Sophistication and Deepning of Numerical Calculation and Active Control of Fan Noises
| Project/Area Number |
17K06949
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| Research Category |
Grant-in-Aid for Scientific Research (C)
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| Allocation Type | Multi-year Fund |
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| Section | 一般 |
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| Research Field |
Aerospace engineering
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| Research Institution | Kyushu University |
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Principal Investigator |
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| Co-Investigator(Kenkyū-buntansha) |
猪口 雄三 九州大学, 工学研究院, 准助教 (30274509)
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| Project Period (FY) |
2017-04-01 – 2020-03-31
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| Project Status |
Completed (Fiscal Year 2019)
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| Budget Amount *help |
¥4,680,000 (Direct Cost: ¥3,600,000、Indirect Cost: ¥1,080,000)
Fiscal Year 2019: ¥1,300,000 (Direct Cost: ¥1,000,000、Indirect Cost: ¥300,000)
Fiscal Year 2018: ¥1,040,000 (Direct Cost: ¥800,000、Indirect Cost: ¥240,000)
Fiscal Year 2017: ¥2,340,000 (Direct Cost: ¥1,800,000、Indirect Cost: ¥540,000)
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| Keywords | aeroacoustics / fan noise / CAA / active noise contol / acoustic mode / digital control / CFD / ANC / 空力音響 / 音響ライナ / ファン騒音 / 能動制御 / バイアスフロー / 線形オイラー方程式 / tone noise / axial flow fan / passive noise control / active noise control / acoustic liner |
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| Outline of Final Research Achievements |
For the fan with passive-noise-control blade count, the CFD and the acoustic calculation were executed and the effects of geometrical shape on generated acoustics field and performance were clarified. Moreover, in order to develop the CAA using the Compact scheme, the formulation and implementation of the linear unsteady acoustic calculation of the Euler equations in the frequency domain were performed, and they were validated for various acoustic fields. In addition, we performed the systematic experiments, CAA on two-dimensional active acoustic liners, and original theoretical calculation to develop the numerical calculation methods and elucidate the acoustic flow field. Furthermore, in the fan noise active control experiments, the active acoustic control system using digital microphones was realized and validated.
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| Academic Significance and Societal Importance of the Research Achievements |
航空機のターボファンエンジンからファン騒音は，航空機騒音の支配的なものであり，その低減・予測技術は喫緊の課題である．本研究では，まず，ファン幾何形状を変化させて，発生騒音と性能に及ぼす効果を明らかにした．また，騒音の伝播，放射の解析に計算量が少なく高精度な解析手法を開発して議論した．一方で，ファン騒音を吸音する音響ライナで空気吹き出しにより吸音性能の向上の研究を行った．さらに発生騒音に，2 次音をぶつけて減音する実証システムを開発した．
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Report
(4 results)
Research Products
(11 results)
