Transonic compressor noise the effect of inlet guide vane/rotor spacing

dc.contributor.author	D. A. Kilpatrick	en_US
dc.contributor.author	D. T. Reid	en_US
dc.date.accessioned	2014-10-21T15:56:22Z
dc.date.available	2014-10-21T15:56:22Z
dc.date.issued	1964	en_US
dc.identifier.other	ARC/R&M-3412	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/3996
dc.description.abstract	Comprehensive noise measurements were made in the inlet duct of a model of a typical two-stage transonic fan. The tests covered a range of variations in the inlet guide/rotor axial spacing from normal, in small increments, to a spacing of about one blade-chord length. The effect of compressor speed and flow is pronounced for both the discrete blade tone and the vortex noise. As the axial spacing is increased the discrete blade tone output is reduced, the vortex noise being virtually unaffected.	en_US
dc.relation.ispartofseries	Aeronautical Research Council Reports & Memoranda	en_US
dc.title	Transonic compressor noise the effect of inlet guide vane/rotor spacing	en_US