Turbomeca

Safran Helicopter Engines

Pierre Biscay

Patrick Marconi

Jean-Baptiste Arilla

Hubert Hippolyte Vignau

Jean-Philippe Ousty

Geoffroy Louis-Henri Marie Billotey

Philippe Denis Joubert

Geoffroy Billotey

Denis Boisseleau

Jean-François Escuret

Gilles Cazenave-Larroche

Jean-Francois Escuret

Jean-Bernard Martin

Guillaume Sevestre

Alain J Farrando

Compression assembly for a turbine engine, in particular a turboshaft engine, said assembly comprising an air inlet duct capable of receiving an air flow, at least one air compression stage comprising at least one movable compressor wheel onto which the duct discharges, and a pre-rotation grille which is positioned in the air inlet duct upstream of the movable compressor wheel in order to adjust the speed of the air in said flow at the inlet of the movable wheel and comprises a plurality of variable-setting vanes, the assembly being characterized in that the pitch between two consecutive vanes of the grille is greater than the chord of one of the two vanes at a given height of the air duct, preferably in its upper part.

Compression assembly for a turbine engine

To achieve accurate and rapid acquisition or distribution of fluid&#x2014;at multipoints&#x2014;with good spatial resolution and minimal bulk, a twisted arrangement of ducts is provided in the acquisition/distribution zone making it possible to perform several acquisitions/distributions over several heights with one and the same device. The device is a pressure probe in which a probe body exhibits a first part or section for acquiring pressure forming a cylinder less than 6 mm in diameter. The probe exhibits internal ducts forming parallel helicoidal traces on the section and channels formed in a metal alloy body between the ducts and inlet orifices. The number of internal ducts is advantageously equal to nine, including three orifices being disposed over three different heights of the probe body.

Device for multipoint acquisition/distribution of fluid, in particular probe for tapping pressure in a turbomachine air inlet

A compressor impeller including at least one blade connected to an impeller hub via a junction of curved shape, the blade extending along a defined chord between a leading edge and a trailing edge of the blade. The junction presents the shape of an ellipse that varies along the chord.

Compressor impeller blade with variable elliptic connection

The invention provides a regulating system (23) for controlling the heating of the gases on the downstream side of the regulating system, attenuating the aerodynamic noise produced by the gyratory flow on the downstream side of the directing vanes (24) of the regulating system and facilitating the endoscopic inspection of the blades and vanes of a compressor (3) owing to the provision of a throughway passage (27) in the regulating system (23), and in particular a throughway opening in at least one directing vane (24).

System for regulating air supply conditions of a turbo shaft machine

Growing community of inventors

Lons, France

Pierre Biscay