Abstract: A turbine or compressor stage for a turbine engine is provided. The stage includes a disk including a metal material configured to be coupled to a shaft of the turbine engine, an airfoil including a ceramic matrix composite material, and an interface part that is distinct from the airfoil and that is configured to be fastened to the disk and to fasten the airfoil. The interface part includes a ceramic or a ceramic matrix composite material.

Abstract: A turbine engine vane is made of composite material comprises a hollow airfoil with an internal passage extending along its entire length, an inner platform, and an outer platform. The airfoil is extended on the outside of the outer platform by an upstream attachment portion and a downstream attachment portion for mounting the vane in a casing. The attachment portions are formed by an attachment extending from the outer longitudinal ends of the pressure side wall and the suction side wall of the airfoil with continuity of the fiber reinforcing texture of the composite material between the walls and the attachment tabs.

Abstract: A gas turbine engine including at least a first composite part configured for mounting in a second metal part of the engine, the first composite part including an interface surface configured to be in surface contact with the second metal part, the engine including a metal protection removably mounted on the first composite part and configured to cover the interface surface.

Abstract: A turbine engine wheel, in particular for a low pressure turbine, is provided. The wheel includes blades, each including an airfoil connected by a platform to a middle wall or tang extending radially and itself extended radially inwards by a root mounted in a slot of a disk, the platform and the tang defining two side cavities arranged on either side of the tang, which cavities are circumferentially open and are situated facing corresponding cavities in the directly adjacent blades, and sealing members being housed in the cavities adjacent to the blades. An annular sealing end plate is mounted on the upstream or downstream end of the disk, between the platforms and the disk, so as to face the slots and the roots of the blades, and includes a rotary coupling device for coupling with at least one of the sealing members.

Abstract: A device for attaching blades to a rotor disk of a turbine engine is provided. The device includes: a rotor disk provided at its outer periphery with a plurality of slots, each slot being formed between two adjacent disk teeth and extending axially between front and rear faces of the disk; a plurality of blades, each having a respective root mounted in a slot of the disk; and at least one pin mounted in the rotor disk to pass through the roots of at least two adjacent blades and extending between the front and rear faces of the rotor disk so as to attach the blades to the rotor disk.

Abstract: A composite material turbine nozzle blade including an airfoil adapted to have a cooling fluid flow through it and extending between a shroud and a root is provided. The shroud is shaped to be attached to one or more turbine casings of a turbomachine and the root is shaped to provide a junction with a turbine internal casing. The root is produced with a loosened texture and includes an external upstream side loosened texture lug and an external downstream side loosened texture lug. The ends of the two external side lugs extend radially relative to the rotation axis of the turbomachine to form a device for supporting and centering the internal casing.

Abstract: A composite material turbine nozzle blade including an airfoil adapted to have a cooling fluid flow through it and extending between a shroud and a root is provided. The shroud is shaped to be attached to one or more turbine casings of a turbomachine and the root is shaped to provide a junction with a turbine internal casing. The root is produced with a loosened texture and includes an external upstream side loosened texture lug and an external downstream side loosened texture lug, the ends of the two external side lugs extending axially relative to the rotation axis of the turbomachine to form a device for supporting and centering the internal casing.

Abstract: A turbine or compressor stage suitable for being included in airplane turbojets. According to the invention, the stage comprises a disk (30) configured to be coupled to a shaft of the turbine engine, and at least one airfoil (20), the disk (30) comprising a metal material, the airfoil (20) comprising a ceramic matrix composite material, and the stage further including an interface part (40) that is distinct from the airfoil (20) and that is configured to be fastened to the disk (30) and to fasten said at least one airfoil (20), said interface part (40) comprising a ceramic or a ceramic matrix composite material.

Abstract: The invention relates to a turbine engine wheel (2), in particular for a low pressure turbine (1), the wheel having blades (4), each comprising an airfoil (5) connected by a platform (6) to a middle wall or tang (7) extending radially and itself extended radially inwards by a root (8) mounted in a slot of a disk (3), the platform (6) and the tang (7) defining two side cavities (19) arranged on either side of the tang (7), which cavities (19) are circumferentially open and are situated facing corresponding cavities (19) in the directly adjacent blades (4), sealing members (18) being housed in the cavities (19) adjacent to the blades (4). An annular sealing end plate (26) is mounted on the upstream or downstream end of the disk (3), between the platforms (6) and the disk (3), so as to face the slots and the roots (8) of the blades (4), and including rotary coupling means (27) for coupling with at least one of the sealing members (18).

Abstract: A turbine engine vane is made of composite material comprises a hollow airfoil with an internal passage extending along its entire length, an inner platform, and an outer platform. The airfoil is extended on the outside of the outer platform by an upstream attachment portion and a downstream attachment portion for mounting the vane in a casing. The attachment portions are formed by an attachment extending from the outer longitudinal ends of the pressure side wall and the suction side wall of the airfoil with continuity of the fiber reinforcing texture of the composite material between the walls and the attachment tabs.

Abstract: A gas turbine engine including at least a first composite part configured for mounting in a second metal part of the engine, the first composite part including an interface surface configured to be in surface contact with the second metal part, the engine including a metal protection removably mounted on the first composite part and configured to cover the interface surface.

Abstract: The invention provides a device for attaching blades to a rotor disk of a turbine engine, comprising: a rotor disk provided at its outer periphery with a plurality of slots, each formed between two adjacent disk teeth and extending axially between front and rear faces of the disk; a plurality of blades, each having a respective root mounted in a slot of the disk; and at least one pin mounted in the rotor disk to pass through the roots of at least two adjacent blades and extending between the front and rear faces of the rotor disk so as to attach the blades to the rotor disk.

Abstract: Composite material turbine nozzle blade including an airfoil (10) adapted to have a cooling fluid flow through it and extending between a shroud (11) and a root (12), said shroud being shaped to be attached to one or more turbine casings (6, 7) of a turbomachine and said root being shaped to provide a junction with a turbine internal casing (5), wherein its root (12) is produced with a loosened texture and includes an external upstream side loosened texture lug (122) and an external downstream side loosened texture lug (124), the ends of the two external side lugs extending radially relative to the rotation axis of the turbomachine to form means for supporting and centering said internal casing.

Abstract: Composite material turbine nozzle blade including an airfoil (10) adapted to have a cooling fluid flow through it and extending between a shroud (11) and a root (12), said shroud being shaped to be attached to one or more turbine casings (6, 7) of a turbomachine and said root being shaped to provide a junction with a turbine internal casing (5), wherein its root (12) is produced with a loosened texture and includes an external upstream side loosened texture lug (122) and an external downstream side loosened texture lug (124), the ends of the two external side lugs extending axially relative to the rotation axis of the turbomachine to form means for supporting and centering said internal casing.

Abstract: The segmented ring has the gaseous hot flow of the turbomachine passing through it and comprises: a plurality of segments assembled by means of sealed connection involving sealing strips, provided in the mutually-facing radial faces of said segments the internal lateral faces of which delimit the flow path along which the hot gaseous flow travels; and through-orifices, formed in said segments, to carry external fresh air towards their radial and internal faces. Advantageously, one, the lower one, of the sealing strips of the means of connection is designed to lie close to the lateral internal faces of said segments and to run parallel to them, passing through a cooling chamber formed in the radial faces of the segments and into which said orifices open.