Safran Aircraft Engines

Guilhem Camille François Verron

Maurice Guy Judet

Damien Bonneau

Tangi Brusq

Antoine Bruno Van Noort

Clement Raphael Laroche

Florence Valérie Bon

Guillaume Michel Maurice Giliberti

Clement Jarossay

A device for controlling clearance between the tips of rotating blades of an aircraft turbomachine and a casing. An air circulation path allows air to be blown onto the casing in order to change its temperature. In addition, heating means heat the circulating air.

Control of clearance between aircraft rotor blades and a casing

Labyrinth seal for a turbine engine, in particular of an aircraft, including a rotor element rotating about an axis of rotation, and a stator element extending around the rotor element The rotor element includes a series of annular lips extending radially outwards and surrounded by at least one abradable element carried by the stator element. Each lip includes an inner peripheral body portion, an outer peripheral body portion and an upstream annular face for impact of an air flow during operation. At least one lip has, looking from the upstream annular face, a first annular cavity with a concave rounded cross-section on its inner peripheral body portion and a second annular cavity with a concave rounded cross-section on its outer peripheral body portion.

Labyrinth seal for a turbine engine of an aircraft

Growing community of inventors

Moissy-Cramayel, France

Guilhem Camille François Verron