Compressor, seal gas delivery, and method

Abstract

A seal gas delivery system for an end seal on a turbo machine rotor shaft includes a seal gas passageway for delivering a seal gas to the end seal and a seal gas distributor for receiving at least a portion of the seal gas from the seal gas passageway, the seal gas distributor having a plurality of holes for distributing the seal gas about the rotor shaft during turbo machine standstill; the holes are located on a cylindrical surface and are typically arranged all around said rotor shaft, preferably regularly all around said rotor shaft.

What is claimed is: 
     
         1 . A seal gas delivery system for an end seal on a turbo machine rotor shaft, the seal gas delivery system comprising:
 a seal gas passageway for delivering a seal gas to the end seal;   a seal gas distributor for receiving at least a portion of the seal gas from the seal gas passageway, the seal gas distributor comprising a plurality of holes for distributing the seal gas about the rotor shaft during turbo machine standstill,   wherein the holes are located on a cylindrical surface.   
     
     
         2 . The seal gas delivery system of  claim 1 , wherein the holes are arranged circularly. 
     
     
         3 . The seal gas delivery system of  claim 1 , wherein the holes are arranged around the rotor shaft. 
     
     
         4 . The seal gas delivery system of  claim 1 , wherein the holes are spaced apart relative to a circumferential surface of the rotor shaft. 
     
     
         5 . The seal gas delivery system of  claim 1 , wherein the holes are spaced apart relative to a longitudinal surface of the rotor shaft. 
     
     
         6 . The seal gas delivery system of  claim 1 , wherein each of the holes defines an axis and the axis is at a non-zero angle relative to a radial line extending from a longitudinal axis of the rotor shaft through a center of the each of the holes. 
     
     
         7 . The seal gas delivery system of  claim 6 , wherein a labyrinth seal is disposed proximately of the end seal, and the seal gas distributor further comprises a ring portion extending from the labyrinth seal. 
     
     
         8 . The seal gas delivery system of  claim 5 , wherein the seal gas distributor further comprises an arc segment or full cylinder. 
     
     
         9 . The seal gas delivery system of  claim 5 , wherein seal gas distributor further comprises a ring. 
     
     
         10 . The seal gas delivery system of  claim 1 , wherein the end seal is a dry gas seal. 
     
     
         11 . A turbo machine, comprising:
 a stator;   a rotor shaft rotatable relative to the stator;   an end seal disposed between the stator and the rotor shaft;   a seal gas passageway for delivering a seal gas to the end seal; and   a seal gas distributor for receiving at least a portion of the seal gas from the seal gas passageway, and distributing the seal gas about the rotor shaft during turbo machine standstill,   wherein the seal gas distributor comprises a plurality of holes, and wherein the holes are located on a cylindrical surface.   
     
     
         12 . The turbo machine of  claim 11 , wherein the holes are arranged circularly. 
     
     
         13 . The turbo machine of  claim 11 , further comprising a container containing the seal gas, wherein the container is fluidly connected to the seal gas distributor. 
     
     
         14 . A method of operating a turbo machine including an end seal on a rotor shaft thereof, the method comprising:
 delivering a seal gas to the end seal during turbo machine standstill; and   distributing the seal gas about the rotor shaft through a plurality of holes arranged around the rotor shaft to prevent uneven heating of the rotor shaft.   
     
     
         15 . The method of operating a turbo machine of  claim 14 , wherein the seal gas flow ejected from at least some of the holes is inclined with respect to a corresponding radial direction defined in relation to a longitudinal axis of the rotor shaft. 
     
     
         16 . The method of operating a turbo machine of  claim 14 , wherein the seal gas flow ejected from all of the holes is inclined with respect to a corresponding radial direction defined in relation to a longitudinal axis of the rotor shaft. 
     
     
         17 . The seal gas delivery system of  claim 1 , wherein the holes are arranged regularly around the rotor shaft. 
     
     
         18 . The seal gas delivery system of  claim 2 , wherein the holes are arranged around the rotor shaft. 
     
     
         19 . The seal gas delivery system of  claim 2 , wherein the holes are spaced apart relative to a circumferential surface of the rotor shaft. 
     
     
         20 . The seal gas delivery system of  claim 2 , wherein each of the holes defines an axis and the axis is at a non-zero angle relative to a radial line extending from a longitudinal axis of the rotor shaft through a center of the each of the holes.