and the fourth-layer noise reduction effect can be achieved.
Preferably, the noise reduction plate is located between two adjacent honeycomb assemblies.
Preferably, the noise reduction plate extends in a direction parallel to the direction of extension.
Preferably, the noise reduction plate is disposed downstream of any one of the honeycomb assemblies.
Preferably, each of said noise reduction panels extends from a first layer of said noise reduction devices to a last layer of said noise reduction devices in a plurality of layers of said noise reduction devices.
In this scheme, each board of making an uproar all is fallen by the multilayer and falls the device sharing of making an uproar, and the shaping of water conservancy diversion stator blade is convenient, and is favorable to improving the overall stability of water conservancy diversion stator blade.
Preferably, the tail part of the guide stator blade is provided with a saw-toothed structure.
In the scheme, the sawtooth structure can weaken the trailing edge vortex structure, reduce the trailing edge noise and realize the function of fifth layer noise reduction.
The invention also provides a turbofan engine which comprises the guide stator blade.
On the basis of the common knowledge in the field, the above preferred conditions can be combined randomly to obtain the preferred embodiments of the invention.
The positive progress effects of the invention are as follows:
in this water conservancy diversion stator blade, after the water conservancy diversion stator blade was used to the turbofan engine, the wake that the upper reaches fan rotor rotation drops beat this outer duct water conservancy diversion stator blade after, because stator blade surface is the arc structure, the air current can follow its surface downstream motion, and the noise can get into the first perforation on arc surface, and first perforation increases air damping attenuation noise, consequently can solve smooth air current and noise reduction problem, realizes the effect of making an uproar that falls of first layer. Compared with the prior art, the scheme has the advantages of simple structure and better noise reduction effect.
Drawings
Fig. 1 is a schematic structural view illustrating a guide stator vane applied to a turbofan engine according to a preferred embodiment of the present invention.
Fig. 2 is a schematic view of an internal structure of a guide stator blade according to a preferred embodiment of the present invention.
Fig. 3 is a schematic perspective view of a stator vane according to a preferred embodiment of the present invention.
Description of reference numerals:
10-flow-guide stator blade
20 fan rotor blade
30 arc panel
301 first perforation
40 honeycomb structure
50 porous material
60 noise reduction plate
70 saw tooth like structure
Detailed Description
The invention is further illustrated by the following examples, which are not intended to limit the invention thereto.
As shown in fig. 1 to 3, in the present embodiment, a stator vane 10 is disclosed, an outer surface of the stator vane 10 is an arc-shaped structure, and a plurality of first through holes 301 are formed on the outer surface of the stator vane 10.
In this embodiment, after the stator blade 10 is applied to the turbofan engine, the wake dropped by the rotation of the upstream fan rotor blade 20 hits the bypass stator blade 10, because the surface of the stator blade 10 is of an arc-shaped structure, that is, the stator blade 10 has the arc-shaped panel 30, the airflow can move downstream along the surface thereof, the noise can enter the first through hole 301 of the arc-shaped surface, and the first through hole 301 increases the air damping attenuation noise, so that the smooth airflow and noise reduction problems can be solved, and the first layer noise reduction effect is realized. Compared with the prior art, the scheme has the advantages of simple structure and better noise reduction effect.
It should be noted that, as shown in fig. 2-3, the first perforations 301 are schematically distributed in a circumferentially scattered manner.
As shown in fig. 2 to 3, a plurality of honeycomb assemblies are provided inside the stator blade 10 in the spanwise direction, and each honeycomb assembly includes a plurality of honeycomb structures 40 arranged at intervals in an extending direction different from the spanwise direction.
After noise enters the honeycomb cavity, the noise can be rubbed and attenuated in the honeycomb cavity, and the noise reduction effect of the second layer can be realized. Wherein, the distribution of honeycomb subassembly makes stator guide vane's inside divide into a plurality of regions, is favorable to improving noise reduction.
As shown in fig. 2 to 3, for any one of the honeycomb assemblies, the gap between two adjacent honeycomb structures 40 is filled with the porous material 50, and the internal pores of at least one honeycomb structure 40 are filled with the porous material 50.
The porous material 50 has the advantage of wide sound absorption frequency band, and the gaps between the honeycomb structures 40 or the pores of the honeycomb structures are filled with the porous material 50, so that the effective noise reduction bandwidth can be increased, and the third layer noise reduction effect is realized.
It should be noted that, in alternative embodiments, the porous material may be filled only in the gap between two adjacent honeycomb structures 40, or only in the internal pores of at least one honeycomb structure 40. In addition, in this embodiment, the porous material filled in the gap between two adjacent honeycomb structures 40 and the porous material filled in the internal pore of at least one honeycomb structure 40 may be the same or different materials.
Specifically, in the present embodiment, the filled porous material 50 is a foamed metal as an exemplary embodiment.
As shown in fig. 2-3, a noise reduction plate 60 is disposed downstream of at least one of the honeycomb assemblies, and a plurality of second perforations are disposed in the noise reduction plate.
Wherein the second through holes of the noise reduction plate 60 have the functions of increasing air damping and attenuating noise energy. The rear side of the honeycomb structure 40 is designed with a perforated noise reduction plate 60, and the second perforations are utilized to continue secondary noise attenuation and provide a lower layer channel for noise, so that a fourth layer noise reduction effect can be realized.
Further, the noise reduction plate 60 is positioned between two adjacent honeycomb assemblies. The noise reduction plate extends in a direction parallel to the aforementioned direction of extension. As an illustrative embodiment, a noise reduction plate 60 is provided downstream of any one of the honeycomb assemblies.
In a preferred embodiment, each noise reduction plate 60 extends from a first layer of noise reducers to a last layer of noise reducers in the plurality of layers.
Each noise reduction plate 60 is shared by a plurality of layers of noise reduction devices, and the guide stator blade 10 is convenient to form and beneficial to improving the overall stability of the guide stator blade 10.
It should be noted that fig. 2 and 3 schematically illustrate a honeycomb assembly, wherein the honeycomb structures 40 of a plurality of honeycomb assemblies at the same height along the extending direction may be formed as a whole structure or as a plurality of scattered honeycomb structures. In addition, it should be noted that fig. 2 and 3 only schematically show two honeycomb structures 40 by reference numeral 40, and actually, the short tubular structures in fig. 2 and 3 are both honeycomb structures 40. Likewise, the noise reduction plate 60 and the porous material 50 are also only schematically illustrated with one reference numeral 60 and 50, respectively.
It should be noted that the noise reduction plate 60 is provided with a connection hole for connecting with the honeycomb structure 40 or a through hole (not shown) for passing the honeycomb structure 40, in addition to the second through hole. Wherein, if a plurality of honeycomb structures 40 along the spanwise direction are an integer, the noise reduction plate 60 is provided with a through hole for the integral structural member composed of a plurality of honeycomb structures 40 to pass through; if the plurality of honeycomb structures along the spanwise direction are scattered structures, the noise reduction plate 60 is further provided with connection holes for connecting with the honeycomb structures 40.
In addition, as shown in fig. 2 to 3, the trailing portion of the guide stator blade 10 is provided with a saw-toothed structure 70.
The sawtooth structure 70 can weaken the trailing edge vortex structure, reduce the trailing edge noise, and realize the function of fifth layer noise reduction.
The present embodiment also provides a turbofan engine including the above-described guide stator blade 10.
In the turbofan engine, the noise reduction effect is better achieved on the premise that the aerodynamic performance, the structure and the weight performance of the fan are basically not affected by the noise reduction of the first layer to the fifth layer of the stator guide vane 10.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and that the scope of the invention is defined by the appended claims. Various changes or modifications to these embodiments may be made by those skilled in the art without departing from the principle and spirit of this invention, and these changes and modifications are within the scope of this invention.
Claims (11)
1. The utility model provides a water conservancy diversion stator blade which characterized in that, the surface of water conservancy diversion stator blade is the arc structure, just be equipped with a plurality of first perforation on the surface of water conservancy diversion stator blade.
2. The guide stator blade according to claim 1, wherein a plurality of layers of noise reducing devices are provided inside the guide stator blade, each layer of noise reducing devices includes a plurality of honeycomb assemblies in a spanwise direction, and each honeycomb assembly includes a plurality of honeycomb structures arranged at intervals in an extending direction different from the spanwise direction.
3. The guide stator blade as claimed in claim 2, wherein for any one of the honeycomb assemblies, the gap between two adjacent honeycomb structures is filled with a porous material;
and/or the inner pore space of at least one honeycomb structure is filled with a porous material.
4. The guide stator vane according to claim 3, wherein the porous material is a metal foam.
5. The guide stator vane of claim 2, wherein a noise reduction plate is disposed downstream of at least one of the honeycomb assemblies, and the noise reduction plate is provided with a plurality of second perforations.
6. The guide stator vane according to claim 5, wherein the noise reduction plate is located between two adjacent honeycomb assemblies.
7. The guide stator blade according to claim 5, wherein the noise reduction plate extends in a direction parallel to the extending direction.
8. The guide stator vane as claimed in claim 5, wherein the noise reduction plate is provided downstream of any one of the honeycomb assemblies.
9. The guide stator blade according to claim 5, wherein each of the noise reduction plates extends from a first layer of the noise reduction devices to a last layer of the noise reduction devices in the plurality of layers of the noise reduction devices.
10. The guide stator blade according to any one of claims 1 to 9, wherein the tail part of the guide stator blade is provided with a saw-toothed structure.
11. A turbofan engine, characterized in that it comprises a guide stator vane according to any of claims 1-10.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111075344.5A CN115807790A (en) | 2021-09-14 | 2021-09-14 | Guide stator blade and turbofan engine comprising same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111075344.5A CN115807790A (en) | 2021-09-14 | 2021-09-14 | Guide stator blade and turbofan engine comprising same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115807790A true CN115807790A (en) | 2023-03-17 |
Family
ID=85481446
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111075344.5A Pending CN115807790A (en) | 2021-09-14 | 2021-09-14 | Guide stator blade and turbofan engine comprising same |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115807790A (en) |
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2021
- 2021-09-14 CN CN202111075344.5A patent/CN115807790A/en active Pending
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