CMC turbine nozzle adapted to support a metallic turbine internal casing by an axial contact
View Patent ↗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.
1. An assembly comprising:
a turbine nozzle including an assembly of composite material blades and a metallic turbine internal casing, said blades including an airfoil extending between a shroud at an upper radial end thereof and a root at a lower radial end thereof,
wherein an upstream end of the shroud and a downstream end of the shroud present an internal upper upstream lug and an external upper upstream lug at the upstream end of the shroud, and an internal upper downstream lug and an external upper downstream lug at the downstream end of the shroud,
wherein an upstream end of the root and a downstream end of the root present an internal lower upstream lug and an external lower upstream lug at the upstream end of the root, and an internal lower downstream lug and an external lower downstream lug at the downstream end of the root,
wherein the external upper upstream lug and the external upper downstream lug attach the shroud to one or more turbine casings of a turbomachine,
wherein end portions of the external lower upstream lug and the external lower downstream lug extend axially relative to a rotation axis of the turbomachine and said internal casing includes a liner presenting a radial support for the end portions of the external lower upstream lug and the external lower downstream lug, and
wherein the liner includes upstream and downstream protuberances protruding radially from the liner to present axial abutments which cooperate with free ends of the end portions of the external lower upstream lug and the external lower downstream lug to support and center the turbine internal casing.
2. The assembly as claimed in claim 1 , wherein the upstream end of the root and the downstream end of the root are each produced within a thickness thereof into two distinct layers of fibers that diverge radially from each other while remaining connected by a ceramic matrix so as to form the internal lower upstream lug and the external lower upstream lug at the upstream end of the root, and the internal lower downstream lug and the external lower downstream lug at the downstream end of the root, and
wherein ends of the internal lower upstream lug and the internal lower downstream lug shape a gas flow.
3. The assembly as claimed in claim 1 , wherein the upstream end of the shroud and the downstream end of the shroud are each produced with a separation within a thickness thereof into two distinct layers of fibers that diverge radially from each other while remaining connected by a ceramic matrix so as to form the internal upper upstream lug and the external upper upstream lug at the upstream end of the shroud, and the internal upper downstream lug and the external upper downstream lug at the downstream end of the shroud, and
wherein ends of the internal upper upstream lug and the internal upper downstream lug shape a gas stream.
4. The assembly as claimed in claim 1 , wherein the liner is able to be deformed elastically by a radial pressure applied by the external lower upstream lug and external lower downstream lug.
5. The assembly as claimed in claim 1 , further comprising at least one cooling tube adapted to route cooling air to the internal casing through said shroud and root, wherein the internal casing includes a device which retains said tube axially and circumferentially and allows translation radially.
6. A turbomachine turbine module including an assembly as claimed in claim 1 .
7. A turbomachine including a turbine module as claimed in claim 6 .
8. The assembly as claimed in claim 1 , wherein an upstream end of the liner cooperates with an upstream flange of the internal casing and a downstream end of the liner cooperates with a downstream flange of the internal casing to retain the liner.
9. The assembly as claimed in claim 5 , wherein the device which retains the tube includes a radially oriented chimney.