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 percent 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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April 1995
Research Papers
Fan Noise Reduction From a Supersonic Inlet During Simulated Aircraft Approach
W. E. Nuckolls,
W. E. Nuckolls
Department of Mechanical Engineering, Virginia Polytechnic Institute and State University, Blacksburg, VA 24061
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W. F. Ng
W. F. Ng
Department of Mechanical Engineering, Virginia Polytechnic Institute and State University, Blacksburg, VA 24061
Search for other works by this author on:
W. E. Nuckolls
Department of Mechanical Engineering, Virginia Polytechnic Institute and State University, Blacksburg, VA 24061
W. F. Ng
Department of Mechanical Engineering, Virginia Polytechnic Institute and State University, Blacksburg, VA 24061
J. Eng. Gas Turbines Power. Apr 1995, 117(2): 237-244 (8 pages)
Published Online: April 1, 1995
Article history
Received:
March 10, 1993
Online:
November 19, 2007
Citation
Nuckolls, W. E., and Ng, W. F. (April 1, 1995). "Fan Noise Reduction From a Supersonic Inlet During Simulated Aircraft Approach." ASME. J. Eng. Gas Turbines Power. April 1995; 117(2): 237–244. https://doi.org/10.1115/1.2814086
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