Aerodynamic performance of scale-model turbofan outlet guide vanes designed for low noise

Hughes, Christopher E.

doi:10.2514/6.2002-374

Cited by 60 publications

(49 citation statements)

References 4 publications

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“…The procedure used for the fan performance testing has been described previously. 2 The fan module hardware configuration included the fixed area nozzle used for acoustic testing to obtain the correct fan operating line and a calibrated bellmouth inlet to measure the fan weight flow. The fan performance was measured using three fixed rakes mounted behind the fan.…”

Section: Test Proceduresmentioning

confidence: 99%

“…Recent aircraft engine noise research by NASA and the aerospace industry [1][2][3][4][5] has focused on identifying the composition of the noise sources in a modern turbofan aircraft engine, their generation mechanisms, and the level of contribution to the total aircraft system noise level. A test was conducted in the NASA Glenn Research Center 9-by 15-Foot Low Speed Wind Tunnel (9x15 LSWT), called the Source Diagnostic Test.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Fan Noise Source Diagnostic Test - Rotor Alone Aerodynamic Performance Results

Hughes¹,

Jeracki²,

Woodward³

et al. 2002

8th AIAA/CEAS Aeroacoustics Conference &Amp;amp; Exhibit

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Section: Test Proceduresmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Fan Noise Source Diagnostic Test - Rotor Alone Aerodynamic Performance Results

Hughes¹,

Jeracki²,

Woodward³

et al. 2002

8th AIAA/CEAS Aeroacoustics Conference &Amp;amp; Exhibit

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“…For this study, the 22-inch diameter NASA/GE Source Diagnostic Test (SDT) fan 5,6,7 is chosen. The SDT fan, shown in Figure 1, has a design corrected tip speed of 1,215 ft/sec, a stage pressure ratio of 1.47, and a bypass ratio of 8.9.…”

Section: Test Configurationmentioning

confidence: 99%

Broadband Liner Optimization for the Source Diagnostic Test Fan

Nark

Jones

2012

18th AIAA/CEAS Aeroacoustics Conference (33rd AIAA Aeroacoustics Conference)

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The broadband component of fan noise has grown in relevance with the utilization of increased bypass ratio and advanced fan designs. Thus, while the attenuation of fan tones remains paramount, the ability to simultaneously reduce broadband fan noise levels has become more appealing. This paper describes a broadband acoustic liner optimization study for the scale model Source Diagnostic Test fan. Specifically, in-duct attenuation predictions with a statistical fan source model are used to obtain optimum impedance spectra over a number of flow conditions for three liner locations in the bypass duct. The predicted optimum impedance information is then used with acoustic liner modeling tools to design liners aimed at producing impedance spectra that most closely match the predicted optimum values. Design selection is based on an acceptance criterion that provides the ability to apply increased weighting to specific frequencies and/or operating conditions. Typical tonal liner designs targeting single frequencies at one operating condition are first produced to provide baseline performance information. These are followed by multiple broadband design approaches culminating in a broadband liner targeting the full range of frequencies and operating conditions. The broadband liner is found to satisfy the optimum impedance objectives much better than the tonal liner designs. In addition, the broadband liner is found to provide better attenuation than the tonal designs over the full range of frequencies and operating conditions considered. Thus, the current study successfully establishes a process for the initial design and evaluation of novel broadband liner concepts for complex engine configurations.

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“…Figure 4 shows a photograph of the model SDT fan installed in the NASA Glenn 9×15 LSWT. 8,9 This test series investigated two rotor and three stator configurations, as well as a unique rotor-alone configuration in which the nacelle was externally supported and aligned with the rotor. SDT results presented herein are for the R4 rotor and baseline 52 vane radial stator, and for the "quietest" configuration with the R4 rotor and a 26-vane swept stator.…”

Section: B Model Turbofansmentioning

confidence: 99%

Comparison of Far-Field Noise for Three Significantly Different Model Turbofans

Woodward

2008

46th AIAA Aerospace Sciences Meeting and Exhibit

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Aerodynamic performance of scale-model turbofan outlet guide vanes designed for low noise

Cited by 60 publications

References 4 publications

Fan Noise Source Diagnostic Test - Rotor Alone Aerodynamic Performance Results

Fan Noise Source Diagnostic Test - Rotor Alone Aerodynamic Performance Results

Broadband Liner Optimization for the Source Diagnostic Test Fan

Comparison of Far-Field Noise for Three Significantly Different Model Turbofans

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