Effect of a blade end slot on supersonic compressor cascade hub-corner separation
Sign Up to like & getrecommendations! Published in 2021 at "Aerospace Science and Technology"
DOI: 10.1016/j.ast.2021.107032
Abstract: Abstract The strong adverse pressure gradient and shock wave/boundary layer interaction that occurs in supersonic compressor cascade corner regions usually leads to large three-dimensional corner separations with extensive total pressure losses. This substantially restricts compressor… read more here.
Keywords: end slot; blade end; corner separation; corner ... See more keywords