About
43
Publications
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643
Citations
Citations since 2017
Introduction
Additional affiliations
January 2011 - September 2012
Position
- Newton International Research Fellow
Description
- Research on acoustic analogies in ducted swirling mean flow. Aeroacoustics - Analytical modeling - Acoustic analogies - turbomachinery noise
January 2009 - December 2010
Position
- Post doctorate
Description
- Research on aircraft engine noise : Analytical modelling - Fan noise - Broadband noise
November 2005 - December 2008
Position
- PhD sutdent
Description
- Fan broadband noise prediction accounting for cascade effects: Analytical modelling - fan noise - cascade effect
Publications
Publications (43)
![Figure 1. Sketch of the experimental set-up from Jacob et al. [13]....](profile/David-Lamidel/publication/356144883/figure/fig1/AS:1088981701799937@1636644878089/Sketch-of-the-experimental-set-up-from-Jacob-et-al-13-Dimensions-are-in-millimeters_Q320.jpg)
A Large-Eddy Simulation of the tip leakage flow of a single airfoil is carried out. The configuration consists of a non-rotating, isolated airfoil between two horizontal plates with a gap of 10 mm between the tip of the airfoil and the lower plate. The Mach number of the incoming flow is 0.2, and the Reynolds number based on the chord is 9.3 x 10e5...
A numerical investigation of the tip leakage flow of a single airfoil is carried out. The configuration consists of a non-rotating, isolated airfoil between two horizontal plates with a gap of 10 mm between the tip of the airfoil and the lower plate. The Mach number is 0.2 and the Reynolds number based on the chord is 9.3 × 10e5. With the aim of mo...
Sound transmission through a finite lined section in a rigid annular duct with swirling and sheared mean flow is analyzed with a new mode-matching method based on the conservation of the total enthalpy and the mass flow, which does not reduce to the conservation of the pressure and the axial velocity when the swirl is non zero. It relies on a new p...
This work, realized in the framework of the European project TurboNoiseBB, presents an advanced aeroacoustic design methodology of Outlet Guide Vanes (OGVs) with leading edge serrations, including details on their broadband noise and aerodynamic performance. The serrated OGV corresponds to a modified stator from an aeroengine fan stage tested at th...
A benchmark dedicated to RANS-informed analytical methods for the prediction of turbofan rotor–stator interaction broadband noise was organised within the framework of the European project TurboNoiseBB. The second part of this benchmark focuses on the impact of the acoustic models. Twelve different approaches implemented in seven different acoustic...
A benchmark of Reynolds-Averaged Navier-Stokes (RANS)-informed analytical methods, which are attractive for predicting fan broadband noise, was conducted within the framework of the European project TurboNoiseBB. This paper discusses the first part of the benchmark, which investigates the influence of the RANS inputs. Its companion paper focuses on...
This work, realized in the framework of the European project TurboNoiseBB, presents the aeroacoustic design of serrated OGVs (Outlet Guide Vanes), including details on their broadband noise and aerodynamic performance. The serrated OGV corresponds to a modified stator from a turbofan model tested at the AneCom facility (Germany) and shared by the C...
The present work extends a recent two-dimensional analytical model for sound generation and transmission in an axial-flow outlet guide vanes row, by taking into account vane camber and stagger, as well as cut-on/cut-off or cut-off/cut-on transitions of inter-vane channel modes.It is aimed at demonstrating that such transitions may have a significan...
The acoustics of a straight annular lined duct containing a swirling mean flow is considered. The classical Ingard-Myers impedance boundary condition is shown not to be correct for swirling flow. By considering behaviour within the thin boundary layers at the duct walls, the correct impedance boundary condition for an infinitely thin boundary layer...
This paper gives a modified Myers boundary condition in swirling inviscid flow, which differs from the standard Myers boundary condition by assuming a small but non-zero boundary layer thickness. The new boundary condition is derived and is shown to have the correct quadratic error behaviour with boundary layer thickness and also to agree with prev...
Future aircraft architecture may involve ultra high bypass ratio engines (UHBR), associated with large diameters which will require a shorter nacelle. As a result, the relative weight of the interstage liner, liner between fan and outlet guide vanes (OGV), may become more significant compared to the inlet liner. The mean flow in the interstage regi...
This presentation will focus on calculating the modes and Green’s function for swirling flow in an finite duct. We will consider solutions to the linearised Euler equations for a compressible, perfect gas which will be either homentropic or isentropic. The base flow velocity will be have both varying shear and swirl. The duct will have hard walls o...
The present study aims at addressing the effect of a swirling and sheared mean flow on the behavior of the liners in an annular duct. When the swirl is non zero in the vicinity of the wall, it is shown that the classical Myers boundary condition is no longer the correct limit for infinitely thin boundary layers. Indeed, centrifugal effects shall be...
The present work deals with the analytical modeling of two aspects of outlet guide vane aeroacoustics in axial-flow fan and compressor rotor-stator stages. The first addressed mechanism is the downstream transmission of rotor noise through the outlet guide vanes, the second one is the sound generation by the impingement of the rotor wakes on the va...
This paper is concerned with modelling the effects of swirling flow on turbomachinery noise. We develop an acoustic analogy to predict sound generation in a swirling and sheared base flow in an annular duct, including the presence of moving solid surfaces to account for blade rows. In so doing we have extended a number of classical earlier results,...
An analytical model for the rotor-stator broadband noise is improved by accounting for the rotor acoustic shielding. Both the analytical models for the stator broadband noise and for the rotor scattering are strip-theory approaches based on previously published formulations of the three-dimensional unsteady blade loading for a rectilinear cascade....
The present study aims at investigating the effect of a swirling mean flow and a lined annular duct on rotor trailing-edge noise. The objectives are to investigate these effects on the eigenvalues and a tailored Green's function on one hand and on the realistic case of the fan trailing-edge noise on the other hand. Indeed, the mean flow in between...
This paper introduces a two-stagger angles method to take into account some effects of camber in cascade-gust interaction noise through a simple extension of a flat-plate based analytical model. The emphasis is put here on cascade-gust interaction tonal noise, for which camber effects are known to be significant, but the present method can be simil...
This work aims at evaluating some technological effects usually not included in analytical or semi-analytical tonal fan noise prediction models. The methodology consists in comparing unsteady Computational Fluid Dynamics data, taking successively into account some realistic effects, with the results from a cascade response based model for rotor/sta...
The present study aims at accounting for swirling mean flow effects on rotor trailing-edge noise. Indeed, the mean flow in between the rotor and the stator of the fan or of a compressor stage is highly swirling. The extension of Ffowcs-Williams & Hawkings' acoustic analogy in a medium at rest with moving surfaces and of Goldstein's acoustic analogy...
The present study aims at developing an acoustic formulation for the sound generated by the interaction of solid surfaces (such as blades) with an unsteady flow in an annular duct with swirl. Indeed, the mean flow in between the rotor and the stator of the fan or of a compressor stage is highly swirling. As a result, in order to properly predict th...
An analytical model of the broadband noise produced by both the interaction of ingested turbulence with a fan rotor blades and the rotor-wake impingement on downstream stator vanes is proposed and detailed. The noise prediction methodology is a strip-theory approach based on a previously published formulation of the three-dimensional unsteady blade...
The present paper is aimed at assessing an analytical prediction model for the broadband noise produced by the impingement of turbulence on a cascade, using a dedicated experiment. The model is a strip-theory approach based on a previously published formulation of the unsteady blade loading for a rectilinear cascade. The experimental setup is made...
The effects of the wake modelling on the prediction of the broadband noise generated by the impingement of the turbulent wakes on a stationary blade row are studied. The analysis focuses on the description of the wake shape that is usually approximated by a Gaussian curve for acoustical purposes. The prediction of the broadband noise is achieved us...
The present study aims at improving and assessing an analytical model for the broad- band noise produced by the impingement of turbulence downstream of a rotor on a down- stream stator with a preliminary account of the rotor acoustic shielding. The analytical model for the broadband noise of the isolated stator is a strip-theory approach based on a...
In order to improve the prediction of fan tonal and broadband noise, the use of unsteady numerical simulations to predict the unsteady pressure loading on a blade is evaluated and compared to a recently developed analytical model for a flat plate cascade at zero angle of attack submitted to 3D gusts. Unsteady Reynolds-Averaged Navier-Stokes data on...
This paper extends an existing analytical model of the aeroacoustic response of a rectilinear cascade of flat-plate blades to three-dimensional incident vortical gusts, by providing closed-form expressions for the acoustic field inside the inter-blade channels, as well as for the pressure jump over the blades in subsonic flows. The extended formula...
The present paper extends an existing analytical model of the aeroacoustic response of a rectilinear cascade of flat-plate blades to three-dimensional incident vortical gusts, to the prediction of the noise generated by a three-dimensional annular blade-row. The extended formulation is meant to be implemented in a fan broadband noise prediction too...
The present study aims at developing and assessing an analytical model for the sound transmission through an annular blade row, by comparing with the Finite Element Method Solver of Virtual Lab Acoustics in a configuration without mean flow. The model reformulates a three-dimensional annular model dedicated to turbulence interaction noise to deal w...
A recently developed analytical model for the predictions of the fan tonal and broadband noises has been tested by comparing the unsteady blade loading with results provided by numerical unsteady simulations on a realistic compressor rotor-stator configuration (CME2). Both a blade slice and the actual full blade span have been investigated with the...
Fan noise becomes a major contribution to the total noise in modern turbofan engines. Moreover sound quality of ventilation systems becomes a major selection criterion. Fast noise prediction tools are needed at early design stage. The present paper focuses on the effects of the main geometrical blade parameters on the scattering of a three-dimensio...
The present study aims at improving and assessing a previously presented analytical model for the broadband noise produced by the impingement of turbulence on a blade row, and to extend it to the case of a stator downstream of a rotor. The noise prediction model is a strip-theory approach based on a previously published formulation of the three-dim...
The broadband noise contribution of a fan is expected to become relatively more and more
significant in modern turbofan engines. Prediction schemes, including the cascade effect of
adjacent blades, thus become essential in designing quieter fans. This thesis aims at developing
a rather fast-running model including cascade effects to predict the fan...
The broadband noise contribution of a fan is expected to become relatively more and moresignificant in modern turbofan engines. Prediction schemes, including the cascade effect ofadjacent blades, thus become essential in designing quieter fans. This thesis aims at developinga rather fast-running model including cascade effects to predict the fan br...
The present paper adresses the analytical modelling of the broadband noise pro-
duced by the impingement of turbulence on a cascade. The noise prediction model is
a strip-theory approach based on a previously published formulation of the unsteady
blade loading for a rectilinear cascade. It is re-adressing the comparison with refer-
ence three-dimen...
The present paper is aimed at assessing an analytical model for the broadband noise
produced by the impingement of turbulence on a cascade, using a dedicated experiment.
The noise prediction model is a strip-theory approach based on a previously published
formulation of the unsteady blade loading for a rectilinear cascade. The model is first com-
p...
Projects
Project (1)
This project has begun with my PhD thesis and aims at developing an analytical model for wake interaction noise in the fan stage of modern turbofan engines. The objectives are as follows:
1. The first objective is to extend a two-dimensional mode-matching based model of sound generation and transmission in axial-flow Outlet Guide Vanes (OGV) for cambered vanes. An interesting aspect of sound propagation in cambered inter-vane channels is the phenomenon of cut-off/cut-on transitions of acoustic modes, which drastically changes the acoustic behavior.
2. The second objective is to adapt the sound transmission model for the fan by adding rotational effects and considering highly staggered and weakly cambered blades, typical of modern fan geometries near the tip.
3. Finally, the third objective is to model the whole rotor-stator stage in order to investigate blade screen effects and the occurrence of trapped modes in the inter-stage.
