TIP SHROUDED HIGH ASPECT RATIO COMPRESSOR STAGE

摘要

A gas turbine engine compressor stage includes a rotor (70). Compressor blades (71) are supported by the rotor (70). The blades (71) include an inner flow path surface each supporting an airfoil that has a chord (80) that extends radially along a span (78) to a tip. A shroud (82) is supported at the tip and provides an outer flow path surface. The shroud (82) provides a noncontiguous ring about the compressor stage.