Overlap seal for turbine nozzle assembly

Abstract

Systems for thermally regulating portions of a turbine are disclosed. In one embodiment, a turbine nozzle assembly includes: an outer diaphragm ring; a vane physically connected to the outer diaphragm ring; and an inner diaphragm ring physically connected to the vane, the inner diaphragm ring including a first axial tooth configured to interact and substantially form a seal with a second axial tooth disposed on a bucket shank.

1 . A turbine nozzle assembly comprising:
 an outer diaphragm ring;   a vane physically connected to the outer diaphragm ring; and   an inner diaphragm ring physically connected to the vane, the inner diaphragm ring including a first axial tooth configured to interact and substantially form a seal with a second axial tooth disposed on a bucket shank.   
     
     
         2 . The turbine nozzle assembly of  claim 1 , wherein the inner diaphragm ring includes a first plurality of axial teeth configured to interact and substantially form a seal with a second plurality of axial teeth disposed on the bucket shank. 
     
     
         3 . The turbine nozzle assembly of  claim 1 , wherein the first axial tooth includes a radially extending tip portion, the radially extending tip portion being configured to extend toward the second axial tooth. 
     
     
         4 . The turbine nozzle assembly of  claim 1 , wherein the second axial tooth includes a radially extending tip portion, the radially extending tip portion being configured to extend toward the first axial tooth. 
     
     
         5 . The turbine nozzle assembly of  claim 4 , wherein the first axial tooth includes a radially extending tip portion, the radially extending tip portion being configured to extend toward the second axial tooth. 
     
     
         6 . The turbine nozzle assembly of  claim 1 , wherein the first axial tooth and the second axial tooth are configured to substantially fluidly separate two portions of a turbine, enabling a pressure differential to be maintained there between. 
     
     
         7 . A turbine bucket comprising:
 a blade; and   a bucket shank coupled to the blade, wherein the bucket shank includes a first axial tooth configured to extend toward a nozzle, substantially forming a seal with the nozzle.   
     
     
         8 . The turbine bucket of  claim 7 , wherein the bucket shank includes a first plurality of axial teeth configured to interact and substantially form a seal with a second plurality of axial teeth disposed on the nozzle. 
     
     
         9 . The turbine bucket of  claim 7 , wherein the first axial tooth includes a radially extending tip portion, the radially extending tip portion being configured to extend toward a second axial tooth disposed on the nozzle. 
     
     
         10 . The turbine bucket of  claim 9 , wherein the second axial tooth includes a radially extending tip portion, the radially extending tip portion being configured to extend toward the first axial tooth. 
     
     
         11 . The turbine bucket of  claim 10 , wherein the first axial tooth and the second axial tooth are configured to substantially fluidly separate two portions of a turbine, enabling a pressure differential to be maintained there between. 
     
     
         12 . A turbine, comprising:
 a stator;   a working fluid passage substantially surrounded by the stator;   a drum rotor configured radially inboard of the working fluid passage;   a cooling circuit fluidly connected to the drum rotor; and   an overlap seal disposed between a nozzle coupled to the stator and a turbine bucket coupled to the drum rotor, the overlap seal substantially fluidly separating the working fluid passage and the cooling circuit, the overlap seal comprising:
 a first axial tooth disposed upon the nozzle; and 
 a second axial tooth disposed upon the turbine bucket, the second axial tooth being configured to interact and substantially form a seal with the first axial tooth. 
   
     
     
         13 . The turbine of  claim 12 , further comprising a packing head including a coolant delivery passage fluidly connected to the cooling circuit and a snout disposed within the packing head, wherein the coolant delivery passage is configured to obtain a fluid from the snout and channel the fluid to the cooling circuit. 
     
     
         14 . The turbine of  claim 12 , wherein the cooling circuit includes a pressurized fluid, the pressurized fluid creating a positive pressure differential in the cooling circuit with respect to the working fluid passage. 
     
     
         15 . The turbine of  claim 12 , wherein the turbine bucket includes an axial passage fluidly connected to the cooling circuit. 
     
     
         16 . The turbine of  claim 12 , wherein the turbine bucket includes a first plurality of axial teeth configured to interact and substantially form a seal with a second plurality of axial teeth disposed on the nozzle. 
     
     
         17 . The turbine of  claim 12 , wherein the first axial tooth includes a radially extending tip portion, the radially extending tip portion being configured to extend toward the second axial tooth. 
     
     
         18 . The turbine of  claim 12 , wherein the second axial tooth includes a radially extending tip portion, the radially extending tip portion being configured to extend toward the first axial tooth. 
     
     
         19 . The turbine of  claim 18 , wherein the first axial tooth includes a radially extending tip portion, the radially extending tip portion being configured to extend toward the second axial tooth. 
     
     
         20 . The turbine of  claim 12 , further comprising a plurality of overlap seals disposed between a plurality of nozzles and a plurality of turbine buckets.