FLEXIBLE FUEL COMBUSTION SYSTEM FOR TURBINE ENGINES

Abstract

A fuel burner system (10) configured to inject a liquid fuel and a gas fuel into a combustor (12) of a turbine engine (14) such that the engine (14) may operate on the combustion of both fuel sources (20, 24) is disclosed. The fuel burner system (10) may be formed from a nozzle cap (16) including one or more first fuel injection ports (18) in fluid communication with a first fuel source (20) of syngas and one or more second fuel injection ports (22) in fluid communication with a second fuel source (24) of natural gas. The fuel burner system (10) may also include an oil lance (26) with one or more oil injection passages (28) that is in fluid communication with at least one oil source (30) and is configured to emit oil into the combustor (12). The oil lance (26) may include one or more fluid injection passages (32) configured to emit air to break up the oil spray and water to cool the combustor (12), or both.

Claims

1-13. (canceled)

14. fuel burner system for a turbine engine, comprising: at least one combustor formed from a combustor housing and at least one nozzle cap; and wherein the at least one nozzle cap includes at least one first fuel injection port in fluid communication with at least one first fuel source and at least one second fuel injection port in fluid communication with at least one second fuel source; wherein the at least one first fuel source contains a first fuel that is different than a second fuel contained within the at least one second fuel source; and at least one oil lance projecting from the at least one nozzle cap, wherein the at least one oil lance has at least one oil injection passage that is in fluid communication with at least one oil source and is configured to emit oil into the at least one combustor, wherein the at least one oil lance has at least one fluid injection passage that is in fluid communication with at least one compressed air source and is configured to emit compressed air into the at least one combustor.

15. The fuel burner system of claim 14, wherein the at least one first fuel source contains syngas, and the at least one second fuel source contains natural gas.

16. The fuel burner system of claim 14, wherein the at least one first fuel injection port and the at least one second fuel injection port are configured to simultaneously inject the first fuel from the at least one first fuel source and the second fuel from the at least one second fuel source into the at least one combustor.

17. The fuel burner system of claim 16, wherein the at least one first fuel source contains syngas, and the at least one second fuel source contains natural gas.

18. The fuel burner system of claim 17, further comprising at least one oil lance projecting from the at least one nozzle cap, wherein the at least one oil lance has at least one oil injection passage that is in fluid communication with at least one oil source and is configured to emit oil into the at least one combustor simultaneously with the syngas and natural gas.

19. The fuel burner system of claim 14, wherein the fuel burner system is configured to inject oil from the at least one oil lance and syngas from the at least one first fuel source simultaneously.

20. The fuel burner system of claim 14, wherein the fuel burner system is configured to inject oil from the at least one oil lance and natural gas from the at least one second fuel source simultaneously.

21. The fuel burner system of claim 14, wherein the at least one oil lance has at least one fluid injection passage that is in fluid communication with at least one water source for emitting water into the at least one combustor.

22. The fuel burner system of claim 14, further comprising at least one oil lance projecting from the at least one nozzle cap, wherein the at least one oil lance has at least one fluid injection passage that is in fluid communication with at least one compressed air source and is configured air to emit compressed air into the at least one combustor.

23. The fuel burner system of claim 14, further comprising at least one oil lance projecting from the at least one nozzle cap, wherein the at least one oil lance has at least one fluid injection passage that is in fluid communication with at least one water source and is configured to emit water into the at least one combustor.

24. The fuel burner system of claim 23, wherein the at least one oil lance projecting from the at least one nozzle cap has at least one oil injection passage that is in fluid communication with at least one oil source and is configured to emit oil into the at least one combustor.

25. A fuel burner system for a turbine engine, comprising: at least one combustor formed from a combustor housing and at least one nozzle cap; and wherein the at least one nozzle cap includes at least one first fuel injection port in fluid communication with at least one first fuel source and at least one second fuel injection port in fluid communication with at least one second fuel source; wherein the at least one first fuel source contains a first fuel that is different than a second fuel contained within the at least one second fuel source; wherein the at least one first fuel injection port and the at least one second fuel injection port are configured to simultaneously inject the first fuel from the at least one first fuel source and the second fuel from the at least one second fuel source into the at least one combustor; wherein the at least one first fuel source contains syngas, and the at least one second fuel source contains natural gas; and at least one oil lance projecting from the at least one nozzle cap, wherein the at least one oil lance has at least one oil injection passage that is in fluid communication with at least one oil source and is configured to emit oil into the at least one combustor.

26. The fuel burner system of claim 25, wherein the at least one oil lance has at least one oil injection passage that is in fluid communication with at least one oil source and is configured to emit oil into the at least one combustor simultaneously with syngas and natural gas be emitted by the at least one first and second fuel injection ports.

27. The fuel burner system of claim 25, wherein the fuel burner system is configured to inject oil from the at least one oil lance and syngas from the at least one first fuel source simultaneously.

28. The fuel burner system of claim 25, wherein the fuel burner system is configured to inject oil from the at least one oil lance and natural gas from the at least one second fuel source simultaneously.

29. The fuel burner system of claim 25, wherein the at least one oil lance has at least one fluid injection passage that is in fluid communication with at least one compressed air source and is configured to emit compressed air into the at least one combustor.

30. The fuel burner system of claim 25, wherein the at least one oil lance has at least one fluid injection passage that is in fluid communication with at least one water source for emitting water into the at least one combustor.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0011] The accompanying drawings, which are incorporated in and form a part of the specification, illustrate embodiments of the presently disclosed invention and, together with the description, disclose the principles of the invention.

[0012] FIG. 1 is a cross-sectional view of a portion of a turbine engine including the fuel burner system.

[0013] FIG. 2 is detailed, cross-sectional side view of a combustor with the fuel burner system taken at section line 2-2 in FIG. 1.

[0014] FIG. 3 is a partial cross-sectional, perspective view of the fuel burner system with the nozzle cap.

[0015] FIG. 4 is a cross-sectional view of the fuel burner system with the nozzle cap taken at section line 4-4 in FIG. 3.

[0016] FIG. 5 is an end view of the fuel burner system with the nozzle cap.

DETAILED DESCRIPTION OF THE INVENTION

[0017] As shown in FIGS. 1-5, a fuel burner system 10 configured to inject a liquid fuel and a gas fuel into a combustor 12 of a turbine engine 14 such that the engine 14 may operate on the combustion of both fuel sources is disclosed. The fuel burner system 10 may be formed from a nozzle cap 16 including one or more first fuel injection ports 18 in fluid communication with a first fuel source 20 of syngas and one or more second fuel injection ports 22 in fluid communication with a second fuel source 24 of natural gas. The fuel burner system 10 may also include an oil lance 26 with one or more oil injection passages 28 that is in fluid communication with at least one oil source 30 and is configured to emit oil into the combustor 12. The oil lance 26 may include one or more fluid injection passages 32. In at least one embodiment, the fluid injection passages 32 in the oil lance 26 may be configured to emit air to break up the oil spray or water to cool the combustor, or both. The fuels may be co-fired, and in at least one embodiment, natural gas, oil and syngas may be co-fired together while water is injected into the combustor 12 to reduce emissions, augment power and reduce combustor temperatures.

[0018] In at least one embodiment, as shown in FIG. 1, the fuel burner system 10 may be formed from one or more combustors 12 formed from a combustor housing 34 and one nozzle caps 16. As shown in FIGS. 3-5, the nozzle cap 16 may include one or more first fuel injection ports 18 in fluid communication with one or more first fuel sources 20 and one or more second fuel injection ports 22 in fluid communication with one or more second fuel sources 24. The first fuel source 20 may contain a first fuel that is different than a second fuel contained within the second fuel source 24. In at least one embodiment, the first fuel in the first fuel source 20 may be syngas and the second fuel in the second fuel source 24 may be natural gas. The first fuel injection port 18 may be formed from a port 18 that is larger in size than the second fuel injection port 22. The first fuel injection port 18 with a larger size may be configured to emit highly diluted syngas or low BTU fuels. The smaller second fuel injection port 22 may be configured to emit natural gas or high BTU fuels. In at least one embodiment, the first fuel injection port 22 and the second fuel injection port 22 may be configured to simultaneously inject the first fuel from the first fuel source 20 and the second fuel from the second fuel source 24 into the combustor 12. The flow of the first fuel from the first fuel source 20 to the first fuel injection port 18 may be controlled via one or more valves 54, and the flow of the second fuel from the second fuel source 24 to the second fuel injection port 22 may be controlled via one or more valves 52. Combusting the two or more fuels in the combustor 12 at the same time is co-firing. In least one embodiment, the first fuel source 20 may contain syngas, and the second fuel source 24 contains natural gas which may be co-fired within the combustor 12.

[0019] As shown in FIG. 4, the fuel burner system 10 may also include one or more oil lances 26 projecting from nozzle cap 16. The oil lance 26 may have one or more oil injection passages 28 that is in fluid communication with one or more oil sources 30. The oil injection passage 28 may be configured to emit oil into the combustor 12 simultaneously with the syngas and natural gas. The flow of oil from the oil source 30 may be controlled via one or more valves 48 to the oil injection passage 28. The fuel burner system 10 may be configured to inject oil from the oil lance 26 and syngas from the first fuel source 20 simultaneously. In at least one embodiment, the fuel burner system 10 may be configured to inject oil from the oil lance 26 and natural gas from the second fuel source 24 simultaneously.

[0020] The oil lance 26 may have one or more fluid injection passages 32 that is in fluid communication with one or more compressed air sources 38 and is configured to emit compressed air into the combustor 12. The flow of compressed air from the compressed air sources 38 may be controlled via one or more valves 50 to the fluid injection passage 32. The oil lance 26 may also have one or more fluid injection passages 32 that is in fluid communication with one or more water sources 40 for emitting water into the combustor 12. The fluid injection passages 32 may be configured to emit water into the combustor 12. The flow of water from the water source 40 may be controlled via one or more valves 50 to the fluid injection passage 32. While being configured to emit water into the combustor 12, the oil lance 26 may include one or more oil injection passages 28 that is in fluid communication with one or more oil sources 30 and is configured to emit oil into the combustor 12.

[0021] During operation, the oil injection passage 28 of the oil lance 26 may be used for ignition and low-load operation of the turbine engine 14. For ignition, oil may be injected through the oil injection passage 28 into the combustor 12 and compressed air may be injected through the fluid injection passage 32 from the compressed air source 40. The compressed air may be used to break up the oil spray to increase the efficiency of combustion of the oil in the combustor 12. During higher load operation when oil is at least a partial fuel source, water may be injected through the fuel injection passage 32 to limit NOx emissions and to cool the combustor 12.

[0022] The fuel burner system 10 may be operated such that oil and syngas may be co-fired, such as, but not limited to, via simultaneous injection into the combustor 12. In another embodiment, the fuel burner system 10 may be operated such that natural gas and syngas may be co-fired, such as, but not limited to, via simultaneous injection into the combustor 12. In yet another embodiment, the fuel burner system 10 may be operated such that natural gas and oil may be co-fired, such as, but not limited to, via simultaneous injection into the combustor 12. In still another embodiment, the fuel burner system 10 may be operated such that three fuels, such as, but not limited to, syngas, natural gas and oil, may be co-fired at the same time. The fluid injection passage 32 of the oil lance 26 may be used to inject water into the combustor 12 during co-firing or two fuels or during co-firing of the syngas, natural gas and oil together to reduce emissions, augment power and reduce combustor temperatures.

[0023] In at least one embodiment, the fuel burner system 10 may be operated to inject steam into the combustor 12 during natural gas or oil operation to reduce emissions or reduce metal temperatures, or both. The steam may be injected via the fluid injection passage 32 of the oil lance 26 from a steam source 42. The steam may also be injected via other means as well. The flow of steam from one or more steam sources 42 may be controlled via one or more valves 46 to the fluid injection passage 32.

[0024] In at least one embodiment, the fuel burner system 10 may be operated to inject nitrogen into the combustor 12 during natural gas or oil operation to reduce emissions or reduce metal temperatures, or both. The nitrogen may be injected via the fluid injection passage 32 of the oil lance 26 from a nitrogen source 44. The nitrogen may also be injected via other means as well. The flow of nitrogen from one or more nitrogen sources 44 may be controlled via one or more valves 46 to the fluid injection passage 32.

[0025] The foregoing is provided for purposes of illustrating, explaining, and describing embodiments of this invention. Modifications and adaptations to these embodiments will be apparent to those skilled in the art and may be made without departing from the scope or spirit of this invention.