Initial Characterization of Three-Dimensional Flow Separation in a Compressor Stator (Preprint)
Abstract
A research program is underway seeking to effect a net decrease in aerodynamic loss of a moderately loaded axial compressor stator passage across varying operating conditions. Three dimensional boundary layer separation, typical at the suction surface corners, can differ greatly from classical two dimensional separation, and is the dominant loss and blockage generating feature in the diffusing flowfield of compressor stators. The initial research phase is presently described, wherein a typical modern stator configuration has been designed, and numerical simulations have been used to characterize the aerodynamic performance and key flow features of the baseline stator configuration. The evaluation has been conducted at the high subsonic inlet Mach design condition as well as off-design conditions, including varying incidence angle and inlet Mach number. Refinement and analysis of the baseline configuration is on-going, but the design's performance suggests it is a typical modern stator, providing a good benchmark for the planned competitive approaches towards performance improvement.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 2008
- Accession Number
- ADA486375
Entities
People
- Grant A. Hile
- S. T. Bailie
- Steven L. Puterbaugh
Organizations
- Air Force Research Laboratory