Effects of Inlet Distortion on the Development of Secondary Flows in a Subsonic Axial Inlet Compressor Rotor.
Abstract
Detailed flow measurements were taken inside an isolated axial compressor rotor operating subsonically near peak efficiency. Laser Anemometer measurements were made with two inlet velocity profiles. One profile consisted of an unmodified baseline flow, and the second profile was distorted by placing axisymmetric screens on the hub and shroud well upstream of the rotor. A primary flow is defined in the rotor and deviations from this primary flow for each inlet flow condition are identified. A comparison between the two flow deviations is made to assess the development of a passage vortex due to the distortion of the inlet flow. A comparison of experimental results with computational predictions from a Navier-Stokes solver showed good agreement between predicted and measured flows. Measured results indicate that a distorted inlet profile has minimal effect on the development of the flow i the rotor passage and the resulting passage vortex.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1991
- Accession Number
- ADA240930
Entities
People
- Albert K. Owen
Organizations
- National Aeronautics and Space Administration