| 摘要 |
The compressor has multiple compression stages, each with annular rows of movable blades (12) rotating inside a double wall casing (18), and annular rows of straightened fixed blades (14) carried by an inner wall of the casing. The inner wall is formed of integrated ferrules (30, 32) aligned end-to-end and independently suspended to an outer wall (20) of the casing by edge springs (34, 36). The ferrules (30, 32) respectively surround the annular rows of movable blades and the annular rows of straightened fixed blades. An independent claim is also included for a jet prop engine or jet engine of aircraft. |
