Turbine blade tip gap reduction system for a turbine engine

Abstract

A turbine blade gap control system configured to move a vane carrier and attached ring segments of a turbine engine axially relative to a turbine blade assembly to reduce the gaps between the tips of the turbine blades and the ring segments to increase the efficiency of the turbine engine once operating in a steady state condition. The turbine blade assembly may be formed from a plurality rows of turbine blades extending radially from a rotor, wherein each row may be formed from a plurality of turbine blades and wherein the turbine blades may have tips positioned at an acute angle relative to a rotational axis of the turbine blade assembly. A vane carrier may be positioned concentric with the rotor and positioned radially outward from the turbine blades, and a plurality of ring segments may be attached to the vane carrier.

1 . A turbine engine, comprising:
 a turbine blade assembly formed from a plurality rows of turbine blades extending radially from a rotor, wherein each row is formed from a plurality of turbine blades and wherein the turbine blades have tips positioned at an acute angle relative to a rotational axis of the turbine blade assembly;   a vane carrier concentric with the rotor and positioned radially outward from the turbine blades;   a plurality of ring segments attached to the vane carrier and positioned between the vane carrier and the tips of the turbine blades in each row, wherein an inner surface of each of the ring segments is offset radially outward from the tips of the turbine blades creating gaps and wherein the ring segments are positioned at an acute angle substantially equal to the acute angle at which the turbine blade tips are positioned; and   a turbine blade gap control system configured to move the vane carrier and attached ring segments axially relative to the turbine blade assembly to reduce the gaps between the tips of the turbine blades and the ring segments.   
     
     
         2 . The turbine engine of  claim 1 , wherein the turbine blade gap control system comprises at least one hydraulic arm attached to the vane carrier for moving the vane carrier axially relative to the turbine blade assembly. 
     
     
         3 . The turbine engine of  claim 2 , wherein the at least one hydraulic arm is attached to an outer cylinder positioned radially outward from the vane carrier. 
     
     
         4 . The turbine engine of  claim 3 , wherein the at least one hydraulic arm comprises four hydraulic arms positioned around the outer cylinder. 
     
     
         5 . The turbine engine of  claim 4 , wherein the hydraulic arms are positioned generally 90 degrees from each other around the outer cylinder. 
     
     
         6 . A turbine engine, comprising:
 a turbine blade assembly formed from at least one row of turbine blades extending radially from a rotor, wherein the at least one row is formed from a plurality of turbine blades and wherein the turbine blades have tips positioned at an acute angle relative to a rotational axis of the turbine blade assembly;   a vane carrier concentric with the rotor and positioned radially outward from the turbine blades;   a plurality of ring segments attached to the vane carrier and positioned between the vane carrier and the tips of the turbine blades in the at least one row, wherein an inner surface of each of the ring segments is offset radially outward from the tips of the turbine blades creating gaps and wherein the ring segments are positioned at an acute angle substantially equal to the acute angle at which the turbine blade tips are positioned; and   a turbine blade gap control system configured to move the vane carrier and attached ring segments axially relative to the turbine blade assembly to reduce the gaps between the tips of the turbine blades and the ring segment;   wherein the turbine blade gap control system comprises at least one hydraulic arm attached to the vane carrier for moving the vane carrier axially relative to the turbine blade assembly.   
     
     
         7 . The turbine engine of  claim 6 , wherein the at least one hydraulic arm is attached to an outer cylinder positioned radially outward from the vane carrier. 
     
     
         8 . The turbine engine of  claim 7 , wherein the at least one hydraulic arm comprises four hydraulic arms positioned around the outer cylinder. 
     
     
         9 . The turbine engine of  claim 8 , wherein the hydraulic arms are positioned generally 90 degrees from each other around the outer cylinder. 
     
     
         10 . A method of reducing gaps between tips of turbine blades in a turbine engine and adjacent ring segments, comprising:
 operating a turbine engine by bringing the turbine engine to a steady state operating condition, wherein the turbine engine comprises:
 a turbine blade assembly formed from a row of turbine blades extending radially from a rotor, wherein the row is formed from a plurality of turbine blades and wherein the turbine blades have tips positioned at an acute angle relative to a rotational axis of the turbine blade assembly; 
 a vane carrier concentric with the rotor and positioned radially outward from the turbine blades; 
 a plurality of ring segments attached to the vane carrier and positioned between the vane carrier and the tips of the turbine blades in the row, wherein an inner surface of each of the ring segments is offset radially outward from the tips of the turbine blades creating gaps and wherein the ring segments are positioned at an acute angle substantially equal to the acute angle at which the turbine blade tips are positioned; and 
 a turbine blade gap control system configured to move the vane carrier and attached ring segments axially relative to the turbine blade assembly to reduce the gaps between the tips of the turbine blades and the ring segment; and 
   reducing the gaps between the tips of the turbine blades and the ring segment by using the turbine blade gap control system to move the vane carrier axially relative to the turbine blade assembly.   
     
     
         11 . The method of  claim 10 , wherein operating the turbine engine comprises operating a turbine engine wherein the turbine blade gap control system comprises at least one hydraulic arm attached to the vane carrier for moving the vane carrier axially relative to the turbine blade assembly. 
     
     
         12 . The method of  claim 11 , wherein operating the turbine engine comprises operating a turbine engine wherein the at least one hydraulic arm is attached to an outer cylinder positioned radially outward from the vane carrier. 
     
     
         13 . The method of  claim 12 , wherein operating the turbine engine comprises operating a turbine engine wherein the at least one hydraulic arm comprises four hydraulic arms positioned around the outer cylinder. 
     
     
         14 . The method of  claim 13 , wherein operating the turbine engine comprises operating a turbine engine wherein the hydraulic arms are positioned generally 90 degrees from each other around the outer cylinder.