초록 ▼

A method of assembling a turbine engine includes defining a first chamber and defining a second chamber. The method also includes forming at least one venturi device oriented with a predetermined venturi step angle greater than approximately 48°. The method further includes coupling the first chambe

A method of assembling a turbine engine includes defining a first chamber and defining a second chamber. The method also includes forming at least one venturi device oriented with a predetermined venturi step angle greater than approximately 48°. The method further includes coupling the first chamber in flow communication with the second chamber via the venturi device therebetween.

대표청구항 ▼

1. A method of assembling a turbine engine, said method comprising: coupling a first chamber in flow communication with a plurality of fuel nozzles and a plurality of air streams, such that the first chamber premixes fuel from the plurality of fuel nozzles with air from the plurality of air streams,

1. A method of assembling a turbine engine, said method comprising: coupling a first chamber in flow communication with a plurality of fuel nozzles and a plurality of air streams, such that the first chamber premixes fuel from the plurality of fuel nozzles with air from the plurality of air streams, wherein the fuel is at least one of natural gas, fuel oil, process gas, and synthetic gas;defining a second chamber configured to combust the premixed fuel and air into a combustion gas stream having a temperature of at least approximately 1100 degrees Celsius, wherein a centerline extends through the second chamber; andcoupling the first chamber in flow communication with the second chamber using at least one venturi device coupled between the two chambers, wherein the at least one venturi device includes at least one first wall substantially parallel to the centerline, at least one second wall oriented with a predetermined venturi step angle that is greater than approximately 48 degrees as defined by the at least one second wall and a line extending substantially parallel to the centerline, and at least one third wall oriented at an oblique angle with respect to the centerline and coupled at an apex to said at least one second wall, and wherein the predetermined venturi step angle facilitates the formation of recirculation zones within the second chamber such that a nitrogen oxide concentration in the combustion gas stream is maintained below about 3 ppmvd, and such that the at least one venturi device defines a cooling fluid plenum and a plurality of cooling fluid passages coupled in flow communication via a plurality of cooling fluid openings, and wherein the plenum is radially outward from the apex and configured to receive cooling fluid through an aperture defined radially outward from and adjacent to the plenum. 2. A method in accordance with claim 1 further comprising: coupling the first wall to the second wall such that the second wall is oriented with the predetermined venture step angle. 3. A method in accordance with claim 2 wherein coupling the first wall to the second wall comprises sizing the venturi step angle to facilitate flame stability within the second chamber. 4. A method in accordance with claim 2 further comprising: forming a plurality of first walls substantially concentrically about the centerline, wherein the plurality of first walls at least partially define at least one first cooling fluid passage therebetween;forming a plurality of second walls oriented to at least partially define at least one second cooling fluid passage therebetween; andcoupling the at least one second cooling fluid passage in flow communication with the at least one first cooling fluid passage. 5. A method in accordance with claim 4 further comprising: forming a plurality of third walls oriented to at least partially define at least one third cooling fluid passage therebetween; andcoupling the at least one third cooling fluid passage in flow communication with the at least one second cooling fluid passage. 6. A combustor assembly comprising: a first chamber coupled in flow communication with a plurality of fuel nozzles and a plurality of air streams, said first chamber configured to premix fuel from said plurality of fuel nozzles with air from said plurality of air streams, wherein the fuel is at least one of natural gas, fuel oil, process gas, and synthetic gas;a second chamber configured to combust the premixed fuel and air into a combustion gas stream having a temperature of at least approximately 1100 degrees Celsius, said second chamber coupled in flow communication with said first chamber, wherein a centerline extends through said second chamber; andat least one venturi device coupled in flow communication between said first and second chambers, wherein said venturi device comprises at least one first wall substantially parallel to the centerline, at least one second wall oriented with a predetermined venturi step angle that is greater than approximately 48 degrees as defined by said at least one second wall and a line extending substantially parallel to the centerline, and at least one third wall oriented at an oblique angle with respect to the centerline and coupled at an apex to said at least one second wall, said predetermined venturi step angle facilitates the formation of recirculation zones within said second chamber such that a nitrogen oxide concentration in the combustion gas stream is maintained below about 3 ppmvd, wherein said at least one venturi device defines a cooling fluid plenum and a plurality of cooling fluid passages, said cooling fluid plenum and said plurality of cooling fluid passages are coupled in flow communication via a plurality of cooling fluid openings, said plenum is radially outward from the apex and is oriented to receive cooling fluid discharged from an aperture defined radially outward from and adjacent to said plenum. 7. A combustor assembly in accordance with claim 6 wherein said at least one second wall is coupled to said at least one first wall such that said at least one second wall is oriented with a predetermined venture step angle. 8. A combustor assembly in accordance with claim 6 wherein: said at least one first wall comprises a plurality of first walls substantially concentric about the centerline, wherein said plurality of first walls at least partially define at least one first cooling fluid passage of said plurality of cooling fluid passages therebetween; said at least one second wall comprises a plurality of second walls oriented to at least partially define at least one second cooling fluid passage of said plurality of cooling fluid passages therebetween, wherein said at least one second cooling fluid passage is coupled in flow communication with said at least one first cooling fluid passage; and said at least one third wall comprises a plurality of third walls oriented to at least partially define at least one third cooling fluid passage of said plurality of cooling fluid passages therebetween, wherein said at least one third cooling fluid passage is coupled in flow communication with said at least one second cooling fluid passage. 9. A combustor assembly in accordance with claim 6 wherein said venturi step angle is sized to facilitate flame stability within the second chamber. 10. A turbine engine, said engine comprising: at least one air source;at least one fuel source;at least one cooling fluid source; anda combustor assembly comprising;a first chamber coupled in flow communication with a plurality of fuel nozzles coupled to said at least one fuel source and a plurality of air streams coupled to said at least one air source, said first chamber configured to premix fuel from said plurality of fuel nozzles with air from said plurality of air streams, wherein the fuel is at least one of natural gas, fuel oil, process gas, and synthetic gas;a second chamber configured to combust the premixed fuel and air into a combustion gas stream having a temperature of at least approximately 1100 degrees Celsius, said second chamber coupled in flow communication with said first chamber and having a centerline extending therethrough; andat least one venturi device coupled in flow communication between said first and second chambers, wherein said venturi device comprises at least one first wall substantially parallel to the centerline, at least one second wall oriented with a predetermined venturi step angle that is greater than approximately 48 degrees as defined by said at least one second wall and a line extending substantially parallel to the centerline, and at least one third wall oriented at an oblique angle with respect to the centerline and coupled at an apex to said at least one second wall, said predetermined venturi step angle facilitates the formation of recirculation zones within said second chamber such that a nitrogen oxide concentration in the combustion gas stream is maintained below about 3 ppmvd, wherein said at least one venturi device defines a cooling fluid plenum and a plurality of cooling fluid passages, said cooling fluid plenum and said plurality of cooling fluid passages are coupled in flow communication via a plurality of cooling fluid openings, said plenum is radially outward from the apex and is oriented to receive cooling fluid from said at least one cooling fluid source discharged from an aperture defined radially outward from and adjacent to said plenum. 11. A turbine engine in accordance with claim 10 wherein said at least one second wall is coupled to said at least one first wall such that said at least one second wall is oriented with the predetermined venturi step angle. 12. A combustor assembly in accordance with claim 10 wherein: said at least one first wall comprises a plurality of first walls substantially concentric about the centerline, wherein said plurality of first walls at least partially define at least one first cooling fluid passage of said plurality of cooling fluid passages therebetween; said at least one second wall comprises a plurality of second walls oriented to at least partially define at least one second cooling fluid passage of said plurality of cooling fluid passages therebetween, wherein said at least one second cooling fluid passage is coupled in flow communication with said at least one first cooling fluid passage; and said at least one third wall comprises a plurality of third walls oriented to at least partially define at least one third cooling fluid passage of said plurality of cooling fluid passages therebetween, wherein said at least one third cooling fluid passage is coupled in flow communication with said at least one second cooling fluid passage. 13. A turbine engine in accordance with claim 12 wherein said at least one first, second and third cooling fluid passages are configured to channel the at least one cooling fluid comprising one of air, steam, water, and ethylene glycol. 14. A turbine engine in accordance with claim 10 wherein said venturi step angle is sized to facilitate flame stability within the second chamber.