| 摘要 |
<p>A double flow compressor for an aircraft jet engine has a ring of stator blades (2) mounted between an outside collar (3) and an inside collar (6). The top (8) of each blade flanges outwards, and is cross-shaped in end view, and is secured by a bolt (10) and nut (11) to the outside collar. The base (13) fits into the inside collar (6) with a flexible seal (15). This seal is of U-section and fits all round a diagonal slot across the inside collar. The base (13) of the blade is rectangular, with a rib (13a) extending downwards underneath. This arrangement permits blades to be easily interchanged after the upper securing bolts (10) have been removed. They are then angled out from the sound deadening panels (5) under the outside collar.</p> |
