Some Viscosity Effects in Axial Flow Compressors

1. A thirty-six inch tip diameter axial flow air compressor, auxiliary apparatus and instrun1entation have been constructed and have been successfully operated for securing accurate test data. 2. Special instruments for detailed flow measurements near bounding surfaces have been constructed and successfully used. 3. On the basis of data secured from the test installation, it has been established that flow energy losses which result from fluid friction on actual compressor blade surfaces are considerably greater than would be expected from measured or calculated two-dimensional results. Furthermore, the range of low-loss operation is significantly reduced. 4. Test results indicate that the outer and inner wall boundary regions, which are affected by fluid friction, may or may not become more extensive through several stages of an axial flow compressor, depending on the specific compressor design. 5. Measurements indicate that a considerable portion of overall compressor losses occur near the outer end inner extremes of the blade sets because of poor flow incidence conditions in the wall boundary regions.