Wall boundary layer development near the tip region of an IGV of an axial flow compressorThe annulus wall boundary layer inside the blade passage of the inlet guide vane (IGV) passage of a low-speed axial compressor stage was measured with a miniature five-hole probe. The three-dimensional velocity and pressure fields were measured at various axial and tangential locations. Limiting streamline angles and static pressures were also measured on the casing of the IGV passage. Strong secondary vorticity was developed. The data were analyzed and correlated with the existing velocity profile correlations. The end wall losses were also derived from these data.
Document ID
19830066754
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lakshminarayana, B. (Pennsylvania State Univ. University Park, PA, United States)
Sitaram, N. (Pennsylvania State University University Park, PA, United States)