FIELD: axially symmetrical adjustable nozzles. SUBSTANCE: proposed hollow drive ring is designed for operating nozzle flaps of aircraft gas-turbine engine by transmitting drive loads from small number of actuating mechanisms to large number of rotary expandable flap members of nozzle. Drive ring has hollow ring design and it includes axially spaced front and rear walls, connecting posts axially between front and rear walls and connecting the walls to each other, and ring arrangements for decreasing ring length L for bending and twisting of at least one of front and rear walls between connecting posts. Rigid arrangements are provided for distributing loads transmitted from connecting posts to one of front and rear walls with use of design crossmembers passing diagonally between connecting posts and one of front and rear walls. EFFECT: improved reliability of operation. 10 cl, 6 dwg
