| 摘要 |
PURPOSE: To prevent surface fatigue of a contacting face of shroud by installing a hoop shroud that is connected to an intermediate part of a rotary blade of low pressure stage in one-piece, having a shroud that divides an air flow into a bypass outer airflow path and an inner airflow path directed to a higher pressure stage of a compressor. CONSTITUTION: A low pressure stage 12 in an axial flow compressor 10 of a jet engine has a series of rotor blades 14 supported by a rotor disk 16, and a series of stator vanes 18 supported by an outer casing 20. In this case, notch 34 is formed in airfoil 30 of each rotor blade 14, an annular hoop shroud 38 circumferentially extending over the series of rotor blade 14 or a whole stage is mounted to the notch 34. The airflow is divided into an outer path 62 extending between the inner and the outer case 27, 20, and an inner path 64 extending radially inward relative to the inner case 27 by the hoop shroud 38.
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