FIELD: aircraft engine building.
SUBSTANCE: design of an adjustable inlet guide vane (IVA) of an axial compressor of a gas turbine engine (GTE). The guide apparatus includes power outer housing (1) with rotary vanes (2) and drive vane (3) rotating in bronze bushings (4), drive lever (5) fastened to drive vane (3) with fitting bolt (6) and self-locking nut (7), drive ring (8) with grooves on the rear surface for installing brackets (9, 10), matched to the size of levers (11) and an inner ring consisting of two rings - front (12) and rear (13). The effect is achieved through the use of a set of simple and reliable design solutions, namely the use of brackets (9) pivotally connected to drive lever (5) and sized levers (11), as well as z-shaped brackets (10) with rollers (20), secured to drive ring (8).
EFFECT: improved accuracy of setting the angle of the rotary vane of the guide vane in relation to the direction of flow in the control range, as well as reduced force applied to the drive vane resulting in improved reliability and extended service life of the compressor guide vane.
1 cl, 10 dwg
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