Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Yves R Berneuil

Gerard E Jourdain

Daniel Germain Kettler

Michel M Lechevalier

Jean-Marie N Pincemin

Xavier J Pasquali

Gilles L Delrieu

Christian W Bettremieux

An actuating system for a variable area exhaust nozzle is disclosed having inner and outer flaps pivotally connected to an airframe whose positions may be varied by a single set of control cylinders. The control cylinders have a case in which is slidably mounted a pair of pistons, each having piston rods extending from one side, which piston rods extend through one end of the cylinder case. The piston rods may be arranged coaxially to minimize the bulk of the actuating cylinder. One of the piston rods is connected to the inner flaps, while the other of the piston rods is connected to the outer flaps. By selectively supplying pressurized fluid to one or more combinations of a first fluid chamber defined between one of the pistons and an end of the case, a second fluid chamber defined between the two pistons, and a third fluid chamber defined between the other of the pistons and the other end of the case the two piston rods can be made to extend or retract so as to move the inner and outer flaps to desired positions.

Actuating system for a variable area exhaust nozzle

A gas turbine engine is provided with a braking device for stopping the compressor drive turbine if a common shaft interconnecting the turbine and compressor rotors breaks, the braking device including a conical ring carried by the turbine rotor at its downstream end and a structural member of a generally conical shape carried by the upstream end of the turbine exhaust casing such that the ring will frictionally interlock with the structural member if the shaft breaks.

Gas turbine engine including a turbine braking device

The system according to the invention has an annular array of converging flaps, diverging flaps and cold flaps attached to the downstream edge of the turbojet engine exhaust duct by several pairs of longitudinally extending support beams. The pairs of beams are interconnected and the flap actuators are located between such interconnected pairs of support beams. The control system has a plurality of generally straight control shafts extending around the circumference of the converging and diverging flaps. The control shafts are interconnected with the actuators, the support beams, the diverging flaps and the cold flaps to ensure that the flaps are synchronously adjusted to their desired positions. Triangularly shaped link members are attached to each end of the control shafts and serve to interconnect adjacent shafts. A base of each of the link members is pivotally attached to an end of the control shaft, while a universal-type ball joint interconnects the adjacent apexes of the triangular link members.

Control system for turbojet engine nozzle flaps

Growing community of inventors

Paris, France

Yves R Berneuil