The control mechanism of the blades to be applied to the gas turbine engines

摘要

1,064,330. Axial flow compressors. ROLLS-ROYCE Ltd. Jan.10, 1966, No.1134/66. Heading F1C. The pivotally mounted stator blades in the high pressure axial flow compressor of a gas turbine by-pass engine are angularly adjustable by axially spaced rings 33, 34 surrounding the compressor casing (15) Fig. 1 (not shown), and engaging ball portions 31 at the opposite ends of levers 27 each attached to the spindle (21) of a blade (20), Fig. 3 (not shown). The rings 33, 34 are rotatable in opposite directions by a pair of rams 35 and thus apply couples to levers 27 to effect rotation of the blades. Springs 40 urge the rings 33, 34 into engagement with the ball portions 31 and may assist in urging the rings towards predetermined relative angular positions. The recesses 32 in the rings engaging ball portions 31 are hemi-spherical and in a modification, Fig. 5 (not shown) the hemispheres are cut away (at 43) to assist assembly of the ball portions therein. The levers 27 have thin portions (30) to accommodate flexing during operation.