Gas turbine seal arrangement

Abstract

A turbine arrangement including a rotor and a stator surrounding the rotor and comprising guide vane segments, each guide vane segment comprising an airfoil and a radially inner vane platform. A seal arrangement includes a static seal inward from the inner vane platforms and having a radially extending face plate, first and second cylindrical seal walls extending from outer and inner ends of the annular face plate, an annular seal plate extending radially from the second cylindrical seal wall, and an angel wing extending between the first cylindrical seal wall and the annular seal plate to define a first annular cavity and a second annular cavity. Circumferentially spaced cut-outs define passages through the annular seal plate between the first and second annular cavities and are aligned with fasteners that attach the annular face plate to a support ring for supporting the inner vane platform.

What is claimed is: 
     
         1 . A turbine arrangement comprising:
 a rotor that rotates about a rotor axis and comprises a plurality of rotor blade segments extending radially outward, each rotor blade segment comprises an airfoil and a radially inner blade platform;   a stator surrounding the rotor so as to form an annular flow path for a hot working gas, the stator comprises a plurality of guide vane segments disposed adjacent the plurality of rotor blade segments, the plurality of guide vane segments extending radially inward, each guide vane segment comprising an airfoil and a radially inner vane platform;   a seal arrangement comprising an annular face plate extending radially inward from the vane platform, a first cylindrical seal wall extending axially from an outer end of the face plate, a second cylindrical seal wall extending axially from an inner end of the face plate, an annular seal plate extending radially from an end of the second cylindrical seal wall, and an angel wing extending from the rotor and having a distal end between the first cylindrical seal wall and the seal plate to define a first annular cavity and a second annular cavity,   wherein:
 the first annular cavity is defined at least by the first and second cylindrical seal walls and the annular seal plate; 
 the second annular cavity is defined at least by the angel wing and the annular seal plate; 
 the first annular cavity is in fluid communication with the annular flow path via a first annular seal passage between the first cylindrical seal wall and the angel wing; 
 the first annular cavity is in fluid communication with the second annular cavity via a second annular seal passage between the angel wing and an outer end of the annular seal plate; 
   the annular face plate is attached to a support ring that supports the inner vane platform, including a plurality of circumferentially spaced fasteners passing through apertures in the annular face plate into the support ring; and   a plurality of circumferentially spaced cut-outs in the annular seal plate defining passages between the first and second annular cavities.   
     
     
         2 . The turbine arrangement according to  claim 1 , characterized in that the fasteners include fastener heads that are located in the first annular cavity. 
     
     
         3 . The turbine arrangement according to  claim 2 , characterized in that the cut-outs in the annular seal plate are each circumferentially aligned with a fastener head. 
     
     
         4 . The turbine arrangement according to  claim 3 , characterized in that the cut-outs are each defined by a sidewall that is angled circumferentially in a direction of rotor rotation extending from the second annular cavity toward the first annular cavity. 
     
     
         5 . The turbine arrangement according to  claim 1 , characterized in that a cylindrical flange extends parallel to the first and second cylindrical seal walls into the first annular cavity from the outer end of the annular seal plate. 
     
     
         6 . The turbine arrangement according to  claim 1 , characterized in that a surface at the outer end of the annular seal plate is angled radially inward from the first cavity toward the second cavity. 
     
     
         7 . The turbine arrangement according to  claim 6 , characterized in that the surface at the outer end of the annular seal plate is defined by an inner seal member affixed to the cylindrical flange and cooperates with the angel wing to define the second annular seal passage. 
     
     
         8 . The turbine arrangement according to  claim 6 , characterized in that the surface at the outer end of the annular seal plate is stepped radially inward from the first cavity toward the second cavity. 
     
     
         9 . The turbine arrangement according to  claim 6 , characterized in that an outer seal member is affixed to an inner side of the first cylindrical seal wall and cooperates with the angel wing to define the first annular seal passage. 
     
     
         10 . The turbine arrangement according to  claim 1 , characterized in that the distal end of the angel wing is formed with a hammerhead configuration cooperating with surfaces at the first cylindrical seal wall and the outer end of the annular seal plate to define the first and second annular seal passages, respectively. 
     
     
         11 . The turbine arrangement according to  claim 1 , characterized in that the outer end of the annular seal plate is formed with a knife-edge and cooperates with the angel wing to define the second annular seal passage. 
     
     
         12 . The turbine arrangement according to  claim 11 , characterized in that a knife-edge extends radially inward from the first cylindrical seal wall and cooperates with the angel wing to define the first annular seal passage. 
     
     
         13 . A turbine arrangement comprising:
 a rotor that rotates about a rotor axis and comprises a plurality of rotor blade segments extending radially outward, each rotor blade segment comprises an airfoil and a radially inner blade platform;   a stator surrounding the rotor so as to form an annular flow path for a hot working gas, the stator comprises a plurality of guide vane segments disposed adjacent the plurality of rotor blade segments, the plurality of guide vane segments extending radially inward, each guide vane segment comprising an airfoil and a radially inner vane platform;   a seal arrangement comprising an annular face plate extending radially inward from the vane platform, a first cylindrical seal wall extending axially from an outer end of the face plate, a second cylindrical seal wall extending axially from an inner end of the face plate, an annular seal plate extending radially from an end of the second cylindrical seal wall, and an angel wing extending from the rotor and having a distal end between the first cylindrical seal wall and the seal plate to define a first annular cavity and a second annular cavity,   wherein:
 the first annular cavity is defined at least by the first and second cylindrical seal walls and the annular seal plate; 
 the second annular cavity is defined at least by the angel wing and the annular seal plate; 
 the first annular cavity is in fluid communication with the annular flow path via a first annular seal passage between the first cylindrical seal wall and the angel wing; 
 the first annular cavity is in fluid communication with the second annular cavity via a second annular seal passage between the angel wing and an outer end of the annular seal plate; 
   the annular face plate is attached to a support ring that supports the inner vane platform, including a plurality of circumferentially spaced fasteners passing through apertures in the annular face plate into the support ring; and   a plurality of circumferentially spaced cut-outs in the annular seal plate defining passages between the first and second annular cavities, wherein the cut-outs are each circumferentially aligned with a fastener and are defined by a sidewall that is angled circumferentially in a direction of rotor rotation extending from the second annular cavity toward the first annular cavity.   
     
     
         14 . The turbine arrangement according to  claim 13 , characterized in that a cylindrical flange extends parallel to the first and second cylindrical seal walls into the first annular cavity from the outer end of the annular seal plate. 
     
     
         15 . The turbine arrangement according to  claim 14 , characterized in that an inner seal member is affixed to the cylindrical flange and cooperates with the angel wing to define the second annular seal passage. 
     
     
         16 . The turbine arrangement according to  claim 15 , characterized in that the inner seal member has an outer sealing surface that has a reduced downstream radial dimension adjacent to the second annular cavity in comparison to the upstream radial dimension of the honeycomb seal adjacent to the first annular cavity. 
     
     
         17 . A turbine arrangement comprising:
 a rotor that rotates about a rotor axis and comprises a plurality of rotor blade segments extending radially outward, each rotor blade segment comprises an airfoil and a radially inner blade platform;   a stator surrounding the rotor so as to form an annular flow path for a hot working gas, the stator comprises a plurality of guide vane segments disposed adjacent the plurality of rotor blade segments, the plurality of guide vane segments extending radially inward, each guide vane segment comprising an airfoil and a radially inner vane platform;   a seal arrangement comprising an annular face plate extending radially inward from the vane platform, a first cylindrical seal wall extending axially from an outer end of the face plate, a second cylindrical seal wall extending axially from an inner end of the face plate, an annular seal plate extending radially from an end of the second cylindrical seal wall, and an angel wing extending from the rotor and having a distal end between the first cylindrical seal wall and the seal plate to define a first annular cavity and a second annular cavity,   wherein:
 the first annular cavity is defined at least by the first and second cylindrical seal walls and the annular seal plate; 
 the second annular cavity is defined at least by the angel wing and the annular seal plate; 
 the first annular cavity is in fluid communication with the annular flow path via a first annular seal passage between the first cylindrical seal wall and the angel wing; 
 the first annular cavity is in fluid communication with the second annular cavity via a second annular seal passage between the angel wing and an outer end of the annular seal plate; and 
   a cylindrical flange extends parallel to the first and second cylindrical seal walls into the first annular cavity from the outer end of the annular seal plate.   
     
     
         18 . The turbine arrangement according to  claim 17 , characterized in that a plurality of circumferentially spaced cut-outs in the annular seal plate define passages between the first and second annular cavities. 
     
     
         19 . The turbine arrangement according to  claim 18 , characterized in that the annular face plate is attached to a support ring that supports the inner vane platform, and a plurality of circumferentially spaced fasteners pass through apertures in the annular face plate into the support ring and are located in circumferential alignment with the cut-outs. 
     
     
         20 . The turbine arrangement according to  claim 17 , characterized in that an inner seal member is affixed to the cylindrical flange and cooperates with the angel wing to define the second annular seal passage.