Quiet Technology Demonstrator 2 Intake Liner Design and Validation

Yu, Jia; Nesbitt, Eric; Kwan, H. W.; Uellenberg, Stefan; Chien, Eugene; Premo, John; Ruiz, Marta; Czech, Micheal

doi:10.2514/6.2006-2458

Cited by 24 publications

(6 citation statements)

References 1 publication

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“…Specifically, Astley et al [39] showed, using finite-element solutions of the wave propagation problem, that the extended liner "does not behave simply as an extension to the cylindrical barrel liner." Further, the benefits of this liner configuration were demonstrated in flight tests reported by Yu et al [40] and in tests on a 1/3-scale fan rig by Gantie et al [41]. The present investigation complements these earlier studies by establishing a physical rationale for the observed behavior.…”

Section: Discussionsupporting

confidence: 75%

Dispersion, dissipation and refraction of shock waves in acoustically treated turbofan inlets

Prasad¹,

Topol

2015

Journal of Sound and Vibration

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Section: Discussionsupporting

confidence: 75%

Dispersion, dissipation and refraction of shock waves in acoustically treated turbofan inlets

Prasad¹,

Topol

2015

Journal of Sound and Vibration

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“…Finally, the lip liner is integrated with the nose cone to limit aero performance losses [32]. The technology is a result of collaboration between Boeing and Goodrich Aerostructures, and the investigators showed reductions of inlet radiated fan noise of up to 13dB [32]. However, per discussions with NASA researchers during ERA technology workshops, the noise reduction applied is -3dB on approach and -1dB on takeoff.…”

Section: Nose Lip Linermentioning

confidence: 98%

“…This reduces the scatter of tonal noise. Finally, the lip liner is integrated with the nose cone to limit aero performance losses [32]. The technology is a result of collaboration between Boeing and Goodrich Aerostructures, and the investigators showed reductions of inlet radiated fan noise of up to 13dB [32].…”

Section: Nose Lip Linermentioning

confidence: 99%

Noise Assessment of NASA Environmentally Responsible Aviation (ERA) Technologies and Concepts

Jiménez

Pfaender

Havrilesko

et al. 2012

12th AIAA Aviation Technology, Integration, and Operations (ATIO) Conference and 14th AIAA/ISSMO Multidisciplinary Analysis And

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We present a comprehensive assessment of NASA Environmentally Responsible Aviation Project technologies across aircraft component, single event, and multi-event levels. Modeling capabilities appropriate for each level of abstraction are introduced. We examine noise technologies in terms of component-level performance effects, modeling considerations, and aircraft-level impacts. Single event performance results include discussion of reference vehicle models and their accuracy, as well as modeled vehicle performance in the form of noise certification point measurements and single event contours. We then present an assessment of the technology portfolio in the context of a generic airport multi-event study where the noise performance of industry project aircraft expected to enter the market over the next decade is also approximated. Results discussed provide a comprehensive characterization of noise reductions achievable with technologies in question and provide further analytical support for their continued development.

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“…The PAA T-fan chevron nozzle was tested with and without the core chevron nozzle in configurations 2 and 4 providing for the determination of the possible interaction effect of the fan and core chevrons. Both of these configurations included an Acoustically Smooth Inlet (ASI) that removed liner splices, moved the acoustic liner closer to the fan rotor, and added a lip liner 15 . The baseline nozzles were tested on both Configs.…”

Section: Flight Test Configurationsmentioning

confidence: 99%

Flight Test Results for Uniquely Tailored Propulsion-Airframe Aeroacoustic Chevrons: Community Noise

Mengle

Ganz

Nesbitt

et al. 2006

12th AIAA/CEAS Aeroacoustics Conference (27th AIAA Aeroacoustics Conference)

Self Cite

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The flow/acoustic environment around the jet exhaust of an engine when installed on an airplane, say, under the wing, is highly asymmetric due to the pylon, the wing and the high-lift devices. Recent scale model tests have shown that such Propulsion Airframe Aeroacoustic (PAA) interactions and the jet mixing noise can be reduced more than with conventional azimuthally uniform chevrons by uniquely tailoring the chevrons to produce enhanced mixing near the pylon. This paper describes the community noise results from a flight test on a large twin-engine airplane using this concept of azimuthally varying chevrons for engines installed under the wing. Results for two different nozzle configurations are described: azimuthally varying "PAA T-fan" chevrons on the fan nozzle with a baseline no-chevron core nozzle and a second with PAA T-fan chevrons with conventional azimuthally uniform chevrons on the core nozzle. We analyze these test results in comparison to the baseline no-chevron nozzle on both spectral and integrated power level bases. The study focuses on the peak jet noise reduction and the effects at high frequencies for typical take-off power settings. The noise reduction and the absolute noise levels are then compared to model scale results. The flight test results verify that the PAA T-fan nozzles in combination with standard core chevron nozzles can, indeed, give a reasonable amount of noise reduction at low frequencies without high-frequency lift during take-off conditions and hardly any impact on the cruise thrust coefficient.

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Quiet Technology Demonstrator 2 Intake Liner Design and Validation

Cited by 24 publications

References 1 publication

Dispersion, dissipation and refraction of shock waves in acoustically treated turbofan inlets

Dispersion, dissipation and refraction of shock waves in acoustically treated turbofan inlets

Noise Assessment of NASA Environmentally Responsible Aviation (ERA) Technologies and Concepts

Flight Test Results for Uniquely Tailored Propulsion-Airframe Aeroacoustic Chevrons: Community Noise

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