Safran Aircraft Engines

Xavier Jean Yves Alain Agneray

Michel Gilbert Roland Brault

Julien Fabien Patrick Becoulet

Christophe Paul Jacquemard

Thierry Georges Paul Papin

Cédric Zaccardi

Mathieu Daniel Marie Van Gansen

Eric Pierre Georges Le Marechal

Disclosed is a main shaft for an aircraft turbine engine drive line extending longitudinally from front to rear along an axis and having a rear portion configured for receiving a front portion of a rear shaft by interlocking, the main shaft having: —a front retaining member and a rear retaining member together defining a prison and each having a central opening, —a connecting ring, located in the prison, having a rear end configured to be screwed to a front end of the rear shaft extending into the central opening of the rear retaining member, the connecting ring having a gripping member formed on the inner surface and accessible from a front portion of the main shaft by a tool extending via the central opening of the front retaining member.

Aircraft turbine engine drive line shaft comprising a connecting ring for disassembling the drive line

A turbine engine includes a fan. The fan includes a first shaft driven in rotation via a reduction gear, the first shaft being guided in rotation with respect to a support of a fixed structure via an upstream bearing and a downstream bearing, the downstream bearing guiding in rotation the first shaft with respect to a downstream branch of the support, the first shaft and the support together defining an enclosure. The reduction gear includes a ring gear fixed to the structure via a shell. The turbine engine also includes a lubricator composed of at least one pipe for conveying a liquid lubricant, wherein the pipe is located in the enclosure, the pipe passing through an orifice made in the shell and an opening made in the downstream branch.

Aircraft turbine engine with reduction gear

A bypass turbine engine is described. The engine includes a system for bleeding gas from a primary stream to a secondary stream. The system may include two coaxial rings extending one around the other. A perforated internal first ring may be situated at the level of an outer casing and may extend substantially in a continuation of the outer casing. A perforated external second ring may be mounted such that it slides circumferentially on the first ring between a first position in which the perforations of the rings do not communicate with one another and a second bleed position in which the perforations of the rings communicate with one another.

Bypass turbomachine fitted with bleed system

Growing community of inventors

Moissy-Cramayel, France

Xavier Jean Yves Alain Agneray