Shock Structure Measured in a Transonic Fan Using Laser Anemometry
Abstract
Shock structure measurements acquired in a low aspect ratio transonic fan rotor are presented and analyzed. The rotor aspect ratio in 1.56 and the design tip relative Mach number is 1.38. the rotor flowfield was surveyed at near maximum efficiency and near still operating conditions. Intra-blade velocity measurements acquired with a laser fringe anemometer on blade-to-blade planes in the supersonic region from 10 to 60 percent span are presented. The three-dimensional shock surface determined from the velocity measurements is used to determine the shock surface normal Mach number in order to properly calculate the ideal shock jump conditions. The ideal jump conditions are calculated based upon the Mach numbers measured on a surface of revolution and based upon the normal Mach number to indicate the importance of accounting for shock three dimensionality in turbomachinery design. Comparison of the shock locations with those predicted by 3D Euler code showed very good agreement and indicated the usefulness of integrating computational and experimental work to enhance understanding of the flow physics occurring in transonic turbomachinery passages.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1987
- Accession Number
- ADP005506
Entities
People
- Anthony J. Strazisar
- Jerry R. Wood
- P. S. Simonyi
Organizations
- National Aeronautics and Space Administration