A Numerical Study on Aircraft Noise Mitigation Using Porous Stator Concepts
This manuscript presents the application of a recently developed noise reduction technology, constituted by poro-serrated stator blades on a full-scale aircraft model, in order to reduce rotor-stator interaction noise in the fan stage. This study was carried out using the commercial lattice Boltzman...
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| Format: | Article |
| Language: | English |
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MDPI AG
2022-01-01
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| Series: | Aerospace |
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| Online Access: | https://www.mdpi.com/2226-4310/9/2/70 |
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| author | Christopher Teruna Leandro Rego Damiano Casalino Daniele Ragni Francesco Avallone |
| author_facet | Christopher Teruna Leandro Rego Damiano Casalino Daniele Ragni Francesco Avallone |
| author_sort | Christopher Teruna |
| collection | DOAJ |
| description | This manuscript presents the application of a recently developed noise reduction technology, constituted by poro-serrated stator blades on a full-scale aircraft model, in order to reduce rotor-stator interaction noise in the fan stage. This study was carried out using the commercial lattice Boltzmann solver 3DS-SIMULIA PowerFLOW. The simulation combines the airframe of the NASA High-Lift Common Research Model with an upscaled fan stage of the source diagnostic test rig. The poro-serrations on the stator blades have been modeled based on a metal foam with two different porosity values. The results evidence that the poro-serrations induce flow separation on the stator blades, particularly near the fan-stage hub. Consequently, the thrust generated by the modified fan stage is lower and the broadband noise emission at low frequencies is enhanced. Nevertheless, the tonal noise components at the blade-passage frequency and its harmonics are mitigated by up to 9 dB. The poro-serrations with lower porosity achieve a better trade-off between noise emission and thrust penalty. An optimization attempt was carried out by limiting the application of porosity near the tip of the stator blades. The improved leading-edge treatment achieves a total of <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mn>1.5</mn></mrow></semantics></math></inline-formula> dB in sound power level reduction while the thrust penalty is below <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mn>1.5</mn></mrow></semantics></math></inline-formula>%. This demonstrates that the aerodynamic effects of a leading-edge treatment should be taken into account during the design phase to fully benefit from its noise reduction capability. |
| first_indexed | 2024-03-09T22:53:54Z |
| format | Article |
| id | doaj.art-1988cab5c9fd46958b1a307454482684 |
| institution | Directory Open Access Journal |
| issn | 2226-4310 |
| language | English |
| last_indexed | 2024-03-09T22:53:54Z |
| publishDate | 2022-01-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj.art-1988cab5c9fd46958b1a3074544826842023-11-23T18:14:11ZengMDPI AGAerospace2226-43102022-01-01927010.3390/aerospace9020070A Numerical Study on Aircraft Noise Mitigation Using Porous Stator ConceptsChristopher Teruna0Leandro Rego1Damiano Casalino2Daniele Ragni3Francesco Avallone4Department of Wind Energy, Delft University of Technology, 2628 CD Delft, The NetherlandsDepartment of Wind Energy, Delft University of Technology, 2628 CD Delft, The NetherlandsDepartment of Wind Energy, Delft University of Technology, 2628 CD Delft, The NetherlandsDepartment of Wind Energy, Delft University of Technology, 2628 CD Delft, The NetherlandsDepartment of Wind Energy, Delft University of Technology, 2628 CD Delft, The NetherlandsThis manuscript presents the application of a recently developed noise reduction technology, constituted by poro-serrated stator blades on a full-scale aircraft model, in order to reduce rotor-stator interaction noise in the fan stage. This study was carried out using the commercial lattice Boltzmann solver 3DS-SIMULIA PowerFLOW. The simulation combines the airframe of the NASA High-Lift Common Research Model with an upscaled fan stage of the source diagnostic test rig. The poro-serrations on the stator blades have been modeled based on a metal foam with two different porosity values. The results evidence that the poro-serrations induce flow separation on the stator blades, particularly near the fan-stage hub. Consequently, the thrust generated by the modified fan stage is lower and the broadband noise emission at low frequencies is enhanced. Nevertheless, the tonal noise components at the blade-passage frequency and its harmonics are mitigated by up to 9 dB. The poro-serrations with lower porosity achieve a better trade-off between noise emission and thrust penalty. An optimization attempt was carried out by limiting the application of porosity near the tip of the stator blades. The improved leading-edge treatment achieves a total of <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mn>1.5</mn></mrow></semantics></math></inline-formula> dB in sound power level reduction while the thrust penalty is below <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mn>1.5</mn></mrow></semantics></math></inline-formula>%. This demonstrates that the aerodynamic effects of a leading-edge treatment should be taken into account during the design phase to fully benefit from its noise reduction capability.https://www.mdpi.com/2226-4310/9/2/70aeroacousticsrotor-stator interaction noiseporous material |
| spellingShingle | Christopher Teruna Leandro Rego Damiano Casalino Daniele Ragni Francesco Avallone A Numerical Study on Aircraft Noise Mitigation Using Porous Stator Concepts Aerospace aeroacoustics rotor-stator interaction noise porous material |
| title | A Numerical Study on Aircraft Noise Mitigation Using Porous Stator Concepts |
| title_full | A Numerical Study on Aircraft Noise Mitigation Using Porous Stator Concepts |
| title_fullStr | A Numerical Study on Aircraft Noise Mitigation Using Porous Stator Concepts |
| title_full_unstemmed | A Numerical Study on Aircraft Noise Mitigation Using Porous Stator Concepts |
| title_short | A Numerical Study on Aircraft Noise Mitigation Using Porous Stator Concepts |
| title_sort | numerical study on aircraft noise mitigation using porous stator concepts |
| topic | aeroacoustics rotor-stator interaction noise porous material |
| url | https://www.mdpi.com/2226-4310/9/2/70 |
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