Safran Helicopter Engines

Turbomeca

Olivier Pierre Descubes

Olivier Bedrine

Mathieu Cladiere

Jean-Michel Pierre Claude Py

Bertrand Guillaume Robin Pellaton

Yannick Cazaux

Jean-Luc Pierre Sahores

Jean-Maurice Casaux-Bic

Jean-Luc Breining

Armand Bueno

Christophe Nicolas Henri Viguier

Carole Jaureguiberry

Stephane Vergez

Isabelle Germaine Claude Ladeveze

Sylvain Gourdant

Olivier Tuot

Frédéric Ferdinand Jacques Batlle

Stéphane Raphaël Yves Richard

Gabriel Gorka Exilard

Nicolas Christophe Perra

Jerome Dinquel

Stéphane Vergez

Sebastien Detry

Geoffroy Billotey

Jean-Michel Pierre Py

Isabelle Germaine Ladeveze

Mathieu Pierre Cladiere

Sébastien Detry

An assembly for a turbomachine includes at least one turbine having a turbine disc with an internal bore and an annular cavity which is arranged upstream of the disc. The assembly further includes a fire safety system with a cooling device that supplies the cavity with cooling air via injection means. The fire safety system includes means that divide the annular cavity into first and second cavities. A cooling air speed is maintained at the outlet of the injection means and the cooling air in the first cavity is guided to the internal bore of the turbine disc. A diffuser co-operates with the injection means and an annular cover co-operates with the diffuser and covers first attachment members arranged in the cavity. A radially outer surface of the cover at least partially guides the cooling air at the outlet of the diffuser.

Fire safety system for a turbomachine comprising means for maintaining a cooling air speed and corresponding turbomachine

A toothed coupling mechanism for an assembly of rotating elements of an aircraft gas turbine engine includes a pair of coupling halves having an axial toothed coupling interface therebetween. Each coupling half has a plurality of splined teeth inter-engaged about an axis for transmitting torque therebetween. A protrusion is located on one of the splined teeth of one of the coupling halves. A splined tooth of the other coupling half comes into contact with the protrusion in a situation of uncoupling of said coupling halves.

Curvilinear coupling for aircraft turbomachinery

The invention relates to a system () for the recovery of energy from exhaust gases from at least one turboshaft engine, comprising a turbine () fitted rotatably around a recovery shaft (), adapted to bleed off at least a part () of the exhaust gases, known as bleed gases (), and to expand said bleed gases () to become expanded gases () at a pressure below atmospheric pressure, a first heat exchanger (), adapted to use a cold source () to cool said expanded gases () to become cooled gases (), and a compressor () fitted rotatably around said recovery shaft (), adapted to compress said cooled gases () to atmospheric pressure.

System for recovering exhaust gas energy

The invention relates to a mechanical fuse intended to be rigidly mounted between a drive unit (), and a receiver unit (), each rotating about the same axis () of rotation, said fuse comprising a body () extending in a longitudinal direction parallel to said axis () of rotation, once the fuse is mounted between said drive unit () and receiver unit (). The invention is characterized in that said body () comprises a plurality of longitudinal bars (), each bar () being deformable by bending, such as to form a twist-breakable mechanical fuse.

Twist-breakable mechanical fuse and cooling unit of a turbine engine fitted with such a fuse

The invention relates to an architecture of a propulsion system of a multiple-engine helicopter comprising turboshaft engines (), characterised in that it comprises: at least one hybrid turboshaft engine () that is capable of operating in at least one standby mode during a stable flight of the helicopter, the other turboshaft engines () operating alone during this stable flight; an air turbine () that is mechanically connected to the gas generator () of the hybrid turboshaft engine () and is suitable for rotating said gas generator (); means for withdrawing pressurised air from the gas generator () of a running turboshaft engine (); and a duct () for routing this withdrawn air to said air turbine ().

Method for assisting a turboshaft engine in standby of a multiple-engine helicopter, and architecture of a propulsion system of a helicopter comprising at least one turboshaft engine that can be in standby

A method of notifying an authorization to shut down completely an aircraft gas turbine engine, the method being applied after detecting that the engine has passed to an idling speed, and including a) an evaluation step of using a value of a first operating parameter of the engine to evaluate a value for a second parameter TMG wherein a thermal behavior of a part of the engine that might be subjected to coking; b) a comparison step (E) of comparing the value of the second parameter TMG with a predefined threshold value Tthresh corresponding to a value of the second parameter that does not lead to coking of the part; and c) a notification step of notifying authorization to shut down completely the engine if the value of the second parameter TMG is lower than the value of the predefined threshold Tthresh, else reiterating steps a) to c).

Method and device for notifying an authorization to completely shut down an aircraft gas turbine engine

A method and structure negating thermal inertia of a solid portion, such as shielding, which influences mechanical behavior of parts of an engine structure, by reducing forces transmitted to the engine structure during an event in which a turbine blade ruptures, while preserving mechanical strength and vibratory positioning. The structure includes a flexible fastener for a shield, enabling producing a fusible section. An assembly for mounting a shielding onto a casing of the engine structure of a turbine includes connection lugs and points for attachment to the casing and shielding. The attachment points are sufficiently spaced apart in accordance with curvature of the shielding and casing so connection between the lugs and the shielding or casing, and connection of the attachment points, are substantially tangential. The lugs are sized so the connection has sufficient flexibility to control vibratory positioning thereof and ensure sufficient mechanical strength under thermo-mechanical loads.

Method for mounting shielding on a turbine casing, and mounting assembly for implementing same

A lubrication device including a bypass valve with an inlet connected to a feed circuit, a first outlet to be connected to elements to be lubricated, and a second outlet connected to a bypass circuit. The valve includes a valve member slidable between first and second positions, and separating a cavity into first and second chambers. The first chamber is connected to the inlet. In the first position, a fluid flow passage from the first chamber to the second chamber is open, and from the first chamber to the first outlet is closed. In the second position, a fluid flow passage from the first chamber to the first outlet is open, and from the first chamber to the second outlet is closed. At least in the second position, the valve member separates the chambers in substantially leaktight manner, while the second chamber remains in fluid flow communication with the second outlet.

Lubricating device having a bypass valve

A mechanical protection device including: a transmission shaft having a main axis of rotation and an element that is frangible under a torsional overload; a movable member secured to the transmission shaft to rotate about the main axis and configured to move radially outwards relative to the main axis from a first position to a second position; a spring urging the movable member towards the first position; and a tangential abutment configured to stop rotation of the movable member about the main axis when the movable member is in the second position. The movable member and the spring are calibrated so that from a predetermined trigger angular speed the movable member moves from the first position to the second position under effect of centrifugal force greater than prestress of the spring.

Mechanical protection device

A centrifugal compressor wheel including a hub, a web extending radially from the hub, and a plurality of blades carried by the wheel. The web includes an erosion indicator of the wheel.

Erosion indicator for a compressor wheel

A device for filtering intake air of an internal combustion engine, including at least one filtering element including an inlet for air being treated, a first clean air outlet toward the engine, and a second air outlet toward the outside, and a ventilation mechanism driving the air from the second air outlet. The ventilation mechanism includes a fan wheel driven by a turbine set into motion by a gas flow taken from the engine.

Growing community of inventors

Nay, France

Olivier Pierre Descubes