GAS-TURBINE ENGINE AXIAL-FLOW COMPRESSOR Russian patent published in 1999 - IPC

FIELD: gas-turbine engines. SUBSTANCE: compressor has housing with guide apparatus fitted with blades mounted inside it. Tail-pieces of blades are provided with levers articulated with synchronizing rings. Drive shaft mounted rotatably on housing in parallel with its axis is connected with drive mechanism by means of lever articulated with adjustable rod of drive and synchronizing rings by means of levers articulated with adjustable rods of rings. Feedback mechanical device mounted in lower portion of housing includes pair of shafts located coaxially and rigidly interconnected by means of end splines; these shafts are provided with measuring levers having hinges at their ends. Hinge of one of measuring levers is connected with one of synchronizing rings and hinge of other lever is connected with drive mechanism through additional adjustable rod and feedback lever of fuel injection pump. Hinge of one of measuring levers in feedback mechanical device is connected with synchronizing ring of inlet guide apparatus. Longitudinal axis of shafts is located in vertical radial plane at right angle relative to axis of rotation of compressor rotor. EFFECT: enhanced reliability of compressor; possibility of control of blade turn in case of disconnection of on-board program control system. 3 cl, 5 dwg