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

Jean-Marie N Pincemin

Georges Mazeaud

Pascal Noel Brossier

Pascal C Wurniesky

Bruno Albert Beutin

Daniel Germain Kettler

Michel M Lechevalier

Michel G Hugues

Christophe J Thorel

Yves R Berneuil

Gilles Claude Massot

Xavier J Pasquali

Michel Gilbert Brault

Francis Georges Garnier

Carole Claudine Touron

Gerard M Vennin

Christian W Bettremieux

Claude P Maignan

Jean-Loic H Lecordix

Jean-Pierre Donnadieu

Joel Creti

A cooling device for an aircraft turboshaft engine includes a boundary layer suction device formed by a perforated external wall portion of the aircraft, a collector on the inside of the wall portion for receiving the air flowing in through the perforations, and a discharge device discharging the air from the collector. The cooling device is completed by a heat exchanger which is disposed in the path of the air flow through the collector, a pump for pumping fluid to be cooled through the heat exchanger from a circuit of the engine, and a regulator regulating the fluid flow through the exchanger to control the temperature of the fluid. The fluid which is cooled may be from the lubrication circuit, the fuel circuit, or an air circuit of the engine, and the boundary layer suction device is preferably disposed in the pod of the engine.

Cooling device for a turboshaft engine on an aircraft

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.

System for regulating oil and fuel temperatures of a turbojet engine

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 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. The array of second hot flaps is also movable between a forward thrust position, wherein the upstream edges of the second hot flaps are urged into contact with the downstream edges of the first hot flaps and a reverse thrust position wherein the upstream edges of the second hot flaps are displaced away from the downstream edges of the first hot flaps. In the reverse thrust position, the downstream edges of the second hot flaps are in contact with each other so as to effectively block the exhaust gases and to redirect them in a direction which will induce a reverse thrust force onto the engine structure.

Combination turbojet engine nozzle and thrust reverser

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.

Aircraft engine layout

Growing community of inventors

Crosne, France

Jean-Marie N Pincemin