Turbomachine including flow improvement system

Abstract

A turbomachine includes a housing including a fluid path, and a first stage arranged within the housing. The first stage includes a first plurality of airfoil members and a second plurality of airfoil members. A second stage is arranged within the housing relative to the first stage. The second stage includes a third plurality of airfoil members and a fourth plurality of airfoil members. A flow improvement system is associated with each of the first and second stages. The flow improvement system establishes a predetermined clocking of each of the first plurality of airfoil members relative to corresponding ones of each of the third plurality of airfoil members, and each of the second plurality of airfoil members relative to each of the fourth plurality of airfoil members. The predetermined clocking is configured and disposed to improve flow characteristics along the flow path.

1 . A turbomachine comprising:
 a housing including a fluid path;   a first stage arranged within the housing, the first stage including a first plurality of airfoil members and a second plurality of airfoil members positioned along the fluid path;   a second stage arranged within the housing relative to the first stage, the second stage including a third plurality of airfoil members and a fourth plurality of airfoil members positioned along the fluid path; and   a flow improvement system associated with each of the first and second stages, the flow improvement system establishing a predetermined clocking of each of the first plurality of airfoil members relative to corresponding ones of each of the third plurality of airfoil members, and each of the second plurality of airfoil members relative to each of the fourth plurality of airfoil members, the predetermined clocking being configured and disposed to improve flow characteristics along the flow path.   
     
     
         2 . The turbomachine according to  claim 1 , wherein each of the first plurality of airfoil members is circumferentially off-set relative to corresponding ones of each of the third plurality of airfoil members by a first margin. 
     
     
         3 . The turbomachine according to  claim 2 , wherein each of the second plurality of airfoil members are circumferentially off-set relative to each of the fourth plurality of airfoil members by a second margin. 
     
     
         4 . The turbomachine according to  claim 3 , wherein the first margin is substantially identical to the second margin. 
     
     
         5 . The turbomachine according to  claim 1 , wherein the turbomachine constitutes a turbine portion. 
     
     
         6 . A turbomachine comprising:
 a housing including a fluid path;   a first stage arranged within the housing, the first stage including a first plurality of airfoil members positioned along the fluid path;   a second stage arranged within the housing relative to the first stage, the second stage including a second plurality of airfoil members positioned along the fluid path; and   a flow improvement system associated with each of the first and second stages, the flow improvement system establishing a predetermined clocking of each of the first plurality of airfoil members relative to corresponding ones of each of the second plurality of airfoil members, the predetermined clocking being configured and disposed to set up a spinning wave from the second stage that is configured and disposed to interfere with another spinning wave from the first stage.   
     
     
         7 . The turbomachine according to  claim 6 , wherein the first plurality of airfoil members constitute a first plurality of rotating airfoil members and the second plurality of airfoil members constitute a second plurality of rotating airfoil members. 
     
     
         8 . The turbomachine according to  claim 6 , wherein the first plurality of airfoil members constitutes a first plurality of rotating airfoil members and a first plurality of stationary airfoil members, and the second plurality of airfoil members constitute a second plurality of rotating airfoil members and a second plurality of stationary airfoil members. 
     
     
         9 . The turbomachine according to  claim 8 , wherein the spinning wave reduction system establishes the predetermined clocking of the second plurality of rotating airfoil members relative to the first plurality of rotating airfoil members. 
     
     
         10 . The turbomachine according to  claim 8 , wherein the second plurality of stationary airfoil members are spaced one from another to form a plurality of second stage stationary airfoil passages. 
     
     
         11 . The turbomachine according to  claim 10 , wherein the spinning wave reduction system establishes the predetermined clocking so as to cause the first spinning wave passing from the first plurality of rotating airfoil members to pass through the plurality of second stage stationary airfoil passages and interfere with the second spinning wave passing from the second plurality of rotating airfoil members. 
     
     
         12 . The turbomachine according to  claim 6 , wherein the turbomachine constitutes a compressor portion. 
     
     
         13 . A method of improving flow in a turbomachine, the method comprising:
 guiding a fluid flow across a first turbomachine stage including a first plurality of airfoil members and a second plurality of airfoil members; and   guiding the fluid flow across a second turbomachine stage having a third plurality of airfoil members circumferentially off-set relative to the first plurality of airfoil members and a fourth plurality of airfoil members circumferentially off-set relative to the second plurality of airfoil members to improve flow characteristics along the flow path.   
     
     
         14 . The method according to  claim 13 , wherein guiding the fluid flow across the first plurality of airfoil members includes passing the fluid flow across a plurality of stationary airfoil members. 
     
     
         15 . The method of  claim 14 , wherein guiding the fluid flow over the second plurality of airfoil members includes passing the first fluid across a plurality of rotating airfoil members arranged downstream of the plurality of stationary airfoil members. 
     
     
         16 . The method of  claim 13 , wherein passing the fluid flow over the first plurality of airfoil members includes passing the fluid flow over a first turbomachine stage having a first predetermined number of stationary airfoil members and passing the fluid flow over the third plurality of airfoil members includes passing the fluid flow over a second turbomachine stage having a second predetermined number of stationary airfoil members that is identical to the first predetermined number. 
     
     
         17 . The method of  claim 13 , wherein passing the fluid flow over the first plurality of airfoil members includes passing the fluid flow over a first turbomachine stage having a first predetermined number of stationary airfoil members and passing the fluid flow over the third plurality of airfoil members includes passing the fluid flow over a second turbomachine stage having a second predetermined number of stationary airfoil members that is distinct from the first predetermined number. 
     
     
         18 . The method of  claim 13 , wherein passing the fluid flow over the second plurality of airfoil members includes passing the fluid flow over a first turbomachine stage having a first predetermined number of rotating airfoil members and passing the fluid flow over the fourth plurality of airfoil members includes passing the fluid flow over a second turbomachine stage having a second predetermined number of rotating airfoil members that is identical to the first predetermined number. 
     
     
         19 . The method of  claim 13 , wherein passing the fluid flow over the second plurality of airfoil members includes passing the fluid flow over a first turbomachine stage having a first predetermined number of rotating airfoil members and passing the fluid flow over the fourth plurality of airfoil members includes passing the fluid flow over a second turbomachine stage having a second predetermined number of rotating airfoil members that is distinct from the first predetermined number. 
     
     
         20 . A turbomachine comprising:
 a housing including a fluid path;   a first stage arranged within the housing, the first stage including a first plurality of airfoil members and a second plurality of airfoil members positioned along the fluid path;   a second stage arranged within the housing relative to the first stage, the second stage including a third plurality of airfoil members and a fourth plurality of airfoil members positioned along the fluid path; and   a flow improvement system associated with each of the first and second stages, the flow improvement system establishing a predetermined clocking of each of the first plurality of airfoil members relative to corresponding ones of each of the third plurality of airfoil members, and each of the second plurality of airfoil members relative to each of the fourth plurality of airfoil members, the predetermined clocking being configured and disposed to improve flow characteristics along the fluid path and to set up a spinning wave from the second stage that is configured and disposed to interfere with another spinning wave from the first stage.