| 摘要 |
<p>1,216,920. Axial-flow compressors. GENERAL ELECTRIC CO. Sept. 16, 1968 [Sept. 22, 1967], No.43866/68. Heading F1C. In an axial-flow compressor, e.g. of an aircraft gas turbine engine, having at least one row of pivotal stator vanes 30, Fig. 2, adjustable simultaneously on angular movement of an adjustor ring 20 about the compressor axis, each vane is connected to the adjustor ring via a respective lever arm 18 rigidly bolted at 36 to the vane and ball jointed at 40 to the radially outer surface of the adjustor ring. During adjustment of the vanes the relative motions between the lever arms and the adjustor ring are taken by the ball joints and by flexure of the lever arms. The adjustor ring may be of aluminium or titanium and formed from two shells joined together. Headed bushings 48, which may be of hardened steel, are secured to the adjustor ring as by swaging at their inner ends. The compressor may have several rows of pivotal stator vanes, with the respective adjustor rings connected through links to a common actuating lever (24), Fig. 1 (not shown).</p> |
