Snecma

Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Snecma Moteurs

Didier Merville

Gerard E Jourdain

Denis J Sandelis

Gerard Y Barbier

Jean-Paul D Alary

Hanna Reiss

Francois J Mirville

Vincent Perrot

Christophe Jean Champenois

Daniel Bernard Dao

Lucie Galons

Maurice Jean Cabaret

Antoine Jean

Jean-Pierre Caubet

Jacques G Havard

Bruno R Masse

Corine G Delahaye

Paul Mackovic

Serge R Muccioli

Ralph M Stelter

Jean-Pierre Poitevin

Bruno Tournaire

Gilles A Le Rumeur

Christophe G Gourio

Laurent Villaines

Jean-Francois Escuret

Alain Henri Daniel Bouron

Alain Henri Bouron

Villaines Laurent

A one-block bladed disk includes blades, a leading edges of which has sweep and dihedral angles, both strongly variable and increasingly large upon approaching a connection to a hub to improve mechanical strength of the whole and obtain good distribution of gas flow over the height of the blade.

One-block bladed disk provided with blades with adapted foot profile

A method of checking turbomachine blades is presented that may be implemented using a computer and a measuring device. Turbomachine blades compatible with embodiments of the method have a profile including a centerline, suction face, pressure face, leading edge and trailing edge. The method measures geometrical coordinates of many points on a blade section profile, calculates an aerodynamic parameter of the blade section as a function of the measured coordinates, verifies whether the calculated aerodynamic parameter value departs from a valid range of parameters from a reference blade, and validates or rejects the blade depending upon whether the value of the aerodynamic parameter falls within the valid range.

Checking of turbomachine blades

In a turbomachine compressor stator comprising a plurality of variable-pitch vanes ( ), each vane mounted in rotation, about an axis of pivoting ( ), in a wall ( ) forming a surface of revolution about a longitudinal central axis of rotation of the turbomachine ( ), being inclined by a specified angle (&agr;) with respect to a plane perpendicular to this longitudinal central axis, there is provision for this wall to be machined locally opposite an end part of each vane ( ) so as to form a spherical portion or pocket ( ) whose center is positioned on the axis of pivoting and whose radius is determined so as to ensure, over the entire range of operation of the vane, a predetermined minimum clearance between this end part of each vane and the opposite machined spherical pocket while limiting the depth of machining of this pocket.

Compressor stator having a constant clearance

A separator-diffuser for a gas turbine engine is disclosed wherein the diffuser includes axial walls which function as a guide vane stage for the oxidizer compressor. By incorporating the last, or downstream, guide vane stage into the diffuser structure, the overall axial length and bulk of the gas turbine engine may be significantly reduced. The separator-diffuser has a wall defining a generally annular oxidizer flow passage extending around the central axis of the gas turbine engine, the passage having an oxidizer inlet located downstream of the last rotor stage of the oxidizer compressor so as to enable the oxidizer to pass from the oxidizer compressor into the oxidizer flow passage. A generally annular separator member is located in the oxidizer flow passage downstream of the oxidizer inlet so as to divide the oxidizer flow passage into at least two separate oxidizer flow paths, each flow path having a separate oxidizer outlet. The oxidizer outlets are positioned so as to direct the oxidizer towards one of the annular array of fuel injection heads. A plurality of circumferentially spaced apart, axially extending primary arms connect the separator member to the diffuser walls so as to support the separator within the oxidizer passageway and to serve as a guide vane stage for the oxidizer emanating from the oxidizer compressor.

Gas turbine engine having an integral guide vane and separator diffuser

A gas turbine engine impeller having a plurality of blades attached to a rotor disk and an integral, annular collar defining openings through which the blades extend which acts as a platform extending between the adjacent blades. The annular collar is formed as an integral, annular structure and may be formed from a composite material, or other material which is resistant to high temperatures and high centrifugal forces. The annular collar defines a plurality of openings to accommodate the blade portion of the plurality of blades and to enable the blades to extend radially outwardly from the collar. The openings may be formed in the annular collar when the collar itself is formed, or may be machined therein after the collar has been fabricated.

Gas turbine engine impeller having an annular collar platform

Growing community of inventors

Breuillet, France

Didier Merville