A JT15D fan stage was acoustically tested in the NASA Lewis anechoic chamber as part of the joint Lewis-Langley Research Center investigation of flight simulation techniques and flight effects using the JT15D engine as a common test vehicle. Suspected rotor-downstream support strut interaction was confirmed through the use of simulated support struts which were tested at three axial rotor-strut spacings. Tests were also performed with the struts removed. Inlet boundary layer suction in conjuction with an inflow control device was also explored. The removal of the boundary layer reduced the fan fundamental tone levels suggesting that the mounting and mating of such a device to the nacelle requires careful attention. With the same inflow control device installed good acoustic agreement was shown between the engine on an outdoor test stand and the fan in the anechoic chamber.
Tone Generation by Rotor-Downstream Strut Interaction
1983
17 pages
Report
No indication
English
Tone generation by rotor-downstream strut interaction
NTRS | 1983
|Tone generation by rotor-downstream strut interaction
NTRS | 1983
|Tone generation by rotor-downstream strut interaction
AIAA | 1983
|Tone generation by rotor-downstream strut interaction
NTRS | 1984
|Tone generation by rotor-downstream strut interaction
AIAA | 1984
|