Abstract: The invention relates to a vane (10) of a diffuser (5) for a radial or mixed-flow compressor (2) of an engine (1), including a leading edge (11) arranged facing a flow of gas, a trailing edge (12) being opposite the leading edge (11), a side upper surface wall (13) and a side lower surface wall (14) which connect the leading edge (11) to the trailing edge (12), and a profile including a curved line (15) having at least two points of inflection (I1, I2) between the leading edge (11) and the trailing edge (12). The invention also relates to a corresponding radial diffuser (2).

Abstract: The invention relates to a vane (10) of a diffuser (5) for a radial or mixed-flow compressor (2) of an engine (1), including a leading edge (11) arranged facing a flow of gas, a trailing edge (12) being opposite the leading edge (11), a side upper surface wall (13) and a side lower surface wall (14) which connect the leading edge (11) to the trailing edge (12), and a profile including a curved line (15) having at least two points of inflection (I1, I2) between the leading edge (11) and the trailing edge (12). The invention also relates to a corresponding radial diffuser (2).

Abstract: A diffuser for a mixed flow or centrifugal compressor of a gas turbine. The diffuser includes at least one vane presenting a pressure side, a suction side, and a first flank. The vane includes a plurality of orifices opening out into the suction side and/or the pressure side and communicating with at least one cavity formed in the vane, the cavity extending transversely relative to the vane and opening out into its first flank. The cross section of the cavity varies in the transverse direction of the vane, the cross section increasing towards the first flank.

Abstract: A centrifugal impeller for a compressor, through which a fluid is to pass. The impeller includes blades each having a leading edge and a trailing edge, the rotation of the impeller sucking fluid in through the front of the impeller, the fluid leaving the impeller via its outer periphery, the trailing edges of the blades being such that in a radial section plane intersecting the trailing edges of the blades, they are curved in the direction opposite to the direction of rotation of the impeller, and the trailing edge portions of the blades are redirected in the direction of rotation of the impeller to form respective end fins serving to deflect the flow of the fluid by redirecting it radially.

Abstract: A diffuser for a mixed flow or centrifugal compressor of a gas turbine. The diffuser includes at least one vane presenting a pressure side, a suction side, and a first flank. The vane includes a plurality of orifices opening out into the suction side and/or the pressure side and communicating with at least one cavity formed in the vane, the cavity extending transversely relative to the vane and opening out into its first flank. The cross section of the cavity varies in the transverse direction of the vane, the cross section increasing towards the first flank.