Stator vane assembly for a turbomachine

A stator vane assembly for a gas turbine engine (10) compressor (16) comprises a plurality of circumferentially arranged stator vanes (44A) and a plurality of circumferentially arranged load bearing struts (46). The leading edges (45,47) of the stator vanes (44A) and the struts (46) are arranged in...

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Bibliographische Detailangaben
Hauptverfasser:	GALLIMORE, SIMON J, HALL, JOHN
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A stator vane assembly for a gas turbine engine (10) compressor (16) comprises a plurality of circumferentially arranged stator vanes (44A) and a plurality of circumferentially arranged load bearing struts (46). The leading edges (45,47) of the stator vanes (44A) and the struts (46) are arranged in a common plane. The leading edges (45,47) of the stator vanes (44A) and the struts (46) have substantially the same profile. The spacing (B) between adjacent struts (44A) in any group is the same. The spacing (C) between the suction surface (50) of one of the struts (46A) of the adjacent pair of struts (46) and an adjacent stator vane (44A) is less than the spacing (B) between adjacent stator vanes (44A) and the spacing (D) between the pressure surface (52) of the other of the struts (46B) of the adjacent pair of struts (46) and an adjacent stator vane (44A) is greater than the spacing (B) between adjacent stator vanes (44A) to equalise aerodynamic loading of the stator vanes (44A) and to reduce the aerodynamic losses of the struts (46).