Abstract: A turbomachine rotor blade including a blade root and a blade tip spaced apart by a blade height, including at least one intermediate segment between the blade root and the blade tip that presents forward sweep over at least 50% of the blade height, and a distal segment with backward sweep between the intermediate segment and the blade tip, the distal segment also presenting a positive tangential angle of inclination.

Abstract: A turbine engine has at least two successive annular rows of stationary vanes, e.g. formed by the vanes of a nozzle and by an annular row of casing arms arranged downstream from the nozzle Each casing arm extends substantially in a radial plane passing between the trailing edges of two adjacent stationary vanes of the nozzle, and the pitch between these two stationary vanes is greater than the pitch between the other stationary vanes of the nozzle, in such a manner that the wakes formed at the trailing edges of these two stationary vanes pass respectively on either side of the corresponding casing arm.

Abstract: An assembly including an airfoil for a bladed wheel together with a platform, the airfoils in association with such platforms forming a bladed wheel. The platform surface presents a circumferential depression between a leading edge of an airfoil at 60% of the airfoil going downstream. A skeleton curve designates a curve plotting variations in a skeleton angle of the airfoil as a function of position along the axis of the wheel; and a linearized skeleton curve designates a curve that provides a straight line connection between points representing the skeleton angle respectively at 10% and at 90% of an axial extent of the airfoil from its leading edge, and, in a vicinity of the platform, a lowered portion of the skeleton curve lying under the linearized skeleton curve extends axially over at least half of an axial extent of the depression.

Abstract: An assembly including an airfoil and a platform on which the airfoil may be mounted, the surface of the platform presenting a circumferential depression between a leading edge and trailing edge of the airfoil, a deepest section of the depression being situated in an upstream half of the airfoil. A skeleton curve designates a curve of variations of a skeleton angle of the airfoil as a function of position along the axis of the wheel, and a linearized skeleton curve designates a curve of variations of an angle as a function of position along the axis of the wheel, the curve being a straight line connecting together points representing the skeleton angle respectively at 10% and at 90% of the axial extent of the airfoil from the leading edge. In a vicinity of the platform, the skeleton curve presents a raised portion that lies above the linearized skeleton curve.

Abstract: A turbomachine rotor blade including a blade root and a blade tip spaced apart by a blade height, including at least one intermediate segment between the blade root and the blade tip that presents forward sweep over at least 50% of the blade height, and a distal segment with backward sweep between the intermediate segment and the blade tip, the distal segment also presenting a positive tangential angle of inclination.

Abstract: A diffuser which straightens the flow of air issuing from a centrifugal compressor in a turbine engine is provided. The diffuser having a cylindrical shape and including a first part having the form of two substantially parallel discs extending substantially radially relative to the axis of symmetry of the diffuser, a second bent part, and a third part intended to open out into a downstream cavity, positioned downstream of the diffuser and fed with air issuing from the compressor. The first part is traversed by a plurality of channels distributed evenly over its circumference and opening out on its downstream face so as to bring the air contained in the downstream cavity into communication with a bleed cavity situated upstream of the diffuser.

Abstract: An assembly including an airfoil for a bladed wheel together with a platform, the airfoils in association with such platforms forming a bladed wheel. The platform surface presents a circumferential depression between a leading edge of an airfoil at 60% of the airfoil going downstream. A skeleton curve designates a curve plotting variations in a skeleton angle of the airfoil as a function of position along the axis of the wheel; and a linearized skeleton curve designates a curve that provides a straight line connection between points representing the skeleton angle respectively at 10% and at 90% of an axial extent of the airfoil from its leading edge, and, in a vicinity of the platform, a lowered portion of the skeleton curve lying under the linearized skeleton curve extends axially over at least half of an axial extent of the depression.

Abstract: An assembly including an airfoil and a platform on which the airfoil may be mounted, the surface of the platform presenting a circumferential depression between a leading edge and trailing edge of the airfoil, a deepest section of the depression being situated in an upstream half of the airfoil. A skeleton curve designates a curve of variations of a skeleton angle of the airfoil as a function of position along the axis of the wheel, and a linearized skeleton curve designates a curve of variations of an angle as a function of position along the axis of the wheel, the curve being a straight line connecting together points representing the skeleton angle respectively at 10% and at 90% of the axial extent of the airfoil from the leading edge. In a vicinity of the platform, the skeleton curve presents a raised portion that lies above the linearized skeleton curve.

Abstract: A turbine engine has at least two successive annular rows of stationary vanes, e.g. formed by the vanes of a nozzle and by an annular row of casing arms arranged downstream from the nozzle Each casing arm extends substantially in a radial plane passing between the trailing edges of two adjacent stationary vanes of the nozzle, and the pitch between these two stationary vanes is greater than the pitch between the other stationary vanes of the nozzle, in such a manner that the wakes formed at the trailing edges of these two stationary vanes pass respectively on either side of the corresponding casing arm.

Abstract: Diffuser intended to straighten the flow of air issuing from a centrifugal compressor in a turbine engine, the said diffuser having a cylindrical shape and comprising a first part having the form of two substantially parallel discs extending substantially radially relative to the axis of symmetry of the diffuser, a second bent part and a third part intended to open out into a downstream cavity, positioned downstream of the said diffuser and fed with air issuing from the said compressor, characterized in that the first part is traversed by a plurality of channels distributed evenly over its circumference and opening out on its downstream face so as to bring the air contained in the said downstream cavity into communication with a bleed cavity situated upstream of the said diffuser.