Final-Stage Internal Collar Gasket Of An Axial Turbine Engine Compressor

Abstract

The invention relates to an axial turbine engine guide vane assembly that comprises an annular row of blades which extend radially, an internal collar disposed at the internal ends of the blades. The internal collar comprises a circular gasket in elastomer or in silicon which is disposed on one of the upstream or downstream sides of said collar, so as to ensure airtightness with a sealing surface of the intermediate casing of the turbine engine. The internal collar comprises a cavity in which the gasket is housed, the cavity being integrally formed in the material of the internal collar and/or with the help of one or a plurality of added members. The invention allows the airtightness in the event of vibrations to be improved, while at the same time increasing the rigidity of the internal collar without increasing the production cost. The invention likewise relates to an axial turbine engine.

What is claimed is: 
     
         1 . An axial turbine engine compressor guide vane assembly, said guide vane assembly comprising:
 an annular row of blades which extend radially; and   an internal collar disposed at the internal ends of the blades, the collar comprising:
 a circular gasket dispose on one of and upstream and a downstream side of the collar, the gasket structured and operable to ensure airtightness with a sealing surface of an intermediate casing of the turbine engine; and 
 a cavity in which the gasket is housed. 
   
     
     
         2 . The guide vane assembly according to  claim 1 , wherein the cavity is formed in the material of the internal collar, 
     
     
         3 . The guide vane assembly according to  claim 2 , wherein the collar is realized in at least one of a polymer material and a composite material with an organic matrix. 
     
     
         4 . The guide vane assembly according to Claim to  2 , wherein in that the cavity is formed by a portion of the collar and one or more members added to the collar. 
     
     
         5 . The guide vane assemble according to  claim 4 , wherein the internal collar and each added member a realized in composite materials with an organic matrix. 
     
     
         6 . The guide vane assembly according to  claim 4  further comprising a hook that forms the cavity structured and operable to hold the gasket against the sealing surface of the casing and against the internal collar. 
     
     
         7 . The guide vane assembly according to  claim 6 , wherein the cavity forms an annular throat substantially opened axially. 
     
     
         8 . The guide vane assembly according to  claim 6  further comprising an annular shoulder delimiting the cavity axially, wherein the shoulder is formed by at least one of an annular flange extending radially, and the annular collar, and each added member. 
     
     
         9 . The guide vane assembly according to  claim 8  further comprising a substantially tubular face delimiting the inside of the cavity radially, the tubular face being formed on at least one of the annular collar and each added member. 
     
     
         10 . The guide vane assembly according to  claim 9 , wherein at least one added member tubular face is structured and operable to compress the gasket radially against an internal surface of the internal collar. 
     
     
         11 . The guide vane assembly according to  claim 9 , wherein the gasket is disposed at least one of axially and radially inside the cavity, and the gasket comprises an elastomer material. 
     
     
         12 . The guide vane assembly according to  claim 11 , wherein the gasket comprises a substantially toroidal form, wherein the revolution profile of the gasket is substantially one of a circle, a triangle, and a quadrilateral. 
     
     
         13 . The guide vane assembly according to  claim 12 , wherein the gasket is structured and operable to provide airtightness between the internal collar and each added member. 
     
     
         14 . The guide vane assembly according to  claim 13 , wherein each added member is fixed to the internal collar, and each added member is one of:
 interlocked and bonded adhesively to the internal collar, and   fixed to the blades with a fixing means by material engagement.   
     
     
         15 . The guide vane assembly according to  claim 14 , wherein each added member extends over a substantial portion of the axial length of the internal collar and is disposed against the internal surface of the internal collar. 
     
     
         16 . The guide vane assembly according to  claim 15 , wherein the length of the internal collar is greater than twice the chord of each blade. 
     
     
         17 . The guide vane assembly according to  claim 16 , wherein the length of each added member is greater than the chord of each blade. 
     
     
         18 . The guide vane assembly according to  claim 16  further comprising an annular layer of abradable material disposed on the upstream side or downstream side of the internal collar that is axially opposed to that which has the circular gasket disposed therein, the abradable layer extending axially up to the material delimiting the cavity. 
     
     
         19 . An axial turbine engine, said engine comprising:
 a casing including a sealing surface; and   at least one compressor including a guide vane assembly that cooperates in an airtight manner with the sealing surface, the guide vane assembly comprises:   an annular row of blades which extend radially; and   an internal collar disposed at the internal ends of the blades, the collar comprising:
 a circular gasket dispose on one of and upstream and a downstream side of the collar, the gasket structured and operable to ensure airtightness with a sealing surface of an intermediate casing of the turbine engine; and 
 a cavity in which the gasket is housed such that the gasket is compressed axially between the guide vane assembly and the sealing surface of the casing. 
   
     
     
         20 . Turbine engine according to  claim 19  further comprising:
 axial play between the casing and the internal collar, wherein the gasket extending axially over the entire axial play; 
 at least one turbine; and 
 at least one fan, wherein the casing is an intermediate casing of the turbine engine and is structured and operable to withstand the forces of each compressor, each turbine and each fan.