Turbine rotor seal plate with integral flow discourager

Abstract

A seal plate for a turbine engine is provided. The turbine engine has a central axis. The seal plate comprises a forward face extending radially from the central axis. The forward face comprises a flat portion extending circumferentially around the central axis, and a front flow discourager coupled to the flat portion and extending outward from the flat portion.

1 . A seal plate for a turbine engine having a central axis, the seal plate comprising:
 a forward face extending radially from the central axis, the forward face comprising:
 a flat portion extending circumferentially around the central axis; and 
 a front flow discourager coupled to the flat portion and extending outward from the flat portion. 
   
     
     
         2 . The seal plate of  claim 1 , wherein the front flow discourager comprises a metal. 
     
     
         3 . The seal plate of  claim 2 , wherein the front flow discourager is attached using a diffusion bonding technique. 
     
     
         4 . The seal plate of  claim 2 , wherein the front flow discourager comprises a nickel-based superalloy. 
     
     
         5 . The seal plate of  claim 2 , wherein the front flow discourager comprises a cobalt-based superalloy. 
     
     
         6 . The seal plate of  claim 1 , wherein the front flow discourager comprises a thermal barrier coating. 
     
     
         7 . The seal plate of  claim 6 , wherein the thermal barrier coating comprises yttria-stabilized zirconia. 
     
     
         8 . The seal plate of  claim 1 , wherein the flat portion and the front flow discourager comprise different materials. 
     
     
         9 . A seal plate assembly for a turbine engine having a central axis, the seal plate assembly comprising:
 a forward face extending radially outward relative to the central axis, the forward face comprising:
 a first flat portion extending circumferentially around the central axis; and 
 a front flow discourager coupled to the first flat portion and extending away from the first flat portion; and 
   a rear face extending radially outward relative to the central axis, the rear face comprising:
 a second flat portion extending circumferentially around the central axis; and 
 a rear flow discourager coupled to the second flat portion and extending away from the second flat portion. 
   
     
     
         10 . The seal plate assembly of  claim 9 , wherein the first flat portion and the front flow discourager are comprised of different materials. 
     
     
         11 . The seal plate assembly of  claim 9 , wherein the front flow discourager comprises a curved surface. 
     
     
         12 . The seal plate assembly of  claim 11 , wherein the curved surface is curved away from the central axis as the front flow discourager approaches the first flat portion. 
     
     
         13 . The seal plate assembly of  claim 9 , wherein the front flow discourager comprises a rear discourager face extending radially outward, and the front flow discourager contacts a turbine blade platform along the rear discourager face. 
     
     
         14 . A turbine engine assembly having a central axis comprising:
 a turbine blade platform having a front terminating in a radially inward direction; and   a front seal plate having an integral forward flow discourager.   
     
     
         15 . The turbine engine assembly of  claim 14 , wherein the integral forward flow discourager extends away from the front of the turbine blade platform. 
     
     
         16 . The turbine engine assembly of  claim 14 , wherein the integral forward flow discourager comprises a superalloy containing at least one of:
 cobalt and nickel.   
     
     
         17 . The turbine engine assembly of  claim 14 , wherein the integral forward flow discourager comprises a thermal barrier coating. 
     
     
         18 . The turbine engine assembly of  claim 14 , further comprising a rear seal plate, the rear seal plate having an integral rear flow discourager. 
     
     
         19 . The turbine engine assembly of  claim 18 , wherein the turbine blade platform further has a rear terminating in a radially inward direction, and the integral rear flow discourager extends away from the rear of the turbine blade platform.