GAS-TURBINE ENGINE AXIAL-FLOW COMPRESSOR Russian patent published in 1998 - IPC

FIELD: mechanical engineering; turbojet engines. SUBSTANCE: compressor is designed for building high pressure of air in two-circuit turbojet engines with high bypass ratio. Adjustment of variants of angles of setting and intervals of angles of vane turning of guide vane assemblies is provided simultaneously by power mechanisms of drives 20, 21. Efforts from drives 20, 21 are conveyed synchronously in one direction to controllable tie-rods 42 and hinge joint 46 of lever 41 by synchronously rotating drive shafts 22, 23. Drive shafts 22, 23 engage through hinge joints 27, 28, 29 of other levers 24, 25, 26 with controllable tie-rods 17, 18, 19 and rotate synchronizing rings 14, 15, 16 circumferentially through hinge joints 43, 44, 45. Rings 14, 15, 16 hinge coupled with turnable levers 11, 12, 13 engage at turning along circumference with tail pieces 8, 9, 10, thus providing required angles of vane setting of guide valve assemblies at all duties of operation of multiple stage compressor of gas turbine engine. EFFECT: enhanced reliability of operation. 4 dwg