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

Corine G Delahaye

Denis J Sandelis

Gerard Y Barbier

Jean-Paul D Alary

Didier Merville

Francois J Mirville

Bruno R Masse

Jacques G Havard

Ralph M Stelter

Serge R Muccioli

Paul Mackovic

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

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Mormant, France

Corine G Delahaye