Safran Aircraft Engines

Snecma

Aircelle Limited

Safran Nacelles

Carmen Gina Ancuta

Bruno Albert Beutin

Bruna Manuela Ramos

Pierre Caruel

Patrick Boileau

Olivier Kerbler

Kevin Morgane Lemarchand

Jeremy Edmond Fert

Jérémy Edmond Fert

Lambert Olivier Marie Demoulin

Mélody Seriset

Melody Seriset

A turbomachine comprises an inter-flow compartment extending radially between first and second intermediate walls, gas bypass ducts passing through the second intermediate wall and communicating with evacuation outlets opening up into a secondary gas flow; an oil reservoir arranged in the inter-flow compartment, and a surface air-oil heat exchanger communicating with the oil reservoir for fluid circulation. Circumferentially in relation to the inter-flow compartment, the surface air-oil heat exchanger extends at least partially between the evacuation outlets which pass through the first intermediate wall.

Turbomachine comprising a surface air-oil heat exchanger built into an inter-flow compartment

An aircraft propulsion assembly including a bypass turbojet having a stationary inter-compressor casing positioned upstream from a space between passages, a nacelle including at its downstream end an inner wall that defines the outside of the space between passages and the inside of the bypass stream flow passage, and an outer wall arranged around the inner wall and that defines the outside of the bypass stream flow passage, at least a portion of the inner wall being suitable for moving between a maintenance position and a working position, and a thrust-reverser including a downstream element of the outer wall that is movable in translation between a retracted position and a thrust-reversal position in which it allows bypass stream deflector elements to be deployed in a radial direction, the deployment of the stream deflector elements being controlled by guide rods.

Aircraft propulsion unit having thrust reverser flaps connected to an inter-compressor casing located between the engine compressors

An aircraft propulsion assembly having a thrust reverser with moving guards, including an engine covered by a front cover and a rear cover that are both mobile; moving guards supported by the rear cover, the guards being covered by the front cover in normal operation, and extending into a space separating the front cover from the rear cover when the rear cover is moved to the rear; two arcuate frames, which are spaced apart and surround the engine in order to support actuators for moving the rear cover; the space located between the two arcuate frames being uncovered when the front and rear covers are moved to the front and rear; and wherein the two arcuate frames jointly support a series of elements forming steps which constitute a ladder for quick access to the top of the propulsion assembly.

Aircraft propulsion assembly provided with steps allowing an operator to reach the top of same

Turbine engine, comprising two structural annular casings () which are interconnected by connecting rods (), characterized in that the turbine engine further has at least one accessory gearbox () which is fixed to a first of the casings () and which is connected by the connecting rods to the other of the casings ().

Turbine engine provided with means for absorbing stresses from the thrust of the engine thereof

A gearbox for driving equipment of a turbomachine, including a substantially V-shaped box having two arms joined together by a joining part, the arms containing gear trains joined together at the joining part, and an attachment to the turbomachine. The attachment include a mechanism for insetting and/or for attaching the joining part and a suspension device of the arms.

V-shaped gearbox for driving turbomachine equipment

Aircraft turbomachine comprising at least one heat exchanger () and a gearbox () in a V-shaped overall configuration and comprising two lateral arms () joined together by a central joining piece, the heat exchanger being mounted between the arms of the gearbox.

Electroformed nickel-chromium alloy

The present disclosure relates to a propulsion unit for an aircraft including a nacelle which surrounds a turbojet engine. The nacelle has an inner structure surrounding a downstream compartment of the turbojet engine, and the inner structure includes two annular half-portions. The propulsion unit also includes a rail/guide unit and to move the annular half-portions between a working position and a maintenance position. In particular, the rail/guide unit radially moves away the annular half-portions relative to a longitudinal axis of the nacelle, during a translation movement of the annular half-portions. The nacelle is provided with a connecting rod which is connected to the annular half-portions and to the turbojet engine and so that the connecting rod contributes to rotate the annular half-portions about the rail.

Propulsion unit for an aircraft

Turbine engine, comprising means for absorbing the thrust forces from its engine, which comprise longitudinal connecting rods, the ends of which are connected to structural annular casings of the turbine engine, characterized in that it comprises means for supporting at least one item of equipment on said thrust-absorbing connecting rods and/or for suspending at least one item of equipment from said thrust-absorbing connecting rods.

Growing community of inventors

Paris, France

Carmen Gina Ancuta