GB1085472A - Improvements relating to variable area tur bine nozzles - Google Patents

Abstract

1,085,472. Turbine inlet nozzle guide vane assembly. UNITED AIRCRAFT CORPORATION. May 2, 1966, No. 19205/66. Heading F1T. The invention relates to an adjustable area inlet nozzle guide vane assembly for a turbine, the assembly comprising inner and outer support rings, guide vanes extending between the rings and supported thereby, each of the guide vanes at one end being hinged individually on one of ;the support rings for movement about an axis disposed at an acute angle to the axis of the one support ring, there being means for relatively moving the support rings so as to produce adjustment of the vanes. In a first embodiment as applied to the turbine inlet nozzle guide vanes of a gas turbine engine, the guide vanes 30 each comprise a shroud member 46 at the radially inner end and a shroud member 54 at the radially outer end. A stem 34 projects from the inner shroud 46 and a part-spherical member 36 is secured thereon, the member 36 being received in a part-spherical seat in a socket member 40 which is located in an inner support ring 28. The outer shroud ring 54 is formed integrally with a projection 84 and flanges 86, 88, a pin 82 extending through the flanges and a sleeve 80 being carried by the pin between the flanges. The axis 92 of the pin 82 is disposed at an acute angle to the axis 93 of the engine, Fig. 6 (not shown). The sleeve 80 is received in a radial slot 78 formed in an actuator ring 62 - see also Fig. 3, the ring being supported by means of balls 66 in a stationary ring 68 secured to the outer casing 10 of the engine whereby the actuator ring may be moved circumferentially. The actuator ring has a flange 94, Fig. 4 to which is connected a link 96, the link being connected also to a stud secured eccentrically to a radially mounted stub shaft 100. The stub shaft may be rotated by means of a driving spline 106 thus causing rotational movement of the actuator ring 62 which will result in the guide vane 30 pivoting circumferentially about the pivot point 36, 40 as indicated in Fig. 2, between the position shown in full lines and that in broken lines. Sealing devices 50 and 58 are disposed adjacent the radially inner and radially outer shrouds 46 and 54 respectively. A plurality of stub shafts 100 may be provided, the stub shafts being interconnected for simultaneous rotation by means of a ring gear 102. In a second embodiment, Fig. 8 the guide vanes are mounted at their radially inner ends on pins 124 which are inclined to the axis of the engine, the radially outer ends of the vanes being movable circumferentially through a small angle in a manner similar to that of the first embodiment. The pin 124 has at one end a flange 125 formed with a part-spherical surface 132 which engages with a part-spherical seating surface 134 formed in the lug 130 which is integral with the inner shroud 126. The other end of the pin 124 engages in a radial slot 136 formed in the other lug 128 integral with the shroud 126.