Diffuser for gas turbine system

Abstract

A diffuser for a gas turbine system having a longitudinal axis is disclosed. The diffuser includes a plurality of diffuser ducts. Each of the plurality of diffuser ducts is disposed annularly about the longitudinal axis and has an inlet, an outlet, and a passage extending between the inlet and the outlet. The outlet of each of the plurality of diffuser ducts is tangentially offset from the inlet of the respective diffuser duct. Each of the plurality of diffuser ducts is configured to flow a gas flow therethrough, reducing the gas flow velocity.

1 . A diffuser for a gas turbine system having a longitudinal axis, the diffuser comprising:
 a plurality of diffuser ducts, each of the plurality of diffuser ducts disposed annularly about the longitudinal axis and having an inlet, an outlet, and a passage extending between the inlet and the outlet,   wherein the outlet of each of the plurality of diffuser ducts is tangentially offset from the inlet of the respective diffuser duct,   and wherein each of the plurality of diffuser ducts is configured to flow a gas flow therethrough, reducing the gas flow velocity.   
     
     
         2 . The diffuser of  claim 1 , wherein the outlet of each of the plurality of diffuser ducts is longitudinally offset from the inlet of the respective diffuser duct. 
     
     
         3 . The diffuser of  claim 1 , wherein the outlet of each of the plurality of diffuser ducts is radially offset from the inlet of the respective diffuser duct. 
     
     
         4 . The diffuser of  claim 1 , wherein gas flow exits the diffuser flowing in a generally tangential direction. 
     
     
         5 . The diffuser of  claim 1 , wherein gas flow exits the diffuser flowing in a generally longitudinal direction. 
     
     
         6 . The diffuser of  claim 1 , wherein each of the passages includes a guide portion disposed adjacent the inlet of the respective diffuser duct, the guide portions configured to guide the gas flow from a generally longitudinal flow direction to a generally tangential flow direction. 
     
     
         7 . The diffuser of  claim 6 , wherein the guide portions are further configured to guide the gas flow to a generally radial flow direction. 
     
     
         8 . The diffuser of  claim 6 , wherein each of the passages extends in a generally linear manner downstream of the guide portion with respect to the gas flow. 
     
     
         9 . The diffuser of  claim 6 , wherein each of the passages extends in a generally curvilinear manner downstream of the guide portion with respect to the gas flow. 
     
     
         10 . The diffuser of  claim 1 , wherein each of the passages includes a guide portion disposed adjacent the outlet of the respective diffuser duct, the guide portions configured to guide the gas flow from a generally tangential flow direction to a generally longitudinal flow direction. 
     
     
         11 . The diffuser of  claim 10 , wherein the guide portions are further configured to guide the gas flow from a generally radial flow direction. 
     
     
         12 . The diffuser of  claim 10 , wherein each of the passages extends in a generally linear manner upstream of the guide portion with respect to the gas flow. 
     
     
         13 . The diffuser of  claim 10 , wherein each of the passages extends in a generally curvilinear manner upstream of the guide portion with respect to the gas flow. 
     
     
         14 . The diffuser of  claim 1 , wherein each of the passages is generally conically shaped. 
     
     
         15 . A gas turbine system having a longitudinal axis, the gas turbine system comprising:
 a compressor section for compressing a gas flow;   a diffuser configured to reduce the velocity of the gas flow, the diffuser comprising a plurality of diffuser ducts, each of the plurality of diffuser ducts disposed annularly about the longitudinal axis and having an inlet, an outlet, and a passage extending between the inlet and the outlet, wherein the outlet of each of the plurality of diffuser ducts is tangentially offset from the inlet of the respective diffuser duct, and wherein each of the plurality of diffuser ducts is configured to flow the gas flow therethrough; and   a combustor section configured to accept the gas flow from the diffuser.   
     
     
         16 . The gas turbine system of  claim 15 , wherein the compressor section is free from guide vanes. 
     
     
         17 . The gas turbine system of  claim 15 , the combustor section comprising a plurality of combustor cans, each of the combustor cans configured to accept the gas flow from one of the plurality of diffuser ducts. 
     
     
         18 . The gas turbine system of  claim 15 , wherein the outlet of each of the plurality of diffuser ducts is longitudinally offset from the inlet of the respective diffuser duct. 
     
     
         19 . The gas turbine system of  claim 15 , wherein the outlet of each of the plurality of diffuser ducts is radially offset from the inlet of the respective diffuser duct. 
     
     
         20 . The gas turbine system of  claim 15 , wherein each of the passages is generally conically shaped.