Snecma

Mathieu Dakowski

Romain Nicolas Lunel

Stephane Pierre Guillaume Blanchard

Alain Dominique Gendraud

Thomas Daris

Claire Dorin

Vincent Philippot

Maurice Guy Judet

Daniel Georges Plona

Guillaume Sevi

Stéphane Pierre Guillaume Blanchard

Nicolas Pommier

Fabrice Marcel Noel Garin

Laurent Bernard Cameriano

Alain Pierre Page

Guy Lapergue

Wilfried Lionel Schweblen

Eric Lefebvre

Fabrice Garin

Laurent Pierre Joseph Ricou

Delphine Roussin-Leroux

Sandrine Gandelot

Olivier Kreder

Daniel Olivier Bainachi

Fabrice Marcel Noël Garin

Stephane Pierre Blanchard

Claire Dorine Dorin-Coppee

Nicolas Auguste Marcel Pommier

Eric Jacques Lefebvre

A turbomachine high-pressure turbine including a rotor disc with upstream and downstream annular flanges separating a radially internal annular cavity in which the hub of the disc extends from two radially external annular cavities, of which one is upstream of the disc and receives a ventilation air flow and of which the other is downstream of the disc, the upstream flange of the disc including a mechanism connecting to the upstream eternal cavity and the internal cavity for ventilating the hub of the disc.

Ventilation of a high-pressure turbine in a turbomachine

A stationary vane assembly for a turbine engine including an inner casing and at least two angular sectors forming a high-pressure guide vane assembly, each angular sector including a fastening tab for fastening the angular sector on the casing. The stationary vane assembly including a ring of abradable material fixed on the casing, on the side of a mobile vane assembly using a plurality of screw-nut assemblies, the stationary vane assembly also including radial retaining pins for the angular sectors introduced into first bores formed in the fastening tabs and in the mounting clip, the bores having axes substantially parallel to the longitudinal axis, the mounting clip being fixed on the casing by the same screw-nut assemblies as those fixing the ring of abradable material support on the casing.

Fixed vane assembly for a turbine engine having a reduced weight, and turbine engine comprising at least one such fixed vane assembly

An assembling of a guide vane assembly of a turbomachine turbine, formed by an annular row of stationary flow-stabilizing vanes. An outer edge of the guide vane assembly is axially bearing on a line of an external casing of the turbine and an inner edge of the guide vane assembly is in axial sliding connection with the line of the internal casing of the turbine, the axial sliding connection allowing the inner edge to be free along the motor axis with the axial stop being achieved by the axial bearing of the outer edge of the vane.

High-pressure turbine for turbomachine, associated guide vane sector and aircraft engine

A stationary vane assembly of a turbine engine including an inner casing and a high-pressure turbine guide vane assembly including at least two angular sectors including blades, the angular sectors being fixed on the casing, each angular sector including a platform and a fastening tab. The fastening tab protrudes from the platform radially inwardly. The casing includes a first annular groove receiving the fastening tabs, radial retaining pins for the angular sectors being introduced into bores made in the casing and the fastening tabs, the axial retaining pins being axially stopped by a ring mounted in a second annular groove of the casing.

Stationary vane assembly for a turbine engine having a reduced weight, and turbine engine comprising at least one such stationary vane assembly

An air bleed device for cooling components in a turbine engine, including an annular conduit having a substantially rectangular cross-section formed in a housing and having a radially internal wall swept by an airflow is disclosed. The device includes an air inlet orifice, and a flap valve for controlling the airflow entering through the orifice, formed by a plate borne by a maneuvering member mobile in translation parallel to the axis of the orifice between a position in which the plate closes off the orifice and a position in which the plate opens the orifice.

Cooling air bleed device in a turbomachine

Air bleed device for cooling components in a turbine engine, including an annular conduit () having a radially internal portion swept by an airflow () and which comprises at least one air inlet orifice () formed in an upstream radial wall () of the conduit (), a flap valve () for controlling the airflow entering through the orifice () and of which the flapper () includes a plate () applied against the wall () and capable of being moved by sliding on said wall () by a maneuvering member () mobile in translation parallel to the wall () between a position in which the plate () closes off the orifice () and a position in which the plate () opens said orifice.

Cooling air bleed device in a turbine engine

A turbine stage in a turbomachine including ring sectors arranged about a turbine impeller, and an annular support supporting the ring sectors and attached to a turbine casing is disclosed. The annular support is able to be deformed elastically in the radial direction to cushion at least a portion of the deformations of the turbine casing in operation.

Turbine stage in a turbomachine

Device () for the tapping of air for the cooling of flaps of a turbojet nozzle, comprising an annular duct () having a radially internal wall () swept by a stream of air () and which comprises at least one air inlet orifice (), a flap valve () for controlling the flow rate of air entering through the orifice (), formed of an elastically deformable metal plate () of which a downstream end is fixed on an edge of the orifice (), and of which an upstream end can be displaced by a manoeuvring member () mobile in translation parallel to the axis () of the orifice between a position where the plate () seals this orifice and a position where the plate () opens this orifice.

Device for tapping cooling air in a turbomachine

A high-pressure turbine of a turbomachine, including at least one upstream guide vane element and an impeller mounted so as to rotate inside ring sectors attached to an annular support which is suspended from an outer casing, the upstream guide vane element including, at its radially inner end, a mechanism for attachment to an inner casing and, at its radially outer end, a mechanism for pressing axially on a fixed element of the turbine that is suspended from the outer casing independently of the annular support for attachment of the ring sectors.

High-pressure turbine of a turbomachine

A turbine stator for an aircraft turbine engine is disclosed. The turbine stator includes a stator wall supporting a high pressure air injector fixed on the downstream side, and an annular abradable element support. The lower radial end of the element support is fixed to the high pressure air injector and the upper radial end of the element support is fixed to the stator wall, such that they jointly delimit a cavity under pressure. The turbine stator also includes at least one vibration damping device located in the cavity under pressure. The vibration damping device is in contact with each of the two elements taken among the stator wall and the annular support.

Turbine stator for aircraft turbine engine including a vibration damping device

A turbine stage in a turbine engine, including a wheel with blades rotating inside a sealing ring held by a casing of the turbine, and an annular thermal protection sheet mounted between the casing and the sealing ring is disclosed. The annular thermal protection sheet is formed by a plurality of curved plates mounted end-to-end and attached by pins to the casing.

Control of clearance at blade tips in a high-pressure turbine of a turbine engine

An exhaust cone of composite material. The exhaust cone is mounted to extend an adapter ring and it is held by an elastically deformable element that acts axially.

Exhaust cone for channeling a stream of gas downstream from a turbine

The jet engine of the invention comprises an exhaust nozzle of variable section, comprising at least one flap pivot mounted about a pin, the pin being joined to the fixed structure of the jet engine via two braces each comprising a bore for housing the pin, the flap being pivot commanded by an actuating cylinder, connected to two fasteners which each comprise a bore through which the pin passes and about which they rotate. The jet engine is characterized by the fact that the pin, the bores of the braces and bores of the fasteners are arranged so that the contacts between the pin with the bore walls of the braces and with the bore walls of the fasteners are made over convex surfaces. Therefore, when in operation, in the event of pin bending the contact surfaces follow this convex shape and are suitably distributed.

Jet engine with a variable section nozzle of which at least one flap pivots about a pin, pins for flaps

A variable-section turbomachine nozzle comprises a plurality of moving flaps, and a moving flap control system comprising control levers each associated with a respective moving flap, the control levers comprising both controlled levers that are actuated directly by actuators, and follower levers that are actuated by the controlled levers via transmission links. When the nozzle is at rest, the flaps associated with the follower levers present a radial offset relative to the flaps associated with the controlled levers.

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Sucy en Brie, France

Mathieu Dakowski