Numerical aeroacoustic analysis of propeller designs

Chirico, Giulia; Barakos, George N.; Bown, Nicholas

doi:10.1017/aer.2017.123

Cited by 30 publications

(27 citation statements)

References 57 publications

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“…Few studies have been conducted so far on the aeroacoustic properties of interacting propellers and are mainly related to counter-rotating propellers [16,17] and drones [18][19][20][21][22], where the distance between rotor hubs is a crucial aspect. In Reference [23], numerical aeroacoustic analyses of innovative propeller geometries have been carried out, accounting for a single propeller mounted on a wing. In Reference [24] a parametric study for a single open rotor aimed at reducing noise has been reported whereas in Reference [25], a new method has been presented to estimate the influence of the number of blades on noise contribution.…”

Section: Introductionmentioning

confidence: 99%

Numerical Characterisation of the Aeroacoustic Signature of Propeller Arrays for Distributed Electric Propulsion

et al. 2020

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This paper presents an investigation of the aerodynamic and aeroacoustic interaction of propellers for distributed electric propulsion applications. The rationale underlying the research is related to the key role that aeroacoustics plays in the establishment of the future commercial aviation scenario. The sustainable development of airborne transportation system is currently constrained by community noise, which limits the operations of existing airports and prevents the building of new ones. In addition, the substantial saturation of the existing noise abatement technologies inhibits the further development of the existing fleet, and imposes the adoption of disruptive configurations in terms of airframe layout and propulsion technology. Simulation-based data may help in clarifying many aspects related to the acoustic impact of such innovative concepts. Blended-wing-body equipped with distributed electric propulsion is one of the most promising, due to the beneficial effect of the substantial shielding induced by its geometry. Nevertheless, the novelty of the layout requires a thorough investigation of specific aspect for which no previous experience is available. Herein, the interaction between propellers is analysed for a fixed propeller geometry, as a function of their mutual distance and compared to the acoustic pattern of the isolated one. The aerodynamic results have been obtained using a boundary integral formulation for unsteady, incompressible, potential flows which accounts for the interaction between free wakes and propellers. For the aeroacoustic analyses, the Farassat 1A boundary integral formulation for the solution of the Ffowcs Williams and Hawkings equation has been used. These results provide an insight into the minimum distance between propellers to avoid aerodynamic/aeroacoustic interaction effects, which is an important starting point for the development of distributed propulsion systems.

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Section: Introductionmentioning

confidence: 99%

Numerical Characterisation of the Aeroacoustic Signature of Propeller Arrays for Distributed Electric Propulsion

et al. 2020

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“…Good agreement was found in terms of aerodynamics and acoustics [18,24]. HMB3 solves the Navier-Stokes equations in integral form and are discretised using a cell-centred finite volume approach on a multi-block grid.…”

Section: Computational Fluid Dynamicsmentioning

confidence: 88%

“…It uses the in-house flow solver HMB3, and couples Computational Fluid Dynamic (CFD) and Computational Structural Dynamics (CSD). The core functionality of HMB3 is CFD, however its use has been extended in recent years to include whole engineering applications, including helicopter rotor aeroelasticity [17], propeller aeroacoustics [18], flight mechanics [19] and missile trajectory prediction [20].…”

Section: Computational Methodology: Hmb3mentioning

confidence: 99%

“…where i, j, k represent the cell index, W and R are the vector of conservative variables and flux residual respectively and V i, j,k is the volume of the cell i, j, k. Greater detail on the numerical techniques employed can be found within the previous investigations conducted using HMB3 [17][18][19][20][24][25][26][27]. Several turbulence models, of both URANS and hybrid LES/URANS families, are available in the HMB3 solver.…”

Section: Computational Fluid Dynamicsmentioning

confidence: 99%

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High-Fidelity Computational Fluid Dynamics Methods for the Simulation of Propeller Stall Flutter

et al. 2019

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Brown, N. (2019) Highfidelity computational fluid dynamics methods for the simulation of propeller stall flutter. A time-marching aeroelastic method developed for the study of propeller flutter is presented and validated. Propeller flutter can take many forms with stall, whirl and classical flutter being the primary responses. These types of flutter require accurate capture of the non-linear aerodynamics associated with propeller blades. Stall flutter in particular needs detailed unsteady flow modelling. With the development of modern propeller designs potentially adjusting the flutter boundary and the development of faster computing power, CFD is required to ensure accurate capture of aerodynamics. Given the lack of reliable experimental stall flutter data for propellers, the method was focused on observing the correct qualitative behaviour with a comparison made between URANS and Scale-Adaptive Simulation (SAS). Greek α s m = Model amplitude of mode m of solid s (m/kg) ζ m = Damping coefficient (-) ρ = Fluid density (kg/m 3 ) ψ s m = Normalised m th mode displacement of solid s (m/kg) ψ s = Normalised displacement of solid s (m/kg) ω m = Natural frequency of mode m Ω CV = Control volume size Subscripts i, j, k = Mesh cell indices

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“…For this investigation, the in-house CFD solver HMB3 is used. The core functionality of HMB3 is CFD, however its use has been extended in recent years to include whole engineering applications, including helicopter rotor aeroelasticity (12) and propeller validation (13,14) . In addition to this, the time-marching aeroelastic method of HMB3 has been validated with respect to propeller stall flutter for the Commander propeller blade (15,16) .…”

Section: Computational Methodology: Hmb3mentioning

confidence: 99%

Estimation of three-dimensional aerodynamic damping using CFD

Higgins

Barakos

Jinks³

2019

Aeronaut. j.

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Aeroelastic phenomena of stall flutter are the result of the negative aerodynamic damping associated with separated flow. From this basis, an investigation has been conducted to estimate the aerodynamic damping from a time-marching aeroelastic computation. An initial investigation is conducted on the NACA 0012 aerofoil section, before transition to 3D propellers and full aeroelastic calculations. Estimates of aerodynamic damping are presented, with a comparison made between URANS and SAS. Use of a suitable turbulence closure to allow for shedding of flow structures during stall is seen as critical in predicting negative damping estimations. From this investigation, it has been found that the SAS method is able to capture this for both the aerofoil and 3D test cases.

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Numerical aeroacoustic analysis of propeller designs

Cited by 30 publications

References 57 publications

Numerical Characterisation of the Aeroacoustic Signature of Propeller Arrays for Distributed Electric Propulsion

Numerical Characterisation of the Aeroacoustic Signature of Propeller Arrays for Distributed Electric Propulsion

High-Fidelity Computational Fluid Dynamics Methods for the Simulation of Propeller Stall Flutter

Estimation of three-dimensional aerodynamic damping using CFD

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