Patent
Method and apparatus for actively controlling fuel flow to a mixer assembly of a gas turbine engine combustor
William Joseph Myers,Alfred Albert Mancini,George Chia-Chun Hsiao,Shui-Chi Li,Shih-yang Hsieh,Hukam Mongia +5 more
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TLDR
An apparatus for actively controlling fuel flow from a fuel pump to a mixer assembly of a gas turbine engine combustor, where the mixer assembly includes a pilot mixer and a main mixer, is described in this article.Abstract:
An apparatus for actively controlling fuel flow from a fuel pump to a mixer assembly of a gas turbine engine combustor, where the mixer assembly includes a pilot mixer and a main mixer. The pilot mixer further includes an annular pilot housing having a hollow interior, a primary fuel injector mounted in the pilot housing and adapted for dispensing droplets of fuel to the hollow interior of the pilot housing, a plurality of axial swirlers positioned upstream from the primary fuel injector. The fuel flow control apparatus further includes: at least one sensor for detecting dynamic pressure in the combustor; a fuel nozzle; and, a system for controlling fuel flow supplied by the fuel nozzle through the valves. The fuel nozzle includes: a feed strip with a plurality of circuits for providing fuel to the pilot mixer and the main mixer; and, a plurality of valves associated with the fuel nozzle and in flow communication with the feed strip thereof. The control system activates the valves in accordance with signals received from the pressure sensor.read more
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Patent
Gas turbine combustor
Eigo Takasago Res. Dvlpt Ctre Mitsubishi Kato,Mitsuru Takasago Res. Dvlpt Ctre Mitsubishi Kondo,T. Takasago Res Dvlpt Ctre Mitsubishi Ishiguro,Masaki Ono,Tetsu Konishi,T. Takasago Machinery Works Mitsubishi Iwamoto +5 more
TL;DR: In this article, a gas turbine combustor with a fuel injection nozzle using a fluid other than liquid fuel to atomize the liquid fuel and that can suppress a reduction in power generation efficiency resulting from a heat loss while promoting the atomization of liquid fuel.
Patent
Pilot fuel injector for mixer assembly of a high pressure gas turbine engine
TL;DR: In this article, a mixer assembly for a gas turbine engine is described, where a primary injector has a central axis for injecting a primary fuel spray into a primary air stream, wherein fuel is provided at a desired rate and droplets of the fuel spray are within a desired size range.
Patent
Dual orifice pilot fuel injector
TL;DR: In this article, a gas turbine engine fuel nozzle assembly has concentric primary and secondary pilot fuel nozzles (58, 59) with circular primary and annular secondary exits (98, 100) respectively.
Patent
Automated tuning of gas turbine combustion systems
TL;DR: In this paper, a system for tuning the operation of a gas turbine is provided based on measuring operational parameters of the turbine and directing adjustment of operational controls for various operational elements of turbine.
Patent
High fidelity integrated heat transfer and clearance in component-level dynamic turbine system control
TL;DR: In this article, a rotary system consisting of a rotor and a housing forming a gas path is described, and the control law controls flow along the gas path, and an estimator estimates the rotor and housing temperatures based on the time derivatives, such that the errors are minimized and flow is controlled.
References
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Patent
Combustor mixer having plasma generating nozzle
TL;DR: In this paper, a mixer assembly for use in a combustion chamber of a gas turbine engine is described. But it is not shown how to use the mixture of fuel and air through the outlet to the combustion chamber.
Patent
Fuel nozzle assembly for reduced exhaust emissions
Harjit S. Hura,Paul Edward Sabla,James Neil Cooper,Beverly Stephenson Duncan,Hukam Mongia,Lohmueller Steven Joseph +5 more
TL;DR: A two-stage fuel nozzle assembly for a gas turbine engine is described in this article, where the primary combustion region is centrally positioned and includes a fuel injector that is surrounded by one or more swirl chambers to provide a fuel air mixture that is ignited to define a first stage combustion zone.
Patent
Mixer having multiple swirlers
TL;DR: A mixer assembly for use in a combustion chamber of a gas turbine engine is described in this article, which includes a pilot mixer and a main mixer with axial swirlers positioned upstream from the pilot fuel nozzle.
Patent
Multiple annular swirler
TL;DR: In this paper, a gas turbine engine is equipped with a mixture of a first and a second fuel injector for high power settings of the engine and a main swirler adjacent to the pilot and upstream from the second injector.
Patent
Optical sensing of combustion dynamics
Emily Y. Shu,Dale M. Brown +1 more
TL;DR: In this article, an optical radiation detector such as a silicon carbide photodiode ultraviolet radiation detector was employed for real time, noninvasive monitoring and diagnosis of combustion dynamics in gas turbine engines.