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

Snecma

Snecma Moteurs

Georges Mazeaud

Pascal Noel Brossier

Pascal C Wurniesky

Jean-Louis Picard

Jean-Marie N Pincemin

Francois J Mirville

Antoine Emmanuel Cousin

Claudine L Planquet

Bruno Albert Beutin

Christophe Pieussergues

Alain M Lardellier

Gerard E Jourdain

Denis J Sandelis

Jean-Louis Charbonnel

Robert Kervistin

Jeremy Edmond Fert

Didier Jean-Louis Yvon

Carmen Miraucourt

Marc G Loubet

Jean-Paul Lagrange

Francois M Marlin

Jean L Picard

Didier Marie Mortgat

Michel Gilbert Brault

Francois E Crozet

Christian J Cattaneo

Patrick W Saillot

Christian Kaincz

Claude W Pascal

Jean M Payen

Jacky Derenes

Noel B Pascal

Michel Chaumeret

Didier Yvon

Fabien Burdin

Josiane M Labatut

Jeremy Fert

A device for supporting and housing auxiliaries in a bypass turbojet is disclosed. The device includes two coaxial case rings arranged one inside the other and connected by tubular radial arms through which fluid ducts and electric cables pass. At least one of the radial arms includes on a lateral face a detachable panel whose removal allows access to turbojet equipment situated radially inside the internal case ring in alignment with the radial arm.

Device for supporting and housing auxiliaries in a bypass turbojet

A turbofan jet engine includes an outer fan duct, an inner fan duct, fluid-conveying ancillaries located outside the outer fan duct, fluid-conveying ancillaries located inside the inner fan duct. At least one removable modular arm forming a connection for ancillaries is arranged between the outer fan duct and the inner fan duct. The removable arm provides a connection of ancillaries outside the outer fan duct to ancillaries inside the inner fan duct.

Turbojet engine comprising a connector arm for ancillary systems, and the connector arm for ancillary systems

A turbofan jet engine includes an outer casing supported by arms, an inner casing facing the outer casing, ancillaries, and an ancillaries distribution support. The ancillaries distribution support is formed along the axis of an arm on the inner casing. The ancillaries distribution support includes a first sole plate for reception of ancillaries on the outer side of the inner casing and a second sole plate for reception of ancillaries on the inner side of the inner casing. Such a turbofan jet engine reduces the longitudinal dimension necessary for the ancillaries to pass through.

Turbofan jet engine with ancillaries distribution support

An air intake layout for a turboprop. A nacelle surrounding an intake section of the turboprop behind the fan propeller can be moved away from the main part of the nacelle and can be divided into two parts that may be extracted so as to leave full access to the panel leading to equipment in a central compartment, whereas the panel was partially covered by the air intake leading edge.

Air input device for a turboprop engine

The carrier structure of the invention is used for carrying a turboprop and it is designed to be mounted beneath and/or in front of an airplane wing. In characteristic manner, the carrier structure comprises:

Turboprop carrier structure and an assembly including such a carrier structure

The turbojet according to the invention is designed to be fixed onto the upper part of the aft section of the fuselage of an aircraft using at least one coat hanger, the turbojet comprising a fan, a forward casing, an aft casing, accessories arranged around the periphery of the forward casing, the forward casing comprising attachment points, for the coat hanger. The attachment points are arranged so that the turbojet can be installed indifferently on either side of the aircraft fuselage, accessories being arranged on the casing so that they are accessible from the outside of the fuselage regardless of which side the installation is done.

Turbojet designed to be fixed onto the AFT part of the fuselage of an aircraft, in upper position

A suspension system for an aircraft powerplant attached to an aircraft frame and having a housing. The suspension system includes a spindle mounted in a spindle support rigidly joined to the aircraft frame, a bearing cage affixed to the housing and having a bearing positioned therein, a pair of suspension arms connected to the spindle support, and a pair of lateral linkrods configured to link the housing and the suspension arms. The side surfaces of the bearing cage and the suspension arms define a clearance therebetween concentric to the Y-axis. The bearing cage is configurable along the spindle such that the bearing cage is limited to displacement relative to the longitude of the spindle while maintaining contact with the spindle.

Suspension system with intrinsic safety features for aircraft powerplants

The particle trap (15) that extends behind an elbow in the air flow stream (6) in a turbo-prop engine is delimited at the back by an end plate (12) to which intake housing suspension rods (10) supporting the front of the rotating shaft (2), are fastened. It is divided by suspension arms (11) which may be drilled (21) to restore the continuity of the annular chamber forming the trap. Therefore the intake housing suspension device extends through the trap. This type of trap makes use of the inertia of solid bodies carried by the air drawn in, and which could damage the engine blades, and to collect them.

Particle traps for turbo-prop 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 combustion chamber for a gas-turbine engine is disclosed in which the walls defining the combustion chamber may be easily attached to and removed from the engine structure. A dome member is attached to the engine structure such that it partially encloses the fuel injector nozzle in an upstream direction. The shape of the dome-member is such that it splits the incoming oxidizer flow into inner and outer flows which pass along the inner and outer sides of the combustion chamber. The inner and outer walls of the combustion chamber may be attached to an upstream end wall of the combustion chamber such that this assembly is removable as a unit from the dome member. The inner and outer walls, as well as the end wall, are releasably attached to the dome member such that the assembly can be removed from the gas-turbine engine without the necessity of removing or displacing the fuel injector nozzles or the dome member. Alternatively, the end wall of the combustion chamber is fixedly attached to the dome member while the inner and outer walls of the combustion chamber are releasably attached to the end wall. This enables the inner and outer walls to be separately removed from the gas-turbine engine, again without disturbing the fuel injector nozzles or the dome member.

Gas-turbine engine with detachable combustion chamber

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

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

A jet engine has a central turbojet stream and a peripheral ram jet stream which can be in turn obstructed or freed by flaps. The flaps can be opened outwardly and are located on an intake cone and at an inlet of the peripheral stream. The operation of the flaps is a function of the sought operating mode. This arrangement permits a very good guidance of gases.

Combined jet engine provided with means for switching between two

A turbo-engine includes a compressor connected by a shaft to a turbine and includes a plurality of disk stages subjected to a thermal gradient, a gas vein in which the gas circulates from upstream to downstream of the compressor, and a mechanism for ventilating the disks so as to limit their thermal gradient. The ventilation mechanism includes at least, a first and a second source for obtaining the gas from the vein, as well as an operating device so as to independently bring the gas obtained from the first source and the gas obtained from the second source to the disks of the compressor and the turbine. The operating device includes a gas pipe coaxial and outside the shaft, wherein between the pipe and the shaft a cylindrical passage for the gas is provided.

Circuit for ventilating compressor and turbine disks

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.

Growing community of inventors

Yerres, France

Georges Mazeaud