Safran Aircraft Engines

Arnaud Baudran

Antoine Jean-Philippe Beaujard

David René Pierre Le Cair

Thomas Roger Jacques Angevin

Yannick Schini

Eric Charles Pean

Victor Henri Marius Varenne

Brice Cyril Edwiges

Philippe Robert Jean Goffinon

A turbomachine—for aircraft has a primary annular flow path and a cold flow channel extending around the primary annular flow path. The turbomachine includes an impeller, a compressor, a combustion chamber, a first turbine having a first turbine rotor, a second turbine having a second turbine rotor, a first connecting shaft and a second connecting shaft, an inter-turbine stator arranged between the first turbine and the second turbine, and a first cooling circuit having successively: a first cooling inlet located between the impeller and the compressor, a first passage extending into the inter-turbine stator, and a first cooling outlet extending into the cold flow channel.

Turbine engine for an aircraft

The invention relates to an assembly () for a turbomachine comprising a pipe () connected at one end () to means () for supplying pressurized air and at one opposite end () to an item of equipment () of the turbomachine, the pipe () having a bent portion () intended for forming in use a low point of the pipe (), said bent portion () having a hole () for first draining water from the pipe (), wherein it further comprises an orifice () arranged downstream of the drain hole ().

Defrosting a drain hole

A hydraulic and pneumatic control circuit for a turbojet, a main hydraulic line having an oil/fuel heat exchanger with a function of transferring heat from the oil flowing in an oil circuit of the turbojet to the fuel flowing in the main hydraulic line, the circuit having a first hydraulic line for feeding fuel to a combustion chamber of the turbojet, a second hydraulic line for feeding fuel to one or more actuators for controlling variable geometry equipment, each actuator being fed with fuel via an electrohydraulic servovalve, a pneumatic line for feeding air to a pneumatic control member for bleed valves of a compressor and a blade tip clearance control valve of a turbine of the turbojet, and a fuel/air heat exchanger positioned on the second hydraulic line upstream from the hydraulic servovalve and on the pneumatic line upstream from the pneumatic control member.

Hydraulic and pneumatic control circuit having a fuel/air heat exchanger for a turbojet

A fuel pressure accumulator for a fuel supply circuit of a turbine engine having at least one pipe is provided. The fuel pressure accumulator generally includes at least one housing adjacent to said pipe and receiving at least one deformable enclosure confining a gas and having at least one movable wall in contact with the fuel in order to dampen a fuel overpressure, where the housing is coaxial with the pipe and the accumulator has a permeable chamber delimited at least partially by the housing, pressurizing the deformable enclosure and communicating with the main fuel flow via a grid with staged walls tilted, with respect to a direction of the flow flowing along the grid, substantially in the direction of the deformable enclosure.

Growing community of inventors

Paris, France

Arnaud Baudran