Safran Aircraft Engines

Safran Ceramics

Baptiste Dorian Lawniczek

Didier René André Escure

Clémentine Charlotte Marie Mouton

Alexandre Thanh Nhan Nguyen

Nicolas Xavier Trappier

Patrice Jean-Marc Rosset

Patrick Joseph Marie Girard

Sébastien Serge Francis Congratel

Matthieu Arnaud Gimat

Julian Nicolas Girardeau

Simon Jean-Marie Bernard Cousseau

Arthur De Castro

A bladed assembly () includes two adjacent blades (). Each blade () a platform () located at a free radial end. The platform () of the first blade () includes a lateral face () which is located circumferentially opposite an associated lateral face () of the platform () of the second blade (). The platform () of the second blade () comes into contact with the platform () of the second blade () only via an excrescence () which projects circumferentially with respect to the lateral face () of the platform () of the first blade () in the direction of the platform () of the second blade (), and the excrescence () is received in a groove () formed in the platform () of the second blade.

Turbomachine blading assembly comprising means for limiting vibration between platforms

A turbine rotor of a turbine engine of an aircraft, the rotor comprising a rotor disc provided at its periphery with a plurality of cavities for receiving the root of a blade. Each blade includes a circumferential coupling rib, a plurality of platforms, a main wall that is extended at its two ends by an upstream radial wall and by a downstream radial wall, the two longitudinal edges of each platform comprising a groove for receiving part of said coupling rib of one of the two blades between which this platform is assembled, and in that the height of each upstream radial wall is such that said wall extends radially inwards beyond the bottom of the cavity, until it is in front of the upstream face of the rotor disc.

Turbine rotor and platform for such a rotor

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.

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 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.

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MOISSY-CRAMAYEL, France

Baptiste Dorian Lawniczek