CASCADE TESTING OF SUPERSONIC COMPRESSOR BLADE ELEMENTS.
Abstract
An experimental study was made of the aerodynamic behavior of a series of supersonic compressor blade elements. A two-dimensional cascade facility permitted the measurement of the mid-passage static pressure rise and the wake total pressure distribution. From these measurements the mass averaged total pressure recovery and loss coefficients were evaluated. Flow visualization studies were also performed. Comparisons between the measured loss parameters and simplified loss prediction techniques were made. For small values of the diffusion factor (and in this case where shock losses are relatively small) one may approximate the loss processes by summing the dump diffusion losses and the Lieblein loss correlation. At higher diffusion factors (and as shock losses become more important) a better correlation can be obtained by summing shock losses and the dump diffusion losses. In an effort to minimize the dump diffusion losses, the trailing edge of each blade design was modified. The resulting total pressure and loss parameters exhibit marked improvement. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1969
- Accession Number
- AD0689822
Entities
People
- John W. Steurer
- Ronald L. Haugen
Organizations
- Air Force Research Laboratory