The present invention provides a gas turbine combustor that has 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 the liquid fuel. The gas turbine combustor is adapted to mix liquid fuel with combustion air led from a compressor, burn the mixture, and supply combustion gas generated to a gas turbine. The gas turbine combustor includes a fuel injection nozzle that atomizes the liquid fuel into fine liquid droplets. The fuel injection nozzle includes a first system adapted to supply the liquid fuel and a second system adapted to supply a fluid for atomizing the liquid fuel. Low-boiling liquid fuel is supplied to the second system as the fluid. The second system is adapted to heat and supply the low-boiling liquid fuel.

Gas turbine combustor

An air fuel mixer is disclosed having a mixing duct, a shroud surrounding the upstream end of the mixing duct having contained therein a fuel manifold in flow communication with a fuel supply and control means, a set of inner and outer counter-rotating swirlers adjacent the upstream end of the mixing duct, hollow vanes in at least the outer swirler having passages therethrough in fluid communication with the fuel manifold to inject fuel into the mixing duct, and a hub separating the inner and outer swirlers to allow independent rotation thereof, wherein high pressure air from a compressor is injected into the mixing duct through the swirlers to form an intense shear region and fuel is injected into the mixing duct from the swirler vanes so that the high pressure air and the fuel is uniformly mixed therein so as to produce minimal formation of pollutants when the fuel/air mixture is exhausted out the downstream end of the mixing duct into the combustor and ignited. Further, the air fuel mixer of the present invention may include passages in the wall of the mixing duct in fluid communication with the fuel manifold, a centerbody in the mixing duct having a passage therethrough to admit air into the downstream end of the mixing duct, and tubes extending from the passages in the swirler vanes and/or mixing duct wall to inject liquid fuel downstream of the swirlers.

Air fuel mixer for gas turbine combustor

The present invention provides a gas turbine combustor which makes it possible to achieve both a high combustion efficiency and low NOx emissions characteristics over a wide output power range without using a device that can vary the flow rate of the air used for combustion, by burning a lean mixture using high-temperature burned gas. The gas turbine combustor 10 comprises pre-mixture injection tubes 16 which conduct a mixture of fuel and air into a combustion chamber 11 . The mixture from the pre-mixture injection tubes 16 is injected toward burned gas 19 a present on the downstream side of the flame 19 , which is injected from burners 15 that open into the combustion chamber 11 , and this mixture is mixed with the burned gas 19 a . Even in a mixture which is leaner than the lower limit of inflammability, the radicals in the burned gas 19 a are effective in initiating reactions, so that the combustion of the mixture can be started. Since the burned gas has a lower oxygen concentration than fresh mixture, and since the pre-mixture is dispersed in space, the generation of NOx can be suppressed.

In a gas turbine (10), a plurality of combustors (14), each having a plurality of fuel nozzles (32) arranged about a longitudinal axis of the combustor, and a single combustion zone (70), each fuel nozzle having a diffusion passage (74) and a premix passage (60), the premix passage communicating with a plurality of premix fuel distribution tubes (66) located within a dedicated premix tube (46) adapted to mix the premix fuel and combustion air prior to entry into the single combustion zone (70) located downstream of the premix tube (46).

Dry low NOx single stage dual mode combustor construction for a gas turbine

A method and system of controlling a gas turbine engine is disclosed. The engine has sensors to detect one or more parameters and actuators adapted to respond to commands. The method includes receiving data from the sensors of the engine for one or more measured or sensed parameters, estimating a state of the engine by estimating one or more unmeasured or unsensed parameters using the data from the sensors and a predictive model of the engine, generating commands for the actuators based on the state using an optimization algorithm; and transmitting the commands to the engine. The system includes a state estimator adapted to estimate a state of the engine by estimating one or more unmeasured or unsensed parameters using data from the sensors of the engine for one or more measured or sensed parameters. The estimator includes a model of the engine. The system also includes a control module adapted to generate commands for the actuators based on the state. The control module includes an optimization algorithm for determining the commands.

Model-based control systems and methods for gas turbine engines

A combustor comprises a passage area changing mechanism which relatively moves a flame holder relative to a premixed combustion nozzle in an axial direction so that the area of passage for premixed gas between an injection edge of the premixed combustion nozzle and a peripheral edge of the flame holder can be changed. Stable combustion can be maintained over a wide load range and reduction in NOx can be achieved.

Combustor and method of operating same

A gas turbine combustor including a first-stage combustion chamber being arranged to serve as a premix chamber for a second-stage combustion chamber and an auxiliary burner provided in the first-stage combustion chamber and arranged to effect, when fired, combustion and holding of a flame in the first-stage combustion chamber and to effect, when extinguished, feed a flame from the first-stage combustion chamber to the second-stage combustion chamber; and a method of driving the gas turbine combustor including a step of preparing the auxiliary burner in the first stage combustion chamber, the auxiliary burner being sparked when said combustion is fired, and causing the first-stage combustion camber to serve as the premixing chamber for the second-stage combustion chamber by extinguished the auxiliary burner.

Gas turbine combustor and method of running the same

PURPOSE: To image and measure the density values of plural components of an intermediate product produced in an elementary reaction process of combustion instantaneously at the same time by synthesizing laser light beams which match the absorption spectrum wavelength of a body to measured together, putting the light beams into a sheet shape and irradiating the body to be measured with the light beams. CONSTITUTION: The laser light beams from dye lasers 12 and 13 are tuned and mixed through a mirror 14, a dichroic mirror 15, a cylindrical lens system 16 and a beam splitter 17 so as to match absorption spectra of plural materials to be measured at the same time, and then the beams are changed from circular section to sheet section, and the body to be measured is irradiated with the beams. Consequently, materials in the section absorb light energy to rise in energy potential from base states to excited states and then return to the original base states in short times to emit fluorescent light. The fluorescent light is observed on a lower-wavelength side than the absorption spectrum wavelength. Those two kinds of the fluorescent light are observed by a high-sensitivity camera device 24 arranged at right angles to the tomographic surface. The fluorescent light beams are separated by an optical filter 18, so simultaneous video formation becomes possible. COPYRIGHT: (C)1991,JPO&Japio

Flame tomographic measuring method

PURPOSE: To reduce cooling air amount led to flow into a connecting part between a combustor liner and a tail cylinder, and sufficiently cool a plate spring body and the end part of the combustor liner. CONSTITUTION: A cooling hole 9 which is communicated outside and inside of the liner 1 is opened to a combustor inner 1 covered with a plate spring body 8 in a fitting part between the combustor liner 1 and a tail cylinder 4, and a hood 10 is arranged inside the cooling hole 9 so as to form a channel which is approximately in parallel with the inner wall of the combustor liner 1. A side from the top part of the plate spring body 8 to the combustor liner 1 is formed in such a way that, for example, the width of a slit 8s is widened so as to diminish fluid resistance, and a side from the top part of the plate spring body 8 to the tail cylinder side 4 is formed in such a way that, for example, the width of the slit 8s is diminished as much as possible so as to increase the fluid resistance. COPYRIGHT: (C)1996,JPO

Gas turbine and gas turbine combustion device

PURPOSE: To provide a gas turbine combustor, permitting reduction of NOx, by a method wherein combustion air is supplied into a premixing device without disturbing the flow of combustion air in the premixing device to retain the mixing ratio of fuel to air in combustion zone so as to be uniform regardless of the flow rate of combustion air. CONSTITUTION: A flow regulating ring 18, having lattice type slits for dividing the flow passage of air which flows into a premixing device 15, is arranged at the combustion air intake unit 19 of the premixing device 15. A lid body, covering the flow regulating ring 18, or an air flow rate regulating valve 20, having a cylindrical shape and provided with lattice type slits, is arranged at the outer periphery of the flow regulating ring 18. The air flow rate regulating valve 20 is moved into the axial direction of a gas turbine combustor whereby the opening area of the flow regulating ring 18 is regulated and the flow rate of air, which flows into the premixing device 15, can be controlled.

Air flow rate regulator for gas turbine combustor

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