Abstract: An airfoil assembly defining a primary airflow path for a turbine engine comprising a platform, an airfoil extending from the platform and into at least a portion of the primary airflow path, a secondary airflow path comprising air from the primary airflow path, and a deflector provided within the secondary airflow path.

Abstract: A turbine engine having counter-rotating rotors comprising a first rotor, rotating in a first rotational direction, defining a first rotor set of blades axially spaced to define a gap, and a second rotor, rotating in a second rotational direction counter the first rotational direction. The second rotor further including a second set of blades received within the gap of the first rotor. A plurality of fluid passages is formed in the first rotor with an outlet facing the gap.

Abstract: A turbine clearance control system is provided. The turbine clearance control system includes a cooling air source and a turbine casing surrounding a portion of a turbine, wherein the turbine casing defines an integral cooling duct within the turbine casing, the integral cooling duct including apertures on an interior surface of the turbine casing.

Abstract: A turbine clearance control system is provided. The turbine clearance control system includes a cooling air source and a turbine casing surrounding a portion of a turbine, wherein the turbine casing defines an integral cooling duct within the turbine casing, the integral cooling duct including apertures on an interior surface of the turbine casing.

Abstract: Aspects of the disclosure generally relate to a turbine engine and method of operating, wherein a change in sealing status can be determined within a cavity between an outer casing and a rotor within the turbine engine. Aspects of the disclosure further relate to a supply of air to the cavity within the turbine engine.

Abstract: An airfoil assembly defining a primary airflow path for a turbine engine comprising a platform, an airfoil extending from the platform and into at least a portion of the primary airflow path, a secondary airflow path comprising air from the primary airflow path, and a deflector provided within the secondary airflow path.

Abstract: A turbine engine having counter-rotating rotors comprising a first rotor, rotating in a first rotational direction, defining a first rotor set of blades axially spaced to define a gap, and a second rotor, rotating in a second rotational direction counter the first rotational direction. The second rotor further including a second set of blades received within the gap of the first rotor. A plurality of fluid passages is formed in the first rotor with an outlet facing the gap.

Abstract: In a gas turbine for aeronautic engines, a stator body delimited by an outer lateral surface is cooled by an air cooling device having a plurality of circumferential tubes for distributing air on the outer lateral surface; each circumferential tube having a plurality of outlets for guiding respective cooling airflows towards the outer lateral surface and into a respective circumferential channel obtained between two groups of circumferential channels adjacent to each other and lapped by the flow of air leaving the circumferential channel.

Abstract: A filtering net, in particular for a rotary separator, has a plurality of cells, which are substantially equal to one another and are defined by the replication of a base cell along two transversal directions of replication; the base cell comprises at least one intermediate filament and a first and a second end filament, arranged on opposite sides of the intermediate filament; the intermediate filament and the end filaments extend along respective longitudinal axes which are parallel; cross-sectioning the base cell with any plane orthogonal to the longitudinal axes of the filaments and joining, on said plane, the trace of each longitudinal axis with the trace of the adjacent longitudinal axis by a respective straight line, the two straight lines are incident at the trace of the longitudinal axis of the intermediate filament and form an incidence angle of between approximately 90° and 160°.

Abstract: In a gas turbine engine stage, a labyrinth seal has a layer of abradable material arranged on a static part and radially delimited by a cylindrical surface, which is continuous and has a constant diameter in an initial assembly configuration; the seal has at least three tabs, which are arranged on the rotating part, radially facing the abradable material, and are constituted by two side tabs and an intermediate tab having a smaller radial height; this height still allows the abradable material to be engraved, due to the effect of thermal expansion and of the relative rotation during operation; the tabs are positioned axially in such a way that, in the running operational configuration, the layer of abradable material has two seats, which have been fretted by the tips of the two side tabs during operation, and are axially separated by a step, while the intermediate tab is arranged at said step.

Abstract: A filtering body, in particular for a rotary separator, extends about an axis and has a two opposite axial faces, a radially outer surface and a radially inner surface; the filtering body comprises a filtering net constituted by filaments defining a plurality of pores between them; a frame, which is defined by non-porous solid elements, supports the filtering net and made in one piece with a filtering net; the frame has at least one element arranged in an intermediate radial position between the radially outer and inner surfaces.

Abstract: In a turbine for aeronautic engines, a first and at least a second turbine disk rotating around a common axis respectively carrying a first and a second moving-blade crown, with which first and, respectively, second axial passages are defined through which a cooling air mass for the turbine disks can pass, a device for conveying cooling air being interposed between the first and the second axial passages to receive the mass of air passing through the first axial passages and send it through the second axial passages.

Abstract: A bladed rotor of a gas turbine for aeronautic engines is cooled by making an air mass flow through a plurality of passages, each one defined by a turbine disk on one side and by a root of a corresponding blade coupled to this turbine disk on the other, the incoming air of each passage being subdivided into two or more airflows and each flow being directed towards the turbine disk in a predefined direction.

Abstract: A filtering body, in particular for a rotary separator, which extends about an axis, has two opposite axial faces and is provided with a filtering net constituted by filaments defining a plurality of pores between them and with a frame, which is defined by non-porous solid elements, supports the filtering net and is made in one piece with the filtering net; at least some of the filaments of the filtering net extend from one of the axial faces along respective longitudinal axes, which are parallel.

Abstract: A filtering body, in particular for a rotary separator, which extends about an axis, has two opposite axial faces and is provided with a filtering net constituted by filaments defining a plurality of pores between them and with a frame, which is defined by non-porous solid elements, supports the filtering net and is made in one piece with the filtering net; at least some of the filaments of the filtering net extend from one of the axial faces along respective longitudinal axes, which are parallel.

Abstract: A filtering net, in particular for a rotary separator, has a plurality of cells, which are substantially equal to one another and are defined by the replication of a base cell along two transversal directions of replication; the base cell comprises at least one intermediate filament and a first and a second end filament, arranged on opposite sides of the intermediate filament; the intermediate filament and the end filaments extend along respective longitudinal axes which are parallel; cross-sectioning the base cell with any plane orthogonal to the longitudinal axes of the filaments and joining, on said plane, the trace of each longitudinal axis with the trace of the adjacent longitudinal axis by a respective straight line, the two straight lines are incident at the trace of the longitudinal axis of the intermediate filament and form an incidence angle of between approximately 90° and 160°.

Abstract: A filtering body, in particular for a rotary separator, extends about an axis and has a two opposite axial faces, a radially outer surface and a radially inner surface; the filtering body comprises a filtering net constituted by filaments defining a plurality of pores between them; a frame, which is defined by non-porous solid elements, supports the filtering net and made in one piece with a filtering net; the frame has at least one element arranged in an intermediate radial position between the radially outer and inner surfaces.

Abstract: In a turbine for aeronautic engines, a first and at least a second turbine disk rotating around a common axis respectively carrying a first and a second moving-blade crown, with which first and, respectively, second axial passages are defined through which a cooling air mass for the turbine disks can pass, a device for conveying cooling air being interposed between the first and the second axial passages to receive the mass of air passing through the first axial passages and send it through the second axial passages.

Abstract: A bladed rotor of a gas turbine for aeronautic engines is cooled by making an air mass flow through a plurality of passages, each one defined by a turbine disk on one side and by a root of a corresponding blade coupled to this turbine disk on the other, the incoming air of each passage being subdivided into two or more airflows and each flow being directed towards the turbine disk in a predefined direction.

Abstract: A blade for a stator of a variable-geometry turbine, particularly for aircraft engines; the blade has an airfoil profile hinged to a structure of the stator to rotate about an axis, and having a pressure front wall and a suction rear wall; the blade also has two end walls, which are located at opposite ends of the airfoil profile, cooperate in sliding manner with the structure of the stator, and are cooled, in use, by air flowing through a number of holes; the outlets of the holes are located close to the outer edges between the end walls and the front wall to generate a tangential stream of cooling air by virtue of the pressure difference acting on the front and rear walls.