Circumferential sealing assembly with duct-fed hydrodynamic grooves

A circumferential sealing assembly for use within a housing of a turbine engine for separating a lower-pressure side with a lubricant therein and a higher-pressure side with a hot gas therein comprising:

• (a) a rotatable runner;
• and
• (b) a sealing ring disposed about said rotatable runner;
• wherein,
• said rotatable runner comprises an outer sealing surface interposed between a higher-pressure end and a lower-pressure end;
• said sealing ring comprises an inner sealing surface interposed between a higher-pressure face and a lower-pressure face;
• a plurality of grooves disposed along said inner sealing surface and arranged to form a plurality of groups wherein each said group includes at least two said grooves;
• either a single duct provided for each one of said groups wherein said duct passes through said rotatable runner from an inlet at said higher-pressure end to at least two outlets at said outer sealing surface or a plurality of ducts provided for each one of said groups wherein each said duct passes through said rotatable runner from an inlet at said higher-pressure end to an outlet at said outer sealing surface;
• said duct(s) of each one of said groups rotates with said rotatable runner;
• said duct(s) of each one of said groups in use receives said hot gas at said higher-pressure end via said inlet and directs said hot gas toward said inner sealing surface via said outlets;
• said hot gas sweepingly impinges said grooves of said groups as said outlets rotate with said rotatable runner thereby causing a hydrodynamic flow by said hot gas within said grooves;
• said grooves of each said group redirect said hot gas in direction of said outer sealing surface to form a thin film between said outer sealing surface and said inner sealing surface;
• said thin film resists migration of said lubricant from said lower-pressure side to said higher-pressure side;
• said grooves and said duct(s) of said groups avoid backflow of said hot gas to prevent migration of said lubricant to said higher-pressure side.

A circumferential sealing assembly for use within a housing of a turbine engine for separating a lower-pressure side with a lubricant therein and a higher-pressure side with a hot gas therein comprising:

• (a) a sleeve contacting and rotatable with a shaft;
• and
• (b) a sealing ring disposed about said sleeve;
• wherein,
• said sleeve comprises an outer sealing surface interposed between a higher-pressure end and a lower-pressure end;
• said sealing ring comprises an inner sealing surface interposed between a higher-pressure face and a lower-pressure face;
• a plurality of grooves disposed along said outer sealing surface and arranged to form a plurality of groups wherein each said group includes at least two said grooves;
• each said group provided with either a single duct which communicates with said grooves or a plurality of said ducts wherein each said duct communicates with a different said groove, said duct(s) passes through said sleeve from an inlet at said higher-pressure end to an outlet at said grooves;
• said grooves and said duct(s) of each said group rotate with said sleeve;
• said duct(s) of each said group in use receives said hot gas at said higher-pressure end via said inlet and directs said hot gas into said grooves at said outlets;
• said hot gas entering said grooves of each said group in use via said duct(s) in combination with rotation of said grooves with said sleeve in use cause said hot gas to form a hydrodynamic flow within said grooves;
• said grooves of each said group redirect said hot gas in direction of said inner sealing surface to form a thin film between said outer sealing surface and said inner sealing surface;
• said thin film resists migration of said lubricant from said lower-pressure side to said higher-pressure side;
• said grooves and said duct(s) of said groups avoid backflow of said hot gas to prevent migration of said lubricant to said higher-pressure side.

A circumferential sealing assembly for use within a housing of a turbine engine for separating a lower-pressure side with a lubricant therein and a higher-pressure side with a hot gas therein comprising:

• (a) a sleeve contacting and rotatable by a shaft;
• and
• (b) a sealing ring disposed about said sleeve;
• wherein,
• said sleeve comprises an outer sealing surface interposed between a higher-pressure end and a lower-pressure end;
• said sealing ring comprises an inner sealing surface interposed between a higher-pressure face and a lower-pressure face;
• a plurality of grooves disposed along said inner sealing surface and arranged to form a plurality of groups wherein each said group includes at least two said grooves;
• either a single duct provided for each one of said groups wherein said duct passes through said sleeve from an inlet at said higher-pressure end to at least two outlets at said outer sealing surface or a plurality of said ducts provided for each one of said groups wherein each said duct passes through said sleeve from an inlet at said higher-pressure end to an outlet at said outer sealing surface;
• said duct(s) of each one of said groups rotates with said sleeve;
• said duct(s) of each one of said groups in use receives said hot gas at said higher-pressure end via said inlet and directs said hot gas toward said inner sealing surface via said outlets;
• said hot gas sweepingly impinges said grooves of each said group as said outlets rotate with said sleeve thereby causing a hydrodynamic flow by said hot gas within said grooves;
• said grooves of each one of said groups redirect said hot gas in direction of said outer sealing surface to form a thin film between said outer sealing surface and said inner sealing surface;
• said thin film resists migration of said lubricant from said lower-pressure side to said higher-pressure side;
• said grooves and said duct(s) of said groups avoid backflow of said hot gas to prevent migration of said lubricant to said higher-pressure side.