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

Jacques G Havard

Denis J Sandelis

Gerard Y Barbier

Jean-Paul D Alary

Francois J Mirville

Didier Merville

Bruno R Masse

Gerard Louis Zanolin

Michel R Jouardet

Ralph M Stelter

Serge R Muccioli

Paul Mackovic

Corine G Delahaye

Jean-Yves M Loreau

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

The process makes it possible to produce partitioned boxes by carrying out the fastening or fixture from the outside of said boxes. Use is made of two successive inclined laser beam shots or flashes (8A,8B), which intersect at the upper surface (1B) of the part (1) constituting the assembly head. The two laser welding axes (8A,8B) intersect two upper corners (2C) of the part (2) serving as the base of the T. The welding device is positioned outside the box, i.e. on the side of the upper surface (1B) of the head (1) of the T. Application to the manufacture of the arms of the outer duct of a turbojet engine.

Laser welding process for an assembly of two metal parts

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Moissy-Cramayel, France

Jacques G Havard