Noise due to interaction of inlet turbulence with isolated stators and rotors

Mani, R.

doi:10.1016/0022-460x(71)90459-7

Cited by 73 publications

(13 citation statements)

References 3 publications

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“…Mani [50], in considering the effect of homogeneous isotropic turbulence, calculated broad band noise with peaks at blade passing frequency in the case of the rotor. Pickett [23], considering anisotropic turbulence, found the same type of spectrum although with sharper tones.…”

Section: Broad Band Noisementioning

confidence: 99%

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REVIEW—A Critical Review of Turbomachinery Noise

Cumpsty

1977

Journal of Fluids Engineering

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The review is written from the point of view of an engineer wanting to understand, reduce, and predict noise from turbomachines. In consequence knowledge gained by theory and, in particular, experiment is emphasized rather than the details of theoretical treatments. Attention is drawn to the surprisingly small interaction between theory and experiment and to the small amount of application that the theories have received. In describing the theoretical models it is the validity or applicability of their assumptions that is emphasized; despite the large number of theoretical treatments published the range of assumptions is quite small. Inevitably the review reflects the emphasis on funding for research by describing mainly high-speed, aeronautical turbomachinery noise. The overall conclusions drawn are rather depressing, with relatively little known even now about noise mechanisms for high speed machinery.

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Section: Broad Band Noisementioning

confidence: 99%

“…Mani [50] applied his calculation method to an input consisting of homogeneous, isotropic turbulence. The interaction with a rotor did indeed produce humps at the harmonics of blade passing frequency, Fig.…”

Section: Fig 5 Comparison Of Measured and Predicted Acoustic Pressurmentioning

confidence: 99%

REVIEW—A Critical Review of Turbomachinery Noise

Cumpsty

1977

Journal of Fluids Engineering

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“…Models for noise generation by turbulence-blade interaction are well known and long-standing (e.g. Sharland 1964;Mani 1971;Homicz & George 1974), and we mention in particular here Amiet (1975) and Paterson & Amiet (1982), who developed a foundational model for the far-field noise due to a single flat-plate aerofoil in terms of the turbulent energy spectrum and the aerofoil response function. In these models the turbulence is not distorted by the (uniform) mean flow as it convects towards the aerofoil.…”

Section: Introductionmentioning

confidence: 99%

Noise generation by turbulence–propeller interaction in asymmetric flow

Robison

Peake

2014

J. Fluid Mech.

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This paper is concerned with a particular source of both broadband and tonal aeroengine noise, termed unsteady distortion noise. This noise arises from the interaction between turbulent eddies, which occur naturally in the atmosphere or are shed from the fuselage, and the rotor. This interaction produces broadband noise across a broad frequency spectrum. In cases in which there is strong streamtube contraction, which is especially true for open rotors at low-speed conditions (such as at take-off or for static testing), tonal noise at frequencies equal to multiples of the blade passing frequency are also produced, owing to the enhanced axial coherence caused by eddy stretching. model for unsteady distortion noise was developed in axisymmetric flow. However, asymmetric situations are also of much interest, and in this paper we consider two cases of asymmetric distortion: firstly that induced by the proximity of a second rotor, and secondly that caused by non-zero inclination to the flight direction, as found at take-off. This requires significant extension of the previous axisymmetric analysis. We find that the introduction of asymmetric flow features can have a significant decibel effect on the radiated sound power. For instance, in low-speed conditions we find that the tonal level is reduced significantly by the proximity of a second rotor, compared to the axisymmetric case, while the effect on the broadband levels is rather modest.

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“…The effect of U /A 2 on the spectrum is the same as that 3,i 3 iõ btained by Homicz [8]. However, the effect of RT/Ai on the spectrum for constant U /Ai ' is the opposite of that claimed by Mani [15]. Further, as the rotational speed increases, the bandwidth and the level at the blade-passing frequency: and its multiples are increased, and as the axial flow velocity increases, the blade-passing frequency and its multiples appear clearly.…”

Section: Uc(s) Smentioning

confidence: 42%

Rotor noise due to blade turbulence interaction

Ishimaru¹

1984

The Journal of the Acoustical Society of America

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Noise due to interaction of inlet turbulence with isolated stators and rotors

Cited by 73 publications

References 3 publications

REVIEW—A Critical Review of Turbomachinery Noise

REVIEW—A Critical Review of Turbomachinery Noise

Noise generation by turbulence–propeller interaction in asymmetric flow

Rotor noise due to blade turbulence interaction

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