Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
  • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
  • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
  • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
  • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
  • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
  • F23R3/34—Feeding into different combustion zones
  • F23R3/346—Feeding into different combustion zones for staged combustion

Definitions

• This invention is directed generally to turbine engines, and more particularly to fuel system for turbine engines.
• gas turbine engines include a plurality of injectors for injecting fuel into a combustor to mix with air upstream of a flame zone.
• the fuel injectors of conventional turbine engines may be arranged in one of at least three different schemes.
• Fuel injectors may be positioned in a lean premix flame system in which fuel is injected in the air stream far enough upstream of the location at which the fuel/air mixture is ignited that the air and fuel are completely mixed upon burning in the flame zone.
• Fuel injectors may also be configured in a diffusion flame system such that fuel and air are mixed and burned simultaneously.
• fuel injectors may inject fuel upstream of the flame zone a sufficient distance that some of the air is mixed with the fuel.
• Partially premixed systems are combinations of a lean premix flame system and a diffusion flame system.
• fuel is injected into the combustion chamber through the injectors into three or four stages, such as a pilot nozzle, an A-stage, a B-stage, and a C-stage (for configurations having tophat injection or pilot premix features).
• the pilot nozzle may also be formed from premix and diffusion stages.
• the pilot nozzle provides fuel that is burned to provide a mini-diffusion flame injector and also provides stability for the premixed A-, B-, and C-stages.
• turbine engines are run using high levels of airflow, thereby resulting in lean fuel mixtures with a flame temperature low enough to prevent the formation of a significant amount of NO x .
• lean flames have a low flame temperature, lean flames are prone to high CO production. And because excess CO production is harmful, a need exists to limit CO emissions.
• Turbine engines often operate at higher fuel to air ratios at partial loads rather than at full load.
• turbine engines are designed for full loads.
• nozzles designed to run at full load run excessively lean at partial loads.
• IGVs Inlet guide vanes
• IGVs may only be used to restrict air flow a limited amount.
• Fuel staging is used to control fuel injection at loads below which IGVs may be used effectively.
• Fuel staging is a process of emitting fuel from less than all of the injectors in a fuel system. By reducing the number of injectors through which fuel is ejected, the amount of fuel passed through the injectors during operation of the turbine engine at partial loads is increased, and thus, burnout is improved.
• using fuel staging requires duplicative auxiliary piping, orifice fuel flow meters, pressure sensors, temperature sensors, and sensors for determining pressure differences. Thus, a need exists for creating efficiencies in a fuel system while maintaining acceptable engine dynamics and NOx emissions.
• a fuel system for a turbine engine for improving the efficiency in a fuel system where a major stage and secondary stage can be combined and held to a relatively constant fuel ratio while maintaining acceptable engine dynamics and NOx
• the fuel system may be formed from a first premix injector assembly stage positioned upstream from a combustor basket, whereby the first premix injector assembly stage is a secondary injector system.
• the fuel system may be formed from a first primary injector assembly stage, which is a main injector system, positioned downstream from the first premix injector assembly.
• the first premix injector assembly stage and the first primary injector assembly stage may be coupled together such that the fuel system is capable of emitting fuel into a combustor of the turbine engine via the first premix injector assembly stage and the primary injector assembly stage simultaneously.
• the fuel system for a turbine engine may include a first premix injector assembly stage comprising at least one injector positioned upstream from a combustor basket, whereby the first premix injector assembly stage is a secondary injector system.
• the fuel system may also include a first primary injector assembly stage comprising at least one injector positioned downstream from the first premix injector assembly, whereby the first primary injector assembly is a main injector system.
• the first premix injector assembly stage and the first primary injector assembly stage may be positioned such that a distance between the first premix injector assembly stage and a flame in the combustor is greater than a distance between the first primary injector assembly stage and the flame in the combustor.
• the first premix injector assembly stage and the first primary injector assembly stage may be coupled together such that the fuel system is capable of emitting fuel into a combustor of the turbine engine via the first premix injector assembly stage and the primary injector assembly stage simultaneously.
• the first premix injector assembly stage and the first primary injector assembly stage may be coupled together via a fuel manifold such that fuel supplied to the fuel manifold is distributed to the first premix injector assembly stage and the first primary injector assembly stage.
• a tuning orifice plate may be positioned inline with the first premix injector assembly stage to regulate a fuel ratio of the combined first premix injector assembly stage and the first primary injector assembly stage.
• the first premix injector assembly stage may be positioned upstream from a preswirler positioned within the fuel system.
• the first primary injector assembly stage is positioned at the preswirler or may be positioned downstream from the preswirler.
• the fuel system may be configured such that the first premix injector assembly stage may inject between about 10 percent and about 20 percent of the total fuel injected into the combustor.
• the first primary injector assembly stage may be configured to inject between about 25 percent and about 45 percent of the total fuel injected into the combustor.
• the fuel system may also include a pilot stage formed from at least one injector positioned downstream from the first premix injector assembly stage. In at least one embodiment, the pilot stage may be configured to inject less than 10 percent of the total fuel injected into the combustor.
• the fuel system may also include a second primary injector assembly stage comprising at least one injector positioned downstream from the first premix injector assembly, whereby the second primary injector assembly is a main injector system.
• the first primary injector assembly stage may emit at least 40 percent of a total fuel injected by the main injectors of the fuel system.
• the first primary injector assembly stage may emit at least 50 percent of a total fuel injected by the main injectors of the fuel system.
• An advantage of the fuel system is that the fuel system can combine primary and secondary fuel injector assembly stages while maintaining acceptable engine dynamics and NOx emissions, thereby eliminating the need for duplicative auxiliary piping, orifice fuel flow meter, pressure sensor, temperature sensor, and sensors for determining pressure differences.
• Figure 1 is a cross-sectional view of a portion of a turbine engine including a fuel system according to the instant invention.
• Figure 2 is detailed, cross-sectional side view of a combustor with the fuel system including aspects of this invention.
• Figure 3 is a detailed, cross-sectional side view of an alternative embodiment of the fuel system.
• Figure 4 is a side view of the combustor with the fuel system.
• Figure 5 is a graph of typical engine fuel flow for a primary fuel stage and a secondary fuel stage.
• Figure 6 is a schematic diagram of the fuel system with a combined primary fuel stage and secondary fuel stage.
• a fuel system 10 for a turbine engine 12 for improving the efficiency in the fuel system 10 where a major stage 14 and secondary stage 16 can be combined and held to a relatively constant fuel ratio while maintaining acceptable engine dynamics and NOx emissions is disclosed.
• the fuel system 10 may be formed from a first premix injector assembly stage 18 positioned upstream from a combustor basket 20, whereby the first premix injector assembly stage 18 is a secondary injector system.
• the fuel system 10 may be formed from a first primary injector assembly stage 22, which is a primary injector system, positioned downstream from the first premix injector assembly stage 18.
• the first premix injector assembly stage 18 and the first primary injector assembly stage 22 may be coupled together such that the fuel system 10 is capable of emitting fuel into a combustor 24 of the turbine engine 12 via the first premix injector assembly stage 18 and the primary injector assembly stage 22 simultaneously.
• the fuel system 10 for a turbine engine may include a first premix injector assembly stage 18 formed from one or more injectors 26 positioned upstream from the combustor basket 20, as shown in Figures 1 -3.
• the first premix injector assembly stage 18 may be a secondary injector system 16.
• the first premix injector assembly stage 18 may be configured such that the first premix injector assembly stage 18 may inject between about 10 percent and about 20 percent of the total fuel injected into the combustor 24 at full load.
• the fuel system 10 may also include a first primary injector assembly stage 22 formed from one or more injectors 28 positioned downstream from the first premix injector assembly, whereby the first primary injector assembly is a main injector system, as shown in Figures 1 -3.
• the first premix injector assembly stage 18 and the first primary injector assembly stage 22 may be positioned such that a distance between the first premix injector assembly stage 18 and a flame 30 in the combustor 24 is greater than a distance between the first primary injector assembly stage 22 and the flame 30 in the combustor 24.
• the first premix injector assembly stage 18 and the first primary injector assembly stage 22 may be coupled together such that the fuel system 10 is capable of emitting fuel into the combustor 24 of the turbine engine 12 via the first premix injector assembly stage 18 and the first primary injector assembly stage 22 simultaneously, as shown in Figure 6.
• the fuel system 10 is capable of emitting fuel into the combustor 24 of the turbine engine 12 via the first premix injector assembly stage 18 and the first primary injector assembly stage 22 simultaneously, as shown in Figure 6.
• the first primary injector assembly stage 22 may be configured to inject between about 25 percent and about 45 percent of the total fuel injected into the combustor 24 at full load.
• the first premix injector assembly stage 18 and the first primary injector assembly stage 22 may be coupled together via a fuel manifold 32, as shown in Figure 6, such that fuel supplied to the fuel manifold 32 is distributed to the first premix injector assembly stage 18 and the first primary injector assembly stage 22.
• a tuning orifice plate 34 may be positioned inline with the first premix injector assembly stage 18 to regulate a fuel ratio of the combined first premix injector assembly stage 18 and the first primary injector assembly stage 22. The fuel ratio may be controlled and kept nearly constant throughout the engine load range, as shown in Figure 5.
• the first premix injector assembly stage 18 may be positioned upstream from a preswirler 36 positioned within the fuel system 10.
• the first primary injector assembly stage 22 may be positioned at the preswirler 36, as shown in Figure 3, such that the downstream end dispensing fuel is at the preswirler 36.
• the first primary injector assembly stage 22, and specifically the downstream end dispensing fuel may be positioned downstream from the preswirler 36.
• the fuel system 10 may also include a pilot stage 38 formed from one or more injectors 40 positioned downstream from the first premix injector assembly stage 18.
• the pilot stage 38 may be configured to inject less than 10 percent of the total fuel injected into the combustor 24.
• the fuel system 10 may also include a second primary injector assembly stage 42 formed from one or more injectors 44 positioned downstream from the first premix injector assembly stage 18, whereby the second primary injector assembly is a main injector system.
• the first primary injector assembly stage 22 may emit at least 40 percent of a total fuel injected by the main injectors of the fuel system 10. In another embodiment, the first primary injector assembly stage 22 may emit at least 50 percent of a total fuel injected by the main injectors of the fuel system 10.
• the fuel system 10 is that the fuel system 10 can combine primary and secondary fuel injector assembly stages 14, 16, such as the first premix injector assembly stage 18 and the first primary injector assembly stage 22 while maintaining acceptable engine dynamics and NOx emissions, thereby eliminating the need for duplicative auxiliary piping, orifice fuel flow meter, pressure sensor, temperature sensor, and sensors for determining pressure differences.
• the combined primary and secondary fuel injector assembly stages 14, 16, such as the first premix injector assembly stage 18 and the first primary injector assembly stage 22, may be activated at the same time and operated at the same fuel ratio through the engine loads, such as between 40 percent load and 100 percent load, as shown in Figure 5.
• the pilot stage 38 and the second primary injector assembly stage 42 may be operated together with the combined the first premix injector assembly stage 18 and the first primary injector assembly stage 22 to achieve desired engine loads and engine dynamics and not exceeding threshold NOx emissions.

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• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)

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• 2013
  • 2013-11-13 US US14/078,920 patent/US20150128600A1/en not_active Abandoned
• 2014
  • 2014-10-30 JP JP2016531025A patent/JP2017502237A/ja active Pending
  • 2014-10-30 EP EP14799290.3A patent/EP3069081A1/en not_active Withdrawn
  • 2014-10-30 CN CN201480062078.4A patent/CN105723155A/zh active Pending
  • 2014-10-30 WO PCT/US2014/063065 patent/WO2015073215A1/en active Application Filing

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