Fuel nozzle assembly and methods of assembling same

Abstract

A fuel nozzle assembly for use with a turbine engine is provided. The fuel nozzle assembly includes a tube that is configured to channel at least a first type of fuel through the turbine engine. A flow member includes a first end portion and a second end portion that is removably coupled to the tube such that the flow member is severally removable from the tube to enable a plurality of different types of fuel to be channeled through the turbine engine for operation of the turbine engine.

What is claimed is: 
     
         1 . A fuel nozzle assembly for use with a turbine engine, said fuel nozzle assembly comprising:
 a tube configured to channel at least a first type of fuel through the turbine engine; and   a flow member comprising a first end portion and a second end portion that is removably coupled to said tube such that said flow member is severally removable from said tube to enable a plurality of different types of fuel to be channeled through the turbine engine for operation of the turbine engine.   
     
     
         2 . A fuel nozzle assembly in accordance with  claim 1 , wherein said flow member comprises an exterior tube and an interior tube that is integrally formed within said exterior tube. 
     
     
         3 . A fuel nozzle assembly in accordance with  claim 2 , wherein said interior tube comprises an interior tube first end portion, an interior tube second end portion, and a plurality of openings extending from said interior tube first end portion to said interior tube second end portion. 
     
     
         4 . A fuel nozzle assembly in accordance with  claim 2 , wherein said interior tube comprises a channel defined therein and is configured to channel fluid therethrough. 
     
     
         5 . A fuel nozzle assembly in accordance with  claim 4 , wherein said tube comprises a channel defined therein, said interior tube channel is concentrically aligned with said tube channel when said flow member is coupled to said tube. 
     
     
         6 . A fuel nozzle assembly in accordance with  claim 1 , wherein said flow member second end portion comprises a plurality of grooves. 
     
     
         7 . A fuel nozzle assembly in accordance with  claim 6 , wherein said tube comprises a tube end portion that is configured to receive said plurality of grooves therein. 
     
     
         8 . A turbine engine comprising:
 a compressor;   a combustion assembly coupled to said compressor, wherein said combustion assembly comprises at least one combustor;   at least one fuel nozzle assembly coupled within said at least one combustor, said at least one fuel nozzle assembly comprises:
 a tube that is configured to channel at least a first type of fuel through said turbine engine; and 
 a flow member comprising a first end portion and a second end portion that is removably coupled to said tube such that said flow member is severally removable from said tube to enable a plurality of different types of fuel to be channeled through said turbine engine for operation of said turbine engine. 
   
     
     
         9 . A turbine engine in accordance with  claim 8 , wherein said flow member comprises an exterior tube and an interior tube that is integrally formed within said exterior tube. 
     
     
         10 . A turbine engine in accordance with  claim 9 , wherein said interior tube comprises an interior tube first end portion, an interior tube second end portion, and a plurality of openings extending from said interior tube first end portion to said interior tube second end portion. 
     
     
         11 . A turbine engine in accordance with  claim 10 , wherein said interior tube comprises a channel defined therein and is configured to channel fluid therethrough. 
     
     
         12 . A turbine engine in accordance with  claim 11 , wherein said tube comprises a channel defined therein, said interior tube channel is concentrically aligned with said tube channel when said flow member is coupled to said tube. 
     
     
         13 . A turbine engine in accordance with  claim 8 , wherein said flow member second end portion comprises a plurality of grooves. 
     
     
         14 . A turbine engine in accordance with  claim 13 , wherein said tube comprises a tube end portion that is configured to receive said plurality of grooves therein. 
     
     
         15 . A method of assembling a fuel nozzle assembly for use with a turbine engine, said method comprising:
 providing a tube that is configured to channel at least a first type of fuel through the turbine engine;   coupling a flow member to the tube to enable the first type of fuel to be channeled through the turbine engine; and   removing the flow member from the tube to enable a plurality of different types of fuel to be channeled through the turbine engine for operation of the turbine engine.   
     
     
         16 . A method in accordance with  claim 15 , wherein coupling a flow member further comprises coupling a flow member that includes an exterior tube and an interior tube integrally formed within the exterior tube. 
     
     
         17 . A method in accordance with  claim 15 , wherein coupling a flow member further comprises coupling a flow member that includes an exterior tube and an interior tube that includes an interior tube first end portion, an interior tube second end portion, and a plurality of openings extending from the interior tube first end portion to the interior tube second end portion. 
     
     
         18 . A method in accordance with  claim 15 , wherein coupling a flow member further comprises coupling a flow member that includes an exterior tube and an interior tube that includes a channel defined therein and is configured to channel fluid therethrough. 
     
     
         19 . A method in accordance with  claim 15 , wherein coupling a flow member further comprises coupling a flow member that includes a first end portion and a second end portion that includes a plurality of grooves. 
     
     
         20 . A method in accordance with  claim 19 , wherein coupling a flow member further comprises coupling the flow member second end portion to a tube end portion that is configured to receive the plurality of grooves therein.