Abstract: A low pressure turbine, in particular for a gas turbine engine, extends along an axis, has an annular conduit for guiding a gas flow and is provided with a plurality of stator arrays of blades and a plurality of rotor arrays of blades; the last of the stator arrays, considering the advancement direction of the gas flow, has a plurality of blades, which define a plurality of spaces between them in circumferential direction; the spaces are split by respective splitters into a radially outer conduit and into a radially inner conduit; the radial position of the splitters is in the neighborhood of a radial reference position such that at least one acoustic mode is of the cut-on type in the radially inner conduit.

Abstract: A low pressure turbine, in particular for a gas turbine engine, extends along an axis, has an annular conduit for guiding a gas flow and is provided with a plurality of stator arrays of blades and a plurality of rotor arrays of blades; the last of the stator arrays, considering the advancement direction of the gas flow, has a plurality of blades, which define a plurality of spaces between them in circumferential direction; the spaces are split by respective splitters into a radially outer conduit and into a radially inner conduit; the radial position of the splitters is in the neighborhood of a radial reference position such that at least one acoustic mode is of the cut-on type in the radially inner conduit.

Abstract: An axial turbine for aeronautical applications has a casing housing a stator, which is provided with an array of airfoil profiles, which are positioned angularly equidistant from one other about the axis of the turbine, define associated spaces between one another for the passage of a flow of gas and are hinged to an annular structure, each one about an associated hinge axis incident to the axis of the turbine; in service, the airfoil profiles are simultaneously actuated to rotate by an identical angle of adjustment by means of a ring actuated by actuators outside the casing and connected to each airfoil profile via an associated lever.

Abstract: A stator of a variable-geometry axial turbine for aeronautical applications has an axis an is provided with an annular duct that has a diameter increasing along the axis, is delimited radially by an outer surface and by an inner surface and houses an array of air foil profiles; the profiles are rotatable relative to the outer and inner surfaces about respective axes of adjustment incident to the axis of the stator and each have an associated pair of end edges opposite each other and each slidably at a predetermined clearance from an associated shaped zone of the outer and inner surfaces, each shaped zone has a form complementary to an ideal surface generated by rotation of the associated end edges about the axis of adjustment so as to maintain a constant clearance between the profiles and the inner and outer surfaces.

Abstract: A vane for a stator of a variable-geometry turbine, in particular for aeronautical engines, has an airfoil profile and a pair of hinge portions, which are carried by the airfoil profile and enable the airfoil profile to be coupled to a support structure of the stator so as to be rotatable about an axis of adjustment; the vane also has internal channels that allow a flow of air to pass through in order to cool the hinge portions.

Abstract: A method of positioning arrays of stages of a turbine, particularly for aircraft engines; the turbine having an axis and a first, a second and a third array of blades arranged consecutively, and of which the first and third array have a relative velocity about the axis with respect to the second array; the method including the steps of determining the paths of wakes moving inside gaps defined by the blades in the second array and towards the third array; distinguishing, for each wake, a first and at least one second zone differing from each other; selecting one of the first and second zone; and regulating the position of the third array with respect to the first array by aligning the leading edges of the blades in the third array with the paths of the selected wake zones.

Abstract: An axial turbine for aeronautical applications has a casing housing a stator, which is provided with an array of airfoil profiles, which are positioned angularly equidistant from one other about the axis of the turbine, define associated spaces between one another for the passage of a flow of gas and are hinged to an annular structure, each one about an associated hinge axis incident to the axis of the turbine; in service, the airfoil profiles are simultaneously actuated to rotate by an identical angle of adjustment by means of a ring actuated by actuators outside the casing and connected to each airfoil profile via an associated lever.

Abstract: A vane for a stator of a variable-geometry turbine, in particular for aeronautical engines, has an airfoil profile and a pair of hinge portions, which are carried by the airfoil profile and enable the airfoil profile to be coupled to a support structure of the stator so as to be rotatable about an axis of adjustment; the vane also has internal channels that allow a flow of air to pass through in order to cool the hinge portions.

Abstract: A method of positioning arrays of stages of a turbine, particularly for aircraft engines; the turbine having an axis and a first, a second and a third array of blades arranged consecutively, and of which the first and third array have a relative velocity about the axis with respect to the second array; the method including the steps of determining the paths of wakes moving inside gaps defined by the blades in the second array and towards the third array; distinguishing, for each wake, a first and at least one second zone differing from each other; selecting one of the first and second zone; and regulating the position of the third array with respect to the first array by aligning the leading edges of the blades in the third array with the paths of the selected wake zones.