GAS-TURBINE ENGINE COMPRESSOR STATOR Russian patent published in 1998 - IPC

FIELD: variable-speed gas-turbine engines for flying vehicles. SUBSTANCE: during stator assembly, turning blades are installed in each half of frame and levers are secured on them. Drive rings are pulled onto the latter in each half of stator. Levers are attached to rings by means of radial pins and the latter are locked in position. Two halves of frame are joined together by means of fastenings. Then two removable inserts are inserted and pulled onto levers. Inserts are joined with halves of drive ring by means of fastenings. After this procedure, drive ring has equal I-section throughout entire circumference and equal size. Then fuel mechanism is installed on each half of frame and control rack is fixed in specified position. Blades are set in specified position. Angle levers of fuel mechanism are joined with drive rings through dogs and tenders. Cylinder is installed on stator in specified position and joined to fuel mechanism through common adjusting screw. EFFECT: improved reliability, simplified assembly procedure of horizontally split stator, facilitated adjustment of guide blades during assembly and in service. 4 cl, 8 dwg