Analytical Study of the Effects of Wind Tunnel Turbulence on Turbofan Rotor Noise PDF Download
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Category :
Languages : en
Pages : 132
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Author:
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Category :
Languages : en
Pages : 132
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Category : Aeronautics
Languages : en
Pages : 702
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Category : Shock (Mechanics)
Languages : en
Pages : 660
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Category :
Languages : en
Pages : 268
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Author: National Aeronaut Administration (Nasa)
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Category :
Languages : en
Pages : 32
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An advanced model turbofan was tested in the NASA Glenn 9- by 15-Foot Low Speed Wind Tunnel (9x15 LSWT) to explore far field acoustic effects associated with rotor Trailing-Edge-Blowing (TEB) for a modern, 1.294 stage pressure ratio turbofan model. The TEB rotor (Fan9) was designed to be aerodynamically similar to the previously tested Fan1, and used the same stator and nacelle hardware. Fan9 was designed with trailing edge blowing slots using an external air supply directed through the rotor hub. The TEB flow was heated to approximate the average fan exit temperature at each fan test speed. Rotor root blockage inserts were used to block TEB to all but the outer 40 and 20% span in addition to full-span blowing. A configuration with full-span TEB on alternate rotor blades was also tested. Far field acoustic data were taken at takeoff/approach conditions at 0.10 tunnel Mach. Far-field acoustic results showed that full-span blowing near 2.0% of the total flow could reduce the overall sound power level by about 2 dB. This noise reduction was observed in both the rotor-stator interaction tones and for the spectral broadband noise levels. Blowing only the outer span region was not very effective for lowering noise, and actually increased the far field noise level in some instances. Full-span blowing of alternate blades at 1.0% of the overall flow rate (equivalent to full-span blowing of all blades at 2.0% flow) showed a more modest noise decrease relative to full-span blowing of all blades. Detailed hot film measurements of the TEB rotor wake at 2.0% flow showed that TEB was not every effective for filling in the wake defect at approach fan speed toward the tip region, but did result in overfilling the wake toward the hub. Downstream turbulence measurements supported this finding, and support the observed reduction in spectral broadband noise. Glenn Research Center NASA/TM-2007-214666, E-15802, AIAA Paper 2007-1241 TRAILING EDGES; ENGINE NOISE; AIRCRAFT ENGINES; AEROACOUSTICS; SPANWISE BLOWING; TURBOFAN ENGINES; LOW SPEED WIND TUNNELS; NOISE REDUCTION; FAR FIELDS; PRESSURE RATIO; BROADBAND; WAKES; DEFECTS
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Category : Aeronautics
Languages : en
Pages : 1048
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Author:
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Category : Aeronautics
Languages : en
Pages : 310
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Author:
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Category : Aeronautics
Languages : en
Pages : 580
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Author:
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Category : Science
Languages : en
Pages : 1402
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Author: Albert R. George
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Category : Rotors
Languages : en
Pages : 104
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