Inter-stage seal for a turbomachine

Abstract

An inter-stage seal for a turbomachine includes a sealing member extending from a first end to a second end through an intermediate portion having a sealing surface, a first mounting member extending from a first end portion coupled to the sealing member adjacent the first end to a second, cantilevered end portion having a first rotor mounting element, and a second mounting member extending from a first end portion coupled to the sealing member adjacent the second end to a second, cantilevered end portion having a second rotor mounting element.

What is claimed is: 
     
         1 . An inter-stage seal for a turbomachine comprising:
 a sealing member extending from a first end to a second end through an intermediate portion having a sealing surface;   a first mounting member extending from a first end portion coupled to the sealing member adjacent the first end to a second, cantilevered end portion having a first rotor mounting element; and   a second mounting member extending from a first end portion coupled to the sealing member adjacent the second end to a second, cantilevered end portion having a second rotor mounting element.   
     
     
         2 . The inter-stage seal according to  claim 1 , further comprising: a plurality of sealing elements extending outwardly from the sealing surface. 
     
     
         3 . The inter-stage seal according to  claim 1 , wherein the first end is cantilevered from the first mounting member. 
     
     
         4 . The inter-stage seal according to  claim 1 , wherein the second end is cantilevered from the second mounting member. 
     
     
         5 . The inter-stage seal according to  claim 1 , wherein each of the first and second rotor mounting elements comprise dovetail members. 
     
     
         6 . A turbomachine comprising:
 a first stage rotor supporting a plurality of first stage turbine blades and a second stage rotor supporting a plurality of second stage turbine blades;   at least one inter-stage seal extending between the first and second stage rotors, the at least one inter-stage seal comprising:
 a sealing member extending from a first end to a second end through an intermediate portion having a sealing surface; 
 a first mounting member extending from a first end portion coupled to the sealing member adjacent the first end to a second, cantilevered end portion having a first rotor mounting element connected to the first stage rotor; and 
 a second mounting member extending from a first end portion coupled to the sealing member adjacent the second end to a second, cantilevered end portion having a second rotor mounting element connected to the second stage rotor. 
   
     
     
         7 . The turbomachine according to  claim 6 , further comprising: a plurality of sealing elements extending outwardly from the sealing surface. 
     
     
         8 . The turbomachine according to  claim 7 , wherein the at least one inter-stage seal is arranged in a turbine portion of the turbomachine, the plurality of sealing elements extending toward a nozzle. 
     
     
         9 . The turbomachine according to  claim 6 , wherein the first end is cantilevered from the first mounting member. 
     
     
         10 . The turbomachine according to  claim 6 , wherein the second end is cantilevered from the second mounting member. 
     
     
         11 . The turbomachine according to  claim 6 , wherein each of the first and second rotor mounting elements comprise dovetail members. 
     
     
         12 . The turbomachine according to  claim 6 , further comprising: at least one axial locking member provided on one of the first and second stage rotors, the at least one axial locking member constraining axial movement of one or more of the first and second stage blades. 
     
     
         13 . A method of sealing between adjacent stages in a turbomachine, the method comprising:
 positioning an inter-stage seal across a rotor;   axially shifting the inter-stage seal across the rotor;   arranging a sealing member of the inter-stage seal across a gap extending between the rotor and an adjacent rotor;   connecting a first mounting member extending from a first end of the sealing member with the rotor; and   connecting a second mounting member extending from a second end of the sealing member to the adjacent rotor.   
     
     
         14 . The method of  claim 13 , wherein connecting the first mounting member to the rotor includes sliding a dovetail member provided on the first mounting member into a dovetail slot formed in the rotor. 
     
     
         15 . The method of  claim 14 , further comprising: installing an axial entry blade member into the dovetail slot formed in the rotor. 
     
     
         16 . The method of  claim 15 , further comprising: installing an axial locking member to the rotor to constrain axial movement of the blade member. 
     
     
         17 . The method of  claim 14 , wherein connecting the second mounting member to the adjacent rotor includes sliding a dovetail member provided on the second mounting member into a dovetail slot formed in the adjacent rotor. 
     
     
         18 . The method of  claim 13 , further comprising: abutting a portion of the sealing member with a blade member provided in the adjacent rotor. 
     
     
         19 . The method of  claim 13 , wherein positioning the inter-stage seal across the rotor includes straddling the rotor with the first and second mounting members extending axially inwardly on opposing sides of the rotor. 
     
     
         20 . The method of  claim 13 , wherein positioning the inter-stage seal across the rotor includes positioning the inter-stage seal in a turbine portion of the turbomachine.