Snecma

Safran Aircraft Engines

Societe Lorraine De Construction Aeronautique

Mathieu Ange Poisson

Francois Gallet

Francois Robert Bellabal

Mario Cesar De Sousa

Nicolas Pommier

Frederic Noel

Gregory Ghosarossian-Prillieux

Benoit Argemiro Matthieu Debray

François Gallet

Nicolas Marc Florent

Stéphane Orcel

Baghdad Achbari

Jean-Luc Pacary

Guillaume Glemarec

Sylvain Pichon

Antoine Hellegouarch

Stephane Orcel

A turboprop includes a rotary propeller upstream from an engine and an air intake that is not coaxial to the propeller, said air intake defining a conduit for supplying air to the engine and further defining a bypass to said conduit, the bypass having an outlet oriented substantially axially towards the downstream of the engine. The turboprop further includes a nacelle surrounding the engine and the air intake, wherein the air intake is secured to a housing of the engine and is not rigidly connected to the nacelle, so as to allow, during operation, relative movements between the air intake and the nacelle. The outlet is connected by a flexible link to an intake of an air circuit carried by the nacelle.

Turboprop air intake

A suspension structure for suspending a turboprop including two unducted propellers from a structural element of an aircraft, the structure including a suspension frame for fastening to a structural element of the aircraft and including a main beam extending parallel to a longitudinal axis of the turboprop, the suspension frame being fastened to an air intake structure of the turboprop by an attachment frame.

Suspension structure for suspending a turboprop having two unducted propellers from a structural element of an aircraft with rigid fastening of the air intake structure

An assembly including an exhaust casing and an exhaust cone for a gas turbine engine, each including an axial annular flange, the two flanges being inserted into one another, one being radially external and the other radially internal, and held together by a mechanical attachment, and the assembly further including a guide by which, during operation of assembling the annular flanges to each other, the exhaust cone is in a predetermined angular position relative to the exhaust casing.

Gas turbine engine comprising an exhaust cone attached to the exhaust casing

The invention relates to a bypass turbojet comprising an exhaust housing having a central hub () and connecting means () that can transmit the forces generated by the turbojet to the structure of the aircraft that it propels, said connection means being two arms extending radially from the central hub in order to cross the cold flow of said turbojet and being characterized in that they are secured to said central hub and positioned in a diametrically opposed manner in relation to each other. An additional connection means () extends between the hub () and the area () for securing the exhaust housing to the structure () of the aircraft in order to transmit the exceptional dimensioning loads, said connection means being on standby during normal use, without any transmission of force between said hub and said area.

Isostatic suspension of a turbojet by rear double support

A variable geometry suspension structure for suspending a turboprop from a structural element of an aircraft, the structure including a rear cradle for fastening to a structural element of an aircraft and a front cradle for supporting a front portion of the turboprop, the front cradle being connected to the rear cradle, firstly via a pivot connection configured to enable the front cradle to tilt vertically relative to the rear cradle, and secondly by a return spring configured to prevent the front cradle from tilting while thrust from the turboprop is below a predetermined threshold.

Suspension structure with variable geometry of a turboprop engine on a structural element of an aircraft

Growing community of inventors

Moissy-Cramayel, France

Mathieu Ange Poisson