Publication Date:
2019-07-13
Description:
An experimental and computational investigation of the NASA Low-Speed Centrifugal Compressor (LSCC) flow field has been conducted using laser anemometry and Dawes' 3D viscous code. The experimental configuration consists of a backswept impeller followed by a vaneless diffuser. Measurements of the three-dimensional velocity field were acquired at several measurement planes through the compressor. The measurements describe both the throughflow and secondary velocity field along each measurement plane and in several cases provide details of the flow within the blade boundary layers. The experimental and computational results provide a clear understanding of the development of the throughflow momentum wake which is characteristic of centrifugal compressors.
Keywords:
AERODYNAMICS
Type:
NASA-TM-106421
,
E-8258
,
NAS 1.15:106421
,
ARL-TR-331
,
eeting of the AGARD Propulsion and Energetics Panel, Technology Requirements for Small Gas Turbine Engines; Oct 04, 1993 - Oct 06, 1993; Montreal, Ontario; Canada
Format:
application/pdf
