Mounting a turbine nozzle on a combustion chamber having CMC walls in a gas turbine
View Patent ↗The gas turbine comprises an annular combustion chamber having inner and outer walls made of ceramic matrix composite material, and a high pressure turbine nozzle secured to a downstream end of the combustion chamber and comprising a plurality of stationary airfoils extending between the inner and outer walls of an annular flow path through the nozzle for the gas stream coming from the combustion chamber. The turbine nozzle is made of ceramic matrix composite material and it is connected to the downstream end of the combustion chamber by brazing.
1. A gas turbine comprising an annular combustion chamber with inner and outer walls of ceramic matrix composite material, a high pressure turbine nozzle integral with a downstream end of the combustion chamber and comprising a plurality of stationary airfoils extending between the inner and outer walls of an annular flow path through the nozzle for the gas stream coming from the combustion chamber,
wherein the turbine nozzle is made of a ceramic matrix composite material and is connected to the downstream end of the combustion chamber by brazing.
2. A gas turbine according to claim 1 , wherein the downstream portions of the inner and outer walls of the combustion chamber are extended to the downstream end of the turbine nozzle so as form the inner and outer walls of the flow path to which the airfoils are connected by brazing.
3. A gas turbine according to claim 2 , wherein each airfoil is brazed at a first radial end in a housing or indentation formed in the thickness of one of the inner and outer walls of the flow path.
4. A gas turbine according to claim 2 , wherein each of the airfoils is engaged at a second radial end in an opening formed in one of the inner and outer walls of the flow path.
5. A gas turbine according to claim 4 , wherein the airfoils are brazed at their second radial ends in said openings.
6. A gas turbine according to claim 1 , in which the assembly constituted by the combustion chamber and the turbine nozzle is held inside a metal casing comprising an inner metal shroud and an outer metal shroud by means of internal and external linking members connecting said assembly respectively to the inner and outer shrouds,
wherein the linking members comprise: inner linking tabs of ceramic matrix composite material each having a first end connected to the inner metal shroud and a second end connected to the combustion chamber and turbine nozzle assembly, and outer linking tabs made of ceramic matrix composite material each having a first end connected to the outer metal shroud and a second end connected to the combustion chamber and turbine nozzle assembly.
7. A gas turbine according to claim 6 , wherein the second ends of the linking tabs are secured to inner or outer annular ferrules made of ceramic matrix composite material connected respectively to the outside surfaces of extensions of the combustion chamber walls forming the inner and outer walls of the flow path through the turbine nozzle.
8. A gas turbine according to claim 7 , wherein the airfoils are brazed at their second radial ends in said openings, and wherein the second radial ends of the airfoils are also brazed to one of said annular ferrules.
9. A gas turbine according to claim 7 , wherein the inner or outer annular ferrule carries a portion that co-operates with a flange integral with the inner or outer metal shroud to hold a sealing gasket to close off a downstream end of the annular space between the combustion chamber and turbine nozzle assembly and the inner or outer metal shroud.
10. A gas turbine according to claim 6 , wherein the first ends of the inner and outer linking tabs are fastened directly to the inner and outer metal shrouds respectively.
11. A gas turbine according to claim 6 , wherein the first ends of the inner and outer linking tabs are connected to the inner and outer metal shrouds via flexible metal tabs.
12. A gas turbine according to claim 11 , wherein the flexible metal tabs have respective first ends connected to the linking tabs of ceramic matrix composite material and respective second ends integral with a ferrule fastened to the corresponding metal shroud.
13. A gas turbine according to claim 1 , in which the assembly formed by the combustion chamber and the turbine nozzle is held inside a metal casing comprising inner and outer metal shrouds by means of inner and outer linking members connecting said assembly to the inner and outer shrouds, respectively, wherein the linking members comprise inner and outer metal linking tabs having respective first ends connected to the inner and outer metal shrouds, respectively, and respective second ends connected to the combustion chamber and turbine nozzle assembly.
14. A gas turbine according to claim 13 , wherein the second ends of the metal linking tabs are integral with inner and outer sectorized metal platforms fastened respectively on the extensions of the combustion chamber walls forming the inner and outer walls of the flow path through the turbine nozzle.
15. A gas turbine according to claim 14 , wherein the sectorized platforms are mechanically connected to the combustion chamber and turbine nozzle assembly by means of screws passing through the extensions of the combustion chamber walls forming the inner and outer walls of the flow path through the turbine nozzle, and screwed into the airfoils.
16. A gas turbine according to claim 15 , wherein the screws are made of metal.
17. A gas turbine according to claim 15 , wherein the screws are made of ceramic matrix composite material.
18. A gas turbine according to claim 14 , wherein the inner or outer sectorized platform carries a portion that co-operates with a flange integral with the inner or outer metal shroud to hold an annular sealing gasket closing off a downstream end of the annular space between the combustion chamber and turbine nozzle assembly and the inner or outer metal shroud.
19. A gas turbine according to claim 13 , wherein the first ends of the inner and outer metal linking tabs are integral with respective ferrules fastened to the inner and outer metal shrouds, respectively.
20. A gas turbine according to claim 1 , in which the assembly formed by the combustion chamber and the turbine nozzle is held inside a metal casing comprising an inner metal shroud and an outer metal shroud by inner and outer linking members connecting said assembly to the inner and outer shrouds, respectively, wherein means other than the linking members are provided for locking the turbine nozzle in rotation relative to at least one of the metal shrouds so as to avoid the turning forces induced on the airfoils of the nozzle by the gas stream coming from the combustion chamber being taken up by the linking members.
21. A gas turbine according to claim 20 , wherein the means for preventing turning comprise locking elements constraining at least one of inner and outer annular ferrules in rotation with a flange integral with the corresponding inner or outer metal shroud.
22. A gas turbine according to claim 20 , wherein the means for preventing turning comprise locking elements constraining at least one of inner and outer sectorized platforms in rotation with a flange integral with the corresponding inner or outer metal shroud.