Abstract: A system is disclosed for regulating oil and fuel temperatures in a turbojet engine having an engine accessory driven at constant speed by a power transmission which is driven by the turbojet engine. The system has a first closed oil circuit for circulating oil through the turbojet engine, a second closed oil circuit for circulating oil through the power transmission, a fuel circuit for supplying fuel to the turbojet engine, an air/oil heat exchanger connected to the first closed oil circuit to pass oil in heat exchange relationship with air, an oil/fuel heat exchanger connected to the fuel circuit and to the first closed oil circuit downstream of the air/oil heat exchanger to pass oil and fuel in heat exchange relationship, and an oil/oil heat exchanger connected to the first and second closed oil circuits to pass oil in heat exchange relationship, the connection to the first closed oil circuit being downstream of the oil/fuel heat exchanger.

Abstract: 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.

Abstract: A combination converging-diverging exhaust nozzle and thrust reverser for an aircraft turbojet engine is disclosed having a generally annular array of cold flaps extending from a downstream end of a cowling support structure and a generally annular, inner array of hot flaps, located radially inwardly of the cold flap array and extending downstream from an end of the hot gas exhaust duct. The annular array of hot gas flaps comprises two sets of hot flap arrays, an array of first hot flaps being pivotally attached to the downstream edge of the hot gas exhaust duct with the array of second hot flaps having upstream edges that are in contact with downstream edges of the array of first hot flaps. The positions of the arrays of the first and second hot flaps may be adjusted relative to a central longitudinal axis to form a converging-diverging nozzle with a variable cross-sectional area.

Abstract: Aircraft engine, whose ancillary equipment forms a unitary assembly wherein the equipment is located to the rear of the air intake duct in a substantially closed central compartment just upstream of the gas generator. The equipment positioned along the engine axis, which, inter alia, leads to low engine drag in operation.