Turbomachine e.g. jet engine, for aircraft, has diffuser with upstream part having portion inclined with respect to direction perpendicular to axis, towards front of turbomachine, in plane, such that diffuser has gooseneck form

摘要

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.