High temperature seal system

Abstract

A hydrodynamic sealing system for use in an oxidizing environment includes a rotor and a sealing stator. The stator includes a solid lubricant or a surface treatment and the rotor is hardened or the stator is hardened and the rotor includes the solid lubricant or the surface treatment. The stator is located proximate to the rotor to provide a seal. The stator and the rotor are robust at extreme temperatures above 700 degrees Fahrenheit (F) such that at least one of the stator and the rotor have a wear rate and a surface roughness sufficient to maintain an operating gap between the stator and rotor.

1 . A sealing system for use in an oxidizing environment, said system comprising:
 a rotor and a sealing stator;   one of said stator comprising a solid lubricant or a surface treatment with said rotor being hardened and said rotor comprising said solid lubricant or said surface treatment with said stator being hardened; and   said stator located proximate said rotor to provide a seal, said rotor and said stator being robust at temperatures above 700 degrees Fahrenheit such that at least one of said stator and said rotor have a wear rate and a surface roughness sufficient to maintain an operating gap between said stator and said rotor.   
     
     
         2 . The sealing system wherein the operating gap is about 0.0002 inches. 
     
     
         3 . The system of  claim 1  wherein said rotor consists of CrC—NiCr Coated Inconel 718. 
     
     
         4 . The system of  claim 1  wherein said stator comprises Boronized Inconel 718. 
     
     
         5 . The system of  claim 1  wherein said stator comprises hot pressed Hexagonal boron nitride. 
     
     
         6 . The system of  claim 1  wherein said stator comprises NASA PS304 Coated Inconel 718. 
     
     
         7 . The system of  claim 1  wherein said rotor and said stator comprise a high temperature hydrodynamic lift seal. 
     
     
         8 . The system of  claim 1  wherein said rotor and said stator comprise a sump seal for an aircraft engine. 
     
     
         9 . The system of  claim 1  wherein a roughness of said stator is less than 12 micro inches Ra when subjected to a load of about 3.5 psi for about an hour at a temperature of up to about 1200 degrees Fahrenheit. 
     
     
         10 . The system of  claim 1  wherein said stator comprises a surface roughness of less than about 2.0 micro inches Ra. 
     
     
         11 . The system of  claim 1  wherein said stator is robust at temperatures up to about 1200 degrees Fahrenheit. 
     
     
         12 . The system of  claim 1  wherein said stator is robust at temperatures up to about 1000 degrees Fahrenheit. 
     
     
         13 . The system of  claim 1  wherein said stator is robust at temperatures exceeds 1200 degrees Fahrenheit. 
     
     
         14 . The system of  claim 1  wherein said rotor comprises a hard coating having a hardness of at least HRC 70. 
     
     
         15 . A sealing system for use in an oxidizing environment, said system comprising:
 a sliding portion a sealing portion;   one of said sealing portion comprising a solid lubricant or a surface treatment with said sliding portion being hardened, and said sliding portion comprising said solid lubricant or said surface treatment with said sealing portion being hardened; and   said sealing portion located proximate said sliding portion to provide a seal, said sealing portion and said sliding portion being robust at temperatures above 700 degrees Fahrenheit such that at least one of said sealing portion and said sliding portion have a wear rate and surface roughness sufficient to maintain an operating gap between said sealing portion and said sliding portion.   
     
     
         16 . The sealing system wherein said operating gap is about 0.0002 inches. 
     
     
         17 . The system of  claim 15  wherein said sliding portion consists of CrC—NiCr Coated Inconel 718. 
     
     
         18 . The system of  claim 15  wherein said sealing portion comprises Boronized Inconel 718. 
     
     
         19 . The system of  claim 15  wherein said sealing portion comprises hot pressed Hexagonal boron nitride. 
     
     
         20 . The system of  claim 15  wherein said sealing portion comprises NASA PS304 Coated Inconel 718. 
     
     
         21 . The system of  claim 15  wherein said sliding portion and said sealing portion comprise a high temperature hydrodynamic lift seal. 
     
     
         22 . The system of  claim 15  wherein said sliding portion and said sealing portion comprise a sump seal for an aircraft engine. 
     
     
         23 . The system of  claim 15  wherein a roughness of said sealing portion is less than 12 micro inches Ra when subjected to a load of about 3.5 psi for about an hour at a temperature of up to about 1200 degrees Fahrenheit. 
     
     
         24 . The system of  claim 15  wherein said sealing portion comprises a surface roughness of less than about 2.0 micro inches Ra. 
     
     
         25 . The system of  claim 15  wherein said sealing portion is robust at temperatures up to about 1200 degrees Fahrenheit. 
     
     
         26 . The system of  claim 15  wherein said sealing portion is robust at temperatures up to about 1000 degrees Fahrenheit. 
     
     
         27 . The system of  claim 15  wherein said sealing portion is robust at temperatures exceeds 1200 degrees Fahrenheit. 
     
     
         28 . The system of  claim 15  wherein said sliding portion comprises a hard coating having a hardness of at least HRC 70. 
     
     
         29 . The system of  claim 15  wherein said sliding portion and sealing portion remain in contact with one another throughout operation.