Broadband Inlet Liner Design for the DGEN Aero-propulsion Research Turbofan

Nark, Douglas M.; Jones, Michael G.; Sutliff, Daniel L.

doi:10.2514/6.2018-3608

Cited by 8 publications

(6 citation statements)

References 20 publications

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“…To gain further confidence in the tools used within the broadband liner design process, a series of multidegree of freedom (MDOF) liner design studies at increasing technology readiness levels (TRL) have been conducted as the overall optimization methodology has been enhanced. Initial liner designs targeting the NASA Langley Liner Technology Facility 8,9 (LTF) resulted in predicted optimum impedance spectra consistent with those obtained using higher-fidelity, more computationally intensive models 10 . Subsequent design and testing in the NASA Glenn Advanced Noise Control Fan (ANCF) Rig 3,4 and 9-ft x 15-ft Low Speed Wind Tunnel 5,6 provided further confidence in the design process.…”

Section: Introductionmentioning

confidence: 67%

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Design and Acoustic Efficacy of a Broadband Liner for the Inlet of the DGEN Aero-propulsion Research Turbofan

Sutliff

Nark

Jones

et al. 2019

25th AIAA/CEAS Aeroacoustics Conference

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Advanced fan designs (including higher bypass ratios) and shorter engine nacelles have highlighted a need for increased fan noise reduction over a broader frequency range. With these observations in mind, an acoustic liner optimization process has been developed to achieve improved broadband liner designs. A series of advanced liner design studies at increasing technology readiness levels have been conducted as the overall optimization methodology has been enhanced. As part of the analysis, the overall design and evaluation capability was extended such that external observer locations may be included in the optimization process. This enhancement will provide a much wider design space in designing advanced broadband liners. In this work, further validation was pursued through the fabrication and testing of two liner designs for the NASA Glenn DGEN Aero-propulsion Research Turbofan (DART). The DART was used to document the efficacy of acoustic liners installed in the inlet of the DGEN380. An advanced Multi-Degree of Freedom Liner was designed, fabricated, and tested, along with a traditional Single-Degree-of-Freedom liner, and those results compared to a hardwall baseline inlet. Farfield acoustic data were acquired from an external array, evaluated and reported herein terms of overall, broadband, and tonal components of the insertion loss. The predicted attenuation results generally matched expected trends of the measured data for the conditions considered.

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Section: Introductionmentioning

confidence: 67%

“…As mentioned above, the liner design process is described in a previous paper 13 . However, it is useful to provide a brief overview of the methodology for completeness.…”

Section: Acoustic Predictionsmentioning

confidence: 99%

Design and Acoustic Efficacy of a Broadband Liner for the Inlet of the DGEN Aero-propulsion Research Turbofan

Sutliff

Nark

Jones

et al. 2019

25th AIAA/CEAS Aeroacoustics Conference

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“…7,10,15,18 As confidence in the overall methodology increased, design and testing efforts were pursued in the NASA Glenn Advanced Noise Control Fan (ANCF) Rig, 19–21 9- by 15-Foot Low Speed Wind Tunnel, 22,23 and Aeroacoustic Propulsion Laboratory (AAPL). 24 Lessons learned from these projects culminated in the design and flight testing of an advanced inlet liner on the Quiet Technology Demonstrator 3 (QTD3). The contributions of each of these studies to the evolution of the design methodology has been documented in the references above.…”

Section: Application and Assessment Of The Liner Design Methodologymentioning

confidence: 99%

An acoustic liner design methodology based on a statistical source model

Nark

Jones

2021

International Journal of Aeroacoustics

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The attenuation of fan tones remains an important aspect of fan noise reduction for high bypass ratio turbofan engines. However, as fan design considerations have evolved, the simultaneous reduction of broadband fan noise levels has gained interest. Advanced manufacturing techniques have also opened new possibilities for the practical implementation of broadband liner concepts. To effectively address these elements, practical acoustic liner design methodologies must provide the capability to efficiently predict the acoustic benefits of novel liner configurations. This paper describes such a methodology to design and evaluate multiple candidate liner configurations using realistic, three dimensional geometries for which minimal source information is available. The development of the design methodology has been guided by a series of studies culminating in the design and flight test of a low drag, broadband inlet liner. The excellent component and system noise benefits obtained in this test demonstrate the effectiveness of the broadband liner design process. They also illustrate the value of the approach in concurrently evaluating multiple liner designs and their application to various locations within the aircraft engine nacelle. Thus, the design methodology may be utilized with increased confidence to investigate novel liner configurations in future design studies.

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“…However, being a rather new demonstrator, related research is scarce. The associated available literature found can be grouped in 4 categories: performance cycle studies using 0D approximations (Pilet et al, 2011;López de Vega et al, 2019), acoustics and liners research (Berton, 2016;Brown and Sutliff, 2018;Nark et al, 2018;Sutliff et al, 2019;Nagai et al, 2019) including combustion noise (Boyle et al, 2018(Boyle et al, , 2020, experimental and RANS campaigns at wind-milling conditions (Dufour et al, 2015;García Rosa et al, 2015;Dufour and Thollet, 2016) and experimental as well as LES investigations of the flow around the fan and the Outlet-Guide Vanes (OGV) at the nominal operating point (Odier et al, 2017(Odier et al, , 2018.…”

Section: Introductionmentioning

confidence: 99%

Towards the Large-Eddy Simulation of a full engine: Integration of a 360 azimuthal degrees fan, compressor and combustion chamber. Part I: Methodology and initialisation

Arroyo

Dombard

Duchaine

et al. 2021

J. Glob. Power Propuls. Soc.

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Optimising the design of aviation propulsion systems using computational fluid dynamics is essential to increase their efficiency and reduce pollutant as well as noise emissions. Nowadays, and within this optimisation and design phase, it is possible to perform meaningful unsteady computations of the various components of a gas-turbine engine. However, these simulations are often carried out independently of each other and only share averaged quantities at the interfaces minimising the impact and interactions between components. In contrast to the current state-of-the-art, this work presents a 360 azimuthal degrees large-eddy simulation with over 2100 million cells of the DGEN-380 demonstrator engine enclosing a fully integrated fan, compressor and annular combustion chamber at take-off conditions as a first step towards a high-fidelity simulation of the full engine. In order to carry such a challenging simulation and reduce the computational cost, the initial solution is interpolated from stand-alone sectoral simulations of each component. In terms of approach, the integrated mesh is generated in several steps to solve potential machine dependent memory limitations. It is then observed that the 360 degrees computation converges to an operating point with less than 0.5% difference in zero-dimensional values compared to the stand-alone simulations yielding an overall performance within 1% of the designed thermodynamic cycle. With the presented methodology, convergence and azimuthally decorrelated results are achieved for the integrated simulation after only 6 fan revolutions.

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Broadband Inlet Liner Design for the DGEN Aero-propulsion Research Turbofan

Cited by 8 publications

References 20 publications

Design and Acoustic Efficacy of a Broadband Liner for the Inlet of the DGEN Aero-propulsion Research Turbofan

Design and Acoustic Efficacy of a Broadband Liner for the Inlet of the DGEN Aero-propulsion Research Turbofan

An acoustic liner design methodology based on a statistical source model

Towards the Large-Eddy Simulation of a full engine: Integration of a 360 azimuthal degrees fan, compressor and combustion chamber. Part I: Methodology and initialisation

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