GB1492097A - Turbine engine vane actuation system - Google Patents

Abstract

1492097 Turbomachines - guide vane actuation GENERAL MOTORS CORP 18 Sept 1975 [27 Sept 1974] 38325/75 Headings F1C and FIT [Also in Division H2] Adjustment of a row of vanes 38, Fig. 1, of a turbine or, as shown, a compressor 12 in a turbojet by-pass engine, including cranks 40 connected to a control ring 44, is effected by drive actuators 56, 62 and 76 converting rotary inputs into reciprocating movement at cam plates 52, 70 and 79 engaging pins 46 on one or, as shown, two control rings, the actuators being driven via drive cables 97, 99 and 101 from an engine-driven drive transfer unit 22 including, for each drive cable, a pair of electrically energizable fluid gap clutches comprising input rotors 136, 142, Fig. 4, fast with an enginedriven input shaft 100, and two output rotors 148, 154 respectively fast with an output shaft 150 and connected to the shaft via a reversing gear 176 including a central pinion 178 meshing via intermediate gears 180, 182 with a ring gear 184 mounted on a carrier 186 fast with the shaft 150. To balance the controlling input reaction, each actuator 56, 62 and 76 has a cable loop, e.g. 88 for actuator 56, driving a second actuator (90), Fig. 2, (not shown), reciprocating a second cam plate (93) engaging a pin (95) at a point on the ring diametrically opposite pin 46. The clutches may be replaced by magnetic particle clutches. Control may be effected automatically, e.g. in accordance with rotor speed, compressor inlet temperature discharge pressure and turbine discharge temperature.