LES for the Evaluation of Acoustic Damping of Effusion Plates

Andreini, Antonio; Bianchini, Claudio; Facchini, Bruno; Peschiulli, Antonio; Vitale, I.

doi:10.1115/gt2012-68792

Cited by 5 publications

(5 citation statements)

References 34 publications

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“…Furthermore, each plate has been tested with several blowing ratio conditions (M=1.5, 3, 5). For further details, please refer to Andreini et al [16].…”

Section: Experimental Testsupporting

confidence: 87%

Local Source Based CFD Modeling of Effusion Cooling Holes: Validation and Application to an Actual Combustor Test Case

Andreini¹,

Soghe²,

Facchini³

et al. 2013

Journal of Engineering for Gas Turbines and Power

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State-of-the-art liner cooling technology for modern combustion chambers is represented by effusion cooling (or full-coverage film cooling). Effusion is a very efficient cooling strategy typically based on the use of several inclined small diameter cylindrical holes, where liner temperature is controlled by the cornbined protective effect of coolant film and heat removal through forced convection inside each hole. A CFD-based thermal analysis of such components implies a significant computational cost if the cooling holes are included in the simulations; therefore many efforts have been made to develop lower order approaches aiming at reducing the number of mesh elements. The simplest approach models the set of holes as a uniform coolant injection, but it does not allow an accurate assessment of the interaction between hot gas and coolant. Therefore higher order models have been developed, such as those based on localized mass sources in the region of hole discharge. The model presented in this paper replaces the effusion hole with a mass sink on the cold side of the plate, a mass source on the hot side, whereas convective cooling within the perforation is accounted for with a heat sink. The innovative aspect of the work is represented by the automatic calculation of the mass flow through each hole, obtained by a run time estimation of isentropic mass flow with probe points, while the discharge coefficients are calculated at run time through an in-house developed correlation. In the same manner, the heat sink is calculated from a Nusselt number correlation available in literature for short length holes. The methodology has been applied to experimental test cases of effixsion cooling plates and compared to numerical results obtained through a CFD analysis including the cooling holes, showing a good agreement. A comparison between numerical results and experimental data was peiformed on an actual combustor as well, in order to prove the feasibility of the procedure

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“…Furthermore, each plate has been tested with several blowing ratio conditions (M=1.5, 3, 5). For further details, please refer to Andreini et al [16].…”

Section: Experimental Testsupporting

confidence: 87%

Local Source Based CFD Modeling of Effusion Cooling Holes: Validation and Application to an Actual Combustor Test Case

Andreini¹,

Soghe²,

Facchini³

et al. 2013

Journal of Engineering for Gas Turbines and Power

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“…(9) and (13). The analytical models give reactances which are linear with frequency and are therefore not capable of reproducing the experimental trends seen here.…”

Section: Orifice Impedance Datamentioning

confidence: 72%

“…Andreini et al developed a compressible Large Eddy Simulation (LES) technique [12] which has been used to study the acoustic damping properties of the multi-perforated plates used as cooling devices in gas turbine combustors. The CFD method also allowed investigation of the effect on the acoustic damping of geometrical details such as the staggering and angle of the holes [13]. Following the work of [4], Mendez et al applied LES to analyse the damping effect of a perforated liner with bias flow [14].…”

mentioning

confidence: 99%

Measurements and computational fluid dynamics predictions of the acoustic impedance of orifices

Rupp

Garmory

et al. 2015

Journal of Sound and Vibration

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a b s t r a c tThe response of orifices to incident acoustic waves, which is important for many engineering applications, is investigated with an approach combining both experimental measurements and numerical simulations. This paper presents experimental data on acoustic impedance of orifices, which is subsequently used for validation of a numerical technique developed for the purpose of predicting the acoustic response of a range of geometries with moderate computational cost. Measurements are conducted for orifices with length to diameter ratios, L/D, of 0.5, 5 and 10. The experimental data is obtained for a range of frequencies using a configuration in which a mean (or bias) flow passes from a duct through the test orifices before issuing into a plenum. Acoustic waves are provided by a sound generator on the upstream side of the orifices. Computational fluid dynamics (CFD) calculations of the same configuration have also been performed. These have been undertaken using an unsteady Reynolds averaged Navier-Stokes (URANS) approach with a pressure based compressible formulation with appropriate characteristic based boundary conditions to simulate the correct acoustic behaviour at the boundaries. The CFD predictions are in very good agreement with the experimental data, predicting the correct trend with both frequency and orifice L/D in a way not seen with analytical models. The CFD was also able to successfully predict a negative resistance, and hence a reflection coefficient greater than unity for the L=D ¼ 0:5 case.

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“…As both representations are interchangeable, the scattering matrix coefficients can be computed from the transfer matrix coefficients by a simple algebraic transformation have to be determined experimentally or numerically. Indeed, several studies deduced matrix coefficients for acoustically passive combustor parts of varying complexity, e.g., a single orifice [3], a tandem orifice [4], multiperforated liner plates [5], or a premixed nozzle [6]. The acoustic transfer behavior of swirl generators, which are an unavoidable part in swirl stabilized combustion systems, was numerically determined by Gikadi et al [7] and Ni et al [8].…”

Section: Transfer and Scattering Matricesmentioning

confidence: 99%

“…Experience has shown that this kind of analysis provides not only quantitative data on stability limits and dynamics of a combustion system but also important physical insight [9,[11][12][13][14][15][16]. Several previous studies have concentrated on the transfer or scattering matrices of individual combustor elements such as a flame, a burner, a swirl nozzle, or a dissipative element [3][4][5][6]8,9,11,13,14,[17][18][19]. The present study concerns in an integrated fashion a combustor scattering matrix that includes swirler, injection tube, and flame as well as parts of the combustion chamber, see Fig.…”

Section: Transfer and Scattering Matricesmentioning

confidence: 99%

Direct Assessment of the Acoustic Scattering Matrix of a Turbulent Swirl Combustor by Combining System Identification, Large Eddy Simulation and Analytical Approaches

Merk

Silva

Polifke

et al. 2018

Journal of Engineering for Gas Turbines and Power

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This study assesses and compares two alternative approaches to determine the acoustic scattering matrix of a premixed turbulent swirl combustor: (1) The acoustic scattering matrix coefficients are obtained directly from a compressible large eddy simulation (LES). Specifically, the incoming and outgoing characteristic waves f and g extracted from the LES are used to determine the respective transmission and reflection coefficients via System Identification (SI) techniques. (2) The flame transfer function (FTF) is identified from LES time series data of upstream velocity and heat release rate. The transfer matrix of the reactive combustor is then derived by combining the FTF with the Rankine–Hugoniot (RH) relations across a compact heat source and a transfer matrix of the cold combustor, which is deduced from a linear network model. Linear algebraic transformation of the transfer matrix consequently yields the combustor scattering matrix. In a cross-comparison study that includes comprehensive experimental data, it is shown that both approaches successfully predict the scattering matrix of the reactive turbulent swirl combustor.

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LES for the Evaluation of Acoustic Damping of Effusion Plates

Cited by 5 publications

References 34 publications

Local Source Based CFD Modeling of Effusion Cooling Holes: Validation and Application to an Actual Combustor Test Case

Local Source Based CFD Modeling of Effusion Cooling Holes: Validation and Application to an Actual Combustor Test Case

Measurements and computational fluid dynamics predictions of the acoustic impedance of orifices

Direct Assessment of the Acoustic Scattering Matrix of a Turbulent Swirl Combustor by Combining System Identification, Large Eddy Simulation and Analytical Approaches

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