초록 ▼

A method of operating a turbine engine includes providing at least one combustor having a chamber defined therein. The assembly includes at least one combustor wall defining the chamber and a first fluid passage defining a first fluid inlet within the wall. The first fluid passage is coupled in flow

A method of operating a turbine engine includes providing at least one combustor having a chamber defined therein. The assembly includes at least one combustor wall defining the chamber and a first fluid passage defining a first fluid inlet within the wall. The first fluid passage is coupled in flow communication with the chamber and is configured to inject a first fluid stream. The assembly further includes at least one second fluid passage defining at least one second fluid inlet within the wall. The second fluid inlet is adjacent to the first fluid inlet and is coupled in flow communication with the chamber. The method also includes injecting the first fluid stream and injecting the second fluid stream into the chamber at an oblique angle with respect to the first fluid stream, thereby intersecting and mixing the second fluid stream with the first fluid stream.

대표청구항 ▼

What is claimed is: 1. A method of operating a turbine engine, said method comprising: providing at least one combustor assembly having a combustion chamber defined therein, wherein the combustion chamber has a centerline extending therethrough; injecting at least one first fluid stream in flow com

What is claimed is: 1. A method of operating a turbine engine, said method comprising: providing at least one combustor assembly having a combustion chamber defined therein, wherein the combustion chamber has a centerline extending therethrough; injecting at least one first fluid stream in flow communication with a first fluid source into the combustion chamber; injecting at least one second fluid stream in flow communication with a second fluid source into the combustion chamber at an oblique angle with respect to the at least first fluid stream, thereby intersecting and mixing the at least one second fluid stream with the at least one first fluid stream; forming a plurality of local flames within the combustion chamber, wherein the local flames are oriented to combine to form at least one bulk flame within the combustion chamber; wherein the first fluid streams and the second fluid streams are arranged in an alternating annular relationship. 2. A method in accordance with claim 1 wherein injecting at least one second fluid stream into the combustion chamber comprises injecting the at least one second fluid stream at a first velocity and the at least one first fluid stream at a second velocity, wherein the first velocity is greater than the second velocity. 3. A method in accordance with claim 1 wherein injecting at least one second fluid stream comprises injecting the at least one second fluid stream into the chamber to induce a predetermined turbulence that facilitates rapidly mixing the at least one second fluid stream with the at least one first fluid stream, thereby attaining a predetermined combustion residence time prior to combusting at least a portion of the at least one first and second fluid streams. 4. A method in accordance with claim 1 wherein injecting at least one first fluid stream into the combustion chamber comprises at least one of: air; at least one combustion gas; at least one diluent; and at least one fuel. 5. A method in accordance with claim 4 wherein injecting at least one first fluid stream into the combustion chamber further comprises at least one of: purging fuel away from at least one combustor assembly wall to facilitate reducing flashback and flame holding within the combustor assembly; and cooling at least a portion of the at least one combustor assembly wall. 6. A method in accordance with claim 1 wherein injecting at least one second fluid stream into the combustion chamber comprises at least one of: air; at least one combustion gas; at least one diluent; and at least one fuel. 7. A method in accordance with claim 6 wherein injecting at least one second fluid stream into the combustion chamber further comprises at least one of: injecting at least one fuel stream into the combustion chamber via at least one fuel inlet defined within at least one combustor wall, wherein each of the at least one fuel inlets is positioned between a plurality of circumferentially adjacent air inlets; and injecting at least one fuel stream into the combustion chamber via a plurality of fuel inlets defined within the at least one combustor wall, wherein at least some of the plurality of fuel inlets are circumferentially positioned about at least one air inlet. 8. A method in accordance with claim 7 wherein injecting fuel into the combustion chamber via a plurality of fuel inlets comprises configuring the fuel inlets and air inlets to generate a substantially annular swirling flow pattern of a predetermined fuel-air mixture. 9. A method in accordance with claim 8 wherein configuring the fuel inlets and air inlets comprises generating a first circumferential flow pattern from a first ring of fuel inlets and air inlets and a second circumferential flow pattern from a second ring of fuel inlets and air inlets that is adjacent to the first ring, wherein a circumferential direction of the first flow pattern is at least one of: substantially opposite a circumferential direction of the second flow pattern; and substantially the same as the circumferential direction of the second flow pattern. 10. A method in accordance with claim 7 wherein injecting at least one fuel stream into the combustion chamber comprises premixing at least two of fuel, air and a diluent upstream of at least one combustion chamber inlet to facilitate attaining a predetermined fuel-air combustion residence time. 11. A combustor assembly comprising: at least one combustor wall defining a combustion chamber; at least one first fluid passage defining at least one first fluid inlet within said at least one combustor wall, said at least one first fluid passage coupled in flow communication with said combustion chamber and a first fluid source, said at least one first fluid inlet configured to inject a first fluid stream into said combustion chamber; and at least one second passage defining at least one second fluid inlet within said at least one combustor wall, said at least one second fluid inlet is positioned circumferentially adjacent to said at least one first fluid inlet, said at least one second fluid inlet is coupled in flow communication with said combustion chamber and a second fluid source and is configured to inject a second fluid stream into said combustion chamber at an oblique angle with respect to said first fluid stream such that said second and first fluid streams intersect at a predetermined angle of incidence, wherein the first fluid stream and the second fluid stream are differing substances, and wherein the first fluid inlets and the second fluid inlets are arranged in an alternating annular relationship. 12. A combustor assembly in accordance with claim 11 wherein said at least one second fluid inlet comprises a plurality of second fluid inlets circumferentially adjacent to a plurality of first fluid inlets, said plurality of second fluid inlets and said plurality of first fluid inlets configured in at least one substantially circular ring, wherein said plurality of second fluid inlets and said first fluid inlets are configured to cooperate to form at least one substantially circular fluid flow pattern. 13. A combustor assembly in accordance with claim 12 wherein said at least one substantially circular ring comprises a plurality of substantially concentric and annular rings configured to form a first substantially concentric and annular flow pattern having a first substantially circumferential direction and at least one adjacent substantially concentric and annular flow pattern having a second substantially circumferential direction, said first and adjacent substantially concentric and annular flow patterns comprise at least one of: said first substantially circumferential direction is substantially opposed to said second substantially circumferential direction; and said first substantially circumferential direction is substantially similar to said second substantially circumferential direction. 14. A combustor assembly in accordance with claim 11 further comprising at least one swirler assembly wherein said at least one swirler assembly is positioned within said combustor assembly, said at least one swirler assembly configured to mix the first fluid and the second fluid prior to injection into said combustion chamber, said at least one swirler assembly comprising: at least one chamber coupled in flow communication with the second fluid source; at least one swirl vane coupled in flow communication with said at least one chamber and the first fluid source; and the plurality of second fluid inlets configured to facilitate injecting said second fluid stream into said combustion chamber at an oblique angle with respect to said first fluid stream such that said second and first streams intersect at a predetermined angle of incidence. 15. A combustor assembly in accordance with claim 14 wherein said plurality of fluid inlets are configured to be at least one of: a substantially rectangular slot; a substantially elliptical slot; and a substantially circular slot. 16. A combustor assembly in accordance with claim 11 wherein said at least one first fluid stream comprises at least one of: air; at least one combustion gas; at least one diluent; and at least one fuel. 17. A combustor assembly in accordance with claim 11 wherein said at least one second fluid stream comprises at least one of: air; at least one combustion gas; at least one diluent; and at least one fuel. 18. A combustor assembly in accordance with claim 11 further comprising at least one fluid array wherein said at least one fluid array is defined within at least a portion of said at least one combustor wall, said at least one fluid array comprises at least one of: a plurality of second fluid inlets spaced circumferentially about said at least one first fluid inlet; and a plurality of first fluid inlets spaced circumferentially about said at least one second fluid inlet. 19. A combustor assembly in accordance with claim 18 wherein said at least one fluid array comprises a plurality of substantially annular and concentric rings defined within at least a portion of said at least one combustor wall. 20. A combustor assembly in accordance with claim 18 wherein each of said plurality of second fluid inlets is positioned between a pair of circumferentially adjacent first fluid inlets. 21. A combustor assembly in accordance with claim 11 wherein said at least one second fluid inlet is configured to inject second fluid into said combustion chamber with at least one of the following: a radial angle of incidence within a range between approximately 0° to 90° wherein said first fluid stream is injected into said combustion chamber in a plane substantially parallel to a combustion chamber centerline extending through said combustion chamber; and a circumferential angle of incidence within a range between approximately 0° to 90° wherein said first fluid stream is injected into said combustion chamber in a plane substantially parallel to the combustion chamber centerline. 22. A combustor assembly in accordance with claim 11 wherein said at least one second fluid inlet is configured to inject said second fluid stream into said combustion chamber with at least one of the following: a radial angle of incidence within a range between approximately 0° to 90° wherein said first fluid stream injected into said combustion chamber is with an angle oblique to a combustion chamber centerline extending through said combustion chamber; and a circumferential angle of incidence within a range between approximately 0° to 90° wherein said first fluid stream is injected into said combustion chamber with an angle that is oblique to the combustion chamber centerline. 23. A turbine engine, said engine comprising: at least one first fluid source; at least one second fluid source; and a combustor assembly coupled in flow communication with said at least one first fluid source and said at least one second fluid source, said combustor assembly comprising at least one combustor wall, at least one first fluid passage, and at least one second fluid passage, said at least one combustor wall defining a combustion chamber, said at least one first fluid passage defining at least one first fluid inlet within said at least one combustor wall, said at least one first fluid passage coupled in flow communication with said combustion chamber and said first fluid source, said at least one first fluid inlet configured to inject a first fluid stream into said combustion chamber, said at least one second fluid passage defining at least one second fluid inlet within said at least one combustor wall, said at least one second fluid inlet is positioned circumferentially adjacent to said at least one first fluid inlet, said at least one second fluid inlet is coupled in flow communication with said combustion chamber and said second fluid source and is configured to inject a second fluid stream into said combustion chamber at an oblique angle with respect to said first fluid stream such that said second fluid and first fluid streams intersect at a predetermined angle of incidence, wherein the first fluid stream and the second fluid stream are differing substances; and wherein the first fluid inlets and the second fluid inlets are arranged in an alternating annular relationship. 24. A turbine engine in accordance with claim 23 wherein said at least one first fluid source is a compressor. 25. A turbine engine in accordance with claim 23 wherein said at least one second fluid inlet comprises a plurality of second fluid inlets circumferentially adjacent to a plurality of first fluid inlets, said plurality of second fluid inlets and said plurality of first fluid inlets configured in at least one substantially circular ring, wherein said plurality of second fluid inlets and said first fluid inlets are configured to cooperate to form at least one substantially circular fluid flow pattern. 26. A turbine engine in accordance with claim 25 wherein said at least one substantially circular ring comprises a plurality of substantially concentric and annular rings configured to form a first substantially concentric and annular flow pattern having a first substantially circumferential direction and at least one adjacent substantially concentric and annular flow pattern having a second substantially circumferential direction, said first and adjacent substantially concentric and annular flow patterns comprise at least one of: said first substantially circumferential direction is substantially opposed to said second substantially circumferential direction; and said first substantially circumferential direction is substantially similar to said second substantially circumferential direction. 27. A turbine engine in accordance with claim 24 further comprising at least one swirler assembly wherein said at least one swirler assembly is positioned within said combustor assembly, said at least one swirler assembly configured to mix the first fluid and the second fluid prior to injection into said combustion chamber, said at least one swirler assembly comprising: at least one chamber coupled in flow communication with the second fluid source; at least one swirl vane coupled in flow communication with said at least one chamber and the first fluid source; and a plurality of fluid inlets configured to facilitate injecting said second fluid stream into said combustion chamber at an oblique angle with respect to said first fluid stream such that said second and first streams intersect at a predetermined angle of incidence. 28. A turbine engine in accordance with claim 22 wherein said plurality of fluid inlets are configured to be at least one of: a substantially rectangular slot; a substantially elliptical slot; and a substantially circular slot. 29. A turbine engine in accordance with claim 23 wherein said at least one first fluid stream comprises at least one of: air; at least one combustion gas; at least one diluent; and at least one fuel. 30. A turbine engine in accordance with claim 23 wherein said at least one second fluid stream comprises at least one of: air; at least one combustion gas; at least one diluent; and at least one fuel. 31. A turbine engine in accordance with claim 23 further comprising at least one fluid array wherein said at least one fluid array is defined within at least a portion of said at least one combustor wall, said at least one fluid array comprises at least one of: a plurality of second fluid inlets spaced circumferentially about said at least one first fluid inlet; and a plurality of first fluid inlets spaced circumferentially about said at least one second fluid inlet. 32. A turbine engine in accordance with claim 31 wherein said at least one fluid array comprises a plurality of substantially annular and concentric rings defined within at least a portion of said at least one combustor wall. 33. A turbine engine in accordance with claim 31 wherein each of said plurality of second fluid inlets is positioned between a pair of circumferentially adjacent first fluid inlets. 34. A turbine engine in accordance with claim 23 wherein said at least one second fluid inlet is configured to inject second fluid into said combustion chamber with at least one of the following: a radial angle of incidence within a range between approximately 0° to 90° wherein said first fluid stream is injected into said combustion chamber in a plane substantially parallel to a combustion chamber centerline extending through said combustion chamber; and a circumferential angle of incidence within a range between approximately 0° to 90° wherein said first fluid stream is injected into said combustion chamber in a plane substantially parallel to the combustion chamber centerline. 35. A turbine engine in accordance with claim 23 wherein said at least one second fluid inlet is configured to inject said second fluid stream into said combustion chamber with at least one of the following: a radial angle of incidence within a range between approximately 0° to 90° wherein said first fluid stream injected into said combustion chamber is with an angle oblique to a combustion chamber centerline extending through said combustion chamber; and a circumferential angle of incidence within a range between approximately 0° to 90° wherein said first fluid stream is injected into said combustion chamber with an angle that is oblique to the combustion chamber centerline.