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Effectiveness of an inlet flow turbulence control device to simulate flight noise fan in an anechoic chamber
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Shaw, L. M. Mackinnon, M. J. Woodward, R. P. Wazyniak, J. A. |
| Copyright Year | 1977 |
| Description | A hemispherical inlet flow control device was tested on a 50.8 cm. (20-inch) diameter fan stage in the NASA-Lewis anechoic chamber. The control device used honeycomb and wire mesh to reduce turbulence intensities entering the fan. Far field acoustic power level results show about a 5 db reduction in blade passing tone and about 10 dB reduction in multiple pure tone sound power at 90% design fan speed with the inlet device in place. Hot film cross probes were inserted in the inlet to obtain data for two components of the turbulence at 65 and 90% design fan speed. Without the flow control device, the axial intensities were below 1.0%, while the circumferential intensities were almost twice this value. The inflow control device significantly reduced the circumferential turbulence intensities and also reduced the axial length scale. |
| File Size | 706624 |
| Page Count | 22 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19780005913 |
| Archival Resource Key | ark:/13960/t8rc1v70g |
| Language | English |
| Publisher Date | 1977-01-01 |
| Access Restriction | Open |
| Subject Keyword | Acoustics Anechoic Chambers Turbulent Flow Noise Reduction Turbofans Aerodynamic Noise Stator Blades Inlet Flow Intake Systems Honeycomb Structures Sound Pressure Flight Simulation Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
