Snecma

Thomas Daris

Romain Nicolas Lunel

Stephane Pierre Guillaume Blanchard

Mathieu Dakowski

Alain Pierre Page

Jackie Raymond Julien Prouteau

Edgar Brunet

Stéphane Pierre Guillaume Blanchard

Jackie Prouteau

Frederic Henri Paul Schenher

Marc Doussinault

Frederic Schenher

Stéphane Blanchard

Frédéric Schenher

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

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 gate valve for a system controlling cooling in a turbomachine is disclosed. The gate valve includes a gate mounted so that it can pivot about an axis between a position in which it shuts off an air passage orifice and a position in which it opens the orifice, and a rotating device for rotating the gate about the axis. The rotating device includes two superposed coaxial rotary members collaborating with one another via cam surfaces designed such that rotating the first rotary member from the shut-off position causes a translational movement of the second rotary member and of the gate along the axis of rotation followed by a rotation of this member and of the gate about this axis.

Gate valve for a system for circulating cooling air through a turbomachine

A propulsion gas exhaust assembly in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator is disclosed. The exhaust assembly includes a duct which forms a vertical elbow and a nozzle.

Exhaust assembly forming a horizontal propulsion gas elbow in an aircraft

A propulsion gas exhaust assembly in an aircraft propelled by hot gases produced along an axis of the aircraft by a gas generator is disclosed. The propulsion gas exhaust assembly includes a transition element emerging in two duct elements each communicating with an ejection half-nozzle, wherein each of the two duct elements forms an elbow downstream of the transition element.

The present invention relates to a thrust orienting nozzle, shaped in such a way as to divide a principal propulsion gas flow coming from at least one gas generator into a first flow and a second flow for an ejection in a first half-nozzle and in a second half-nozzle and comprising at least one of following two piloting means: a means of dividing the principal flow into each of the two half-nozzles, and a means of orienting the thrust vector produced by each of the two half-nozzles. The invention applies in particular to the yaw control of an aircraft without a vertical tail unit.

Thrust orienting nozzle

A propulsion gas exhaust assembly is presented for use in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator. The assembly may include a first cylindrical duct, two second ducts, two third ducts, and two axial gas-ejection nozzles. The first cylindrical duct element receives the gases downstream of the gas generator. The gasses flow downstream from the first cylindrical duct element to two second duct elements. These two second duct elements are divergent in a first geometric plane. Each of the two second duct elements may guide the flow to their own respective third duct and nozzle. The third ducts may include elbows to assist in stealth. The nozzles may include the means to steer the aircraft.

Growing community of inventors

Paris, France

Thomas Daris