Abstract: A gas turbine combustor, in particular for an aircraft engine, has at least one chamber, through which combustion gas flows in use, and which is defined by a lateral wall with channeling for feeding cooling air into the chamber and cooling the lateral wall; part of the channeling is defined by at least one double wall for guiding a relative stream of cooling air into the chamber in a tangential direction with respect to the lateral wall.

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 method of producing an element of composite material, including the steps of forming a first distribution of first elements defining the matrix of the element of composite material; forming a second distribution of second elements defining the reinforcing structure of the element of composite material; and compacting the first and second elements to obtain a distribution of the reinforcing structure inside the matrix; the first elements being metal wires; and the step of forming the first distribution including the step of assigning each second element an orderly distribution of metal wires.

Abstract: The position of the inner surface of a hollow metal workpiece on a machine tool is detected by connecting an operating member of the machine, preferably a tool, to a first terminal of an electric power source; connecting the inner surface to a second terminal of the power source; moving the operating member gradually towards the inner surface to detect the emission of a signal generated by an emitting device interposed between one of the terminals and the inner surface, and corresponding to a condition in which initial contact is established between the operating member and the inner surface; and determining the position of the operating member at the instant the signal is emitted.

Abstract: A power plant for propeller aircraft has two propulsion devices, each having a propeller, an engine for powering the propeller, and a gear transmission interposed between the engine and the propeller. The transmission has a power input shaft connected directly to the engine, and a power output shaft supporting the propeller and rotated with respect to the input shaft about a hinge axis perpendicular to the output shaft. The gear transmission also has a single gear fitted to the output shaft and having two opposed sets of teeth meshing with a pair of pinions. One of the pinions extends coaxially with the hinge axis, and is connected to the input shaft by a single pair of gears.

Abstract: A bladed member, particularly for an axial turbine of an aircraft engine; the bladed member having at least one aerodynamic profile defined by a back face and an underside face connected to each other along a leading edge and a trailing edge and defining respective nozzles for a stream of gas; the underside face having a projecting rib elongated in a direction crosswise to the leading and trailing edges.

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: A stator of a variable-geometry axial turbine for aeronautical applications has an axis and 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 airfoil 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 coupled slidably with 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 double-wall blade for a turbine, particularly for aeronautical applications, has a streamlined lateral wall, which extends along an axis, surrounds the axis itself, and is defined by an inner wall and an outer wall facing and integral with each other; the blade is provided with inner channeling, which has a cavity into which, in use, cooling air is admitted, and a number of ducts, which are provided tangentially between the inner wall and outer wall, are separated from one another by baffles which are transverse to the axis and have respective intakes which are separate from one another and communicate with the cavity in order, in use, each to have a corresponding flow of cooling air pass through them.

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 pin for connecting a gear to a supporting member has a first and a second longitudinal end portion connectable to the supporting member; a first intermediate portion extending from the first end portion; and a second intermediate portion extending from the second end portion, and which differs in size from the first intermediate portion and has a flexural strength differing from that of the first intermediate portion.

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: A method and machine whereby a continuous-thread disk element from which to form composite materials is formed by winding a thread of reinforcing material about an axis to form a flat coil having a number of turns, and by locking the turns with respect to one another by means of binding threads wound about each turn; the turns being equally spaced with a given spacing by forming, simultaneously with the formation of the coil, a further two flat coils of spacer thread, which are removed from the reinforcing-thread coil once the binding threads are wound about the turns.

Abstract: A face gear transmission, in particular for aircraft application, has a floating input pinion rotating about a respective axis, and two face gears which are positioned facing each other, rotate about a common axis forming an angle of other than 90° with the axis of the pinion, both mesh with the input pinion, and have respective different diameters.

Abstract: A face gear transmission assembly has a supporting structure, and a pair of face gears which are positioned facing each other, rotate with respect to the supporting structure about a common axis, and both mesh with two input pinions and three transmission pinions; the transmission pinions are supported by an auxiliary frame which provides for maintaining the transmission pinions equally spaced angularly, is connected to the supporting structure in angularly fixed manner about the common axis, and is movable along the common axis and at least in one direction crosswise to the common axis.

Abstract: A gear-drive assembly between an input shaft (17, 117) and an output shaft (10, 110) comprises a ring gear (12, 112) having a peripheral portion provided with corresponding and opposite toothings (14, 15, 114, 115) on the two faces thereof. Meshing with each toothing (14, 15, 114, 115) is a pinion of a pair of pinions (16, 25, 116, 125) carried by parallel shafts (17, 22, 117, 122) interconnected with each other by a driving gear (20, 21, 120, 121) to rotate at the same speed and in opposite ways. One of said parallel shafts is the power-input shaft (17, 117). The ring gear (12, 112) is carried by the output shaft (10, 110) in a floating manner to vary the distance of its toothings (14, 15, 114, 115) from the axis of the pinions (16, 25, 116, 125).

Abstract: A gear transmission assembly for transferring a drive torque from at least one power input to a primary user has at least one drive pinion carried by a respective power input shaft and meshing with a pair of facing coaxial counter-rotating ring gears having an axis perpendicular to the axis of the drive pinion and engaging between facing face teeth at least one transmission pinion having an axis perpendicular to the axis of the ring gears. The at least one drive pinion floats in the direction of the axis of the ring gears, while the at least one transmission pinion is supported by elements flexible in a circumferential direction with respect to the ring gears.

Abstract: A blade sector has a plurality of blades and a circular body connecting the ends of the blades defining its own axis and is finished by the working of a lateral surface of the circular body itself; the working of the lateral outer surface is effected with the use of a disc tool having a shaped cutting surface by arranging the cutting surface of the disc tool in contact with the lateral surface and rotating the sector about an axis distinct from the axis of the circular body and, at the same time as the bladed sector is rotated, displacing the blade sector and the disc tool translationally relative to each other in two directions perpendicular to the first axis in such a way that a distance between the axis of the circular body and the instantaneous point of contact of the lateral surface with the disc tool is kept constant during the entire working of the lateral surface itself.

Abstract: A method for the manufacture of gears, in which a gear adapted for meshing with a toothed pinion is formed by means of a disc tool having a cutting edge exactly the same as the contour of the teeth of the pinion; the tool being positioned so that its cutting edge would be coincident, if the gear were meshed with the pinion, with the contour of the teeth of the pinion itself, and is pivoted about an axis perpendicular to its own axis of rotating; about the pivot axis, the gear is moved translationally along a line of action perpendicular to the axis of rotation of the disc tool itself and is rotated about its own axis perpendicular to the line of action; the ratio of the speeds of rotation of the gear about its axis and the speed of pivoting of the disc tool about is axis being variable in dependence on the position of the zone of contact of the disc with the gear.