Seal system for cooling fluid flow through a rotor assembly in a gas turbine engine

Abstract

A sealing system for a rotor assembly in a gas turbine engine is disclosed. The sealing system may include a seal formed from a side block and an upper seal that seals a gap between a radially outward extending first rotor supply channel in a rotor assembly terminating at an inlet of an axially extending second rotor supply channel that is in fluid communication with an internal blade cooling system of a turbine blade. The seal may include components that enhance the flow of cooling fluids over conventional configurations. In another embodiment, the sealing system may include an integrated sealing block configured to seal a gap between adjacent turbine blades at an intersection between the first and second rotor supply channels. The integrated sealing block may be formed from a radially inward extending leg and central body.

1 . A sealing system for a turbine blade and rotor assembly for a gas turbine engine, comprising:
 a rotor assembly having at least one row of turbine blades extending radially outward;   at least one internal rotor cooling system in fluid communication with an internal blade cooling system within at least one turbine blade;   wherein the at least one internal rotor cooling system comprises a radially outward extending first rotor supply channel terminating at a radially outward end of the outward extending first rotor supply channel and at an inlet of an axially extending second rotor supply channel that is in fluid communication with the internal blade cooling system;   at least one side block sealing a portion of a gap between adjacent turbine blades at an intersection between the first and second rotor supply channels, wherein the at least one side block extends partially circumferentially around the rotor assembly, is curved circumferentially, is attached to a radially outer end of a wall defining the first rotor supply channel, and has a generally linear inner surface forming a portion of the first rotor supply channel; and   at least one upper seal sealing a remaining portion of the gap between adjacent turbine blades at the intersection between the first and second rotor supply channels, wherein the at least one upper seal contacts the at least one side block and includes a radially inner surface that is generally flat and flush with an inner surface forming the second rotor supply channel.   
     
     
         2 . The sealing system for a turbine blade and rotor assembly for a gas turbine engine of  claim 1 , further comprising at least one tooth on the at least one upper seal extending radially outward from the at least one upper seal and contacting two turbine blades of the at least one row of turbine blades. 
     
     
         3 . The sealing system for a turbine blade and rotor assembly for a gas turbine engine of  claim 2 , further comprising an arm extending axially from the at least one upper seal away from the intersection between the at least one upper seal and the at least one side block, wherein the at least one tooth extends radially outward from the at least one arm. 
     
     
         4 . The sealing system for a turbine blade and rotor assembly for a gas turbine engine of  claim 3 , wherein the at least one tooth extending radially outward from the at least one arm comprises two teeth extending radially outward from the at least one arm. 
     
     
         5 . The sealing system for a turbine blade and rotor assembly for a gas turbine engine of  claim 3 , wherein at least one tooth forms an interference fit in a cavity in each of the two turbine blades to reduce leakage. 
     
     
         6 . The sealing system for a turbine blade and rotor assembly for a gas turbine engine of  claim 1 , wherein the at least one upper seal further includes at least one tooth extending radially inward from a radially inner surface of the at least one upper seal, wherein the at least one tooth has a width that is less than a width of the at least one side block and the tooth contacts that at least one side block. 
     
     
         7 . The sealing system for a turbine blade and rotor assembly for a gas turbine engine of  claim 1 , wherein the at least one side block further includes at least one wire seal extending radially inward from a radially inner surface of the at least one side block, wherein the at least one wire seal has a width that is less than a width of the at least one side block. 
     
     
         8 . The sealing system for a turbine blade and rotor assembly for a gas turbine engine of  claim 1 , wherein the first rotor supply channel has a diameter of about 15 millimeters. 
     
     
         9 . The sealing system for a turbine blade and rotor assembly for a gas turbine engine of  claim 1 , wherein the at least one side block sealing a portion of a gap between adjacent turbine blades at an intersection between the first and second rotor supply channels extends circumferentially to seal at least two gaps between multiple sets of turbine blades in the at least one row of turbine blades. 
     
     
         10 . A sealing system for a turbine blade and rotor assembly for a gas turbine engine, comprising:
 a rotor assembly having at least one row of turbine blades extending radially outward;   at least one internal rotor cooling system in fluid communication with an internal blade cooling system within at least one turbine blade;   wherein the at least one internal rotor cooling system comprises a radially outward extending first rotor supply channel terminating at a radially outward end of the outward extending first rotor supply channel and at an inlet of an axially extending second rotor supply channel that is in fluid communication with the internal blade cooling system;   at least one integrated sealing block sealing a gap between adjacent turbine blades at an intersection between the first and second rotor supply channels, wherein the at least one integrated sealing block includes a radially inward extending leg and central body;   wherein the at least one integrated sealing block extends partially circumferentially around the rotor assembly, is curved circumferentially,   wherein the radially inward extending leg is attached to a radially outer end of a wall defining the first rotor supply channel and has a generally linear, radially extending, inner surface on the leg forming a portion of the first rotor supply channel; and   wherein the central body includes an axially extending inner surface that is generally flat and flush with an inner surface forming the second rotor supply channel.   
     
     
         11 . The sealing system for a turbine blade and rotor assembly for a gas turbine engine of  claim 10 , further comprising at least one tooth extending axially from the central body into a cavity within a turbine blade forming a portion of the at least one row of turbine blades. 
     
     
         12 . The sealing system for a turbine blade and rotor assembly for a gas turbine engine of  claim 11 , wherein a radially inner surface of the at least one tooth is generally flat and flush with an inner surface forming the second rotor supply channel. 
     
     
         13 . The sealing system for a turbine blade and rotor assembly for a gas turbine engine of  claim 12 , wherein the at least one tooth comprises two teeth extending axially from the central body into cavities within the turbine blade forming a portion of the at least one row of turbine blades, wherein each of the teeth contact at least one surface within each cavity to reduce leakage. 
     
     
         14 . The sealing system for a turbine blade and rotor assembly for a gas turbine engine of  claim 13 , further comprising a filleted intersection between the radially inward extending leg and the central body. 
     
     
         15 . The sealing system for a turbine blade and rotor assembly for a gas turbine engine of  claim 10 , further comprising at least one tooth extending radially outward from the central body and contacting two turbine blades of the at least one row of turbine blades. 
     
     
         16 . The sealing system for a turbine blade and rotor assembly for a gas turbine engine of  claim 15 , further comprising an arm extending axially from the central body away from the intersection between the central body and the radially inward extending leg, wherein the at least one tooth extends radially outward from the at least one arm. 
     
     
         17 . The sealing system for a turbine blade and rotor assembly for a gas turbine engine of  claim 16 , wherein the at least one tooth extending radially outward from the at least one arm comprises two teeth extending radially outward from the at least one arm. 
     
     
         18 . The sealing system for a turbine blade and rotor assembly for a gas turbine engine of  claim 17 , wherein at least one tooth forms an interference fit in a cavity in each of the two turbine blades to reduce leakage. 
     
     
         19 . The sealing system for a turbine blade and rotor assembly for a gas turbine engine of  claim 10 , further comprising at least one wire seal extending radially inward from a radially inner surface of the radially inward extending leg, wherein the at least one wire seal has a width that is less than a width of the radially inward extending leg. 
     
     
         20 . The sealing system for a turbine blade and rotor assembly for a gas turbine engine of  claim 10 , wherein the first rotor supply channel has a diameter of about 15 millimeters.