Turbine nozzle segment and assembly

Abstract

A turbine nozzle segment includes a band having a plurality of circumferentially spaced apart tabs and a single airfoil extending from the band.

1 . A turbine nozzle segment, comprising:
 a first band having a plurality of circumferentially spaced apart tabs; and   a single airfoil extending from said first band.   
   
   
       2 . The turbine nozzle segment of  claim 1  wherein at least one of said plurality of tabs is adjacent a circumferential edge of said first band. 
   
   
       3 . The turbine nozzle segment of  claim 2  wherein said plurality of tabs are integral with said first band. 
   
   
       4 . The turbine nozzle segment of  claim 3  further comprising:
 a second band;   wherein said single airfoil extends between said first band and said second band.   
   
   
       5 . The turbine nozzle segment of  claim 4  further comprising:
 a rail extending from said first band and spaced from said plurality of tabs defining a recess therebetween; and   a leaf seal disposed in said recess.   
   
   
       6 . The turbine nozzle segment of  claim 5  further comprising:
 a pin extending through each of said tabs and said leaf seal; and   a biasing structure associated with each of said pins and biasing said leaf seal in abutting contact with an adjoining component.   
   
   
       7 . The turbine nozzle segment of  claim 1  further comprising:
 a rail extending from said first band and spaced from said plurality of tabs defining a recess therebetween; and   a leaf seal disposed in said recess.   
   
   
       8 . The turbine nozzle segment of  claim 7  further comprising:
 a pin extending through each of said tabs and said leaf seal; and   a biasing structure associated with each of said pins and biasing said leaf seal in abutting contact with an adjoining component.   
   
   
       9 . The turbine nozzle segment of  claim 2  further comprising:
 a rail extending from said first band and spaced from said plurality of tabs defining a recess therebetween; and   a leaf seal disposed in said recess.   
   
   
       10 . The turbine nozzle segment of  claim 9  further comprising:
 a pin extending through each of said tabs and said leaf seal; and   a biasing structure associated with each of said pins and biasing said leaf seal in abutting contact with an adjoining component.   
   
   
       11 . A turbine nozzle segment, comprising:
 a first band having three or more circumferentially spaced apart tabs; and   a plurality of airfoils extending from said first band.   
   
   
       12 . The turbine nozzle segment of  claim 11 , further comprising:
 a rail extending from said first band and axially spaced from said tabs defining a recess therebetween; and   a leaf seal disposed in said recess.   
   
   
       13 . The turbine nozzle segment of  claim 12  further comprising:
 a pin extending through each of said tabs and said leaf seal; and   a biasing structure associated with each of said pins and biasing said leaf seal in abutting contact with an adjoining component.   
   
   
       14 . The turbine nozzle segment of  claim 11  wherein one of said tabs is adjacent a first circumferential edge of said first band and one of said tabs is adjacent a second circumferential edge of said first band. 
   
   
       15 . The turbine nozzle segment of  claim 14  wherein said tabs are integral with said first band. 
   
   
       16 . The turbine nozzle segment of  claim 15  further comprising:
 a second band;   wherein said plurality of airfoils extend between said first band and said second band.   
   
   
       17 . A turbine nozzle assembly, comprising:
 a plurality of turbine nozzle segments assembled together to form an annular ring, each of said segments comprising:
 an outer band having a three or more circumferentially spaced apart tabs and a rail axially spaced from said tabs defining a recess therebetween; 
 a leaf seal disposed in said recess; 
 a pin extending through each of said tabs and said leaf seal; 
 a biasing structure associated with each of said pins and biasing said leaf seal in abutting contact with an adjoining component; 
 an inner band; and 
 a plurality of airfoils extending between said outer band and said inner band. 
   
   
   
       18 . The turbine nozzle assembly of  claim 17  wherein said inner band further comprises:
 three or more circumferentially spaced apart tabs and a rail axially spaced from said tabs defining a recess therebetween;   a leaf seal disposed in said recess;   a pin extending through each of said tabs and said leaf seal; and   a biasing structure associated with each of said pins and biasing said leaf seal in abutting contact with an adjoining component.   
   
   
       19 . The turbine nozzle assembly of  claim 18  wherein one of said tabs on said outer band is adjacent a first circumferential edge of said outer band and one of said tabs on said outer band is adjacent a second circumferential edge of said outer band. 
   
   
       20 . The turbine nozzle assembly of  claim 19  wherein one of said tabs on said inner band is adjacent a first circumferential edge of said inner band and one of said tabs on said inner band is adjacent a second circumferential edge of said inner band.