A series of experiments was conducted to investigate the radiation of fan noise from a supersonic inlet during a simulated aircraft approach. A scaled-down model of an axisymmetric, mixed-compression, supersonic inlet (P-inlet) was used in conjunction with a 10.4 cm (4.1 in) diameter turbofan engine simulator as the noise source. The tests were conducted at an outdoor facility under static conditions. The main goal of the experiment was to reduce the forward radiating fan noise by modifying the auxiliary inlet doors. The modified doors are designed to reduce the inlet distortion to the fan face. In addition, the new door design also uses a converging flow passage in order to take advantage of the noise attenuation due to the choking effect at the auxiliary door. The simulator was tested at 60% design speed in an attempt to match the simulator noise source to that of a real aircraft engine on approach. Both aerodynamic and acoustic measurements were taken in the experiments. The results show that when compared to the original design, the modified auxiliary inlet doors reduced the circumferential inlet distortion to the fan face by a factor of two. The key result is that the blade passing frequency tone has been decreased by an average of 6 dB in the forward sector for the modified door design. Results from the closed auxiliary inlet door case are also presented to provide additional comparisons.
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ASME 1993 International Gas Turbine and Aeroengine Congress and Exposition
May 24–27, 1993
Cincinnati, Ohio, USA
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-7891-0
PROCEEDINGS PAPER
Fan Noise Reduction From a Supersonic Inlet During Simulated Aircraft Approach
W. E. Nuckolls,
W. E. Nuckolls
Virginia Tech, Blacksburg, VA
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W. F. Ng
W. F. Ng
Virginia Tech, Blacksburg, VA
Search for other works by this author on:
W. E. Nuckolls
Virginia Tech, Blacksburg, VA
W. F. Ng
Virginia Tech, Blacksburg, VA
Paper No:
93-GT-279, V03BT16A035; 9 pages
Published Online:
February 25, 2015
Citation
Nuckolls, WE, & Ng, WF. "Fan Noise Reduction From a Supersonic Inlet During Simulated Aircraft Approach." Proceedings of the ASME 1993 International Gas Turbine and Aeroengine Congress and Exposition. Volume 3B: General. Cincinnati, Ohio, USA. May 24–27, 1993. V03BT16A035. ASME. https://doi.org/10.1115/93-GT-279
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