TURBOMACHINE COMPRENANT UN DIFFUSEUR

The turbomachine has an annular diffuser (120) e.g. blade type diffuser, diffusing gas current coming from a centrifugal compressor (110) and directing the current towards an annular combustion chamber (140). The diffuser has an annular upstream part (121) connected to an outlet of the compressor an...

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Bibliographische Detailangaben
Hauptverfasser:	SANDELIS DENIS, PIEUSSERGUES CHRISTOPHE
Format:	Patent
Sprache:	fre
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	The turbomachine has an annular diffuser (120) e.g. blade type diffuser, diffusing gas current coming from a centrifugal compressor (110) and directing the current towards an annular combustion chamber (140). The diffuser has an annular upstream part (121) connected to an outlet of the compressor and an annular downstream part (125) oriented towards the chamber. An external portion of the part (121) is inclined with respect to direction perpendicular to an axis (A) of the turbomachine, towards the front of the turbomachine, in an axial cutting plane, such that the diffuser has gooseneck form.