Hollow-blade turbine vane made from composite material, turbine or compressor including a nozzle or guide vane assembly formed by such blades, and turbomachine comprising same
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.
1. A turbine engine vane, the vane being made of composite material comprising a fiber reinforcing structure densified by a matrix and comprising:
a hollow airfoil having an internal passage extending along its entire length between a pressure side wall and a suction side wall of the airfoil,
an inner platform, and
an outer platform, wherein
the airfoil is extended on the outside of the outer platform by an upstream attachment portion and by a downstream attachment portion for mounting the vane in a casing,
the upstream attachment portion includes an upstream attachment tab that is an extension from the pressure side wall or the suction side wall of the airfoil, the upstream attachment tab being rounded in shape to extend at an angle to the pressure side wall or the suction side wall from which it extends,
the downstream attachment portion includes a downstream attachment tab that is an extension from the pressure side wall or the suction side wall of the airfoil, the downstream attachment tab being rounded in shape to extend at an angle to the pressure side wall or the suction side wall from which it extends, and
the fiber reinforcing texture of each of the upstream attachment tab and the downstream attachment tab is in continuity with the fiber reinforcing texture of the pressure side wall or the suction side wall in line with which the tab is situated.
2. A vane according to claim 1 , wherein the downstream attachment portion includes at least one downstream attachment tab situated in line with a portion of the suction side wall or of the pressure side wall between a leading edge and a trailing edge of the airfoil.
3. A vane according to claim 1 , wherein the upstream attachment portion includes at least one upstream attachment tab situated in line with a portion of the pressure side wall or of the suction side wall in the vicinity of a leading edge of the airfoil.
4. A vane according to claim 3 , wherein the upstream attachment portion comprises two upstream attachment tabs situated respectively in line with a portion of the pressure side wall and in line with a portion of the suction side wall in the vicinity of the leading edge of the airfoil.
5. A vane according to claim 1 , wherein, on the inside of the inner platform, the airfoil is extended by inner tabs extending from inner longitudinal ends of the pressure side and suction side walls of the airfoil with continuity of the reinforcing fiber texture between said walls and said tabs.
6. A vane according to claim 5 , wherein the inner tabs comprise at least a downstream inner tab situated in line with a portion of the suction side wall or with the pressure side wall between the leading edge and the trailing edge of the airfoil.
7. A vane according to claim 5 , wherein the inner tabs comprise at least an upstream inner tab situated in line with a portion of the pressure side wall or of the suction side wall in the vicinity of a leading edge of the airfoil.
8. A vane according to claim 7 , wherein the inner tabs comprise two upstream inner tabs situated respectively in line with a portion of the pressure side wall and with a portion of the suction side wall in the vicinity of the leading edge of the airfoil.
9. A vane according to claim 1 , wherein the fiber reinforcing texture of the airfoil is a fabric obtained by three-dimensional weaving.
10. A vane according to claim 1 , presenting continuity of the fiber reinforcing texture between the airfoil and the inner and outer platforms.
11. A turbine engine turbine comprising a turbine casing and at least one turbine nozzle including a set of vanes according to claim 1 .
12. A turbine according to claim 11 , wherein the vanes are mounted in the turbine casing with a sealing shroud arranged on the outside, and the shroud presents orifices in communication with the internal passages of the airfoils of the vanes.
13. A turbine according to claim 12 , wherein ventilation tubes extend in the internal passages of the vanes and are connected to the shroud by tubular connection parts.
14. A turbine engine having a turbine according to claim 11 .
15. A turbine engine compressor comprising a compressor casing and at least one compressor diffuser including a set of vanes according to claim 1 .
16. A compressor according to claim 15 , wherein the vanes are mounted in the compressor casing with a sealing shroud arranged on the outside, and the shroud presents orifices in communication with the internal passages of the airfoils of the vanes.
17. A compressor according to claim 16 , wherein the ventilation tubes extend in the internal passages of the vanes and are connected to the shroud by tubular connection parts.
18. A turbine engine having a compressor according to claim 15 .
19. A vane according to claim 1 , wherein the upstream attachment tab, the downstream attachment tab, or both, extend generally perpendicular to the pressure side wall or the suction side wall from which it extends.
20. A vane according to claim 1 , wherein the upstream attachment tab and the downstream attachment tab each have a terminal portion that extends substantially axially with a common annular surfaces about an axis that is an axis to which the vane is configured to be mounded.