Assembly for Turbine Engine

Abstract

An assembly for a turbine engine includes an upstream section and a downstream section, each having an annular row of semi-cylindrical radial recesses and a plurality of flanges positioned between two circumferentially adjacent recesses for holding the two sections together. The recesses form a cylindrical opening when the two sections are assembled. The openings receive pivot sections of variable stator vanes.

I claim: 
     
         1 . An assembly for an aircraft turbine engine, comprising:
 an annular row of stator vanes each with an airfoil and a head having a pivot section;   an actuator for pivoting the vanes, the actuator comprising: a ring and connecting rods connecting the ring to each of the vanes;   an outer shroud comprising an upstream section and a downstream section, both comprising an internal guiding surface for the gas flow of the turbine engine, and being axially in contact with each other, the upstream and the downstream sections comprising, each:
 an annular row of recesses having a semi-cylindrical shape; and 
 at least one flange positioned between two circumferentially adjacent recesses of the annular row of recesses; 
   the recesses of the upstream section being arranged radially and circumferentially in correspondence with the recesses of the downstream section so as to form an annular row of openings receiving the pivot sections of the vanes;   each flange of the at least one flange of the upstream section being fixed to a flange of the at least one flange of the downstream section;   the head of each of the vanes having a radial outer portion on the pivot section, the outer radial portion extending circumferentially and/or axially of a length which is greater than the diameter of the respective opening;   the upstream and downstream sections being provided with an annular row of radial thickened portions or bosses within which the recesses are formed; and   the radial thickened portions or bosses being an annular row being interconnected to each other by the flanges.   
     
     
         2 . The assembly according to  claim 1 , wherein the downstream section comprises:
 a seat for receiving the actuator, the seat comprising:
 a cylindrical surface. 
   
     
     
         3 . The assembly according to  claim 2 , wherein the cylindrical surface defines a diameter and downstream of the seat, the downstream section does not extend radially of more than said diameter. 
     
     
         4 . The assembly according to  claim 1 , wherein a flange of the at least one flange is arranged between two circumferentially neighboring recesses of the respective annular row of recesses of the upstream and the downstream section. 
     
     
         5 . The assembly according to  claim 4 , wherein the flange extends circumferentially completely from one recess to the neighboring recess of the two circumferentially neighboring recesses. 
     
     
         6 . The assembly according to  claim 1 , wherein each of the at least one flange comprises two through-holes for receiving screws, each flange having a circumferential length between two neighboring recesses and the through-holes being at a distance from one of the two neighboring recesses that is less than a quarter of the circumferential length of the flange. 
     
     
         7 . The assembly according to  claim 1 , wherein the bosses have an external truncated surface. 
     
     
         8 . The assembly according to  claim 1 , wherein the upstream section comprises a fixation flange at its axial upstream end for assembling the upstream section to a fan casing or a de-icing nozzle. 
     
     
         9 . The assembly according to  claim 1 , further comprising a third section with semi-cylindrical recesses, the third section being connected to the downstream section and the recesses of the third section forming openings with additional semi-cylindrical recesses provided at the downstream end of the downstream section. 
     
     
         10 . An assembly for an aircraft turbine engine, comprising:
 an annular row of stator vanes each with an airfoil and a head having a pivot section;   an actuator for pivoting the vanes, the actuator comprising a ring and being connected to each vanes through connecting rods;   an outer shroud comprising an upstream section and a downstream section, both comprising an internal guiding surface for the gas flow of the turbine engine, and being axially in contact with each other, the upstream and the downstream sections comprising, each:
 an annular row of recesses having a semi-cylindrical shape; and 
 at least one flange positioned between two circumferentially adjacent recesses of the annular row of recesses; 
   the recesses of the upstream section being arranged radially and circumferentially in correspondence with the recesses of the downstream section so as to form an annular row of openings receiving the pivot sections of the vanes;   each flange of the at least one flange of the upstream section being fixed to a flange of the at least one flange of the downstream section;   the head of each of the vanes having a radial outer portion on the pivot section, the outer radial portion extending circumferentially and/or axially of a length which is greater than the diameter of the respective opening, the outer radial portion comprising the connecting rods; and   the airfoil of each vane having a leading edge and a trailing edge, the pivot section having a diameter that is smaller than the distance between the leading edge and the trailing edge; and wherein the radial outer portion, the pivot section and the airfoil are integrally formed.   
     
     
         11 . An assembly for an aircraft turbine engine, comprising:
 an annular row of stator vanes each with an airfoil and a head having a pivot section;   an actuator for pivoting the vanes, the actuator comprising a ring and connecting rods connecting the ring to each of the vanes;   an outer shroud comprising an upstream section and a downstream section, both comprising an internal guiding surface for the gas flow of the turbine engine, and being axially in contact with each other, the upstream and the downstream sections comprising, each:
 an annular row of recesses having a semi-cylindrical shape; and 
 at least one flange positioned between two circumferentially adjacent recesses of the annular row of recesses; 
   the recesses of the upstream section being arranged radially and circumferentially in correspondence with the recesses of the downstream section so as to form an annular row of openings receiving the pivot sections of the vanes;   each flange of the at least one flange of the upstream section being fixed to a flange of the at least one flange of the downstream section;   the head of each of the vanes having a radial outer portion on the pivot section, the outer radial portion extending circumferentially and/or axially of a length which is greater than the diameter of the respective opening;   wherein the downstream section comprises a cylindrical surface and the ring is provided with pads in radial contact with the cylindrical surface; and   wherein each of the flange overlaps radially the ring, and, each of the flange is axially separated from the ring.