| 摘要 |
<p>1,263,435. Turbines; axial-flow compressors. GENERAL MOTORS CORP. April 9, 1970 [July 25, 1969], No. 16967/70. Headings F1C and F1T. The throat area of an assembly of fixed guide vanes 10 for a turbine or compressor can be varied by generally axially movable aerofoil section plugs 40 disposed between adjacent vanes with their span extending generally circumferentially of the assembly. Each plug 40 is supported by a faired strut 51 from an actuating ring 54 which is axially slidable in a chamber defined between a structural ring 11 and a shroud facing ring 15. Cranked brackets 56 connect the actuating ring 54 to arms 60 which at one end 61 are pivotally mounted on a flange on ring 11 and at the other end 65 are connected to a unison ring 64. Thus circumferential movement of the latter causes movement of the plugs 40 in the direction 'B' so as to vary the throat area. Cooling air supplied through holes 36 in ring 11 flows through holes 68 into the interior of actuating ring 54 and thence through struts 51 to the interior of plugs 40, the walls of the latter being porous. Shroud facing rings 15, 20, 22 are also porous to assist cooling. Cooling air can flow to the interior of each vane 10 through its ends and through a hollow supporting spine 26. In a modification, Fig. 3 (not shown), the plug 40 is formed as a 360 degree one piece or segmental ring having a notch (49) at the position of each vane 10.</p> |
