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

Pascal Noel Brossier

Georges Mazeaud

Pascal C Wurniesky

Jean-Marie N Pincemin

Carmen Miraucourt

Marc G Loubet

Philippe Jean-Pierre Pabion

Claudine L Planquet

A thrust reverser is disclosed for a high bypass ratio turbofan jet engine having a fan cowling forming an outer boundary of an airflow duct and a jet engine structure including a jet engine cowling. The thrust reverser has a casing affixed to the jet engine structure, the casing having a plurality of attaching yokes. A first thrust reverser flap is pivotally connected to a corresponding one of the attaching yokes and is located rearwardly of an exit of the airflow duct, each first thrust reverser flap having a distal end and being movable between a forward thrust position, and a reverse thrust position. A second thrust reverser flap is pivotally connected to the distal end of a corresponding one of the first thrust reverser flaps and is also movable between a forward thrust position, and a reverse thrust position, wherein the second thrust reverser flaps also redirect air flow emanating from the air flow duct. A linkrod connected to a corresponding one of the second thrust reverser flaps and the corresponding attaching yoke moves the second thrust reverser flap between its forward and reverse thrust positions as the corresponding first thrust reverser flap is moved between its forward and reverse thrust positions.

Thrust reverser for a high bypass turbofan engine

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 device for suspending a turboprop engine from a structural element of an aircraft comprises a suspension pylon parallel to the longitudinal axis of the engine and fixed to the structural element, resilient connections between the engine and the pylon and an arch fixed to the pylon, and a torsion bar carried by the arch so that the bar can pivot freely about its own axis, the opposite ends of the torsion bar being connected to opposite sides of the engine by respective lever and link rod assemblies so that the torsion bar takes up the reaction torque about the longitudinal axis of the engine.

Suspension device for a turboprop engine

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

A jet engine includes a gas turbine, peripheral ramjet channels located oide the gas turbine and including burners wherein a gas circulation stream in the engine is subdivided over part of its length into a central turbojet stream which flows through the gas turbine, the peripheral ramjet channels and peripheral discharge channels terminating by flowing into a part of the gas circulation stream downstream of the turbine. A plurality of flaps are provided for opening and closing the central stream. A ring surrounds the central stream and extends in front of part of the peripheral discharge channels and ramjet channels. A motor is also provided for rotating the ring wherein the ring has a plurality of slots formed therein, the channels being arranged such that the slots successfully pass, during rotation of the ring in a continuous direction, in front of the discharge channels only, then in front of none of the channels and then in front of the ramjet channels only.

Combined jet engine with RAM jet and turbojet

The rotor of a fan disposed in the annular noncombusted air flow duct of a urbojet propulsion engine of the bypass type is carried by a rotary body which includes the rotor assembly of a multi-stage turbine driven by noncombusted air supplied thereto by an axisymmetrical auxiliary duct which diverts noncombusted air from the primary duct of the engine just downstream of the compressor.

Propulsion engine

A combination turbojet-ramjet engine for powering a hypersonic aircraft is disclosed wherein the intake duct for the ramjet portion of the engine is centrally located within the turbojet portion of the engine in order to improve the access from outside the engine to the turbojet engine portion, as well as to maximize the use of common components and to simplify the control systems for changing from turbojet operation to ramjet operation and vice versa. The ramjet intake duct extends generally parallel to the longitudinal axis of the hypersonic aircraft engine and is located radially inwardly of the compressor, the combustion chamber and the turbine wheel of the turbojet engine portion. Flow control devices are located on the turbojet engine air intake, as well as the ramjet intake duct to control the supply of air to the respective engine portions.

Growing community of inventors

Lieusaint, France

Pascal Noel Brossier