Safran Aircraft Engines

Safran Ceramics

Ge Aviation Systems Limited

Didier René André Escure

Claude Marcel Mons

Baptiste Dorian Lawniczek

Alexandre Thanh Nhan Nguyen

Sébastien Serge Francis Congratel

Gilles Alain Charier

Clémentine Charlotte Marie Mouton

Matthieu Arnaud Gimat

Tewfik Boudebiza

Nicolas Jérôme Jean Tantot

Jean Charles Olivier Roda

Pierre-Alain Jean Philippe Reigner

Thomas Julien Nguyen Van

Stéphane Rousselin

Patrick Joseph Marie Girard

Jean-François Endy Bersot

Arthur De Castro

Ornella Gastineau

Aleksander Szymandera

Marek Malitka

A module having a longitudinal axis, a hydraulic actuator, and a pump for supplying the hydraulic actuator with fluid, the pump can include axial pistons intended to be movable to rotate about the longitudinal axis and configured to transfer the fluid to the hydraulic actuator, a connecting plate connected to the axial pistons and engaging with an annular main plate centered on the longitudinal axis intended to be rotated about the longitudinal axis and tilted relative to the longitudinal axis, the connecting plate being arranged between the main plate and the axial pistons, the axial pistons being movable to rotate in a direction parallel to the longitudinal axis, the tilting of the main plate resulting in the movement of the axial pistons in the direction.

Module for an aircraft turbine engine

An aeronautical propulsion system includes: a drive shaft; a drive turbine; and a fan section. The drive turbine includes a drive turbine stator and a drive turbine rotor. The drive turbine rotor includes a plurality of shrouds, a plurality of turbine disks connected in pairs by a shroud of the plurality of shrouds, and a plurality of turbine blades. At least one shroud connects an upstream turbine disk to a downstream turbine disk of the plurality of turbine disks. The at least one shroud has an outer surface facing the drive turbine stator, and a shroud radius defined as a smallest distance between the longitudinal axis and the outer surface of the shroud. Each of the upstream turbine disk and of the downstream turbine disk is centered on the longitudinal axis and has an outer surface delimiting a plurality of slots distributed about the longitudinal axis.

Aeronautical propulsion system

A blade includes a root to be mounted in a slot of plural slots which opens out at an outer periphery of a rotor disk of a movable wheel of a low-pressure turbine of an aeronautical propulsion system, the rotor disk being centered on a longitudinal axis and the slots being circumferentially distributed about the longitudinal axis, the rotor disk further including blades circumferentially distributed at the outer periphery of the rotor disk, each blade being mounted in a corresponding slot, the root including a first platform which has a radially outer surface, a shroud having a second platform which has a radially inner surface, and an airfoil extending from the root to the shroud, the airfoil having a leading edge and a trailing edge. The shroud is formed of a material and has a defined difficulty.

Blade of a turbomachine turbine including a airfoil extending along a first direction between an internal end and an external end, a base secured to said internal end, and a root secured to said external end and extending, along a second direction perpendicular to said first direction, between an upstream edge and a downstream edge and, along a third direction orthogonal to the first and second directions, between first and second lateral edges, the first side edge having, in a plane including the second and third directions, a shape complementary to that of the second lateral edge. The first lateral edge includes a first portion extending from the upstream edge, and a second portion externally protruding along the third direction at an acute angle with the first portion.

Turbine blade of a turbine engine with self-generated interlock contact force in operation

A propulsion system includes a drive shaft, a drive turbine including a drive turbine stator and a drive turbine rotor, the rotor being connected to the drive shaft and including a turbine disk and turbine blades, and a fan section including a fan rotor and a fan stator, the drive shaft being connected to the fan rotor. The turbine disk has an inner surface, an outer surface delimiting slots distributed about a longitudinal axis, one or more of the turbine blades including a root fixed to the turbine disk in a respective slot. A bore width of the inner surface, and a rim radius of the outer surface of the turbine disk, and a limit speed of the drive shaft are defined in relation to each other.

The invention relates to a turbine blade () for a movable wheel of a low-pressure turbine of an aeronautical propulsion system, comprising a root (), a shroud (), and an aerodynamically profiled airfoil () extending from the root () to the shroud (), wherein a parameter N2S is defined as: where:

Blade and slotted rotor wheel for a gas turbine engine

A blade includes a root to be mounted in a slot of plural slots which open out at an outer periphery of a rotor disk of a movable wheel of a low-pressure turbine of an aeronautical propulsion system, the rotor disk being centered on a longitudinal axis and the slots being circumferentially distributed about the longitudinal axis, the rotor disk having an upstream surface and a downstream surface, each slot being delimited by a bottom surface, the rotor disk including blades circumferentially distributed at the outer periphery of the rotor disk, each blade being mounted in a corresponding slot, the root including a first platform which has a radially outer surface; a shroud having a second platform which has a radially inner surface; and an airfoil extending from the root to the shroud, the airfoil having a leading edge and a trailing edge.

A combustion chamber of an aircraft turbomachine having a main axis includes: a body of revolution coaxial with the main axis having a plurality of combustion tubes extending mainly in the direction of the main axis and being distributed in a ring about the main axis; a first perforated rotary disc mounted at a first axial end of the body and rotatable about the main axis to selectively open or close a first end of each of the combustion tubes; and a second perforated rotary disc mounted at a second axial end of the body and rotatable about the main axis to selectively open or close a second end of each of the combustion tubes. The body includes a plurality of cooling segments extending mainly in the direction of the main axis, which are distributed in a ring about the main axis and around the combustion tubes.

Constant volume turbomachine combustion chamber

A propulsion system includes a drive shaft, a drive turbine including a drive turbine rotor having a turbine disk and turbine blades, and a fan section. The turbine disk has an inner surface, an outer surface, a bore radius, and a rim radius. One or more of the turbine blades includes a root fixed to the turbine disk in a respective slot, a stilt connected to the root and including a platform, and an airfoil connected to the platform and extending within a flowpath. The flowpath includes an outer radius and an inner radius. The drive shaft has a limit speed. The bore radius, the rim radius, the outer radius, the inner radius, and the limit speed satisfy a given relationship.

A blade includes a root to be mounted in a slot of plural slots which opens out at an outer periphery of a rotor disk of a movable wheel of a low-pressure turbine of an aeronautical propulsion system, the rotor disk being centered on a longitudinal axis and the slots being circumferentially distributed about the longitudinal axis, the root including a first platform which has a radially outer surface; a shroud including a second platform which has a radially inner surface; and an airfoil extending from the root to the shroud, the airfoil having a leading edge and a trailing edge.

Growing community of inventors

Moissy-Cramayel, France

Didier René André Escure