Influence of a Moving Endwall on the Tip Clearance Vortex in an Axial Compressor Cascade.
Abstract
This experiment involved the design, construction, validation and testing of a new facility for the investigation of vortices generated by compressor rotor blade tip clearance with a moving endwall. A five-tube pressure rake placed downstream of the trailing edge of a cascade of blades measured the pressure field for flow coefficients ranging from 20 to 1.66 and tip clearances of 0.33, 1.0, 1.7 and 2.4 percent chord. Contour plots of mass averaged pressure loss coefficient appear to show the no-flow tip vortex becomes entrained and diffused by the moving wall boundary layer. The high loss region near the moving wall contracts toward and extends toward the pressure side of the adjacent blade. This contraction results in a reduction in overall blockage in the passage with a corresponding reduction in passage losses, toward an apparent steady-state value, for increasing end wall speed and decreasing tip clearance.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1995
- Accession Number
- ADA306384
Entities
People
- Lawrence J. Peter
Organizations
- Air Force Institute of Technology