Mixed flow and centrifugal compressor for gas turbine engine

Details Mixed flow and centrifugal compressor for gas turbine engine Mixed flow and centrifugal compressor for gas turbine engine

F - Mech Eng,Light,Heat,Weapons

04

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F04D 17/12 (2006.01) F02C 3/08 (2006.01) F04D 17/06 (2006.01) F04D 29/44 (2006.01)

Patent

CA 2420709

A two stage compressor with a mixed flow first stage, a centrifugal second stage, and an intermediate duct. The centrifugal rotor (2) has a circumferential array of radially extending centrifugal flow blades (16) between the centrifugal flow hub and an associated centrifugal flow shroud. An intermediate duct (3) has an inner duct wall (20) defining an axially curvilinear transition surface of revolution between anoutlet end of the mixed flow hub and an inlet end of the centrifugal flow hub and an outer duct wall (21) defining an axially curvilinear transition surface of revolution between an outlet end of the mixed flow shroud and an inlet end of the centrifugal flow shroud.

Cette invention a trait à un compresseur à deux étages, un premier étage héico-centrifuge et un second étage centrifuge, comportant également un conduit intermédiaire. Le rotor centrifuge (2) est pourvu d'un ensemble circonférentiel de pales (16) à flux centrifuge s'étendant radialement entre le moyeu à flux centrifuge et un carénage à flux centrifuge associé. Le conduit intermédiaire (3), qui comprend une paroi interne (20) définissant une surface axiale curviligne de transition de révolution entre une extrémité d'orifice de sortie et une extrémité d'orifice d'entrée du moyeu, comprend également une paroi externe (21) définissant une surface axiale curviligne de transition de révolution entre une extrémité d'orifice de sortie et une extrémité d'orifice d'entrée du carénage.

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