| 摘要 |
FIELD: adjustable guide devices of compressors of multi-mode aircraft gas-turbine engines. SUBSTANCE: during assembly of stator; variable blades 3 are mounted in each half of housing, levers 4 are secured on them, drive rings 5 are moved on levers 4 in each half of stator, levers 4 are secured to drive ring 5 by means of radial pins 6 which are secured by means of locking devices. Two halves of housing are connected by means of fasteners 29, after which two detachable inserts 25 are fitted in place; they are shifted on levers 4 in direction of arrow M. Inserts 25 are connected with halves of drive ring 5 by means of fasteners 28, after which drive ring 5 has similar I-section and similar size over entire circumference. Then each half of housing is provided with mechanism. Rack is secured in fixed rated position. Blades are arranged in rated position. Bell-crank levers of mechanism are connected with drive rings through guides and tenders. Cylinder is mounted on stator in rated position and is connected with mechanism through common adjusting ring. During operation, piston of actuating cylinder moves from one stop to other and its motion is transmitted to variable blades through screw, rack, bell-crank levers, tenders, guides, drive rings 5 and levers 4. If necessary, boundaries of turn of entire group of blades may be displaced by means of adjusting screws. In case of emergency loss of radial pin 6 (because of damaged locking device, for example), device will continue its operation within specified time. No breakdown will place in this case even through somewhat galling occurs over surface in area of duplicating drive. Blades 3 will be in rated position at all times. EFFECT: enhanced reliability, simplified assembly of stator with horizontal joint and ease of adjustment of variable blades during assembly and operation. |
