Assembly for a turbine engine

Abstract

An assembly for a turbomachine including a wall including a guide surface for an airflow and a row of stator blades extending from the wall and arranged annularly around an axis. The surface being inclined relative to the axis. The row of blades includes first blades extending substantially perpendicular to the axis and second blades extending substantially perpendicular to the guide surface. An axial turbomachine including a low-pressure compressor, a high-pressure compressor, and a swan-neck vein arranged axially between the low-pressure compressor and the high-pressure compressor. The swan-neck vein contains the assembly as described above.

1 . An assembly for a turbomachine, comprising:
 a wall including a guide surface for an airflow and a row of stator blades extending from the wall and arranged annularly around an axis, said guide surface being inclined with respect to the axis, wherein the row of stator blades comprises first blades extending substantially perpendicularly to the axis and second blades extending substantially perpendicularly to the guide surface.   
     
     
         2 . The assembly according to  claim 1 , further comprising structural arms axially arranged directly downstream of the row of the stator blades, inter-arm spaces being defined between two circumferentially adjacent structural arms, the first blades circumferentially overlapping the structural arms and the second blades circumferentially overlapping the inter-arm spaces. 
     
     
         3 . The assembly according to  claim 1 , wherein the row of the stator blades is formed by groups of the first blades and by groups of the second blades, said groups of first and second blades alternating circumferentially. 
     
     
         4 . The assembly according to  claim 3 , wherein each of the groups of first blades comprises between 3 and 8 blades. 
     
     
         5 . The assembly according to  claim 3 , wherein each of the groups of second blades comprises between 4 and 10 blades. 
     
     
         6 . The assembly according to  claim 1 , wherein the row of the stator blades further comprises a plurality of third blades circumferentially regularly arranged between the first blades and the second blades, said third blades having a respective orientation that is, excluding boundaries, between the perpendicular orientation to the axis of the first blades and the perpendicular orientation to the guide surface of the second blades. 
     
     
         7 . The assembly according to  claim 6 , wherein the respective orientation of the third blades varies progressively in accordance with the circumferential position of the third blades relative to the first and second blades, the third blades having an orientation closer to that of the first blades the closer they are circumferentially to them, and the third blades having an orientation closer to that of the second blades the closer they are circumferentially to them. 
     
     
         8 . The assembly according to  claim 7 , wherein the third blades have a respective orientation angle that varies progressively by at least 0.5°. 
     
     
         9 . The assembly according to  claim 8 , wherein, as seen in a radial cross-section, the progression of the orientation of the third blades has a triangular profile. 
     
     
         10 . The assembly according to  claim 7 , characterized in that, wherein as seen in a radial cross-section, the progression of the orientation of the third blades has a sinusoidal profile. 
     
     
         11 . The assembly according to  claim 2 , wherein the trailing edge of the first blades has defines a first distance in the direction of the airflow with a leading edge of the structural arms axially arranged directly downstream of the row of the stator blades, and the trailing edge of the second blades defines a second distance in the direction of the airflow with the leading edge of the structural arms, said first distance being greater than the second distance. 
     
     
         12 . The assembly according to  claim 6 , wherein the first blades, the second blades, and the third blades all have a same chord length. 
     
     
         13 . The assembly according to  claim 1 , wherein the guide surface for the airflow forms an inclination angle with the axis between 10° and 60°. 
     
     
         14 . An axial turbomachine, comprising:
 a low-pressure compressor,   a high-pressure compressor, and   a swan-neck vein arranged axially between the low-pressure compressor and the high-pressure compressor, wherein the swan-neck vein contains the assembly according to  claim 1 .   
     
     
         15 . The assembly according to  claim 4 , wherein each of the groups of first blades comprises 4 blades. 
     
     
         16 . The assembly according to  claim 5 , wherein each of the groups of second blades comprises 5 blades.