nozzle stage for a turbine engine

Abstract

A nozzle stage for a turbine engine includes two substantially cylindrical rings, respectively an inner ring and an outer ring, with, extending between them: vanes carried by a first one of the rings; vanes carried by the second ring; and spacer-forming vanes interconnecting the two rings; the vanes of the first and second rings being arranged in alternation.

1 - 13 . (canceled) 
     
     
         14 . A nozzle stage for a turbine engine, the stage comprising:
 two substantially cylindrical rings, of respectively an inner ring and an outer ring, with substantially radial vanes extending between them;   a first series of vanes carried by a first one of the rings;   a second series of vanes carried by the second ring; and   connection means interconnecting the two rings, the vanes of the first ring alternating with the vanes of the second ring.   
     
     
         15 . A nozzle stage according to  claim 14 , wherein the vanes of each series are substantially regularly distributed around the longitudinal axis of the stage. 
     
     
         16 . A nozzle stage according to  claim 14 , wherein the ring connection means comprises spacer vanes having their ends fastened to the first ring and to the second ring, respectively. 
     
     
         17 . A nozzle stage according to  claim 14 , wherein each ring is sectorized and comprises at least two annular sectors mounted end to end. 
     
     
         18 . A nozzle stage according to  claim 16 , wherein each ring is sectorized and comprises at least two annular sectors mounted end to end, and further comprising an annular rail mounted on the inner ring and including an outer annular groove in which an inner annular rim of each sector of the inner ring and the radially inner end of each spacer vane are engaged by sliding in the circumferential direction. 
     
     
         19 . A nozzle stage according to  claim 18 , further comprising undulating spring-forming blades interposed between a bottom of the annular groove in the rail and both the sectors of the inner ring and roots of the spacer vanes. 
     
     
         20 . A nozzle stage according to  claim 14 , wherein the vanes of the first series have free ends that are flush with or at a short radial distance from the second ring, and the vanes of the second series have free ends that are flush with or at a short radial distance from the first ring. 
     
     
         21 . A nozzle stage according to  claim 20 , wherein the radial distance between the free end of each vane of the first and second series and the corresponding ring is less than or equal to 0.05 mm. 
     
     
         22 . A nozzle stage according to  claim 17 , wherein each annular sector of a ring is formed integrally with the vanes carried by the ring sector. 
     
     
         23 . A nozzle stage according to  claim 17 , wherein the vanes carried by each annular sector of a ring are fitted thereto, being fastened to the ring sector. 
     
     
         24 . A nozzle stage according to  claim 16 , wherein the spacer vanes are connected to the rings in a releasable manner. 
     
     
         25 . A nozzle stage according to  claim 16 , wherein the radially outer end of each spacer vane is threaded and is engaged in a radial orifice of the outer ring and receives a nut that bears against the outer ring. 
     
     
         26 . A nozzle stage according to  claim 22 , wherein each annular sector of a ring is formed by casting or by machining with the vanes carried by the ring sector. 
     
     
         27 . A nozzle stage according to  claim 23 , wherein the vanes carried by each annular sector of a ring are fastened thereto by brazing or welding. 
     
     
         28 . A turbine engine, comprising:
 at least one nozzle stage according to  claim 14 .