Safran Aircraft Engines

Safran Nacelles

General Electric Company

Guillaume Glemarec

Quentin Matthias Emmanuel Garnaud

Pierre Caruel

Quentin Garnaud

Jean-Baptiste Manuel Nicolas Vignes

Valerio Capasso

Francois Gallet

Daniel Edward Mollmann

Bruno Albert Beutin

Patrick Boileau

Olivier Kerbler

Jean-Baptiste Vignes

Craig William Higgins

Jonathan Edward Coleman

Mark Edward Linz

Frédéric Dautreppe

Loïc Grall

Gina Ferrier

Hervé Jean Albert Mouton

Nicolas Maurice Herve Aussedat

Ludovic Toupet

Mélody Seriset

Nicolas Maurice Hervé Aussedat

Romuald Muriel Gentils

Mathieu Marc Christian Gaillot

Eric Francois Michel Maingre

Michael Cline

Benoit Bernard René Leclerc

Amadéo Galasso

Daniel E Mollman

Eric François Michel Maingre

A structure for linking and supporting a turbine engine on an aircraft pylon, the structure having a first longitudinal axis intended to extend parallel to a second longitudinal axis of the pylon, the structure including a first axial portion for fastening to the pylon, the first portion having an upper end that defines a substantially horizontal plane of interface with the pylon, and a lower end bearing suspension rods for suspending the turbine engine, which extend in a rear vertical plane; and a second axial portion that is intended to extend forward of the pylon and includes at least one suspension member of the turbine engine in a front vertical plane.

Structure for linking and supporting a turbine engine on an aircraft pylon

A triple-flow turbine engine for an aircraft, this turbine engine having a longitudinal axis and including upstream suspension elements which are located in a first plane perpendicular to the axis and are connected or fixed to the gas generator of the turbine engine; downstream suspension elements which are located in a second plane perpendicular to the axis and are connected or fixed to the gas generator; and thrust-absorbing rods which include first ends which are connected or fixed to the gas generator and opposing second ends which are located in a third plane perpendicular to the axis, wherein the first, second and third planes are located at a cold compartment of the gas generator.

Suspension of a triple-flow aircraft turbine engine

An aircraft propulsion unit including a nacelle and a turbojet engine. The aircraft propulsion unit includes an external envelope, at least one fan casing, at least one actuator, and at least one support structure. The external envelope includes fan cowls. The fan casing cooperates with the fan cowls to define an interior space configured to house a thrust reverser configured to be displaced between a first position and a second position. The actuator configured to move the thrust reverser between the first position and the second position The support structure connects the fan cowls and the fan. The support structure includes at least one aperture configured to allow passage of part of the actuator.

Aircraft propulsion unit

Assembly including an aircraft turbine engine and a pylon for mounting the turbine engine to an element of the aircraft. The pylon includes members for suspending the turbine engine, the members being connected to the turbine engine in at least one plane which is perpendicular to the axis and which is located upstream of the combustion chamber of the turbine engine, such that the turbomachine is cantilevered to the pylon, The assembly further includes at least one damper which connects the turbomachine to the pylon and which is located in a plane perpendicular to the axis located downstream of the combustion chamber, the damper being configured to limit the relative movements between the turbine engine and the pylon without transmitting force.

Assembly comprising an aircraft turbine engine and mounting pylon thereof

Methods, apparatus, systems and articles of manufacture for mounting a gas turbine engine are described. An apparatus for mounting a gas turbine engine to a pylon, the gas turbine including an upstream section and a downstream section, the gas turbine defining a roll axis, a yaw axis, and a pitch axis, the apparatus including: a first mount to couple the upstream section of the gas turbine engine to the pylon; a second mount to couple the upstream section of the gas turbine engine to the pylon, the second mount downstream of the first mount; a thrust linkage to couple the upstream section to the pylon, wherein the downstream section is decouplable from the upstream section without decoupling the first mount, the second mount, and the thrust linkage.

Methods and apparatus for mounting a gas turbine engine

A fan casing for an aircraft bypass turbojet engine includes one single wall configured to form at least one portion of an outer skin of a nacelle. The wall includes at least one reinforcement for stiffening the fan casing. The reinforcement is formed by a portion of the wall forming at least one annular area projecting towards an inside of the nacelle and/or having an overthickness. The reinforcement is further configured for fastening the fan casing to arms crossing a secondary stream flow path of the turbojet engine.

Turbojet engine fan casing

The invention relates to an assembly between an aircraft pylon () and a turbomachine () of longitudinal axis (X), the pylon () and the turbomachine () each comprising front and rear longitudinal regions, the assembly comprising a rear support () configured to connect the rear region of the turbomachine () to the rear region of the pylon (), the assembly being characterized in that the rear support () comprises a sliding pivot connection arranged between the rear region of the turbomachine () and the rear region of the pylon (), so as to allow the turbomachine () only translational and rotational movements along and about the longitudinal axis (X) and along and about a vertical axis (Z) and a rotational movement about a transverse axis (Y).

Assembly between an aircraft pylon and a turbomachine

The invention relates to a turbomachine () extending along an axis (X), comprising a high-pressure body with a high-pressure compressor () coupled in rotation to a high-pressure turbine (), and a low-pressure body including a low-pressure compressor () coupled in rotation to a low-pressure turbine (), an upstream casing () located upstream of the high-pressure compressor (), and means of suspension () for the turbomachine (), intended for attaching the turbomachine () to an aircraft pylon ().

Turbomachine comprising a means of suspension

A nacelle for an aircraft bypass turbomachine, including: an annular envelope extending about a longitudinal axis, a thrust reverser including: an annular movable cowl situated downstream of the annular envelope and able to slide with respect to the annular envelope along the longitudinal axis between a closed position and an open position in which the cowl and the nacelle casing define an opening between one another, at least one first thrust reverser cascade, an actuating mechanism designed to allow a partial or total thrust-cancelling configuration of the thrust reverser, in which configuration the movable cowl is moved into its open position while maintaining the or each first cascade in its retracted position, the opening being occupied by at least one second thrust-attenuating cascade of the thrust reverser, in such a way that the secondary flow passing through the opening exits to the outside of the nacelle with a speed oriented so as to generate a substantially zero or positive thrust along the longitudinal axis.

Nacelle for a bypass turbomachine comprising a thrust reverser, bypass turbomachine comprising such a nacelle, and aircraft comprising at least one such turbomachine

A turbofan propulsion assembly includes a thrust reverser with movable flaps. The propulsion assembly further includes an engine and a nacelle surrounding the engine, and the nacelle includes a thrust reverser with sliding cowls and thrust reverser flaps, and an inner structure. The portion of the inner structure positioned perpendicular to the thrust reverser flaps includes two halves that can open toward the exterior of the nacelle cowls.

Bypass propulsion unit, comprising a thrust reverser with movable cascades

Growing community of inventors

Moissy-Cramayel, France

Guillaume Glemarec